Terrain awareness system

Description of equivalent WO 9810311 A1

TERRAIN AWARENESS SYSTEM

The present invention is a continuation-in-part application of Provisional Patent Application Serial No. 60/025,091, filed September 3, 1996, which is a continuation-in-part of commonly assigned, co-pending patent application Serial No. 08/509,642, entitled "Terrain Awareness System", filed July 31, 1995, the complete disclosures of which are incorporated herein by reference for all purposed.

BACKGROUND OF THE INVENTION

1. Field of the Invention The present invention relates to a terrain awareness system and more particularly to a system for alerting a pilot of an aircraft of a dangerous flight condition based upon stored terrain data which provides relatively longer warning times than known ground proximity warning systems while minimizing nuisance warnings.

2. Description of the Prior Art

Various systems are known in the art that provide warnings and advisory indications of hazardous flight conditions. Among such systems are systems generally known as ground proximity warning systems (GPWS) which monitor the flight conditions of an aircraft and provide a warning if flight conditions are such that inadvertent contact with terrain is imminent. Among the flight conditions normally monitored by such systems are radio altitude and rate, barometric altitude and rate, air speed, flap and gear positions. These parameters are monitored and an advisory signal and/or warning signal is generated when the relationship between the parameters is such that terrain impact is likely to occur. Typical examples of such systems are disclosed in U.S. Patent Nos. 3,715,718; 3,936,796; 3,958,218; 3,944,968; 3,947,808; 3,947,810; 3,934,221;

3,958,219; 3,925,751; 3,934,222; 4,060,793; 4,030,065; 4,215,334; and 4,319,218, all assigned to the same assignee as the assignee of the present invention and hereby incorporated by reference. While the above-referenced systems do provide advisory and warning signals in the event of proximity to terrain, the warnings generated by such systems are based solely upon flight conditions of the aircraft and do not utilize any navigational information. Consequently, the sensitivity of such systems must be adjusted to provide adequate warnings when a hazardous flight condition exists without generating false or spurious warnings. However, such an adjustment can result in a compromise that may still result m nuisance warnings over terrain unique to particular geographic areas and shorter than desired warning times in yet other geographic areas.

Several attempts have been made to improve upon such ground proximity warning systems utilizing ground-based navigational information. For example, U.S. Patent Nos. 4,567,483; 4,646,244; 4,675,823; and 4,914,436 all disclose ground proximity warning systems which monitor the position of the aircraft relative to stored terram data in order to provide modified ground proximity warnings. However, the utility of such systems is limited. For example, the systems disclosed in U.S. Patent Nos 4,567,483 and 4,914,436 disclose ground proximity warning systems which utilize navigational data to modify predetermined warning envelopes surrounding certain particular airports.

U.S. Patent Nos. 4,646,244 and 4,675,823 disclose terrain advisory systems which utilize various ground-based navigational inputs and stored terrain data to provide various ground proximity warning systems based on the position of the aircraft. In order to conserve memory, the terrain data is modeled in various geometric shapes as a function of the elevation of the terrain within the area defined by the geometric shape The warning signals are generated as a function of the position of the aircraft relative to the model. While such systems do provide adequate terrain warnings, such systems may cause nuisance warnings under certain conditions since the predicted trajectory of the aircraft is not taken into consideration.

Another problem with such systems is that they are based upon ground- based navigational systems, such as VOR/DME and LORAN. Such ground-based navigational systems are being replaced with relatively more accurate satellite systems, such as the global positioning system (GPS). Moreover, such ground-based systems are only able to provide two-dimensional position data Thus, with such systems, the altitude of the aircraft must be supplied by an auxiliary device, such as an altimeter, which increases the complexity of the system as well as the cost Enhanced ground proximity warnings (EGPWS), windshear warnings including predictive (PrWS) and reactive (ReWS) and TCAS alerts are provided in U.S. Patent Nos. 5,220,322, 4,433,323, 5, 187,478 and 4,684,948, the complete disclosures of which are incorporated herein by reference. Suitable PrWS and ReWS systems are described in U.S. Patent Nos. 4,905,000, 5,059,964, 4,725,811, 4,947, 164, 5, 153,588 and 4,891,642, the complete disclosures of which are incorporated herein by reference. Suitable commercially available TCAS systems and associated hardware are described in U.S. Patent Nos. 5,122,808, 5,272,725, 4,914,733, 5,008,844 and 4,855,748, and in published documents: "Pilot's Guide TCAS II CAS 67 A/81 A Bendix/King Traffic Alert and Collision Avoidance Systems" and "Pilot's Guide CAS 66A Bendix/King TCAS I

Collision Avoidance System", the complete disclosures of which are incorporated herein by reference. Performance specifications on TCAS may be found in TCAS I - Advisory Circular (AC) 20-TCAS draft dated 08/15/95; TCAS II - Advisory Circular 20-131 dated -3/29/93; DO 181 A RTCA MOPS Mode S Transponder; DO 185 TCAS RTCA MOPS and DO 185 A TCAS RTCA MOPS, the complete disclosures of which are incorporated herein by reference.

SUMMARY OF THE INVENTION The present invention provides a terrain awareness system and method which provides increased warning times to the pilot of an aircraft of a hazardous flight condition while minimizing nuisance warnings. An important aspect of the invention is that the terrain background information as well as the terrain advisory and warning indications may be displayed on a navigational or weather display, normally existing within an aircraft, which reduces the cost of the system and obviates the need for extensive modifications to existing displays, such as a navigational and weather radar type display.

In a specific aspect of the invention, a terrain warning system includes a terrain awareness device for receiving and storing terrain information relative to a position of an aircraft, a visual display for displaying the terrain information to the pilot and a controller for determining when the terrain information is displayed. The controller includes a terrain selection switch for switching between terrain information and other information, such as weather and navigational information. Preferably, the terrain information on the visual display changes color based on the severity of the terrain threat.

In one embodiment, the controller can be moved between a first state, in which the visual display depicts no information, a second state in which the visual display depicts terrain information and a third state in which the visual display depicts weather information. The terrain selection switch moves the controller between the second and third states. A master selection switch (i.e., a WXR switch) moves the controller between the first and second states. For example, when the controller is in the first or no information displayed state, toggling the WXR switch to ON moves the controller to the second state where weather is displayed. Toggling the terrain selection switch from the second state moves the controller to the third state where the terrain information is displayed. The controller moves from the second state back to the first state when the master selection switch is turned OFF.

The present invention also includes a lamp assembly for providing immediate information regarding the terrain threat and the state of the terrain awareness system to the pilot. In one embodiment, the terrain warning system includes a terrain selection lamp for indicating that the terrain information has been selected and a terrain display lamp for indicating that the terrain information is being displayed on the visual display. The warning system also includes a terrain alert lamp for indicating the terrain alert. In this embodiment, the pilot will notice the terrain alert lamp and toggle the terrain selection switch to view the terrain threat. Alternatively, the system may automatically display the terrain during a terrain alert.

BRIEF DESCRIPTION OF THE DRAWINGS FIGS. 1A and IB represent a block diagram of a terrain awareness system

(TAS) in accordance with the present invention;

FIG. 2 is a diagram of the world broken down into various latitude segments and longitude segments in accordance with the present invention;

FIG. 3 is a graphical representation of the various memory map and resolution sequencing in accordance with the present invention;

FIG. 4A is an exemplary representation of the digital header and subsquare mask word for identifying geographical areas in accordance with the present invention; FIG. 4B is a terrain map alternative to FIG. 3;

FIG. 5 is a graphical illustration of the LOOK-AHEAD distance assuming the aircraft turns at a 30^' angle in accordance with the present invention;

FIG. 6 is a graphical representation of a DH terrain floor boundary which forms the bases for a terrain advisory signal and a terrain warning signal in accordance with the present invention;

FIG. 7 is a graphical illustration of a terrain advisory signal for an aircraft relative to the terrain and an airport for a condition when the aircraft flight path angle is less than a first predetermined reference plane or datum in accordance with the present invention;

FIG. 8 is similar to FIG. 7 but for a condition when the aircraft flight path angle is greater than the first predetermined reference plane;

FIG. 9 is a graphical illustration of a terrain warning signal for an aircraft relative to the terrain and an airport for a condition when the aircraft flight path angle is greater than a second reference plane or datum in accordance with the present invention;

FIG. 10 is similar to FIG. 9 but for when the flight path angle of the aircraft is less than the second reference plane or datum;

FIG. 11 is a graphical illustration of a cut-off angle correction boundary for a level flight condition in accordance with the present invention; FIG. 12 is similar to FIG. 11 but for a condition when the flight path angle of the aircraft is greater than a predetermined reference plane or datum;

FIG. 13 is similar to FIG. 11 but for a condition when the flight path angle of the aircraft is less than a predetermined reference plane or datum and also illustrates a BETA sink rate enhancement boundary in accordance with the present invention;

FIG. 14 is a graphical illustration of the terrain advisory and superimposed terrain warning signals for an aircraft relative to the terrain for a condition when the aircraft flight path angle is less than a first reference plane or datum;

FIG. 15 is similar to FIG. 14 but for a condition when the flight path angle is between a first datum and a second datum;

FIG. 16 is similar to FIG. 14 but for a condition when the flight path anεle is less than the second datum; FIG. 17 is a graphical illustration of LOOK-AHEAD/LOOK-DOWN terrain advisory and warning boundaries in accordance with the present invention for a condition when the aircraft is descending;

FIG. 18 is similar to FIG. 17 but for a condition when an aircraft is climbing;

FIG. 19 is a graphical illustration of LOOK-UP terrain advisory and warning boundaries in accordance with the present invention;

FIG. 20 is a graphical illustration of an aircraft during a pull-up maneuver; FIG. 21 is an exemplary block diagram for a system for generating a signal representative of the altitude loss due to pilot reaction time ALPT, as well as altitude loss due to a pull-up maneuver ALPU in accordance with the present invention;

FIG. 22 is a graphical illustration of an alternative methodology for generating a cut-off altitude boundary in accordance with the present invention;

FIG. 23 is a block diagram of the display system in accordance with the present invention;

FIG. 24 is a functional diagram of the display data format in accordance with the ARINC 708/453 standard for a weather radar display;

FIG. 25 is a plan view of a background terrain display illustrating the variable density dot pattern in accordance with the present invention; FIG. 26 is similar to FIG. 25 but additionally illustrates the terrain threat indications;

FIG. 27 is a block diagram illustrating the configuration of a flash ROM for a terrain data base and a RAM used with the present invention;

FIG. 28 illustrates a wedding-cake configuration for a RAM utilized in the present invention;

FIG. 29 is a diagram of the file format of the files in the terrain data base in accordance with the present invention;

FIG. 30 illustrates a terrain map of the terrain data base in accordance with the present invention illustrating the highest elevation in each of the cells within the map;

FIG. 31 is similar to FIG. 30 and illustrates a method for correcting various cells in the vicinity of a runway;

FIG. 32 is a simplified elevational view of certain data illustrated in FIG. 31 ; FIG. 33 is a diagram of a display illustrating the weather radar sweep spokes and the determination of the range increments;

FIG. 34 is a block diagram of the display system in accordance with the present invention illustrating the memory configuration and the data flow; FIG. 34 A is a block diagram of a configuration alternative to that shown in FIG. 34;

FIG. 35 is a diagram of a terrain map illustrating the determination of the look-ahead vector array in accordance with the present invention;

FIG. 36 is a diagram of a display illustrating a radar sweep spoke and a method for determining the range increments of the radar sweep spoke;

FIG. 37 is a terrain map illustrating the computation of the hazardous terrain in accordance with the present invention;

FIG. 38 is a diagram of a terrain map superimposed on a display screen illustrating the sweep range and the determination of the incremental range increments; FIG. 39 is a diagram of a pixel map of the display in accordance with the present invention;

FIG. 40 is a diagram of the different fractal patterns used to provide the variable density display of non-hazardous display indications in accordance with the present invention; FIG. 41 is a diagram illustrating the determination of the X and Y increments of the display screen;

FIG. 42 is a diagram of the method for superimposing the fractal patterns on the displayed pixel map in accordance with the present invention;

Fig 43 is an illustration of a terrain data format in accordance with the present invention;

Fig. 44 is illustrative of steps to build the Terrain database from the original data in accordance with the present invention;

Fig. 45 is illustrative of steps to build the Terrain database from the original data in accordance with the present invention; Fig. 46 is a flow diagram of terrain-weather selection states of one embodiment of the present invention;

Fig. 47 is a flow diagram illustrating a method for displaying terrain information according to one embodiment of the present invention; and Fig. 48 is a block diagram of the terrain selection/deselection and annunciation according to the present invention.

DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to FIG. 1 , a terrain awareness system (TAS), generally identified with the reference number 20, is illustrated. As will be discussed in more detail below, the TAS 20 utilizes inputs from a satellite-based navigational system, such as global positioning system (GPS) 22 (longitude, latitude, altitude, groundtrack, ground speed), and/or an FMS/IRS navigational system which may be updated by the GPS and/or DME/DME, a terrain data base 24, an airport data base 26 and corrected barometric altitude, for example from a barometric altimeter 28 to provide a LOOK- AHEAD warning system which provides relatively longer warning times while minimizing nuisance warnings. Since the TAS 20 does not require a radio altimeter input, the system can be used with certain aircraft, such as commuter aircraft, which are not normally equipped with a radio altimeter.

