Avionic display systems and methods for generating avionic displays including aerial firefighting symbology

Avionics display system and method for generating avionics display including aerial firefighting symbolsTechnical field

[0001] The following disclosure relates generally to aircraft, and more specifically to avionics display systems and methods for generating avionics displays including aerial firefighting symbology, which enhance situational awareness and firefighting operations in the air Help pilots make decisions during this period.

Background technique

[0002] Aerial firefighting usually involves the operation of aircraft (A/C) in low-altitude, high-risk flight environments. Such a flight environment can cover fire-affected areas ranging from sparsely inhabited or uninhabited wilderness areas to densely inhabited urban areas, where A/C can be used to reduce structural fires in high-rise buildings. The flight environment can be characterized by rising and moving thermal gradients, dynamic wind conditions, and updrafts caused by fires. Visibility can be compromised by adverse weather conditions, time of day, and/or by the presence of large amounts of smoke, ash, and other airborne particulate matter. The airspace covering the area affected by the fire can be occupied by other A/C, elevated terrain, man-made structures, and other obstacles. Then, as expected, aerial firefighting operations are often associated with high risk levels. This is emphasized by the fact that aviation-related accidents routinely cause a significant portion of total firefighter deaths on an annual basis. According to the National Institute of Occupational Safety and Health (NI0SH), the main causes of aircraft crashes and deaths during aerial firefighting operations include engine, structural and component failures; pilot loss of control; failure to maintain adequate clearance from terrain, water, and obstacles ( clearance); and dangerous weather conditions.

[0003] Enhanced vision systems (EVS) provide the potential to reduce the number of accidents and deaths that occur during aerial firefighting operations. Generally, an EVS is an aircraft-based system that includes at least one thermal imaging sensor, such as an infrared camera or a millimeter-wave radar sensor, which collects thermal imaging data outside the A/C during flight. The thermal image data collected by the EVS sensor is presented to the crew members as an EVS image, and the EVS image appears on a head-up display (HUD) or a down-view display (HDD) located in the A/C cockpit. In some instances, the EVS image can be combined or mixed with a display related to another database to produce a composite display. For example, the combined vision system (CVS) display can be produced by integrating the EVS image into the synthetic vision system (SVS) image of the synthetic vision primary flight display (SV-PFD). Larger database-related SVS images use the stored terrain database to provide contextual views beyond the scope of the EVS image, while the EVS image provides real-time, sensor-derived visual information that is more closely similar to the actual flight environment of A/C. Such CVS displays, and in particular EVS images, can thus serve as useful visual enhancement tools during aerial firefighting operations where visibility is often hindered.

[0004] Although it is possible to improve pilot visibility during aerial firefighting operations, CVS displays and other avionics displays incorporating EVS images are generally not suitable for solving the unique challenges and mental tasks encountered by pilots in the context of aerial firefighting . Therefore, there is a continuing need for avionics display systems, such as visual enhancement systems with enhanced functionality, which further improve situational awareness and aid pilot decision making during aerial firefighting operations. An embodiment of such an avionics display system is described herein, such as a method for generating an avionics display including aerial firefighting symbols.

Summary of the invention

[0005] An avionics display system for generating an avionics display is provided, the avionics display including symbols or graphics useful in aerial firefighting operations. In an embodiment, the avionics display system includes an avionics display device, a thermal image sensor, and a controller operably coupled to the display device and the thermal image sensor. The thermal image sensor may be an infrared camera, a millimeter wave radar device, or another sensor suitable for collecting thermal image data in the field of view (FOV) of the sensor outside the aircraft (A/C). During system operation, the controller compiles a fire map of the fire-affected area near A/C based at least in part on the thermal image data collected by the thermal image sensor. Concurrently, the controller generates a first avionics display with a display field of view (FOV) on the avionics display device. The first avionics display is generated to include a symbol representing the sensor FOV, and a graphical representation part of the fire diagram located outside the sensor FOV. The first avionics display can be produced as a two-dimensional avionics display, such as a horizontal navigation (HNAV) or vertical navigation (VNAV) display. Alternatively, the first avionics display may be produced as a three-dimensional avionics display, such as a combined vision system (CVS) display.

