Rapid assembly aircraft for ground surveillance

RAPID ASSEMBLY AIRCRAFT FOR GROUND SURVEILLANCE

This invention relates generally to remotely controlled unmanned aircraft; and more particularly to hand launchable aircraft, the components of which are easily assembled in the field, or disassembled so as to fit in a small size package, the aircraft carrying sensor instrumentation for terrain surveillance. The aircraft is inherently stable and therefore simple to operate, and an autonomous deep-stall landing mode requires no piloting skills.

There is a need for small size aircraft of the type described, which will enable data transmission from a sensor such as a television camera carried on board the aircraft, the data to be transmitted by radio frequency, fiber optic cable, or similar means and received by a ground receiver, as for example at the point of launch. Such an aircraft must be capable of transport in a small size container to the point of launch, then quickly assembled and launched, for data retrieval.

Basically, such an aircraft, in accord with the presently preferred embodiment disclosed herein Includes:

a) a fuselage having a relatively enlarged size forward portion for equipment including television camera installation, and a relatively reduced size rearward portion, with vertical tail surface, capable of disassembly for packaging,

b) a propeller, electric motor drive therefor, and electrical battery means for energizing the motor, all carried by said fuselage forward portion,

c) a center wing panel having removable attachment to said fuselage forward portion to extend transversely relative thereto,

d) wing tips having removable attachment to opposite ends of said center panel to extend laterally therefrom,

e) a horizontal tall structure having limited travel from normal flight, but large travel for deep-stall landings,

f) whereby the center wing panel, wing tips and tail structure may be individually fitted ion the package, alongside the fuselage,

g) at least one of such removable attachments including Interfittable connections, for both structural and electrical connection.

Rate gyroscope feed-back control of rudder pivoting, in response to aircraft roll and/or yaw, enhances platform stability of the aircraft for optimum television surveillance of terrain.

Also provided is a package in which wing tips, center wing panel and tail structure are interfitted alongside said fuselage, the package length being substantially less than the overall fuselage length or wing span of the aircraft when assembled.

Typically the center wing panel and each of the wing tips have plug-in pin and socket, or snap fastener interconnection; and the tall structure removable attached to the fuselage rearward portion. Also, the fuselage rearward portion typically comprises a tail boom having removable attachment to the fuselage forward portion, automatically making electrical and mechanical connection for control of tail surfaces.

Further, a surveillance sensor is typically carried by the fuselage forward portion, and a communication link to and from ground equipment is in signal transmitting communication with the sensor. The sensor may comprise a television camera.

Such an aircraft may weigh as little as about five pounds; can be packed in a hand-carried container three feet long and one foot by one foot in cross section, carried to the field quite easily, for assembly of the components at the hand-launch site. Using a coded radio or video link, or a fiber optics cable for FM or AM data transmission, the signal is not detectable by others; and the aircraft is silent, small, and difficult to see at .elevations of 500 td 1000 feet.

These and other objects and advantages of the Invention, as well as the details of an illustrative embodiment, will be more fully understood from the following specification and drawings, in which:

DRAWING DESCRIPTION

Fig. 1 is a perspective view of an aircraft, and the package to contain its components;

Fig. 2 is a plan view of the Fig. 1 aircraft; through the aircraft fuselage forward portion, and also showing the fuselage rearward portion and tail fin; ______

Fig. 2A is a schematic side elevation taken through the aircraft fuselage forward portion, and also showing the fuselage reaward portion and tail fin.

Fig. 3 is a section taken on line 3-3 of Fig. 5;

Fig. 4A is a view taken on lines 4-4 of Fig. 3, and showing connection of fuselage rear and forward portions.