The current longitude and latitude of the aircraft from the GPS 22 are applied to an Airport and Terrain Search Algorithm, indicated by a block 29, which includes location search logic for determining the terrain data, as well as the airport data surrounding the aircraft. Such search logic is described in detail in U.S. Patent Nos. 4,675,823 and 4,914,436 assigned to the same assignee as the present invention and hereby incorporated by reference. The GPS inputs, along with terrain and airport data surrounding the aircraft from the search algorithm, indicated by the block 29, are applied to the LOOK-AHEAD warning generator 30, which provides both terrain advisory and terrain warning signals based upon the position and projected flight path of the aircraft. The LOOK-AHEAD warning generator 30 may provide both an aural warning by way of a voice warning generator 32 and speaker 34, and/or a visual warning by way of a map or a display 36, as discussed below.

GLOBAL POSITIONING SYSTEM The primary positional information for the aircraft is provided by the

GPS 22, such as disclosed in U.S. Patent Nos. 4,894,655; 4,903,212; 4,912,645; 4,954,959; 5, 155,688; 5,257, 195; 5,265,025; 5,293, 163; 5,293.318; and 5,337,242, all hereby incorporated by reference. The GPS 22 includes a GPS receiver 37 and a combination GPS receiver and monitor 38. The positional inputs from the GPS 22 are processed by a dead reckoning algorithm, indicated by the block 40, for example as discussed in detail in U.S. Patent No. 5,257, 195, to compensate for temporary outages of the GPS 22, such as loss or masking of satellites. The dead reckoning algorithm can be replaced by an additional navigational system, such as an FMS or an IRS, which can be used during GPS outages.

A differential GPS receiver 42 can also be used to provide an indication of a GPS altitude. As long as the differential GPS information is received and four more satellites are visible, the differential GPS information from the differential GPS receiver 42 is sufficiently accurate for the TAS 20. If the differential GPS receiver 42 is not available, a compound altitude signal may be generated by the block 44 and connected to the LOOK-AHEAD warning generator 30 by way of a single-pole, double-throw switch 46, under the control of a signal "DIFF GPS AVAILABLE" , which indicates when the differential GPS receiver 42 is available. In a first mode when differential GPS information is available, the switch 46 connects the GPS altitude signal from the GPS 22 to the LOOK-AHEAD warning generator 30. In this position, the GPS altitude signal is generated either from the GPS 22 or from the differential GPS receiver 42, as discussed above. When a differential GPS receiver 42 is not available, a compound altitude signal is provided by the block 44 to the LOOK- AHEAD warning generator 30. During this condition, the switch 46, under the control of a "DIFF GPS AVAILABLE" signal, connects the block 44 to the LOOK-AHEAD warning generator 30 to enable the compound altitude signal to be provided to the LOOK- AHEAD warning generator 30. Within the Differential GPC Receiver 42, the barometric altitude is compared with the GPS altitude to generate a compound altitude signal which could be used to limit the maximum difference between the GPS output altitude signal and the barometric altitude to the maximum expected GPS altitude error. Such a configuration would reduce the effect of erroneous pressure correction settings on the barometric altimeter 28.

TERRAIN AND AIRPORT DATA BASES As mentioned above, the airport data and terrain data are separated into two different data bases 26 and 24, respectively. Such a configuration allows either of the data bases 24 or 26 to be updated without the need to update the other. The airport data base 26 contains various types of information relating to airports, such as runway midpoint coordinates, runway length, runway heading, runway elevation and airport/ runway designation data. Additional data relating to obstacles along the approach path (i.e. , high-rise hotels adjacent Heathrow Airport in England) and a nominal final approach slope could also be included in the airport data base 26. A separate obstacle data base may also be provided, structured similar to the airport data base.

In order for the TAS 20 to be useful, all airports, for example, which commuter planes without radio altimeters can land, would have to be included in the airport data base 26. In areas where the airport data base 26 is not complete, the search algorithm 29 would indicate NO DATA. Since the airport data base 26 is organized in a similar fashion as the terrain data base 24 as described below, additional airport data could be added in a piecewise fashion when available. The estimated size of the airport data base 26 is contemplated to be relatively small, compared to the terrain data base 24, for example less than 200 kilobytes depending on the amount of data stored per airport.

The terrain data base 24 may require up to 40 megabytes of storage space, which makes it compatible with available flash erasable programmable read only memory (ROM) devices, such as a flash EEPROM, or mini hard disk drives, which could take advantage of known data compression techniques to reduce the amount of storage space required and also promote easy data retrieval by the search algorithm 29.

An important aspect of the invention is that the terrain data base 24 is structured to provide varying resolutions of terrain data as a function of the topography of the terrain, as well as distance to airports. For example, a relatively high resolution can be provided close to the airport on the order of 1/4 to 1/8 nautical miles and a medium resolution, for example 1/2 to 1 nautical miles within a 30-mile radius of the airport. Outside of the 30-mile radius from the airport, a coarser resolution is sufficient as will be described below.

FIGS. 2 through 4 illustrate the organization of the terrain data base. Referring first to FIG. 2, the world is divided into a plurality of latitude bands 50, for example each about 4' wide. Each latitude band 50 is then divided into a plurality of longitudinal segments 52, which are about 4' wide around the equator, such that each longitudinal segment 52 is about 256 x 256 nautical miles. In order to maintain a relatively constant segment size, the number of longitudinal segments 52 per latitude band 50 are reduced closer to the poles.

Since the number of latitude bands 50 and the number of longitudinal segments 52 per latitude band 50 is fixed, determination of the particular segment corresponding to the current aircraft position is readily determined. For example, the aircraft current latitude X is used to determine the latitude band number. Next, the number of longitudinal segments 52 associated with that band 50 is determined either by way of a LOOK-UP table or by calculation. Once the number of longitudinal segments 52 in the particular latitude band 50 of interest is determined, the current longitudinal position Y of the aircraft can be used to readily determine the longitudinal segment number.

The minimum data associated with each longitudinal segment 52 corresponds to the highest altitude within that segment. As mentioned above, each of the segments 52 is approximately 256 x 256 nautical miles. As shown in FIG. 3, these longitudinal segments 52 can be broken down into various subsquares to provide varying levels of resolution. For example, each segment 52 may be broken down into a plurality of subsquares 54, each subsquare 54 being 64 x 64 nautical miles to provide a very coarse resolution. The subsquares 54, can, in turn, be further subdivided into a number of subsquares 56, for example, each 16 x 16 nautical miles, to provide a coarse resolution. These subsquares 56, in turn, can be subdivided into a plurality of subsquares 58, for example, each 4 x 4 nautical miles, to provide a medium resolution. The subsquares 58 can also be broken down into a plurality of subsquares 60, for example l x l nautical miles, to provide a fine resolution. In the vicinity around airports, it may even be desirable to break down the subsquares 60 down into smaller subsquares 62 to provide even finer resolution, for example 1/4 x 1/4 nautical miles.

As shown in FIG. 4A, the minimum data associated with each longitudinal segment 52 consists of a header 65 which includes a multiple data byte 66 which includes the reference altimde which corresponds to the highest altitude for all the subsquares within the segment, which assumes that the highest elevation in a square is representative of the entire square elevation. The multiple data byte 66 may also include a flag to indicate when no further subdividing is required for certain geographical areas. For example, for segments representing the ocean, all subsquares would have the same maximum altitude and thus no further subdividing would be required. In order to enable the data base to be created and updated on a piecewise basis, the multiple data byte 66 may also contain a flag bit or code indicating that data corresponding to further subdivisions does not exist for a particular segment 52 containing a code indicating that no map data exists in the segment. For geographical areas, such as mountainous areas and areas in the vicinity of an airport, the longitudinal segments 52 are subdivided as discussed above. In such a situation, the stored data would include a 2-byte mask word 68, which points to the subsquares having different altitudes. For example, as shown in FIG. 4, the 2-byte mask word 68 is illustrated with a pointer in the box 15 within the subsquare 54 within the longimdinal segment 52, which represents a different altitude which points to the next finer layer of resolution as discussed above. The subsquares each include a header 70 including a mask as described above to enable a pointer for each subsquare having a different altimde to point to the next finer layer until the finest resolution level desire is reached as shown. The data base structure provides for flexibility as to resolution required and can be constructed on a piecewise basis at different times. As such, the structure contains the entire framework necessary to add new data or modify existing data without changing any of the software.

The size of the data base is proportional to the resolution and the size of the area to be covered. In order to cover the entire earth's surface, about 149 million square nautical miles, only about 2,500 to 3,500 longimdinal segments 52 are required. Thus, the overhead for the minimum header sizes is relatively small.

Alternatively, the world may be divided into a plurality of, for example, 1 ^° x 1 ' map files or cells 51 as shown in FIG. 4B. The various map files 51 may be formed with variable resolution. More particularly, each of the map files may be subdivided into a plurality of subcells 53 with the highest terrain elevation in each subcell indicated, with the resolution of all of the subcells within a particular map file being of the same resolution. As indicated above, the maps are generally 1 ^° x 1 ^" , which may be combined for coarser resolution (i.e. , 2^° x 2^° or 10' x 10^* ). The size of the subcells 53 is varied to provide varying degrees of resolution. For example, for relatively high resolution, the size of the subcells 53 may be selected as either 15 x 15 arc seconds or 30 x 30 arc seconds. The size of the subcells 53 may also be varied as a function of the terrain in particular geographic areas. For example, the size of the subcells 53 may be selected as 30 x 60 arc seconds at relatively far north longitudes and as 30 x 120 arc seconds at longitudes even further north. The size of the subcells 53 may also be varied as a function of the distance to the nearest airport. For example, for distances greater than 64 miles from an airport, the size of the subcells may be selected as 60 x 60 arc seconds while at distances greater than, for example, 128 miles from the airport, size of the subcell 53 may be selected as 120 x 120 arc seconds. For a course resolution, for example for use during a cruise mode as discussed below, the size of subcells may be selected as 5 x 5 arc minutes. As discussed below and as illustrated in FIG. 27, the data base may be compressed by a compression algorithm and stored in a flash read only memory (ROM), configured as a wedding cake as illustrated in FIG. 28. Various compression algorithms are known and suitable for this application. The compression algorithm does not form a part of the present invention.

In order to simplify computation, each of the map files includes a header 55, which includes, inter alia, the resolution of the particular map file 51 as well as the location of one or more corners, for example, the northwest and southeast corners. The headers 55 as well as the map files 51 are discussed in more detail below and illustrated in more detail in FIG. 29.

For certain terrain, for example, terrain adjacent a runway, the resolution of the map files 51 (i.e. , relatively large size of the subcells 53) may result in errors in runway elevation. More particularly, since each subcell 53 contains the highest elevation within the subcell 53, certain errors relating to runway elevations can occur, depending on the resolution of the map file 51. Correction of the elevations adjacent the runways is discussed in more detail below in conjunction with FIGS. 30-33. Systematic errors may also be introduced by the maps, which are digitized, for example, by the Defense

Mapping Agency, using known averaging algorithms, which are known to fill in valleys and cut-off the tops of sharp peaks of the terrain.

LOOK-AHEAD WARNING GENERATOR As mentioned above, the LOOK-AHEAD warning generator 30 generates both a terrain advisory signal and a terrain warning signal based upon the position and trajectory of the aircraft relative to stored terrain data. There are two aspects of the terrain advisory and terrain warning signals: LOOK-AHEAD distance/direction: and terrain threat boundaries.

LOOK-AHEAD DISTANCE/DIRECTION The LOOK-AHEAD direction for detecting threatening terrain is along the groundtrack of the aircraft. In order to prevent nuisance warnings, the LOOK-AHEAD distance is limited, as will be discussed below. Otherwise, potentially threatening terrain along the current flight path of the aircraft relatively far from its current position could produce nuisance warnings. Two different LOOK-AHEAD distances (LAD) are utilized. The first

LAD is used for a terrain advisory signal (also referred to as a yellow alert LAD). A second LAD is used for terrain warning signals which require immediate evasive action (also referred to as a red-alert LAD).

The LAD for a terrain advisory condition is considered first in determining the LAD because it is assumed that the pilot could make a 30' bank mrn at any time at a turning radius R. The LAD is equal to the product of the speed of aircraft and the total LOOK-AHEAD time. As shown in FIG. 5, the total LOOK-AHEAD time is equal to the sum of the LOOK-AHEAD time T_j for a single turning radius R; the LOOK- AHEAD time T2 for terrain clearance at the top of the mm (i.e. , point 73) plus a predetermined reaction T .

The terrain clearance at the top 73 of the mrn is provided to prevent inadvertent terrain contact as a result of the mrn. This terrain clearance may be selected as a fixed distance or may be made equal to the turning radius R.

As shown in equation (1), the turning radius R is proportional to the square of the speed of the aircraft and inversely proportional to the bank angle TG (ROLL).

( 1) R = V²/G x TG (Roll)

For a 30' bank angle, the turning radius R in nautical miles (nM) as a function of the speed in knots is given by equation (2).

(2) R = 0.000025284*V² The LOOK-AHEAD time T_j for a single turning radius is given by equation (3).

(3) T = R/V

Substituting R from equation (1) into equation (3) yields the LOOK- AHEAD time T_j for a single mm radius as shown in equation (4) as a function of the speed of the aircraft and the bank angle.

(4) T = V/G x TG (Roll)

TABLE 1 provides various LOOK- AHEAD times T^ at various mrning radii and ground speeds.