[0006] In another embodiment, an avionics display system includes an avionics display device and a controller that is operatively coupled to the display device and generates an avionics display thereon. The controller generates the avionics display to include a graphic depicting the fire-affected area near A/C, and symbols indicating the current A/C position and the boundary of the virtual fire alarm envelope surrounding the current A/C position. When, for example, a fire invades the fire alarm envelope, the controller can further selectively generate a visual alarm on the avionics display. The controller may also actively adjust the fire alarm package with respect to the A/C position in response to changes in the current A/C position (current altitude, latitude, and/or longitude), current wind speed, local fire temperature, and/or other such parameters. The boundary of the network. In still other implementations, the controller may also be configured to establish whether the fire escape route is available for A/C based at least in part on the fire map and the fire alarm envelope. Specifically, the controller may repeatedly search for and identify horizontal or substantially horizontal fire escape routes that avoid fire encroachment into the fire alarm envelope and require a minimum (if any) increase in altitude of A/C . If a substantially horizontal fire escape route is established to be available for A/C, the controller generates a graphic identifying the fire escape route on the avionics display. Conversely, if the controller cannot establish a basically horizontal fire escape route, it can be displayed on the avionics display. Generate a visual alert.

[0007] A method for generating an avionics display including aerial fire symbols is further provided. The embodiment of the method is implemented by an avionics display system that includes an avionics display device, a thermal imaging sensor with a sensor FOV (for example, an infrared camera or MMW radar device), and operably coupled to Avionics display equipment and thermal image sensor controller. During the execution of the method, the controller can establish the fire-affected vicinity of A/C by recalling the fire map from the memory, by receiving the fire map via a wireless data link, and/or by compiling the fire map with the thermal image data received from the sensor. Map of the area of the fire. The controller also updates the fire map on a repeated basis, for example, using the thermal image data captured by the thermal image sensor when the sensor F0V scans across the area affected by the fire. The controller uses the fire diagram to generate the first avionics display on the avionics display device. The controller generates the first avionics display to include a symbol referring to the sensor FOV and a graphic representing a part of the fire map located outside the sensor FOV but within the display FOV.

Description of the drawings

[0008] Hereinafter, at least one example of the present disclosure will be described in conjunction with the following figures, in which similar numbers refer to similar elements, and: FIG. 1 is an aircraft (Α) as illustrated in accordance with an exemplary embodiment of the present disclosure. /C) Airborne and suitable for generating packages

A block diagram of an avionics display system for one or more avionics displays including air firefighting symbols; FIG. 2 is an exemplary embodiment enhanced to include air firefighting symbols and generated by the avionics display system of FIG. 1 A screenshot of the three-dimensional combined vision system (CVS) display; FIG. 3 is a picture of a real-world view from the cockpit of Α/C, which may correspond to the screenshot of the CVS display shown in FIG. 2; and FIG. 4 is A screenshot of an exemplary two-dimensional avionics display and in particular a moving map or horizontal navigation (HNAV) display, which further includes an aerial firefighting symbol and which can be generated by the avionics display system of FIG. 1 in combination with the CVS display of FIG. 2 .

Detailed ways

[0009] The following specific embodiments are merely exemplary in nature, and are not intended to limit the present invention or the application and use of the present invention. The term "exemplary" as it appears throughout this document is synonymous with the term "exemplary" and is used repeatedly below to emphasize that the descriptions appearing in the following sections merely provide multiple non-limiting examples of the invention and should not be interpreted It restricts the scope of the present invention as set forth in the claims in any respect. As used herein, the term "local aircraft" or "local aircraft A/C" refers to an aircraft equipped with an avionics display system described below.

[0010] The following describes an avionics display system for generating avionics displays (including symbols or graphics) useful in aerial firefighting operations. The aerial firefighting symbol may include a graphic representing a fire map, which draws or plots an active flammable area or a fire zone above a geographic area. The fire map can also contain other fire-related information, such as a local fire temperature distribution chart, a chart of the density of airborne particulate matter, the location of any fire escape or water resources near A/C, and vector information about the rate and direction of fire propagation. . The fire map can be provided to the local Α/C from an external source initially (for example, transmitted to the Α/C on the way to the fire-affected area) and/or initially used by the avionics display system to be carried by the Α/C At least one thermal imaging sensor of the system is compile. The thermal imaging sensor may be, for example, an infrared camera or millimeter wave (MMV) radar included in an enhanced vision system (EVS). Over time, the avionics display system repeatedly updates the fire map according to the newly received thermal image data provided by the thermal sensor; for example, when the sensor field of view (FOV) scans across different parts of the area affected by the fire, the fire The appropriate area of the map can be updated with thermal image data. The fire map can also be updated according to data received from sources outside the machine A/C, such as those near the fire-affected area. Thermal imaging data supplied by manned A/C, satellite or unmanned A/C. Any newly received fire chart data can be compared with the stored fire chart, and corresponding adjustments can be made to update the fire chart according to the latest available data or reliable data. The avionics display is similarly updated to present the latest version of the fire diagram to the crew members of A/C.