Fig. 4B is a sectional side view of the forward fuselage contents, consisting of control equipment, battery power supply, electric motor propulsion and sensor package with radio frequency or fiber optic down link transmitter;

Fig. 5 is a plan view showing wing tip and wing center panel interconnection;

Fig. 6 is a side view showing stabilizer and fuselage rear portion interconnection;

Fig. 7 is a plan view schematically showing disassembled components of the aircraft;

Fig. 8 is a side elevation showing interfitting of the Fig. 7 components in a package;

Fig. 9 is an enlarged vertical section taken through a pylon and wing center section interconnection;

Fig. 9a is a side elevation showing center wing panel rearward stop connection to a pylon;

Fig. 10 is a control circuit block diagram; and

Fig. 11 is a side elevation showing rate gyroscope tilted mounting to the aircraft.

DETAILED DESCRIPTION 10

In the drawings, the manually launchable aircraft 10 is adapted to be assembled from components as shown in Fig. 7, and that fit closely together in a package 11, as viewed in Fig. 8. That package is substantially shorter in length 15 1 (as for example about 3 feet) than the overall wing ' span w (for example about 9 feet) of the assembled aircraft. In Fig. 7, the components include a fuselage having a relatively enlarged volume section 13, and a relatively reduced size rearward portion 14 with a vertical 20 tail 30.

Also, the components include a center wing panel 18 that is laterally oriented relative to the longitudinal fuselage portions, the panel 18 having removable attachment to the fuselage forward portion via the top 19a of a pylon 25 19 on that portion. See Fig. 9a showing a U-shaped bracket

120 attached at 121 to top 19a. A forwardly elongated tongue 122 closely slidably fits rearwardly into bracket 120, the tongue being integral with the underside of the center wing panel 18. As seen in Fig. 9a, a forward facing 30 stop 123 on the pylon engages shoulder 124 on the tongue to position the panel 18 on the pylon. Propeller 15 and electrical motor drive 16 are carried by the panel 18, and contacts 126 and 127 make up on the panel 18 received on the pylon to electrically connect lithium battery 17 with 35 the drive 16. Wing tips 20a and 20b have plug-in removable attachment to the opposite ends 18a and 18b of the panel 18 to provide dihedral. See for example the pin and socket connections at 21 and 22, and 23 and 24 shown in Fig. 5. The pins are anchored in 18a and are received in metal sleeves 23 and 24 anchored in 20b. See also Fig. 7. Rechargeable batteries can be used.

Further, the components include a horizontal stabilizer 25 having attachment to the fin 30 and pivoted at 61 to the stabilizer and rotated by a strut 21 displaced endwise by a servo motor 30a located in the base of fin 30. The flying surfaces 18, 20a, 20b, 25, and 30 may typically consist of high strength-to-weight fibers and plastics, which may be foamed.

The fuselage rearward portion, and particularly tail boom 32, has removable attachment to the fuselage forward portion, as for example plug-in 33 attachment to socket 33a formed by the fuselage forward portion. See Fig. 4A. Make-up electrical pin and socket connections at 64 and 65, and 64' and 65' prevent relative rotation of 32 and 33. Vertical tall fin 30 is attached to the tail boom, as shown. The rudder 31 may have hinged attachment to the fin 30, at 34, to pivot about a vertical hinge axis, and is pivotally actuated by a rotary solenoid 39 in the base of fin 30. A strut 67 connects the solenoid to a bell crank 68 attached to the rudder to guide the aircraft. Electrical control wires at 164 and 165, and at 164' and 165' for the motors 30a and 39 extend in 13 and 14 (see Fig. 4a) and to make up electrical pin and socket connection 64 and 65, and 64' and 65'.

The invention also contemplates the provision of a sensor 40, as for example a television camera, carried by the fuselage forward portion and aimed toward the ground to help navigate the aircraft and detect installations and targets; as well as provision of a link communication system which typically comprises a radio freguency transmitter 41, or alternatively a fiber optic umbilical cable 42, placing the aircraft in signal transmitting communication with a ground based receiver 43, control unit 44, and TV monitor 45 having a head shroud 46. A spooling bobbin for cable 42 may also be located at 41. A ground controller 44, including flight control stick 44a is connected with transmitter 18 that transmits signals to receiver 20 on the craft, which controls the motor drive 16 as well as flight control actuators 30a and 39, via circuit leads 164 and 165 on the fuselage. Propeller 15 driven by 16, rotates at the rear of section 18, and above the tail boom, as shown.