TABLE 1

Radius Speed ^Tl

(nM) (knots) (sec)

1/2 140 13

1 200 18

2 280 26

3 345 31

4 400 38

5 445 40

6 490 44

By assuming that the fixed terrain clearance at the top 73 of the mm is equal to one mrning radius R, the total LOOK- AHEAD time for two mm radii (i.e. , T_j + T2) is simply twice the time for a single turning radius. Thus, the total LOOK- AHEAD time is 2 * T_j plus the predetermined reaction time T3, for example 10 seconds, as given by equation (5).

<⁵> ^TTOTAL ^{= 2} * ^Tl ^{+ T}3 By substituting R from equation (2) into equation (4), the LOOK-AHEAD time for a single mrn radius is given by equation (6).

(6) Tj = 0.000025284 * V

Thus, if it is assumed that the fixed clearance X at the top of the m 73 is also equal to the turning radius R, the total LOOK-AHEAD time for two turning radii is given by equation (7) below, simply twice the value determined in equation (6).

(7) T_j + T₂ = 2 * 0.000025284 * V

For a predetermined reaction time T , for example 10 seconds, the LOOK-AHEAD distance (LAD) in nautical miles for a terrain advisory signal can be determined simply by multiplying the speed of the aircraft (V) by the total time ^ Q _]_ as shown in equation (8).

(8) LAD = V * (0.0000278 + 2 * 0.000252854 * V) + fixed distance * K,

where K is a constant, for example 0.

However, in order to provide optimal conditions during a terrain advisor)' condition, the LAD is limited with an upper limit and a lower limit. The lower limit may be a configurable amount, for example, either 0.75, 1 or 1-1/2 nautical miles at relatively low speeds (i.e. , speeds less than 150 knots) and limited to, for example, 4 nautical miles at speeds, for example, greater than 250 knots. The LAD may also be limited to a fixed amount regardless of the speed when the distance to the runway is less than a predetermined amount, for example 2 nautical miles, except when the aircraft altimde is greater than 3,000 feet, relative to the runway.

The terrain warning LAD is given by equation (9) below. (9) LAD = k_j * LAD (terrain for LOOK-DOWN/LOOK- AHEAD advisory indication), k₂ * LAD (terrain LOOK-DOWN/LOOK-AHEAD warning), k₃ * LAD (terrain LOOK-UP advisory),

where k_j = 1.5, except when the LAD is limited at its lower limit, in which case ki - 1 , I 3 = 1 and where k₂^*= 0.5, = 2.

TERRAIN THREAT BOUNDARIES

The terrain threat boundaries include a terrain floor boundary, terrain advisory boundaries (yellow alert), as well as terrain warning boundaries (red alert) and are provided along the groundtrack of the aircraft.

TERRAIN FLOOR BOUNDARY

The terrain floor boundary is the basis for the terrain threat boundaries and is similar to the terrain floor developed for the GPWS. The terrain floor relates to a distance DH below the aircraft and is proportional to the distance to the closest runway to prevent nuisance warnings when the aircraft is taking off and landing, while providing adequate protection in otiier modes of operation. As illustrated in equation (10), the terrain floor boundary below the aircraft is essentially based upon providing 100 feet clearance per nautical mile from the runway, limited to 800 feet.

(10) DH = 100(ft/nM) * (distance to runway threshold - an offset) + 100 (ft/nM) * (distance to runway center - 12 nautical miles)

Equation (10) is shown graphically in FIG. 6. Referring to FIG. 6, the horizontal axis represents the distance from the runway, while the vertical axis represents the DH terrain floor boundary beneath the aircraft. The first segment 71 represents the runway length, while the point 72 represents the runway center. After a small offset 74, the next segment 78, which starts at 0 feet, slopes at 100 feet per nautical mile distance from the runway threshold, identified by the point 80, up to a maximum of 500 feet. The 500 foot maximum continues along a segment 82 until the distance to the runway center 72 is a predetermined distance D, for example 12 nautical miles. The next segment 84 slopes up at a 100 feet per nautical mile distance until the distance rises 300 feet from the segment 82 for a total of 800 feet.

The terrain floor DH boundary beneath the aircraft is limited such that the segment 78 begins at 0 and the segment 82 never goes above a predetermined maximum, for example 500 feet. In addition, the terrain floor DH boundary is also limited so that the segment 84 never goes below the vertical height of the segment 82 and rises no more than 300 feet relative to the segment 82. During conditions when the aircraft is 3,000 feet above the terrain, the terrain floor DH boundary is maintained at the upper limit of 800 feet.

TERRAIN ADVISORY BOUNDARIES

Two terrain advisory boundaries are shown graphically in FIGS. 7 and 8. FIG. 7 represents a condition when the aircraft is descending while FIG. 8 represents a condition when the aircraft is ascending. As will be discussed in more detail below, the terrain advisory boundaries are based upon the relationship between the flight path angle g and a first configurable datum, THETAl .

Referring first to FIG. 7, the terrain advisory (yellow alert) boundaries are shown. The first segment of the terrain advisory boundary, identified with the reference numeral 92, corresponds to the DH terrain floor boundary. As mentioned above, the DH terrain floor boundary is a function of the distance from the runway 94. In order to determine the bottom segment 100 of the terrain advisory boundary, it is necessary to determine whether the flight path angle g is more or less than a configurable datum, identified as THETAl . As shown and described herein, THETAl is set for 0. However, it should be clear that other angles for THETAl are within the broad scope of the present invention. For the condition illustrated in FIG. 7, the flight path angle g is less than THETAl . Thus, the segment 100 extends from the DH terrain floor boundary at the angle THETAl to the LOOK-AHEAD distance for a terrain advisory. The final segment 102 is generally parallel to the segment 92 and extends in a vertical direction along the LAD for the terrain advisory boundary.

If the flight path angle g is greater than THETAl as shown in FIG 8. , then different terrain advisory boundaries are provided. The segment 92 will be the same as shown in FIG. 7 and described above. However, when the flight path angle g is greater than THETAl as shown in FIG. 8, a bottom segment 106 is formed by extending a line segment from the bottom of the segment 92, which represents the DH terrain floor, along a direction parallel with the flight path angle g up to the LAD. A veπical segment 108 extends from the bottom segment 106 along the LAD to form the terrain advisory boundaries.

Thus, as shown, if the airplane is climbing, only terrain which penetrates the upward-sloping terrain advisory boundaries will cause an advisory signal, such that if the aircraft clears the terrain by a safe margin, no advisory signal is given, even if the terrain ahead is at or above the present aircraft altimde. However, if terrain penetrates the terrain advisory boundaries, an aural warning, such as "CAUTION, TERRAIN" aural advisory may be given. In addition, visual warnings may be provided.

TERRAIN WARNING BOUNDARIES

The terrain warning boundaries are shown in FIGS. 9 and 10 and, in general, indicate to the pilot of an aircraft conditions when evasive action is required to avoid terrain contact. The terrain warning boundaries are based on the relationship of the flight path angle of the aircraft relative to a second configurable datum, THETA2. The datum THETA2 may be selected with an upslope of, for example, 6" , which is equal to the average climb capability of airliners. The datum THETA2 could be modified, taking into consideration aircraft type, configuration, altimde and time for takeoff. However, because of the longer LOOK-AHEAD distance as discussed above for the terrain warning boundaries, a terrain warning could occur before a terrain advisory indication for extreme terrain conditions.

Referring to FIGS. 9 and 10, two different terrain warning boundaries are illustrated. In particular, FIG. 9 illustrates a condition when the flight path angle g is greater than the second datum THETA2. FIG. 10 illustrates a condition when the flight path angle g is less than the second datum THETA2. In both conditions, the first segment 114 of the terrain warning boundary is extended below the aircraft for a distance 1/2 of the DH terrain floor, which, as mentioned above, is a function of the distance of the aircraft from a runway. As mentioned above, the terrain warning boundaries are dependent on the relationship between the flight path angle g of the aircraft and the datum THETA2.

Referring first to FIG. 9, since the flight path g is less than the second datum THETA2, the bottom segment 118 of the terrain warning boundary is formed by extending a line from the segment 114 at an angle equal to the flight path angle g up to the LOOK-AHEAD distance for a terrain warning as discussed above. A vertical segment 120 extends from the lower segment 118 along the LAD for a terrain warning, forming the terrain warning boundaries illustrated in FIG. 9.

If the flight path angle of the aircraft is less than the slope of the second datum THETA2 as shown in FIG. 10, a bottom segment 122 extends from the segment 114 up to the LOOK-AHEAD distance at an angle equal to the flight path angle g. A segment 124 extends upwardly along the LAD from the segment 122. If any terrain along the groundtrack of the aircraft out to the LAD for the terrain warning penetrates the envelope, aural and/or visual terrain ahead warnings may be given.

CUT-OFF BOUNDARIES In order to avoid spurious warnings when the aircraft overflies a ridge at relatively low altitudes, the warning boundaries may include cut-off boundaries, for example, as illustrated in FIGS. 11, 12 and 13. Without the cut-off boundaries, warnings would be given, although the terrain is virtually below the aircraft and no terrain is visible ahead. Referring first to FIG. 11 , the cut-off boundary 126 begins at a predetermined cut-off offset 128 below the aircraft and extends in a direction in front of the aircraft at a predetermined envelope cut-off angle 130. The envelope cut-off angle 130 is equal to the flight path angle g plus a configurable predetermined cut-off angle, described and illustrated as -6. For level flight as shown in FIG. 11 , the cut-off boundary 126 extends from the cut-off offset 128 in the direction of the envelope cut-off angle 130 toward the front of the aircraft to a point 132 where it intersects a terrain advisory boundary or terrain warning boundary, identified with the reference numeral 134. For level flight, as shown in FIG. 11, the flight path angle g is zero. Thus, the cut-off boundary 126 illustrated in FIG. 11 will extend from the cut-off offset 128 along an angle equal to the cut-off angle, which, as mentioned above, is selected as -6' for illustration. As mentioned above, the cut-off boundary 126 extends from the cut-off offset 128 to the point 132 where it intersects the terrain advisory boundary 134 discussed above. The warning boundary is then selected to be the highest of the terrain advisory boundary 134 and the envelope cut-off boundary 126. Thus, for the example illustrated in FIG. 11 , the terrain advisory boundary would consist of the cut-off boundary 126 up to the point 132, where the envelope cut-off boundary 124 intersects the warning envelope 126. From the point 132 forward, the normal terrain advisory boundary 134, corresponding, for example, to a THETAl slope, is utilized. Thus, if either a terrain advisory boundary or terrain warning boundary is below the cut-off boundary 126, the cut-off boundary 126 becomes the new boundary for the advisory or warning signal.

The cut-off angle 130 is limited such that if the flight path angle g is a relatively high climb angle, the cut-off angle 130 does not exceed a predetermined limit, for example a configurable limit between 0 to 6' as will be illustrated in FIG. 12. In particular, referring to FIG. 12, the flight path angle g is shown at a relatively high climb rate (i.e. , g = 9" ). An unlimited cut-off envelope angle 130 is illustrated by the partial segment 136. As shown, this segment 132 is 6' below the flight path angle g However, in order to decrease the sensitivity of the system 20 during conditions when the flight path angle is relatively large, for example 9' , indicative of a fairly steep climb, the cut-off envelope angle 130 is limited. In the example illustrated in FIG. 12, the cutoff angle limit is selected, for example, to be 1.4^* . Thus, at flight path angles g greater than 7.4' , the cut-off angle will result in an envelope cut-off boundary 140, which is more than 6' below the flight path angle g. As shown, since the cut-off angle limit was selected as 1.4' , the cut-off angle will be limited to 1.4' anytime the flight path angle is greater than 7.4' , even though the cut-off angle will be equal to or more than 6' less than the flight path angle g. Thus, for the conditions illustrated in FIG. 12, the segment 140 begins at the cut-off offset 128 and continues along a line that is 1.4" from the horizon until it intersects the terrain advisory or terrain warning boundary 142 at the point 144. The actual advisory or warning boundary will be formed by the limited cutoff boundary 140 up to the point 144 and will continue with the normal warning boundary 142 beyond the point 144. FIG. 13 illustrates a situation when the aircraft is descending and thus the flight pa± angle g is less than 0. During conditions when the flight path angle g is less than the normal descent angle, the warning boundary is lowered past the cut-off boundary for high sink-rate situations in order to prevent nuisance warnings during step- down approaches. In particular, a BETA sink rate enhancement is provided and is effective anytime the flight path g is below a predetermined configurable descent bias GBBIAS, for example, -4" . During such conditions, an angle BETA is added to the terrain advisory damm (THETAl) as indicated below. In particular, when the flight path angle g is greater than the descent bias angle GBBIAS or the flight path angle g is less than zero, BETA is selected as 0. When the flight path angle g is greater than zero, BETA is given by equation (11).

(11) BETA = g - THETAl ; for g > 0

When the flight path angle g is less than GBBIAS, the value for BETA is selected in accordance with equation (12) below.

(12) BETA = K * (g - GBBIAS),

where k = 0.5, g = flight path angle and GBBIAS is selected as -4" .