[0011] Embodiments of the avionics display system can visually integrate the area of the fire map onto the corresponding part of the two-dimensional (2D) or three-dimensional (3D) display environment. The graphic representing the active combustion area located within the sensor FOV can be visually distinguished from the graphic representing the fire graphic located outside the sensor FOV but within the displayed FOV. In some implementations, the avionics display system can also inform any fire patterns within the sensor FOV to have a changed (eg, more eye-catching) appearance relative to the fire patterns outside the sensor FOV. For example, by applying a fire animation, or by generating a visual representation of real-time thermal data captured by a thermal imaging sensor, the fire graphic within the sensor FOV can be generated to have an active burning appearance. Additionally, in the case of a 3D combined vision system (CVS) display, the boundaries of the EVS image can be visually distinguished by occluding the EVS image, by generating wider graphics around the EVS image, or in another way. In the case of a 2D avionics display (such as a moving map or horizontal navigation (HNAV) display), graphics can be generated to indicate the current spread and range of the sensor FOV.

[0012] Additional graphics or symbols that support aerial firefighting efforts may also be generated on one or more avionics displays generated by the avionics display system. Such graphics can visually convey the distribution of airborne particulate matter, local fire temperatures, and the location of nearby water resources. It can also provide a visual indication of the measured or predicted speed and direction of the fire movement. In some implementations, the avionics display system can generate symbols that identify one or more substantially horizontal fire escape routes (exit passages) available to the local A/C. In other implementations, the avionics display system can generate graphics that indicate the area of the space that surrounds the A/C location and which should be avoided from fire encroachment. The area of this space (hereinafter, "fire alarm envelope") can also be used for alarm functionality. For example, when a fire encroachment into the fire alarm envelope occurs, and/or when the local A/C is unable to move forward at the current altitude without fire encroachment into the fire alarm envelope (or in When advancing on the current flight path with significant sideways, the avionics display system can generate an alert. Similarly, when the avionics display system determines that a substantially horizontal fire escape route is not currently available for the local aircraft A/C, an alarm can be generated. Such an alarm can be generated as a visual appearance (e.g., color coded) expressed on the avionics display as, for example, a fire escape route graphic and/or a fire alarm envelope graphic. Code) in the visual alert of the change. An exemplary embodiment of an avionics display system suitable for generating one or more avionics displays including such aerial firefighting symbols will now be described in conjunction with FIG. 1.

[0013] FIG. 1 illustrates a block diagram of an avionics display system 100 illustrated in accordance with an exemplary and non-limiting embodiment of the present disclosure. As schematically illustrated in FIG. 1, the avionics display system 10 includes the following components or subsystems, each of which may consist of one device or multiple interconnected devices: (i) controller 12, (ii) -One or more avionics display devices 14, (iii) local data source 16, (iv) pilot input interface 18, (ν) memory 20 containing any number of onboard databases 22, and (vi) including antenna 26 of the data link subsystem 24. The controller 12 includes at least first, second, third, and fourth inputs operatively coupled to the local data source 16, the pilot input interface 18, the memory 20, and the data link subsystem 24, respectively. Additionally, the controller 12 includes at least one operatively coupled to the avionics display device, respectively

14. The first, second and third outputs of the memory 20 and the data link subsystem 24. In other embodiments, the avionics display system 10 may include a larger or smaller number of components, which may be implemented in a variety of different ways and using any combination of wireless or wired (for example, avionics bus) connections. interconnection. Although the avionics display system 10 is schematically illustrated as a single unit in FIG. 1, the various elements and components of the avionics display system 10 may use any number of physically different and operationally interconnected pieces of hardware or equipment. It is implemented in a distributed manner.

[0014] The avionics display device 14 may include any number of image generating devices, each of which features a display screen on which one or more graphical displays are produced. The avionics display device 14 will often be fixed to the static structure of the A/C cockpit, whether as a head-up display (HUD) device, a down-view display (HDD) device, or a combination thereof. Alternatively, one or more of the avionics display devices 14 may include or take the following form: a removable display device (for example, a head-mounted display device) carried by the pilot or other crew members into the Α/C cockpit Or a portable display device, such as an electronic flight bag (EFB), tablet or laptop computer. In a further embodiment, the avionics display device 14 may not be deployed on the A/C itself, and may instead be remotely located from there; for example, in some implementations, the A/C may be included in the UAV system In the form of unmanned aerial vehicle (UAV), and the operator or pilot can control the UAV from a remote location. During operation of the avionics display system 10, the controller 12 drives the avionics display device 14 to generate one or more graphical displays thereon. For example, and as schematically indicated on the left side of FIG. 1, the controller 12 may drive the avionics display device 14 to generate: (i) 3D avionics including the aerial fire symbol 30 The sub-science display 28, and (ii) the 2D avionics display 32 including the aerial firefighting symbol 34. The avionics displays 28, 32 can be produced on a single display screen, for example in a side-by-side or picture-in-picture format. Alternatively, avionics shows 28,

32 can be generated on a separate display screen.