A stability augmentation gyro and motor throttle control appears at 80, for controlling flight without pilot connection. That gyro may comprise a rate gyroscope for controlling the rudder, via the control circuit shown in Fig. 10. The control stick 44a transmits rudder control signals via radio link 44 and 68 to receiver 20 on the aircraft. The gyro is connected at 81 with the receiver, and its output is connected at 164' and 165' with the rudder and elevator actuators 39 and 30a. The gyro is carried by the fuselage forward portion, as in Fig. 11.

As shown in Fig. 11, the aircraft has a principal axis 150 which extends forwardly, as shown, through the fuselage. Aircraft yaw axis 151 is normal to axis 150, and intersects it at 152. The rate gyroscope 80 is mounted on the aircraft at or near 152, and has its axis of sensitivity 80a tilted forwardly from axis 151 at ah angle β, which is between 10’ and 50*. Accordingly, the rate gyroscope is responsive to roll of the aircraft about axis 150 to produce a first output that varies with the degree of roll; also, the rate gyroscope is responsive to yaw of the aircraft to produce a second output that varies with the degree of yaw. Since the aircraft is Intended to provide a stable platform for the television camera (defeated by roll and by yaw) and since yaw is generally preceded by roll, the control system optimally senses incipient yaw, and corrects the same. In this regard, the gyro first and second outputs referred to are connected in feedback relation with the rudder actuator 38 to cause the rudder to pivot and counteract the sensed roll and/or yaw. Manual input via stick 44a overrides the gyro output. The two gyro outputs can be a vectored single output.

Note that the aircraft has no ailerons on its wings to control for roll; and that the aircraft wing has substantial dihedral, enabling rate gyro control of stability using rudder control only.

Unusually advantageous features of the invention include:

a) robust, lightweight construction manufactured from fiber-reinforced and foam plastic;

b) collapsibllity of components to fit in a packaged box;

c) simple rudder and elevator control with stability augmentation gyro and motor throttle control;

d) protection of propeller at rear of wing;

e) radio control — or fiber optic control link;

f) stability augmentation gyro; capable of flight without pilot mechanism;

g) hand launch capability by single operator from unprepared terrain without need for launching equipment;

h) electric drive, with long shelf life, ease of starting; and on-off capability in flight for silent operation;

1) television surveillance of terrain capability, with signal transmission to ground receiver via coded radio frequency or fiber optic cable, so signal not detectable by others;

j) deep-stall recovery for stable vertical descent on unprepared terrain with high probability of undamaged landings.

Accordingly, a terrain surveillance,powered aircraft is provided to have an on-board video camera that is not gimballed relative to the aircraft, the aircraft typically comprising multiple components. The method of its operation Includes

a) assembling the components into aircraft configuration at or near a launch site,

b) launching the aircraft at the site with no human pilot on board same,

c) remotely controlling the flight path or the aircraft by radio or cable link, to fly to a location for terrain surveillance,

d) operating the on-board video camera to survey the terrain while varying yaw of the aircraft to provide sweep viewing of the terrain,

e) and recovering the aircraft by controlling its flight to steeply descend to a landing zone.

Typically, the launching step comprises hand launching; and control of aircraft flight to steeply descend includes deep stalling of the aircraft toward a target recovery zone. The aircraft typically Includes a wing and an electrically driven propeller, and said assembling of the components includes installing of said propeller at a rearward location relative to the wing. Assembling of the components typically includes providing the wing with wing tip portion dihedral, between 5 and 8 degrees.

Operation also typically includes viewing, at a ground control station, the terrain being surveyed by the camera and while varying the yaw of the aircraft; and transmitting the video output of the camera, by video link, to a video receiver at the ground control station. That station may be operated in a hand-held mode during video link transmission. The method further typically includes installing a gyroscope on the aircraft to have its sensitive axis tilted relative to the aircraft and to control the rudder of the aircraft in feed-back control 5 mode, thereby to minimize wind induces rolling and yawing of the aircraft, during video camera survey of the terrain.