FIG. 13 illustrates a condition when the flight path angle g is -8' . During this condition, the cut-off angle 130 is selected to be 6' below the flight path angle g and thus defines an envelope cut-off boundary 150 that extends from the cut-off offset 128 along a line which is -14" from the horizontal axis. Since the flight path angle g is less than GBBIAS, the angle BETA is added to the normal warning boundary according to equation (12) above. Thus, for a flight path angle of -8 ' , the BETA angle will be 2° . Thus, the terrain advisory or warning boundary, indicated by the boundary 151 , instead of extending along the THETAl slope, will extend along an angle which is 2" below the THETAl slope to define the enhanced boundary 152. The warning cut-off boundary 152 thus will extend to the point 156 where it intersects the normal terrain advisory or terrain warning boundary 152. Since the cut-off angle boundary 150 is higher than boundary 152 up to the point 156, the cut-off boundary 150 will be utilized as the warning boundary up to the point 156. Beyond point 156, the BETA-enhanced warning boundary 152 will define the warning envelope.

FIGS. 14, 15 and 16 illustrate the composite terrain advisory and terrain warning boundaries for different conditions. The cross-hatched area illustrates terrain in the vicinity of the aircraft. Three conditions are illustrated. In particular, FIG. 14 represents a condition when the flight path angle g of the aircraft is less than the first datum THETAl . FIG. 15 represents a condition when the flight path angle g is between the first damm THETAl and the second damm THETA2. FIG. 16 represents a condition when the flight path angle g is greater than the second datum THETA2. The terrain advisory boundaries are indicated in solid line while the terrain warning boundaries are illustrated by dashed lines.

Referring first to FIG. 14, the terrain advisory boundaries include a boundary 155, which extends from the aircraft to the DH terrain floor. Normally, the lower terrain advisory boundary 157 would extend from the segment 155 along an angle equal to the THETAl slope. However, in this situation, the flight path angle g is illustrated to be greater than the GBBIAS angle; therefore, a BETA-enhanced boundary 159, as discussed above, is utilized which extends along an angle that is equal to the THETAl angle plus the BETA angle, up to the LOOK- AHEAD distance for a terrain advisory. A vertical boundary 158 extends from the first damm THETAl vertically upwardly along the LOOK- AHEAD distance for a terrain advisory. Since the cut-off boundary 157 is higher than the terrain advisory boundary 157 up to the point 169 where the two boundaries intersect, the cut-off boundary 157 becomes the terrain advisory boundary up to the point 169. Beyond the point 169, the boundary 159 is utilized as the warning boundary.

The terrain warning boundary includes a boundary 162 extending to a point equal to 1/2 of the terrain floor as discussed above. A boundary 165 extends from the boundary 162 at the THETA2 slope. A vertical boundary 167 extends from the boundary 165 along the LOOK- AHEAD distance for a terrain warning as discussed above.

FIG. 15 illustrates a situation when the flight path angle g is greater than the THETAl angle and less than or equal to the THETA2 angle. During this condition, the boundary for the terrain warning extends along a segment 180, which is at 1/2 of the DH terrain floor. A sloping boundary 184 extends from the segment 180 to the LOOK- AHEAD distance for a terrain warning (point 186). From there, a vertical boundary 188 extends vertically upwardly to define the terrain warning boundaries. The terrain advisory boundary includes a boundary 185 which extends downwardly to the terrain floor, i.e. , point 187. From point 187, the terrain advisory boundary extends along a segment 189 at the flight path angle g up to a point 191 , the LOOK-AHEAD distance for a terrain advisory. A vertical segment 194 extends along the LAD from the boundary 189 at the point 191. In this illustration, an envelope cut-off boundary 193 cuts off a portion of the terrain advisory indication boundary since the flight path angle g of the aircraft is greater man a predetermined limit. Thus, the portions of the warning boundary 189 below the cut-off angle boundary 193 are ignored; and the segment 193 becomes the effective terrain advisory indication up to the point 195, where the cut-off boundary 193 intersects the terrain advisory indication boundary 189. After the point 195, the boundary 189 will be the effective warning boundary.

FIG. 16 illustrates a situation when the flight path angle g is greater than THETA2. In this situation, a terrain advisory boundary 200 extends from the aircraft to the boundary terrain floor. A lower boundary 202 extends at the flight path angle g from the boundary 200 up to the LOOK- AHEAD distance for a terrain advisory. A vertical terrain advisory boundary 204 extends upwardly along the LOOK-AHEAD distance for the terrain advisory. Since the flight path angle g is illustrated to the greater than GBBIAS, a segment 211 , the cut-off boundary, defines the effective warning boundary up to a point 213 where the terrain advisory boundary intersects the cut-off warning boundary. After that point, segment 202, which is higher, becomes the warning boundary.

The terrain warning boundary extends along a segment 208 down to a point of 1/2 the terrain floor. A lower boundary 210 extends along an angle equal to flight path angle g since it is greater than the THETA2 slope. A vertical terrain warning boundary 212 extends upwardly from the boundary 210 along the LOOK- AHEAD distance for a terrain warning. In order to provide additional sensitivity of the warning system, terrain advisory signals within a predetermined portion of the LAD for a terrain advisory, for example 1/2 LAD, may be treated as terrain wamings. Thus, as shown in FIGS. 14, 15 and 16, vertical boundaries 161, 181 and 201, respectively, are shown, for example, at 1/2 LAD. Based upon the flight path angles shown, these segments define effective terrain advisory envelopes 166, 182 and 203.

ALTERNATIVE TERRAIN THREAT BOUNDARIES

Alternative terrain threat boundaries are illustrated in FIGS. 17-22. Similar to the terrain threat boundary discussed above and illustrated in FIGS. 5-16, the alternative terrain threat boundaries include a terrain floor boundary, terrain advisory boundaries (yellow alert) and terrain warning boundaries (red alert). In the alternative embodiment, the advisory and warning boundaries are further divided into two parts, a LOOK-AHEAD/LOOK-DOWN boundary for detecting terrain ahead or below the aircraft (FIGS. 17 and 18) and a LOOK-UP boundary for detecting precipitous high terrain ahead of the aircraft which may be difficult to clear (FIG. 19).

LOOK-AHEAD/LOOK-DOWN TERRAIN ADVISORY AND WARNING BOUNDARIES As mentioned above, the LOOK-AHEAD/LOOK-DOWN boundaries are illustrated in FIGS. 17 and 18. Referring first to FIG. 17, LOOK-AHEAD/LOOK- DOWN advisory and warning boundaries are illustrated for a condition when the aircraft is descending (i.e. , g < 0). During such a configuration, the first segment of the LOOK-AHEAD/LOOK-DOWN terrain advisory boundary, identified with the reference numeral 300, corresponds to the DH terrain floor boundary. As discussed above, the DH terrain floor boundary is a function of the aircraft from the runway. In order to determine the bottom segment 302 of the LOOK-AHEAD/LOOK-DOWN terrain advisory boundary, the flight path angle g is compared with a configurable damm, THETAl , for example 0' . During descent conditions, the flight path angle g will thus be less than THETAl . Thus, the LOOK-AHEAD/LOOK-DOWN terrain advisory boundary segment will extend from the DH terrain floor boundary segment 300 along the angle THETAl to the look-ahead distance for a terrain advisory (LAD). The final segment 304 extends vertically upwardly from the segment 302 along the LAD.

The LOOK-AHEAD/LOOK-DOWN terrain advisory boundary may also be modified by the BETA sink rate enhancement as discussed above. In this embodiment, the BETA sink rate enhancement ensures that an advisory indication always precedes a warning indication when the aircraft descends into or on top of terrain. The BETA sink rate enhancement is determined as a function of the flight path angle g and two (2) configurable constants KBETA and GBIAS. The BETA sink rate enhancement BETA1 for a LOOK- AHEAD/LOOK-DOWN terrain advisory is provided in equation (13) below for a condition when the aircraft is descending.

(13) BETA1 = KBETA * (g - GBIAS),

where GBIAS is a configurable constant, selected for example, to be zero (0) and KBETA is also a configurable constant selected, for example, to be 0.5.

Referring to FIG. 17, the BETA sink rate enhancement BETA1 for the LOOK-AHEAD/LOOK-DOWN terrain advisory boundary provides an advisory warning at a distance less than 1/2 LAD, unlike the terrain advisory boundary described above). More particularly, for the values defined above for the configurable constants KBETA and GBIAS, the BETA sink rate enhancement BETA1 results in a segment 306 which extends from the DH terrain floor segments 300 at an angle equal to g/2 up to 1/2 of the LAD. Beyond 1/2 LAD, a segment 308 extends at the angle THETAl to a distance equal to the LAD. A vertical segment 310 extends along the LAD to connect the segments 308 to the segment 304. As discussed above, a cut-off boundary may be provided to reduce nuisance wamings. Referring to FIG. 17, the cut-off boundary is identified with the reference numeral 312. The cut-off boundary 312 extends from a vertical distance 314 below the aircraft along a cut-off angle up to the point of intersection 316 with the terrain advisory boundary. For distances less than the intersection 316, the cut-off boundary 312 forms the terrain advisory boundary. For distances beyond the point of intersection 316, the boundaries 306 and 308 form the terrain advisory boundaries. The terrain warning boundary includes the segment 300 extending from the aircraft along the DH terrain floor. A bottom segment 318 connects to the segment 300 and extends along a BETA sink rate enhancement angle BETA2. The BETA sink rate enhancement angle is determined as a function of the flight path angle g and a configurable constant KBETA2 as well as the constant GBIAS discussed above and provided in equation (14) below.

(14) BETA2 = KBETA2 * (GAMMA - GBIAS),

where GBIAS is a configurable constant selected, for example, to be 0 and KBETA2 is also a configurable constant selected, for example, to be 0.25.

For such values of the constants KBETA2 and GBIAS, the BETA enhancement angle KBETA2 will be 1/4 * g. Thus, the segment 318 extends from the segment 300 at an angle equal to 1/4 * g up to 1/2 the LAD. A vertical segment 320 extends along a distance equal to 1/2 * LAD from the segment 318 to define the terrain warning boundary.

Similar to the above, the terrain warning boundaries are also limited by the cut-off boundary 312. Thus, the cut-off boundary 312 forms the terrain warning boundary up to a point 322, where the cut-off boundary 312 intersects the lower terrain warning boundary 318. At distances beyond the point of intersection 322, the segment 318 forms the lower terrain warning boundary up to a distance equal to 1/2 of the LAD.

The terrain advisory and terrain warning boundaries for a condition when the aircraft is climbing (i.e., g > 0) is illustrated in FIG. 18. During such a condition, the BETA sink rate enhancement angles BETA1 and BETA2 are set to a configurable constant, for example, zero (0).

The terrain advisory boundary during a climbing condition is formed by extending a vertical segment 324 from the aircraft for a distance below the aircraft equal to the DH terrain floor. During a climbing condition, a segment 326 is extended from the segment 324 to the LAD at an angle equal to the flight path angle g. At a point 328 where the segment 326 intersects a position equal to 1/2 of the LAD, a vertical segment 330 is extended up from the segment 326, forming a first vertical boundary for the terrain advisory condition. The line segment 326 from the point 328 to the LAD forms the lower terrain advisory boundary while a line segment 332 extending vertically upward from the line segment 326 along the LAD forms a second vertical boundary.

For the exemplary condition illustrated, a cut-off boundary 334 does not intersect the terrain advisory boundaries. Thus, the terrain advisory boundaries for the exemplary condition illustrated is formed by the segments 330 and 332 and that portion of the line segment 326 between the line segments 330 and 332.

The terrain warning boundaries for a condition when the aircraft is climbing includes the vertical segment 324 (FIG. 18) which extends from the aircraft to vertical distance equal to the DH terrain floor below the aircraft forming a first vertical boundary. For a condition when the aircraft is climbing, the line segment 326 extends from the segment 324 at the flight path angle g to form the lower terrain warning boundary. The vertical segment 330 at a distance equal to 1/2 of the LAD forms the second vertical terrain warning boundary. The cut-off boundary 334 limits a portion of the terrain warning boundary.

In particular, the cut-off boundary 334 forms the lower terrain warning boundary up to a point 340, where the cut-off boundary 334 intersects the line segment 326. Beyond the point 340, a portion 342 of the line segment 340 forms the balance of the lower terrain warning boundary up to a distance equal to 1/2 of the LAD.

LOOK-UP TERRAIN ADVISORY AND WARNING BOUNDARIES

The LOOK-UP terrain advisory and terrain warning boundaries are illustrated in FIG. 19. As will be discussed in more detail below, the LOOK-UP terrain advisory and warning boundaries start at altitudes DHYEL2 and DHRED2, respectively, below the aircraft. These altitudes DHYEL2 and DHRED2 are modulated by the instantaneous sink rate (i.e. , vertical speed, HDOT of the aircraft). The amount of modulation is equal to the estimated altitude loss for a pull-up maneuver, for example, at 1/4G (i.e. , 8 ft/sec²) at the present sink rate. The altitudes DHRED2 and DHYEL2 are dependent upon the altitude loss during a pull-up maneuver (A1PU) and the altimde loss due to reaction time (ALRT) discussed below. The estimated altimde loss due to a pull-up maneuver ALPU is best understood with reference to FIG. 20, wherein the vertical axis relates to altimde in feet and the horizontal axis relates to time in seconds. The trajectory of the aircraft from a time shortly before pull-up is initiated to a time when the aircraft has recovered is shown and identified with the reference numeral 344.

Assuming an advisory or warning indication is generated at time T_j at a point 346 along the trajectory 344, the altimde loss due to the reaction time of the pilot (ALRT) is given by equation (15) below.

(15) ALRT = HDOT * T_R,

where HDOT equals the vertical acceleration of the aircraft in feet/sec and T^ equals the total reaction time of the pilot in seconds.