[0015] The controller 12 may include or be associated with any suitable number of individual microprocessors, flight control computers, navigation equipment, memory (including or in addition to memory 20), power supplies, storage devices, interface cards , And other standard components known in related fields. The controller 12 may include or cooperate with any number of software programs (e.g., avionics display programs) or instructions (e.g., as stored in the memory 20), which are designed to implement the various types described more fully herein. Methods, process tasks, calculations and control/display functions. Although illustrated as a separate block in FIG. 1, the memory 20 may be partially or fully integrated into the controller 12 in an embodiment. In one embodiment, the controller 12 and the memory 20 are produced as an application specific integrated circuit (ASIC), a system in package (SiP) or a microelectronic module. The memory 20 may store data used to support the operation of the avionics display system 10. In addition, as noted above, the memory 20 may store any number of databases 22, which may include navigation, weather, and/or terrain databases. One or more of the databases 22 may be included in the Enhanced Ground Proximity Warning System (EGPWS) or the Runway Awareness and Advisory System (RAAS). More specifically, the controller 12 and other components of the avionics display system 10 may be included or communicated with Any number and type of system collaboration often deployed on Α/C aircraft, such as flight management system (FMS), attitude and heading reference system (AHRS), instrument landing system (ILS), and inertia listed as just a few examples Reference System (IRS).

[0016] The data link subsystem 24 can take any form that realizes wireless two-way communication between the local A/C and one or more external data sources, such as the local A/C. Neighboring A/C and/or traffic control authority within the general vicinity. The data link subsystem 24 can be used to provide air traffic control (ATC) data to the local aircraft A/C and/or send information from the local aircraft A/C to the ATC conforming to known standards and specifications. Additionally, in the context of the avionics display system 10, information about air firefighting efforts, such as air traffic information, and instructions for coordinating ground and air-based firefighting teams, may be transmitted to the controller 12 via the data link subsystem 24. Data can also be received wirelessly via the data link subsystem 24, which can be used by the avionics display system 10 to further initially compile, enhance, and update the fire map of the area affected by the fire. In this regard, the data can be wirelessly transmitted to the avionics display system 10, describing the use of other manned A/C, unmanned A/C (e.g., UAV or drone), satellite, or capable of collecting such data. Additional thermal image data of the fire-affected area collected by ground-based resources.

[0017] With continued reference to FIG. 1, the native data source 16 includes a number of on-board sensors and other components suitable for collecting data utilized in implementing the processes described herein. The specific types of data collected by the local data source 16 and provided to the controller 12 will vary among different embodiments of the avionics display system 10. Generally, the local data source 16 will include a number of flight parameter sensors 38, which supply data to the controller 12, which describe the various local A/C used in generating the avionics displays 28, 32 Operating status. The data provided by the local data source 16 can include without limitation: airspeed data listed as just a few examples; ground speed data; altitude data; attitude data, including pitch data and roll data; yaw Data; geographic location data, such as global positioning system (GPS) data; data related to total A/C weight; time/date information; heading information; data describing current and forecast atmospheric conditions, such wind speed and direction measurement results ; Flight path data; tracking data; radar altitude data; geometric altitude data; and data on fuel consumption. The local data source 16 may also include at least one thermal imaging sensor 36 capable of detecting fire heat signs. The thermal imaging sensor 36 may be, for example, an MMW radar or a forward-looking infrared camera located in a radome under the A/C or fixed to the A/C in other ways.

[0018] FIG. 2 is a diagram of an exemplary CVS 40 generated on one of the avionics display devices 14 during operation of the avionics display system 10 (FIG. 1) as illustrated in accordance with an exemplary embodiment of the present disclosure. Screenshots. CVS 40 generally corresponds to the 3D avionics display 28 shown in Figure 1, but uses different reference numbers to emphasize the 3D avionics

The display 28 does not need to take the form of CVS in all embodiments. As indicated in Figure 2, the CVS 40 is generated in the format of a 3D perspective view as seen from the vantage point of the A/C cockpit. In another embodiment, the CVS 40 may be generated from other vantage points, such as the vantage point of the virtual chasing aircraft behind the local aircraft A/C. Combine two images to produce CVS 40: EVS image 42 and synthetic vision system (SVS) image 44 of the synthetic vision primary flight display (SV-PFD). EVS image 42 is combined with SVS image 44 or integrated into SVS image 44 ( For example, a smaller centralized image that is scaled, aligned, and mixed with), the SVS image 44 is larger in scope. The EVS image 42 is generated using real-time thermal imaging data captured by the thermal imaging sensor 36 (FIG. 1). In comparison, the SVS image 44 is generated using information contained in a terrain database, a navigation database, or a similar database included in the database 22 stored in the memory 20 (FIG. 1).

[0019] When a graphic that visually refers to the area of the CVS 40 covered by the EVS image 42 is generated on the CVS 40, such a graphic is generally referred to herein as an "EVS window." An example of such an EVS window 45 is shown in FIG. 2, and is generated as a dashed frame or other boundary graphics referring to the boundary of the SVS image 44. Additionally or alternatively, light blocking or similar visual effects may be applied on the EFV image 42 shown on the CVS 40 to visually distinguish the display area covered by the image 42 from the wider SVS image 44. Therefore, as it appears in this article, the term "EVS window" is used to broadly refer to one or more graphical elements or visual effects that visually distinguish the display area covered by the EVS image (for example, the EVS image 44) from the display area covered by the EVS image (for example, the EVS image 44). Large display image, such as SVS image 44 of CVS 40.

[0020] In addition to the air firefighting symbols or graphics described below, the CVS 40 may also include other graphic elements that visually convey relevant flight parameters to the pilot or crew member. Such additional graphic elements are well known in the avionics industry, and may include horizontal position indicator (HSI) graphics, attitude guidance indicator (ADI) graphics, and airspeed indicator graphics listed as just a few examples , Altitude indicator graphics, flight path vector (FPV) markers and barometric pressure readings. Many of these figures are not shown in Figure 2 to avoid unnecessarily obscuring the drawing. However, several such graphics are shown for context in FIG. 2 and include FPV marks 48 and ADI graphics 50, 52, 54. During operation, the FPV marker 48 moves across the FOV of the CVS 40 to indicate the current flight path of the aircraft A/C. Similarly, the ADI graphics 50, 52, 54 are updated as appropriate to reflect the change in the posture of the native A/C. In the illustrated example, the ADI graphics 50, 52, 54 include the ADI A/C symbol 50 in the form of two L-shaped polygons, a zero pitch reference line 52 and a pitch tape graphic 54_o

[0021] The CVS 40 is further generated to include an aerial firefighting symbol 56 that visually conveys information related to the fire-affected area near the aircraft A/C to the pilot (or other viewers of the CVS 40) . In the illustrated example, the aerial firefighting symbol 56 includes graphics representing multiple active flammable areas or fire zones. Seven fire zones are shown in the current FOV of CVS 40 and SVS scene 44, as represented by fire zone graphics 58 (a)-(g). Despite this example, depending on a given fire distribution, multiple fire zone graphics may not always appear on the CVS 40. For example, in the case of a structural fire, such a structural fire consumes one or more floors of a high-rise building, a single fire zone graphic may appear on the CVS 40 depicting a single fire. In addition, the avionics display system 10 revises the fire zone graphics 58 on the CVS 40 in accordance with changes in the fire distribution, as indicated by the latest version of the fire map stored in the memory 20 (FIG. 1). Therefore, the fire zone graphics 58(a)-(g) may seem to merge, separate, and change in other ways as the real-world fire distribution evolves over time.

[0022] The fire patterns located within the current FOV of the thermal imaging sensor 36 are advantageously generated to have a changing appearance with respect to those fire areas located outside the sensor FOV but within the current FOV of the CVS 40. For example, and as indicated in FIG. 2, those fire areas (or fire area portions) included in the EVS image 42 and covered by the EVS window 45 may visually represent the real-time thermal image data recorded by the thermal image sensor 36, And thus seems to actively burn or have application in

Its a flame-like animation. In contrast, those fire areas located outside the EVS image 42 can be represented by static graphics (for example, relatively thick border lines), which are mapped onto the 3D SVS terrain of the SVS scene 44. In particular, consider the fire zone pattern 58(b) shown in FIG. 2. As can be seen, the leftmost part of the graphic 58(b) resides outside the EVS image 42 and is drawn as a thick boundary line in a static or non-animated format. In comparison, the rightmost part of the graph 58(b) extends into the EVS image 42 and is generated to reflect real-time thermal sensor data, which depicts the active burning fire line mapped onto the 3D SVS terrain.

[0023] In the manner described above, the CVS 40 enables the pilot to quickly distinguish those areas of the displayed fire map that are located within the current FOV of the thermal imaging sensor 36 (and thus represent the real-time thermal imaging data captured by the sensor 36) and Those areas of the displayed fire map that are located outside the current sensor FOV (and thus represent the stored fire map data). This is highly useful in the context of aerial firefighting. Additionally, CVS 40 provides pilots and other crew members with a clear, visual representation of the A/C flight environment, which can be significantly different from the view seen from the A/C cockpit under actual or real-world conditions. This can be appreciated by briefly comparing the screenshot of the CVS 40 shown in FIG. 2 with the corresponding real world view as seen from the A/C cockpit and shown in FIG. 3. As shown in Figure 3, the real-world cockpit view is due to the time of day (for example, night operation), instrument meteorological conditions, and/or significant amounts of smoke, ash, or other airborne particulate matter in the airspace surrounding the fire-affected area The existence within is obscured by poor visibility conditions.