Assuming a pull-up maneuver is initiated at time T₂, the altimde loss due to the pull-up maneuver ALPU may be determined by integrating the vertical velocity HDOT with respect to time as set forth in equation ( 16) below.

(16) HDOT(t) = a * t + HDOT_Q,

where "a" equals the pull-up acceleration and HDOT is a constant.

Integrating both sides of equation (16) yields the altimde loss as a function of time H(t) as provided in equation (17) below.

(17) H(t) = 1/2 * a * t² + HDOTQ t

Assuming a constant acceleration during the pull-up maneuver, the time t until vertical speed reaches zero (point 348) is given by equation (18).

(18) t - -HDOT_Q/a Substimting equation (18) into equation (17) yields equation (19).

( 19) ALPU = -(HDOT₀)²/(2 * a)

Equation (19) thus represents the altitude loss during the pull-up maneuver.

An exemplary block diagram for generating the signals ALTR and ALPU is illustrated in FIG. 21. In particular, a signal representative of the vertical velocity of the aircraft HDOT, available, for example, from a barometric altimeter rate circuit (not shown), is applied to a filter 350 in order to reduce nuisance wamings due to turbulence. The filter 350 may be selected with a transfer function of l/(TAHDOT * S + 1); where TAHDOT is equal to one second. The output of the filter 350 is a signal HDOTf, which represents the filtered instantaneous vertical speed; positive during climbing and negative during descent.

In order to generate the altitude loss due to reaction time signal ALTR, the signal HDOTf is applied to a multiplier 352. Assuming a pilot reaction time Tr, for example, of 5 seconds, a constant 354 equal to 5 seconds is applied to another input of the multiplier 352. The output of the multiplier 352 represents the signal ALTR, which is positive when HDOTf is negative and set to zero if the signal HDOTf is positive, which represents a climbing condition. More particularly, the signal HDOTf is applied to a comparator 356 and compared with a reference value, for example, zero. If the comparator 356 indicates that the signal HDOTf is negative, the signal HDOTf is applied to the multiplier 352. During climbing conditions, the signal HDOTf will be positive. During such conditions, the comparator 356 will apply a zero to the multiplier 352.

The altimde loss due to the pull-up maneuver signal ALPU is developed by a square device 358, a divider 360 and a multiplier 362. The filtered instantaneous vertical speed signal HDOTf is applied to the square device 358. Assuming a constant acceleration during the pull-up maneuver, for example, equal to 8 feet/ sec^*-" (0.25 G), a constant is applied to the multiplier 362 to generate the signal 2a. This signal, 2a, is applied to the divider 360 along with the output of the square device 350. The output of the divider 360 is a signal (HDOT f) /2a, which represents the altimde loss during a pull-up maneuver signal ALPU. These signals ALRT and ALPU are used to modulate the distance below the aircraft where terrain advisory and terrain warning boundaries begin during a LOOKUP mode of operation. More particularly, during such a mode of operation, DH terrain floor segment of the terrain advisory boundary DHYEL2 is modulated by the signals ALRT and ALPU while the DH terrain floor segment of the terrain warning boundary DHRED2 is modulated by the signal ALPU as indicated in equations (20) and (21), respectively.

(20) DHYEL2 = 3/4 * DH + ALRT + ALPU

(21) DHRED2 = 1/2 * 0 + ALPU,

where DH represents the terrain floor as discussed above.

Thus, referring to FIG. 19, the LOOK-UP terrain advisory warning begins at a point 364 below the aircraft; equal to DHYEL2. If the flight path angle g is less than a configurable damm THETA2, a terrain advisory boundary 366 extends from the point 364 to the advisory LAD at an angle equal to THETA2. Should the flight path angle g be greater than THETA2, the lower advisory boundary, identified with the reference numeral 368, will extend from the point 364 at an angle equal to the flight path angle g.

Similarly, the LOOK-UP terrain warning boundary begins at point 370 below the aircraft; equal to DHRED2. If the flight path angle g is less than the angle THETA2, a warning boundary 372 extends from the point 370 at angle THETA2 to the warning LAD. Should the flight path angle g be greater than THETA2, a warning boundary 374 will extend at an angle equal to the flight path angle g between the point 370 and the warning LAD. CUT-OFF ALTITUDE

The cut-off altimde is an altimde relative to the nearest runway elevation; set at, for example, 500 feet. Altitudes below the cut-of altimde are not displayed and are ignored by the terrain advisory and terrain warning computations. The use of a cut-off altimde declutters the display discussed below around airports, especially during a final approach when the aircraft approaches the ground. A second advantage is that nuisance wamings on a final approach, due to altimde errors, terrain data base resolution and accuracy errors are minimized.

However, the use of a cut-off altitude during certain conditions, such as an approach to an aiφort on a bluff (i.e. , Paine Field) at a relatively low altimde or even at an altitude below the aiφort altimde, may compromise system performance. More particularly, during such conditions, the use of a cut-off altimde may prevent a terrain warning from being generated because the threatening terrain may be below the cut-off altimde. In order to account of such situations, the system selects the lower of two cut- off altitudes; a nearest runway cut-off altimde (NRCA) and a cut-off altimde relative to aircraft (CARA). The NRCA is a fixed cut-off altimde, relative to the nearest runway. The CARA is an altimde below the instantaneous aircraft altimde (ACA) by an amount essentially equivalent to DH terrain floor boundary for an advisory condition, which, as discussed above, is a function of the aircraft distance to the nearest runway. Equations (22) and (23) below set forth the NRCA and CARA. As mentioned above, the absolute cut-off altimde (ACOA) is the lower of the NRCA and CARA as set forth in equation (24).

(22) NRCA = COH + RE,

where COH relates to the cut-off height and is a fixed configurable value, initially set between 400 feet and 500 feet; and RE equals the runway elevation.

(23) CARA = ACA - DH - DHO, where ACA is the instantaneous aircraft altimde; DH is the terrain floor which is proportional to the distance to the runway as discussed above; and DHO is a configurable bias, set to, for example, 50 feet.

(24) ACOA = lower of CARA, NRCA,

except where DH DHl, in which case ACOA is always equal to NRCA.

DHl is a point at which the ACOA is forced to be equal to NRCA independent of the aircraft altimde. The point DHl is related to COH, DH and DHO such that on a nominal three (3) degree approach slope, CARA is equal to NRCA when the aircraft is at a distance equal to a distance DH 1 from the aiφort, as illustrated in TABLE 2 below.

TABLE 2

COH DHl DISTANCE TO

(feet) (feet) RUNWAY (n mile)

300 50 1

400 100 1.5

500 150 2

The point DHl forces the cut-off altimde (COH) above the mnway whenever the aircraft is close to the mnway to ensure robustness against nuisance wamings caused by altimde errors and terrain data base resolution margins to disable the terrain advisory and warning indications when the aircraft is within the aircraft perimeter. There are trade-offs between nuisance warnings and legitimate wamings. In particular, the lower COH, the closer the advisory and warning indications are given, making the system more nuisance prone. As indicated above, for a COH of 400, terrain advisory and warning indications are effectively disabled when the aircraft is closer than 1.5 n miles from the aiφort runway. FIG. 22 illustrates the operation of the alternative cut-off altimde boundaries. In particular, FIG. 22 illustrates a condition when the COH is set to 300 feet with DHl equal to 50 feet. The cut-off altimde substantially for area from the mnway, for example, greater than 4 nautical miles, is 300 feet, as indicated by the segment 378 when the glide slope angle is less than a predetermined angle, for example, 3 ' . As the aircraft gets closer to the mnway, the COH is lowered, as illustrated by the segment 388, until the aircraft is within one (1) nautical mile of the mnway, at which point the COH is forced to be 300 feet, which effectively disables any terrain advisory and warning indications within the aircraft is closer than one (1) nautical mile from the mnway, as represented by the segment 382.

During a condition when the aircraft is on a, for example, 3 " glide slope angle, the ACOA is forced to be the NRCA. As shown, the NRCA is illustrated by the segment 382.

DISPLAY SYSTEM

A display system, generally identified with the reference numeral 400, is illustrated in FIGS. 23-42. The display system 400 is used to provide a visual indication of the terrain advisory and terrain warning indications discussed above as a function of the current position of the aircraft. Background terrain information is also provided which provides an indication of significant terrain relative to the current position of the aircraft.

In order to declutter the display, background information may be displayed in terms of predetermined dot patterns whose density varies as a function of the elevation of the terrain relative to the altitude of the aircraft. Terrain advisory and terrain warning indications may be displayed in solid colors, such as yellow and red, relative to the groundtrack of the aircraft.

An important aspect of the invention is that the terrain background information as well as the terrain advisory and warning indications may be displayed on a navigational or weather display, normally existing within an aircraft, which reduces the cost of the system and obviates the need for extensive modifications to existing displays, such as a navigational and weather radar type display. In particular, the terrain data is converted to a weather radar format in accordance with the standard ARINC 708/453 for digital buses on civil aircraft. The terrain data, masked as weather data, can then be easily displayed on an existing navigational or a dedicated weather radar display that conforms with the ARINC 708/453 serial interface standard.

Referring to FIG. 23, the display system 400 includes a weather radar display or navigational display 36 connected to a control bus 404 conforming to an ARINC 429 standard and a terrain data bus switch 406. The terrain data bus switch 406 enables selection between terrain data and weather data for display. More particularly, the data bus switch 406 includes a common pole 408 connected to the display 36 by way of a serial display bus 410. One contact 412 on the data bus switch 406 is connected to a serial weather data bus 414 and, in mm, to a weather radar R/T unit 416, which transmits weather radar data over the weather data bus 414 in conformance with the ARINC 708/453 standard.

An antenna 418 provides weather radar data to the weather radar R/T unit 416. The weather radar R T unit 416 is also connected to the control bus 404, which is used for range and mode data.

In accordance with an important aspect of the invention, the terrain advisory and terrain warning indications, as well as the background information discussed above, are converted to "RHO/THETA" format. The converted terrain data is then applied to a terrain data serial bus 420, which conforms to the ARINC 453 standard, and connected to a contact 422 on the data bus switch 406 to enable selective display of either weather radar or terrain data on the display 36.

The system for converting the terrain advisory and warning indications as well as background terrain data to an ARINC 708/453 standard serial format is indicated as a functional block 424 in FIG. 23 and is described in more detail below. By converting such data into an ARINC 708/453 standard serial format, the data can be displayed on an existing display 36, which conforms to the ARINC 453 standard without the need for relatively complex and expensive modifications to the display's symbol generator.

Referring to FIG. 24, each word 425, in accordance with the ARINC 453/708 standard, is 1600 bits long and represents one spoke or radial 426 of the display 36. Normally, 512 spokes or radials 426 are transmitted for each complete sweep of the display 36. At a transmission rate of, for example, 1 megahertz (MHz), each word 425 takes about 1.6 milliseconds (msec) to transmit. For 512 spokes, one complete sweep will thus take about 4 seconds.

The 1600-bit words 425 include a header 428 and 512 range bins 430 The header 428 includes the control data on the control bus 404 and also includes a 12-bit code representing the antenna scan angle; the angle of the spoke relative to the aircraft heading equivalent to an indicator UP direction. The range bins 430 cover the distance from the antenna 418 to the maximum selected. Each of the 512 range bins includes three intensity bits, encoded into colors as indicated in TABLE 3 below.

TABLE 3

3-BIT RANGE CODE COLOR

000 BLACK

100 GREEN

010 YELLOW

110 RED

001

101 CYAN

011 MAGENTA

111

As will be discussed in more detail below, the display system 400 is capable of displaying background terrain information as well as terrain threat indications as a function of the current position of the aircraft. The threat detection algorithm is run along the groundtrack of the aircraft. Thus, terrain threat indications are typically displayed along the groundtrack while background terrain is displayed relative to the heading of the aircraft.

Referring to FIG 25, the terrain background information is shown on the display 36 As will be discussed in more detail below, the elevation of the highest terrain relative to the altimde of the aircraft is shown as a series of dot patterns whose density varies as a function of the distance between the aircraft and the terrain. For example, a relatively dense dot pattern 432 may be used to indicate terrain that is, for example, 500 feet or less below the aircraft. A medium dense dot pattern 434 may be used to represent terrain that is 1000 feet or less below the aircraft, while a lightly dotted pattem 436 may be used to indicate terrain 2000 feet or less below the aircraft. In order to declutter the display 402, terrain more than, for example, 2000 feet below the aircraft, is not shown. The dots may be displayed in one of the colors indicated in TABLE 3 above, for example, yellow (amber). In addition, in the vicinity of an aiφort, a mnway graph 438, for example, in green, may also be provided. The apparent display resolution may be increased by using more than one color along with the variable density dot patterns, for example, as shown in TABLE 4 below.

TABLE 4

DOT DENSITY HIGH 3000 0 PATTERN

MEDIUM 4000 1000

LOW 5000 2000

COLOR GREEN YELLOW

The display of a terrain threat indication is illustrated in FIG. 26. As shown, the terrain threat indication may be displayed contemporaneously with the background terrain information. Terrain advisory and terrain warning indications are displayed in solid shapes 440 and 442, respectively, for example, "squares"; the displayed terrain map cells which represent a threat painted solid yellow or red. More particularly, at an aspect ratio for the display of, for example, 3 x 4 (vertical to horizontal), the terrain cells will appear "square", particularly at relatively low-range settings. Colors are used to distinguish between terrain advisory and terrain warning indications. For example, red may be used to represent a terrain warning indication 442 while yellow or amber is used to represent a terrain advisory indication 440. By using colored shapes for terrain threat indications and dot patterns of variable density for the terrain background information, clutter of the display 402 is minimized.

The terrain data from the terrain data base 24, for example, as illustrated in FIG. 4B, is used to compute the terrain threat indications as well as background information for the display 36. As discussed above, the terrain data base 24 may be stored in a flash ROM 444 (FIG. 27) for convenience of updates. In order to facilitate update of the display 36 as a function of the position of the aircraft, terrain data from the flash ROM 444 is transferred to a random access memory (RAM) A, identified with the reference numeral 446. As will be discussed in more detail below, the RAM A is mapped with terrain data from the flash ROM 444, centered about the current position of the aircraft, as illustrated in FIG. 27.

In order to provide a relatively large display range, for example, 160 nautical miles, while minimizing processing time as well as the size of the RAM A, the RAM A is configured as a "wedding cake" as generally illustrated in FIG. 28 and configured such that the highest terrain resolution is near the position of the aircraft and the terrain farthest from the aircraft position has the lowest resolution. For example, the RAM A may be provided with four (4) layers. As shown, the instantaneous aircraft position is shown generally centered in layer 1 , having the highest resolution. The resolution of layer 2 lies between the resolution of layer 3 and layer 1. Layer 4 (not shown) is provided with a relatively coarse resolution for use in a cruise mode.

Such a variable resolution display, configured as a layered wedding cake, minimizes the memory size of RAM A as well as the processing time. In order to improve the performance of the system, the flash ROM 444 may also be configured similar to a "wedding cake", as generally illustrated in FIG. 27. As discussed above, the terrain data base 24 may be provided with variable resolution with a relatively fine resolution of, for example, 30 x 20 arc sec (i.e. 1/2 x 1/2 arc min). The relatively coarse resolution of layers 2 and 3 can be formed by combining finer resolution maps. With such a resolution, the configuration of RAM A may be selected in accordance with TABLE 5. TABLE 5

LAYER RESOLUTION LAYER SIZE (MINUTES) (MINUTES)

1 1/2 x 1/2 32 x 32

2 1 x 1 64 x 64

3 2 x 2 128 x 128

4 5 x 5 REMAINING AREA

Each layer is generally centered relative to the aircraft position as shown in FIG. 28 at the time of the update of RAM A. Each layer of the "wedding cake" has its own update boundary. For example, layer 1 of the RAM A includes an update boundary 448. As the aircraft passes through the update boundary 448, the RAM A is updated with new terrain data from the flash ROM 444 (FIG. 27) as will be discussed in more detail below.

Because of the refresh rates required for the display 36, the terrain data may be stored in files alternative to the format illustrated in FIG. 4A. For example, the file format of the terrain data may include an index file or header 55, stored in one or more 128 K byte storage blocks and a plurality of data files 51 , as generally shown in FIG. 29.

As shown, each index file 55 may include pointers to specific data files 51, the length of the map file, as well as the position of one or more of the comer boundaries of the file 51, for example, northwest and southeast corners of each map file 51 , which facilitates updates of the display 36 as a function of the current aircraft position. The index file 55 may contain information regarding the length of the map file 51 , a start of file or altimde offset, the resolution of the map file 51 , and whether and how the file 51 is compressed to enable use of various compression algorithms.

The data files 51 may include a file header 454 as well as data blocks 456 which, as shown, can be grouped according to resolution size. The file header 454 indicates various information about the file. The format of the header 454 may be structured as follows: < MAJOR VERSION BYTE > < MINOR VERSION BYTE > < RLE STATUS BYTE > < ATTRIB BYTE > <HLE NAME (8 CHARACTERS) > < EXTENSION (4 CHARACTERS) > < FILE LENGTH LONGWORD> <TIME STAMP LONGWORD> <CRC LONGWORD>

<SPME LONGWORD>

The major and minor version bytes relate to the revision status of the data in the data files 51. The minor version is set as the inverse of the byte value of the major version such that a default erase will indicate a zero version. The file status byte 457 provides various information regarding the status of the file as discussed below, while the attribute byte is reserved. The file name, extension file length, and spare data are self-explanatory. The time stamp relates to me operational time of the system (i.e., length of time in use) while the CRC data relates to the data files 51. The status byte may be used to provide the following information regarding the data blocks 456, for example, as set forth in TABLE 6 below.

TABLE 6

FLAG BYTE VALUE INFORMATION

FF EMPTY

FE DOWNLOADING

FO VALID

EO READY TO ERASE

RESERVED

RESERVED

00 RESERVED The EMPTY status (FF) is set by erasing the data blocks 456, while the DOWNLOADING status (FE) is set as part of the image. The VALID status (FO) is set when the file is loaded. Lastly, the READY TO ERASE (EO) is set by the file system for obsolete blocks. The file structure may also be as described in Appendix 1. As indicated below, various corrections of the data files 51 may be required in areas near mnway s.

FIG. 30 illustrates a portion of the terrain data base 24 around a particular aiφort, Boeing Field, with a resolution of, for example, 1/2 x 1/2 minute subcells 455, shown with a mnway 456 drawn in. The elevations, as discussed above, are selected to be the highest elevations within the cells 455, rounded up to the next highest resolution increment, for example 100 feet. While such a system provides useful and conservative terrain data for use with the terrain data base 24, such a system in the vicinity of an aiφort can cause the elevations of the mnway 456 to be too high or too low. For example, the elevation of the mnway 456 at Boeing Field is known to be 17/15 feet; rounded off to zero (0) feet. FIG. 30 shows the elevation of mnway 456 to be 200/300 feet, for example, by the averaging algorithm discussed above. Such errors in the mnway elevation can degrade system performance, and, in particular, cause improper performance of the terrain advisory and terrain warning cut-off boundaries below 500 feet, for example, as illustrated in FIG. 22.

In order to solve this problem, the actual elevation of the mnway 456, rounded to the nearest resolution, is used for cells 455 around a perimeter of the mnway 456, as generally shown in FIG. 31. In particular, a first perimeter, illustrated by the dashed box 458, is selected to be about ± 1 cell (i.e., 1/2 minute) from the centerline of the mnway 456. The elevations in all of the cells 455 intersected by the dashed box 458 are set to the actual mnway elevation and rounded to the nearest resolution. For Boeing Field, the elevation for such cells is 0 feet.

Consideration is also given for a narrow approach and a wide approach. The dashed box 460 represents a wide approach while the dashed box 462 represents a narrow approach. The cells 464 and 466, intersected by the wide approach box 460, are set on the actual mnway elevation, rounded to 0 feet. Inside the approach perimeter, as indicated by the arc 467, the elevation for the cells is selected to be either the mnway elevation or the

DH terrain floor (as discussed above). For example, if the comer of the cell 468, closest to the runway 456, is 1.386 nM from the mnway 456, the DH terrain floor will be 86 feet; rounded to nearest 100 feet = 100 feet. Thus, the elevation of cell 468 is selected as 100 feet.

FIG. 32 illustrates the differences between the elevations in selected cells 468, 470 and 472 before and after correction. Before correction, the elevation of cells 468, 470 and 472 was 300 feet. After correction, the elevation of cells 470 and 472 are corrected to the runway elevation and rounded to the nearest resolution (i.e. , 0 feet). The cell 468 is corrected to the DH terrain floor elevation of 100 feet.

FIG. 33 illustrates another situation where the elevation of cells, due to the rounding-off method discussed above, can result in a situation where the cell elevations adjacent a mnway, represented as a staircase 474, are below the mnway elevation. The correction method, discussed above, can also be used to correct the various cells around the mnway 456 up to the mnway elevation in a manner as generally discussed above.

FIG. 34 represents a simplified block diagram for implementation for the display system 400 in accordance with the present invention. The display system 400 may include a microprocessor, for example, an Intel type 80486, 25 MHz type microprocessor ("486") and an Analog Devices type digital signal processor (DSP). The DSP is primarily used for calculating the RHO/THETA conversions to off load the 486.

The display system 400 may have a normal mode and a cruise mode. In a normal mode, the display system 400 displays terrain out to, for example, 100 nautical miles, while in cruise mode out to about 320 nautical miles. In the cruise mode, it is contemplated that the background terrain display levels can be lowered by the pilot such that terrain, for example 10,000 feet or 20,000 feet below the aircraft, can be displayed. Alternatively, the display level could automatically be adjusted to the highest terrain within the selected display range; the value of this level set forth in amber, for example. The 486 runs a "file picker" routine which searches the terrain data base 24 for terrain data covering the area relative to the current position of the aircraft. For example, in a normal mode, the file picker routine searches the terrain data base 24 for terrain data covering an area approximately 256 x 256 minutes relative to the current position of the aircraft. As indicated above, the terrain data base 24 includes index files 55 (FIGS. 4B and 29) which may include the northwest and southeast comers of each map file 51 in order to facilitate the search. A list of files covering the area is assembled and maintained. As indicated above, the index file 55 also includes information as to whether and how the data files 51 are compressed. The files may be compressed/decompressed by a modified Hoffman code, such as PKZIP as manufactured by PKWARE, INC.

If the data files 51 are compressed, the files are decompressed in the background because of the relatively long decompression time and stored in a decompressed file RAM (DFR) 476, for example 256 K bytes. The decompressed files are then transferred to RAM A, identified with the reference number 446. On power-up, one or two files around the aircraft are decompressed and displayed to allow immediate display of a limited range, relative to the position of the aircraft. As more terrain data files are decompressed, the additional range is displayed.

The RAM A may be configured in a plurality of cells 479 (FIG. 34), representative of a terrain area 1/2 x 1/2 minutes, with true north appearing at the top of RAM A as shown. Each cell 479 is two bytes wide and includes data regarding the highest altimde in the cell as well as the identity of each cell 479. As such, the RAM A is addressable by X and Y coordinates and thus represents a map with an altimde in each cell 479. The identity of the cell may be used to distinguish between terrain data, for example, from the terrain data base 24 and obstacle data. As discussed above, in some applications, an obstacle data base may be utilized.

As indicated above, the RAM A may be configured as a wedding cake with various layers, as generally shown in FIG. 28 with the top layer (i.e., layer 1) having die highest resolution (i.e., 1/2 x 1/2 minute cells). Terrain data is loaded into the RAM A such that the aircraft is roughly centered in the top layer, where the terrain advisory and warning detection algorithms are run. Once the aircraft moves outside die update boundary 448 (FIG. 28), die top layer of the RAM A is reloaded with terrain data widi the aircraft centered. The lower layers may also be provided with update boundaries, which enable the lower layers to be updated independently and less frequently than the top layer.

As discussed above and illustrated in FIG. 27, the flash ROM 444 for the terrain data base 24 may also be configured as a wedding cake as illustrated in FIG. 28. In such an implementation, the highest resolution is provided near the airports while the coarser resolution is provided away from the aiφorts as generally shown in FIG. 27. For example, as illustrated in FIG. 34A, the terrain data base 24 may be configured with 1 ' x 1 ' , 2^" x 2' or 10^* x 10" map files. Some of the map files may overlap, similar to a "wedding cake". As shown, the terrain maps closest to aiφorts are provided with the highest resolution, for example 15 x 15 arc seconds. Maps further away from the aiφort may be provided with resolutions of, for example, l x l minute or 2 x 2 minutes while a coarse resolution (i.e., 2' x 2^' or 10' x 10^*) may be provided even further from the aiφort. An upload routine may be used to upsample or downsample terrain or obstacle data into the RAM A from the DFR RAM 476 as shown in FIG. 34. Such a routine is well within the ordinary skill in the art. The top three layers (i.e., layers 1, 2 and 3) of the RAM A (FIG. 28) are updated from the map file source from the flash ROM 444 for the terrain data base 24 having the highest resolution, except for the 5 x 5 minute layer, which is updated only from a 5 x 5 minute file source to reduce processing time.

Alternatively, as shown in FIG. 34A, an additional RAM A*, identified widi the reference numeral 477, may be provided and structured similar to the RAM A 446, forming a "ping-pong" memory arrangement. In this embodiment, one terrain data file 51 is decompressed one file at a time and loaded into the DFR RAM 476 and tiien upsampled to either the RAM A or RAM A*. For example, while the RAM A is being loaded widi additional decompressed files, die terrain direat and display algorithms are executed from the RAM A*. Once the RAM A is updated, the RAM A is then used for the computations while the other RAM A* is updated wi i new data from the DFR RAM 476 to account for changes in die aircraft position. The 5 x 5 minute resolution layer is primarily intended for use in a cruise mode to provide a look-ahead range of about 320 nM. As discussed above and illustrated in FIG. 29, each file includes an index file 55 which contains data relative to die resolution of the terrain data in a particular map file 51. Such information can be used to vary the resolution of the map files as a function of longitude and latitude position. For example, die latitude resolutions of the map files can be decreased at higher latitudes in a northward direction. Moreover, longitude resolution in the RAM A can be varied and provided with, for example, a one degree latitude hysteresis to prevent flipping back and forth as an aircraft cruises northwardly. Once d e terrain data from the terrain data base 24 is loaded into the RAM A, the terrain advisory and warning algorithms ("detection algorithms") are run once per second as discussed below.