[0024] Embodiments of the avionics display system 10 may further generate one or more 2D avionics displays that are enhanced to include aerial firefighting symbols. The 2D avionics display can be produced as a vertical navigation (VNAV) display, such as a vertical position display (VSD); a horizontal navigation (HNAV) display, such as a 2D moving map display; a multi-function display (MFD), etc. To further illustrate this point, FIG. 4 shows a screenshot of an exemplary HNAV display 70, which may be generated by the avionics display system 10 concurrently with a 3D avionics display such as CVS 40 (FIG. 2). The local A/C icon 72 indicates the current horizontal position (longitude and latitude) of the local A/C within the geographic area 74 covered by the HNAV display 70. The aerial firefighting symbol 76 is further generated on the HNAV display 70, and includes a plurality of fire zone graphics 78, which represent the active combustion zone within the FOV of the HNAV display 70. Here, eight fire zones are shown and identified by fire zone graphics 78 (a)-(h). The fire area graphics 78(a)-(h) can be distinguished from other topography included in the geographic area 74 through shading, application of fill patterns, or similar visual effects. If desired, the boundaries of the fire zone graphics 78(a)-(h) may be delimited by relatively thick boundary lines or otherwise indicated visually on the HNAV display 70.

[0025] The HNAV display 70 also includes at least one graphic or icon 80 that identifies the FOV of the SVS image 44 contained in the CVS display 40 (FIG. 2). The icon 80 may be generated as a triangular icon including two wedge-shaped line graphics 82 that converge toward the local A/C icon 72. In this example, the angle between the wedge line icons 82 refers to the extension of the SVS FOV and the extension of the sensor FOV. In an embodiment where the extension of the SVS FOV and the sensor FOV changes, the icon 80 can be changed accordingly. The arc-shaped dashed line 84 is further provided to visually refer to the distance or depth of the sensor FOV. The triangular icon 80 extends beyond the arc-shaped dashed line 84 to further encompass the expanded area 86. The expanded area 86 thus represents a spatial volume further shown in the SVS image 44 and covered by the EVS window 45, but extending beyond the current FOV of the thermal imaging sensor 36. The controller 12 of the avionics display system 10 may further visually distinguish those parts of the fire zone located within the sensor FOV from those parts of the fire zone located outside the sensor FOV but within the display FOV. For example, as indicated by the change in the cross-hatching pattern in Figure 4, those parts of the fire image residing within the sensor FOV can be color-coded as a first color (for example, red or amber); in SVS Those parts of the fire diagram inside the F0V but outside the sensor F0V can be color-coded as a second color (for example, amber); and the SVS F0V outside

Those parts of the partial fire diagram can be generated in a third color (for example, blue, white, or green). In other embodiments, different changes in the visual appearance of the fire graphic can be visually applied to those areas of the fire graphic located within the sensor FOV, such as the opacity of the fire area graphic 78(a)-(h) or Transparency changes.

[0026] With continued reference to FIG. 4, the HNAV display 70 is generated to further include a fire alarm envelope graphic 88, which surrounds the local A/C icon 72 and may be centered on the local A/C icon 72 . The fire alarm envelope graphic 88 identifies the boundary of the visual fire alarm envelope, which surrounds the machine A/C and is designated as a fire buffer or designated fire-free zone into which fire encroachment should be prevented to the extent possible. In some embodiments, the fire alarm envelope represented by graph 88 (FIG. 4) may be defined by a predetermined radius around the current horizontal position of A/C. In this case, the radius can be selected based on the A/C type, the thermal resistance of the A/C component, and other factors. In other embodiments, the fire alarm envelope may have a more complex symmetrical or asymmetrical 3D shape. Additionally or alternatively, the boundaries of the fire alarm envelope can be actively adjusted in response to changes in any number of dynamic factors, such as local temperature, wind speed, and/or fire propagation parameters (eg, measured or predicted fire propagation Speed and direction). In some cases, the boundaries of the fire alarm envelope can also be adjusted based on the Α/C location (altitude, latitude, and longitude). Regarding altitude, in particular, the current above ground level (AGL) altitude of the local machine A/C may be considered in adjusting the fire alarm envelope boundary to adapt to changes in terrain altitude. In further implementation In an embodiment, the shape and/or dimension of the fire alarm envelope can be adjusted by pilot input, by the A/C owner, by the original equipment manufacturer (OEM), or other such entities. In an embodiment in which a graphic representing the boundary of the fire alarm envelope is generated on the HNAV display 70 (or another avionics display), such graphic may be repeatedly or continuously adjusted to reflect the boundary of the fire alarm envelope Such changes. Thus, in some embodiments, the radius and/or shape of the fire alarm envelope graphic 88 shown in FIG. 4 may be changed or changed as appropriate to reflect any adjustments to the fire alarm envelope boundary in real time.