The terrain threat algorithms discussed above are based on a single vector along the groundtrack. The single vector provides acceptable results because the relatively crude resolution of the terrain data base 24 is based upon the highest elevation per cell and d e natural noisiness of die groundtrack angle and position information. However, the single vector approach does not take into account various errors, due to, for example, the terrain data base 24, GPS longitude and latitude errors as well as the published track angle accuracy. As such, the single vector along the groundtrack may be substimted widi an array of vectors, as generally shown in FIG. 35, which takes such errors into account. In particular, the groundtrack vector is identified with the reference numeral 482 originating at the instantaneous aircraft position XQ, YQ. A pair of vectors 484 and 486 are disposed at a configurable distance D_Q , for example 0.2 nM along a segment 488, peφendicular to the vector 482 at points X_j, Y_j and X_r, Y_r A pair of outside vectors 490 and 492, originating at points X_p Y_j and X_p Y_p respectively, are directed at a configurable angle D^p _j^, relative to the vectors 484 and 486. The configurable angle D^p _j^ may be selected as 3 degrees, equivalent to the groundtrack accuracy of the GPS.

The coordinates X_j Y_j and X_p Y_r for the vectors 490 and 492, respectively, are determined. More particularly, the incremental X and Y vectors, DXøpp and DYø p, are determined as set forth in equations (25) and (26) as set forth below.

(25) DX_0Fp = (D_OFF/COS(LAT)} * COS(GROUNDTRACK),

where Døpp is a configurable distance between XQ, YQ and X_p Y_j , for example 0.2 nm and the factor l/COS(LAT) is used to convert DXøpp to nautical miles when DXø p, DYø p is in minutes and Døpp is in nautical miles.

(26) DY_0FF = D_0FF * SIN(GROUNDTRACK)

The coordinates X_p Y_r can be determined in a similar manner.

The threat detection algorithms are initiated by calculating the range increments DELTA X_jvfg and DELTA Y^g along a north-south coordinate system along the groundtrack. Referring to FIG. 36, each spoke 426 has 512 size range bins as discussed above, or 256 double range bins. In order to convert from an X-Y coordinate system to the north-soudi coordinate system, die range increments DELTA X*_\jg, DELTA Y^g are determined in accordance with equations (27) and (28). (The term 1/COS (LATITUDE) is used to convert from arc minutes to nautical miles.)

(27) DELTA X_NS = DETECTION STEP SIZE * SIN (GROUNDTRACK) * 1/COS (LATITUDE)

(28) DELTA Y_NS = DETECTION STEP SIZE *

COS (GROUNDTRACK)

After the range increments DELTA X^g and DELTA Y_jy_j are determined, the direat detection algorithm computation is initiated at die instantaneous position XQ, YQ of the aircraft (FIG. 37). The position is then incremented by the range increments DELTA X_js_j and DELTA Y_{j j}g and die range is incremented by a configurable step size, for example 1/8 unit, as discussed above. After the new coordinates are determined, the cuπent teπain altimde at the new coordinate is determined. The teπain detection algorithms, as discussed above, are then computed for the cuπent advisory LAD, as indicated by die arc 494, defining a yellow direat detection vector 496. In order to provide additional warning time for a teπain warning, the teπain warning indication can be computed out to a distance equal to 1.5 * LAD, as indicated by die arc 498 to define a red direat detection vector 500. The above steps are repeated for the look-ahead vector aπays 490 and 492 (FIG. 35). The entire computation is done at a rate of once per second.

Whenever the threat detection algoridim detects teπain along the look-ahead vector aπays 490 and 492 (FIG. 35), the offending teπain is painted in an expanded cone around the groundtrack as shown in FIG. 37. In particular, die expanded cone includes a plurality of vectors, spaced, for example, 4' apart (configurable value), for +90" (configurable value) on each side of the groundtrack. For an expanded teπain warning, the cone may be expanded out distances, for example as set forth in TABLE 7 below. TABLE 7

(For an expansion factor of 2)

NORMAL EXPANDED

TYPE OF LOOK-AHEAD/ LOOK-UP LOOK-AHEAD/ LOOK-UP THREAT LOOK-DOWN LOOK-DOWN

ADVISORY 1.0 * 2.0 * 2.0 * 4.0 * LAD LAD LAD LAD

WARNING 0.5 * 1.5 * 1.0 * 3.0 * LAD LAD LAD LAD

The teπain threat is painted on die display 36 by calculating die starting vector angle DISPA as set forth in equation (29) when a teπain threat along the groundtrack has been detected.

(29) DISPA = GROUNDTRACK + 30 degrees

The range increments are then determined as set forth in equations (30) and (31).

(30) DELTA X_NS = DISPLAY STEP SIZE * SIN(DISPA) * l/COS(LATTTUDE)

(31) DELTA Y_NS = DISPLAY STEP SIZE * COS(DISPA),

where the display step size is a configurable constant, for example 1/2 unit.

After the range increments DELTA X^g and DELTA Y^g are determined, the instantaneous position of the aircraft XQ, YQ is incremented by die same and die range is incremented by die step size. The altimde is then determined for the cuπent position on the teπain map. Subsequently, the threat detection algoridims are run for the distances as discussed above. Should a threat be detected, a color is loaded into a RAM B, identified with die reference numeral 504 (FIG. 34). At the end of die yellow and red threat vectors 496 and 500, the vector angle DISPA is incremented by 4 degrees widi the above steps being repeated until all vectors are done. In addition to die teπain detection and display algorithms, a background teπain algorithm is also executed relative to the teπain data in RAM A (FIG. 34) once every screen update, about 4 seconds. The background teπain algorithm simply compares die cuπent altimde of the aircraft with die various terrain altimde data in the RAM A. Any of the dot patterns 432, 434 and 436 (FIG. 25) resulting from die computation are stored in die RAM B (FIG. 34) organized in a wedding-cake configuration (FIG. 28), sύmlar to the RAM A

(FIG. 34). In addition, the RAM B is organized in single byte cells containing die color/dot pattem as discussed above. The closest mnway may also be stored in the RAM B as either a circular or square pattem in, for example, a green color.

The color/dot pattem in die RAM B (FIG. 34) is transfeπed to the DSP memory RAM B*, identified widi die reference numeral 506, once per screen update (i.e. , 4 sec) and synchronized to die DSP screen painting period. If a threat is detected as discussed above, a new RAM B image is transfeπed to the DSP RAM B* 206 immediately. The image transfer time typically fits between two spokes. If not, the DSP will send an old spoke stored in its spoke memory 508, 510 twice. The DSP then performs the RHO/THETA conversion on the data in RAM B* 506 using the updated aircraft position, selected range and heading data from the 486, as discussed below. Changes in the selected range are implemented on die fly (i.e., the next spoke) without restarting die sweep.

As discussed above, die ARINC 708/453 weather radar format consists of 512 spokes covering a configurable scan range of typically ±90 degrees and a range selected, for example, on a weather data confrol panel. For ARINC systems, each spoke is calculated twice, once for the left selected range and once for die right selected range. The spokes are then transmitted by way of a serial port 512, interleaved left spoke and right spoke to the bus switch 406 (FIG. 23) by way of a pair of drivers 514 and 516 (FIG. 34). The resolution of the scan conversion is 256 range bins; each range bin actually being a double range bin per the ARINC 708/453 standard format. Such a resolution is sufficient for the dot patterns 518 illustrated in FIGS. 25 and 26.

» The RHO/THETA conversion is best understood with reference to FIG. 38. In particular, once per sweep (i.e., every 4 seconds) die range increment Rl is determined. The range increment is the selected range divided by 256. After the range increment is determined, the starting spoke angle is determined (i.e., the aircraft true heading plus 90 degrees). Lastly, the incremental spoke angle DELTA ALPHA is determined. The incremental spoke angle DELTA ALPHA is the sweep range divided by 512; the total number of spokes per sweep.

Once per spoke (i.e., 512 times per 4 second sweep), die incremental range coordinates DELTA X_m, DELTA Y^ are computed and the spoke angle is incremented by DELTA ALPHA, as discussed above. The incremental range increment coordinates X^ and Y_jj-. are computed in accordance widi equations (32) and (33), respectively.

(32) DELTA X_m = RI * SIN (SPOKE ANGLE) * 1/COS (LATITUDE)

(33) DELTA Y_ns = RI * COS (SPOKE ANGLE)

Once per range increment (i.e., 512 x 256 times per 4 second sweep), the instantaneous aircraft position XQ, YQ is incremented by DELTA X^ and DELTA Y^. The color/pattem for the new position is looked up and output to the display 36. These steps are repeated for the rest of the spoke.

With the use of the DSP, two computations can be done in parallel. In particular, the color/pattem of each range bin including the conversion of the longimde to nautical miles (i.e., multiplication by 1/COS (LAT)). Widi reference to FIG. 38, this computation is performed relative to die true north map coordinate system with die aircraft true heading pointing up and die spoke angles referenced to it. The second computation addresses each display indicator pbcel in order to paint the required dot pattem, relative to the display screen coordinate system.

The generation of dot pattem is illustrated in FIGS. 39-42. In general, the scan conversion is simulated by overlaying each RHO/THETA range bin over a calculated indicator pixel map which includes coπections for display aspect ratio using fractal 8 x 8 dot patterns.

The fractal patterns coπesponding to die variable density dot patterns 432, 434 and 436 (FIG. 25) are illustrated in FIG. 40. The fractal pattem size is selected to be 8 x 8 pixels. The densest pattem 432 includes 1/2, or 32, of the 64 pixels filled. In the medium density pattern 434, 16, or 1/4, of the pixels are filled. In the least dense pattern 4 of 64, or 1/16, of the pixels are filled.

Referring to FIG. 39, the display screen is divided into a pixel map, consisting of, for example, 256 x 256 pixels 520. As mentioned above, the 8 x 8 fractal patterns are overlaid onto die pixel map to provide die variable density dot patterns 432, 434 and 436 illustrated in FIG. 25.

The computation of the dot patterns is best understood with reference to FIGS. 39, 41 and 42. Using an X-Y coordinate system, each spoke is determined at the bottom center of the display 36. For a 256 x 256 pixel display, the starting point coπesponds to 120, 0. Next, d e incremental X and Y coordinates relative to the scan angle ALPHA are determined according to equations (34) and (35).

(34) DELTA X = RI * SIN (ALPHA)

(35) DELTA Y = RI * COS (ALPHA),

where RI = a double range increment and ALPHA = the scan angle. These increments are added to die starting point 128, 0. After each increment, the selected fractal pattem is looked up in the RAM B * to determine whe ier to send the last range increment as either block or colored.

Referring to FIG. 42, the increments DELTA X and DELTA Y are applied to a pair of adders 522 and 524, which, in turn, are applied to an X-counter 526 and a Y-counter 528. As discussed above, the X counter 526 starts at 128 and counts up if DELTA X > 0. If DELTA X < 0, die X-counter counts down, indicating a pixel on d e left (FIG. 39) of the starting position. Since the starting pixel is at the bottom of the display, die Y-counter 528 starts at zero and always counts up. A range counter 528 counts up to 256; the maximum number of double range bins. The range counter 528 is driven by an increment clock such that the pattern/color is pamted once per range increment. The output indicates whether die pixel is to be pamted left black.

As discussed above, the background teπain algorithm determines die particular fractal pattem to be used. This data is applied to the DSP to enable die pixels on the pixel map (FIG. 29) to be pamted or left blank. In particular, the diree least significant bits from the X counter 526 and Y counter 528 are used to select the fractal pattem as shown

The scan conversion simulation is performed in parallel with die RHO/THETA conversion which determines the color/dot pattem of the range bin to be transmitted. The color/dot pattem provided by die RHO/THETA conversion is then overlaid widi the fractal dot pattem to determine whether die range bm color should be black or pamted to provide the proper dot pattem on the display.

Referring now to Figs. 46-48, anodier embodiment of the present invention incoφoratmg a pop-up teπain display based on the aircraft's will now be described The system may be selected by die pilot, or it may automatically assert die visual teπam display whenever a teπain threat is present if the display mode is compatible. In an exemplary embodiment, the display changes color according to die relative severity of the teπam direat. The display is most commonly shared widi an existing display such as weadier radar, and die pdot or alerting system must decide which information is displayed. Of course, it will be recognized diat the teπam display may be separate from existing displays such diat the teπam mformation can be displayed at all times during flight.

Refeπing to Fig. 46, the terrain information system mcludes a WXR switch (not shown) and a teπain momentary selection switch (not shown) for switching between diree different teπain/weadier selection states. In a first state 806, terrain and weadier mformation are not displayed, and die switching relays (not shown) are deasserted. This state is true if the WXR switch 802 is tn the OFF position or deasserted. In tins state 806, toggling the teπam momentary selection switch 804 has no effect on die state of the system. Turmng the WXR switch 802 ON moves the system into a second state 808 in which the weadier display is enabled and displayed when the EFIS display modes are selected on die Mode Control Panel The switching relays are not energized in tins state 808. In die second state 808, toggling or pressing the WXR switch 802 back to the OFF position moves the system back into the first state 806. Toggling or pressmg the teπam selection switch 804 moves the system into a tiiird state 810 in which the teπain display is enabled and teπain is displayed if die EFIS display modes are selected on die Mode Control Panel. In the tiiird state 810, the switching relays are energized and die teπain ON lamp is illuminated. This tiiird state can be asserted only from the second state 808 by asserting teπain selection switch 804. Pressing or toggling the WXR switch 802 to an OFF position retumed the system to the first state 806.