[0027] The appearance of the fire alarm envelope graphic generated on one or more avionics displays generated by the avionics display system 10 will vary among the embodiments. In the embodiment shown in FIG. 4, the fire alarm envelope graphic 88 is generated as a circular mark, which may be overlaid with a partially transparent pattern or filled color. In some implementations, the appearance of the fire alarm envelope graphic 88 can be modified as appropriate to generate visual alarms useful in the context of aerial firefighting. For example, when the avionics display system 10 detects the occurrence of a fire-related alarm event, the shadow of the fire alarm envelope graphic 88 can be changed from a pre-established information color (for example, white or green) to a pre-established reminder or warning color (For example, amber or red). For example, if it is determined that a fire has encroached into the fire alarm envelope represented by the graphic 88, the avionics display system 10 may generate such a visual alarm on the HNAV display 70. Additionally or alternatively, when it is determined that there is no undesirable fire exposure (such as fire encroachment into the fire alarm envelope represented by graph 88), the local machine A/C can no longer be in the forward direction When advancing or continuing to advance on the current flight path (if there is a significant yaw in the case of the rotor A/C), the avionics display system 10 may generate such an alarm.

[0028] The avionics display system 10 may be based on the current A/C position, A/C flight parameters (for example, track, airspeed, altitude, etc.), current wind speed and direction measurement results, terrain topology, and stored fires. The map indicates the fire distribution, fire vector information (for example, the rate and direction of fire spread), etc. to determine whether the above-described alarm conditions are met. In other embodiments, the avionics display system 10 may generate visual alerts on the HNAV display 70 (FIG. 4) and/or CVS 40 (FIG. 2) in different ways. For example, and briefly returning to FIG. 2, a text announcement 90 may be generated on the CVS indicating an alarm condition and perhaps suggesting a response action (eg, the climb of rotor A/C). If so desired, various other audible and/or tactile alarms can also be generated in combination with such visual alarms. In a further embodiment, multiple fire alarm envelopes can be built around the local aircraft A/C and used to display the avionics (multiple) generated by the avionics display system 10.

A series of hierarchical alarms are generated on the sub-learning display, which vary in severity depending on the urgency of the fire alarm condition.

[0029] When located in an area affected by a fire or flying into an area affected by a fire, the embodiment of the avionics display system 10 can further monitor the fire escape route available to the local machine A/C. In one embodiment, the avionics display system 10 continuously monitors the availability of at least one substantially level fire escape route; that is, the fire escape route or path available to A/C, which avoids the fire (or The undesirable A/C exposure to the highly elevated heat level caused by the fire does not require the native A/C to climb by more than a threshold amount. As an example, the avionics display system 10 can establish such a substantially horizontal fire escape route by repeatedly drawing or drawing the predicted horizontal path, which extends from the current position of the aircraft A/C to the fire-free area, and It avoids fire encroachment into the fire alarm envelope described above. In continuously seeking and monitoring the continuous availability of such a basic level of fire escape route, the controller 12 of the avionics display system 10 may consider various factors or parameters, such as the current fire distribution indicated by the fire map route. , The boundaries of the fire alarm envelope, wind direction and speed, nearby flying obstacles, elevated terrain topology, fire escapes (for example, water bodies or areas without plants), and other such information. Additional ground, aviation electricity The sub-science display system 10 can further consider the predicted weather conditions and fire parameters, such as based on the current fire location, wind speed and direction, the nearest direction and speed of fire movement, terrain topology, and any fire escapes near the machine A/C. The expected distribution of fires in the near future.

[0030] When the controller 12 of the avionics display system 10 identifies at least one satisfactory substantially horizontal fire escape route, a corresponding graphic that visually identifies the fire escape route may be presented in the aviation system generated by the system 10. One or more of the electronics displays. An example of the fire escape route graphic 92 generated on the HNAV display 70 is shown in FIG. 4 and generated as a dashed color coded to the information color (eg, white or green). In other embodiments, the fire escape route graphic 92 may be generated to have a different appearance (for example, the appearance of a corridor) and/or may be generated on a different avionics display; for example, in addition to the one generated on the HNAV display 70 In addition to the graphic 92 or instead of the graphic 92 generated on the HNAV display 70, the graphic indicating the fire escape route can also be generated on the CVS 40. In addition, when it is desired to generate a visual alarm on the HNAV display 70, the appearance of the fire escape route graphic 92 can be selectively modified; for example, when the alarm conditions described above are met, the color of the fire escape route graphic 92 can be changed to pre-established Warning or reminder color. Finally, in embodiments in which multiple substantially horizontal fire escape routes are identified by the avionics display system 10, a single preferred or optimized fire escape route may be presented on the HNAV display 70 to prevent display clutter. such The preferred fire escape route can be selected based on any number of criteria, such as estimated pilot workload, fuel efficiency, proximity to other A/Cs, lateral separation between the local A/C and the fire zone, etc.

[0031] One or more avionics displays generated by the avionics display system 10 (FIG. 1) may be enhanced to include further airborne firefighting symbols or graphics. Such additional fire protection symbols may include a visual indication of the local fire temperature, as indicated by the most recent version of the fire map stored in the memory 20. In one embodiment, color coding can be used to indicate the average temperature of the fire zone; for example, as indicated by different cross-hatch patterns in Figure 2, the fire zone graphic 58 (a) in the lower left corner of the CVS 40 can be Generated in a different color relative to the fire zone graphics 58(b)-(e) to indicate that the area covered by the graphics 58(a) has more than the area covered by the graphics 58(b)-(e) Higher average temperature. The avionics display(s) can also be generated to include symbols that indicate the movement of the fire, such as the speed and direction of fire propagation. The fire propagation indicator can be generated to reflect the measured fire propagation metrics, the predicted fire propagation, or a combination thereof. An example of such a graphic is shown in Figure 4, where arrow 94 refers to the direction (as indicated by the arrow orientation) and speed (as indicated by the arrow size) of the fire movement of the fire main body represented by the fire zone graphic 78(c) ).

Such visually conveyed fire propagation information can help the pilot anticipate the fire movement relative to the A/C position of the aircraft and plan accordingly.

[0032] Further aerial firefighting symbols can be generated on the HNAV display 70, on the CVS 40 and/or on another avionics display. For example, graphics (eg, shaded areas 96 further shown in FIG. 4) may provide for demarcation of airspace areas occupied by relatively dense clouds of airborne particulate matter (such as smoke or ash). This can be useful for pilots in planning air firefighting operations, because such areas of dense airborne particulate matter are desirably avoided by the native A/C; for example, to maintain visibility from the A/C cockpit and/or Avoid the A/C engine swallowing excessive foreign matter (FOD). If desired, a graphic indicating the range limit of the thermal sensor can be generated on the CVS 40 and/or HNAV display 70; for example, a text notice 98 identifying the horizontal and vertical sensor range limit can be generated in the SVS window 45 of the CVS 40, such as Shown in Figure 2. As a further possibility, the graphic 100 (Figure 4) referring to the location of the water resources can be marked on the HNAV display 70 and/or the CVS 40. Similarly, if, for example, such water resources are located outside the current display FOV, the location of nearby water resources may be indicated on the HNAV display 70. The arrow diagram 102 further shown in FIG. 4 demonstrates this possibility. The location of nearby water resources can be retrieved from the terrain database included in the database 22, using The thermal imaging sensor 36, the data received via the data link subsystem 24, or it is determined in another way.

[0033] The foregoing has thus provided multiple embodiments of an avionics display system for generating aerial firefighting symbols on an avionics display, which enhances pilot situational awareness and decision making during aerial firefighting operations. In an embodiment, the avionics display system includes an avionics display device, a thermal image sensor (for example, an infrared camera or MMW radar device) configured to detect thermal image data outside the machine, and an avionics display device that is operatively coupled to the avionics Learn the controllers of display devices and thermal image sensors. During the operation of the display system, the controller is configured to: (i) compile a fire map of the fire-affected area near the machine A/C; and (ii) generate the first avionics display on the avionics display device, Include symbols that indicate the FOV of the thermal imaging sensor and the part of the fire diagram outside the FOV of the thermal imaging sensor. In an embodiment, the controller may compile a fire map by recording and compiling thermal imaging data when the FOV of the thermal imaging sensor is scanned across the area affected by the fire. Fire maps can also be compiled from thermal imaging data provided by external sources, such as other manned A/C, unmanned A/C, or satellites. The avionics display may be a 3D avionics display, such as a CVS display including an EVS window referring to the sensor FOV. Additionally or alternatively, the avionics display system may generate a 2D avionics display, such as an HNAV display, which includes a wedge-shaped line or other triangular figure representing the sensor FOV.

[0034] Although at least one exemplary embodiment has been presented in the foregoing specific embodiments, it should be appreciated that there are a large number of variations. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. More precisely, the foregoing specific embodiments will provide those skilled in the art with convenient road maps for implementing exemplary embodiments of the present invention. Various changes may be made in the function and arrangement of the elements described in the exemplary embodiment without departing from the scope of the invention as set forth in the appended claims.