The navigation (NAV) display modes for display of weather or terrain are: center map, map, EXP. VOR/ILS, Exp. NAV. Neither weather or teπain is displayable in the following modes: Plan, Full NAV, Full VOR/ILS. Fig. 48 illustrates a block diagram of d e terrain display selection annunciation and fault logic according to one embodiment of the present invention. As shown, the system includes a Captain's Control Panel 900 with a Captain's Teπain Selection Logic 902 and a First Officer's Control Panel 904 with a First Officer's Selection Logic 906. The system further includes first and second relay assemblies 908, 909 (e.g., 453 bus relays) coupled to die selection logics 902, 904 for activating a number of lamps in die Captain's and First

Officer's lamp assemblies 910, 912, respectively. Of course, it will be recognized by tiiose in the art that a single selection logic and relay assembly may be used for botii control panels and lamp assemblies.

Lamp assemblies 910, 912 each include a teπain display select/deselect push button/Lamp combination switch 914, 916 diat provides a momentary input to teπain selection logics 902, 906. Switches 914, 916 allow the pilot to manually select the teπain display, as discussed above. Control mode data is provided to selection logics 902, 906 from a 429 bus 920 in each Control Panel 904, 906.

Lamp assemblies 910, 912 further include an teπain ON lamp 922, a teπain displayed lamp 926, a teπain alert lamp 930 and a teπain not available lamp 940. Terrain ON lamp 922 indicates diat the teπain display has been selected, and is driven directly from a switching relay 924 witiύn relay assemblies 908, 909. When relay 924 is energized, d e ON lamp 922 is illuminated. Teπain ON lamp 922 function is analogous to the WXR On lamp when the weadier display is activated. The teπain ON lamp 922 does not indicate that actual teπain information is being displayed unless die proper NAV display modes have been selected. Teπain displayed lamp 926 indicates to the pilot diat die teπain has been selected and is actually being displayed. Teπain displayed lamp 926 is the analog of the WXR mode annunciation on the NAV display when weather is displayed. Teπain displayed lamp 926 is illuminated when the teπain display 932 is valid, the coπect NAV display modes (received via 429 bus label 272/273) have been selected and a relay 928 from relay assemblies 908, 909 has been energized. The teπain displayed lamp 926 is preferably wired through a spare relay contact to ensure relay failures are indicated coπectly.

Teπain alert lamp 930 indicates that a teπain alert is present so that die pilot is aware diat the terrain information should be displayed. As shown in Fig. 48, teπain alert lamp 930 receives teπain input signals based on die terrain display input parameters 936, which may include latitude and longimde of the aiφlane, groundspeed, track angle, roll angle, vertical speed, barometric altimde, etc (discussed in detail above). Teπain not available lamp 940 is illuminated if any output signals required for the teπain display and teπain alerting system are invalid, or if the NAV solution is inaccurate, or if a EGPWS hardware failure affecting the terrain display is present. In addition, teπain not avaϋable lamp 940 is illuminated when die EGPWS power is OFF. The teπain system further includes a number of lamps associated widi the aircraft's ground proximity warning system (GPWS), which is described in greater detail above. A GPWS INOP lamp 950 is illuminated if the GPWS computer has failed or if any input signals are invalid. A GPWS ALERT lamp 952 is illuminated during a GPWS alert, and during a teπain alert. A GPWS PULL UP lamp 954 is illuminated during a GPWS warning, and during a teπain warning.

The present invention further includes a teπain display fault indication 960, as shown in Fig. 48. In this embodiment, any detected fault affecting terrain display (e.g., terrain display invalid), causes the teπain not available lamp 940 to be illuminated (a flow diagram of tiiis logic is shown in Fig. 47). Preferably, the relay state is not changed without pilot action so that a blank display 962 is shown when the terrain display 932 is selected (i.e., neither a red "X" or a moving marker is displayed). The terrain display 932 is invalidated if any of the required teπain display input signals 936 are invalid or if die internal EGPWS fault monitor 964 detects a hardware fault. Of course, it will be recognized diat some of the input signals may have default values if not selected, which would prevent invalidation of the teπain display. In an exemplary embodiment, for example, the selected range inputs are defaulted to 10 nautical miles if one range input is invalid or not present (i.e. , no fault indication is given). The teπain selection logics 904, 906 each include a latch 980 for moving the relay assemblies 908, 909 into energized and deenergized states. As shown in Fig. 48, logics 904, 906 include an AND gate 982 which has a positive output if the WXR control is ON, and if die teπain selection switch 914, 916 are pressed. If the latch 980 is in the deenergized state, AND gate 984 will send a positive signal to set the latch 980 to the energized state. In this state, die relay assembly 908 is energized, and the teπain selected and teπain displayed lamps 922, 926 are illuminated. Similarly, if die power is ON, or the WXR is OFF or if the relay has been energized and the terrain selection switch 914, 916 has been pressed, die latch 980 will be reset to the deenergized state. In this state, the teπain selected and teπain displayed lamps 922, 926 are turned OFF.

Obviously, many modifications and variations of die present invention are possible in light of the above teachings. Thus, it is to be understood that, witiiin the scope of die appended claims, the invention may be practiced otherwise than as specifically described above.

APPENDIX 1

TERRAIN DATA STRUCTURE

The teπain data format is made up of four distinct parts, the file indirection table, the group index, the data index, and die compressed elevation data itself. See Figure 43. Notes: All multi-byte numbers are stored Little Endian (LSB...MSB).

File Indirection Table

A file indirection table is provided at die top of die index file block. The file index field is each data index is used to index into this table to get the ASCII filename for file system usage. This filename is then mapped be the file system to the coπect 128kbyte physical memory block. A time stamp is provided for each file, this can be used to match to the time stamp in the file header for each file. This helps check for consistency between die index files and die data files.

SIZE: 16-bits - unsigned

Number of filenames defined: Repeated for each filename FILENAME: 16-bytes - ASCII

ASCII filename with the extension included

< Drive> < File 8 > . < Ext 3 > TIME STAMP: 32 bits - unsigned

The number of seconds since January 1, 1980 (DOS's time base).

Group Index

The group mdex is used to reduce the number of data index's which must be searched to find die area of interest. The group mdexes are built by dividmg the earth mto TBD bands or geographic areas, cuπent thinkmg is 10 degrees bands. These bands need not be of equal size. The group mdex pomts to the coπesponding data mdex block to use for this area The area covered by die group must be a rectangle

Note: the group index and data mdex occupy die same file.

Definitions

SIZE. 16-bιts - unsigned

Number of groups

The following is repeated for each group defined:

INDEX 32-bιts - unsigned

<img file="EP0925518A1_D0001.tif" />

File Index ! offset

File Index. Always 0 for group mdex offset: offset in bytes to start of mdex file for this group

LAT MAX 24-bits - signed NW comer latitude Scaling: LSB = 180 / 2^Λ23 Sign^* (+) = North, (-) = South

LAT MIN 24-bits - signed SE comer latitude Scaling: LSB = 180 / 2^A23

Sign: (+) = North, (-) = South LON MIN: 24-bits - signed

NW comer longitude Scaling: LSB = 180 / 2^A23

Sign: (+) = East, (-) = West LON MAX: 24-bits - signed

SE comer longimde

Scaling: LSB = 180 / 2^A23 Sign: (+) = East, (-) = West

Memory Usage: 16 bytes per group

Assume 60 groups worst case = 9600 bytes

Data Index

The data index contains information defining the coverage, resolution and storage location of each individual teπain data file. The data indexes are grouped together per the group index defined above (i.e., group 2's data indexes immediately follow group l 's data indexes).

Definitions:

SIZE: 16-bits - unsigned Number of index's

The following is repeated for each index defined:

INDEX: 32-bits - unsigned .j

12 - bits j 20 - bits

File Index | offset

File Index: Filename index for data offset: offset in bytes to stan of index file for this group LAT MAX: 24-bits - signed

NW comer latitude

Scaling: LSB = 180 / 2^λ23

Sign: (+) = North, (-) = South LAT RES: 8-bits - unsigned

Number of rows per 1 degree LAT MIN: 24-bits - signed

SE comer latitude

Scaling: LSB = 180 / 2^A23 LON MIN: 24-bits - signed

NW comer longimde

Scaling: LSB = 180 / 2"23

Sign: (+) = East, (-) = West LON RES: 8-bits - unsigned Number of columns per 1 degree

LON MAX: 24-bits - signed

SE comer longitude

Scaling: LSB = 180 / 2^A23

Memory Usage: 18 bytes index (terrain file) Assume 8000 files ^•**■*- 144k-bytes

Data

The following defines the format for -t- he actual elevation data. The index files above are used to locate the desired elevation file, and also contain information on die location, resolution etc. Note: for all data types below, the return elevation values at 16 bit singed values.

First value is always compression type as defined below:

COMPRESSION TYPE: 8 bits - unsigned Compression:

0 = no compression

1 = HUFFCODE - type 1

2 = HUFFCODE - type 2 (cuπently not used) 3 = Run length (cuπently not used)

4 = water or constant elevation For type 0, no compression, the uncompressed elevation values are stored directly. The following definition is for the HUFFCODE compressed data format: The top of the data contains the decode tables needed to uncompress the teπain data. Note: Decompression needs the Number of X and Y values of decoded file (from index file). Decode tables: FIRSTCODE SIZE: 1 byte - unsigned

Size in bytes of firstcode and symbol pointer tables (max 32 bytes) FIRSTCODE TAB: n bytes - unsigned Firstcode table

SYMBOL POINTER TABLE: n words - unsigned

Used widi Firstcode table to index into symbol table. SYMBOL SIZE: 1 word - unsigned

Size in bytes of symbol table (max 256 words) SYMBOL TAB: n words - signed

Symbol table. Contains decoded symbol FIRSTVALUE: 1 word - signed

First elevation value. Used by linear predictor Note: typical words decode table size is less than 150 bytes. ELEVATIONS: Compressed elevation values in binary

Note: padded to align on byte boundary cuπently. For Compression type 4, (water/same elevation value), only 3 bytes are needed. The compression type byte defined above, and die 16 bit elevation value. This is used for files that contain only one elevation value. This will typically be used for water and "no- elevation" areas.

Build System

Figures 44 and 45 show a preliminary look at the steps to build die Teπain database from the original source data.

Some key points: 1. Cuπentiy basic input file is 1 degree at 30 arc-seconds. This matches NO A A data. System should be built to handle any filesize.

2. Build system uses a control file automatically generated from mnway database and a NO A A provided worldwide 1 degree teπain file. Control file contains a list of every 1 degree quad which is needed (i.e., on land), and what the desired resolution of diat 1 degree file should be. Resolution is determined by proximity to an airpon and die maximum elevation value of that one degree file. 1 of 3 resolutions are cuπently output, 30, 60, and 120 arc-seconds. In addition, the control file will indicate which 1 degree quads can be combined into one file. This is done for lower resolution quads in an attempt to keep the filesizes even and reduce the number of files. 3. Enroute data is at 5 minute resolution. Enroute data is separate from hi- resolution data above (overlaps), and is grouped in 10 degree by 10 degree blocks.

4. All files have the mnway extrusion algorithm run on them. Runway extmsion should be run at the resolution that the data will be used in the system, it does not need to be n on the enroute data. 5. Some files will need a special extmsion run on them. This will be defined in a separate control file.

Grouping and packaging control files are needed to ensure that the build system groups the files into the coπect structure. Notes on "Teπain Data Embedded Format"

Maps are read from die file system, decompressed, and then used to update "RAM A" as the aircraft moves across it. Due to the slow speed of die decompression, two RAM A's are used. The detection and display algorithm uses one RAM A while the file picker updates die other RAM A with the latest maps. After the file picker has updated its RAM A, die RAM's are swapped and the process starts over.

The file picker process starts by the TAD asking the file system to open a file with a known, fixed name ("TERRAIN.IDX"?). This file contains the file indirection table, the group index table, and die data index tables. The TAD then periodically scans the group index table to find map groups that cover the general vicinity of the aircraft. This scan is done once for each source set of maps (cuπently two: hi-res and en-route). This step quickly reduces die number of maps mat need to be considered for decompression from several diousand down to a few hundred. It identifies candidate groups by comparing the group bounding box stored in the group index table entry against the aircraft's cuπent position. The number of group index table entries is stored at the top of die table, and all die entries immediately follow.

When a candidate group is found, the TAD uses die &lt; fileindex &gt; in the group index table entry to locate the file containing the data index tables. If the number is zero (the usual case), it indicates that die data is in the main index file (the one we are already reading). A fumre option would be to make the number non-zero. It would dien identify a secondary index file named in the file indirection table. Once the file containing die data index table is opened, die TAD seeks to the &lt; offset &gt; in the group index table entry and starts reading the data index table for that group.

Each data index table begins with its number of entries. The TAD scans each of the data index table entries looking for any of die maps needed for the cuπent aircraft position.

If a data index table entry is found to describe one of the maps we need, die TAD uses die &lt; fileindex &gt; to get d e name of the map package file from the file indirection table. A map package file is a concatenation of a couple hundred compressed maps. From there it reads the compression type and calls die coπect decompression algorithm to decompress the file. The decompressed data is dien up-sampled or down-sampled into the appropriate tiers of RAM A. When up-sampling (filing higher resolution tiers with lower resolution data), die highest resolution data is used. To support this TAD must keep track of the cuπent resolution used to fill each cell of RAM A. For down-sampling the highest elevation is always used. The enroute tier of RAM A is always filled with only enroute data. When all map files within the aircraft's area have been processed RAM A is released.