REDUCTION OF THE VISUAL & AUDIBLE SIGNATURES OF THE UAV TO MINIMISE DETECTION DURING LONG DURATION SURVEILLANCE OPERATIONS

Abstract

The invention comprises of a UAV designed to limit visually contrast and audibility in flight for covert surveillance operations, a method of configuring the UAVs structure to further reduce its visual signature to take account for the atmospheric and terrestrial environment it will operate in and a method of conducting a covert surveillance operation to actively minimise the UAVs visual & auditory signature from the viewpoint of an individual under surveillance. Both passive and active illumination are used to reduce the visual signature of the UAV. The UAV is actively camouflaged using lighting techniques that utilises the limitations of the human visual system and the optical effects of light interacting with the terrain, atmosphere and aircraft. The visual camouflage is directional. The audible signature of the UAV is reduced through the design of the propulsion system and the mode in which the UAV is operated.

Claims

1. An unmanned aircraft (UAV) adapted to minimise visual and audible detection during flight that is comprised of: a flattened, angular shaped body; an angular shaped tail boom and tail; one or more motors for driving; one or more propellers; one or more wings; one or more light sensors capable of measuring the amount of visible light incident on UAV's surface; a camera; and a controller; wherein the one or more wings comprise an upper surface with an outside coating of diffuse dark coloured material, an internal surface of the upper surface comprising a high reflective lining, one or more light sources attached horizontally to the reflective lining on the upper surface pointing downwards when the aircraft is flying straight and level, a translucent or transparent lower surface and a diffuse translucent mesh attached to the internal surface of the lower surface.

2. The UAV according to claim 1, wherein the surface of the body is comprised of a number of angled trapezoid sections that are connected so that no surface is curved or at right angles to an adjacent surface.

3. The UAV according to claim 2, wherein the surfaces of the body are orientated relative to one another to minimise specular reflection.

4. The UAV according to claim 2, wherein the surfaces of the body are orientated relative to one another to minimise specular reflection from a view point of an observer viewing the UAV at an angle of 45° to the side of the body from a range of 1000 m where the body is at an altitude of 1000 m.

5. The UAV according to claim 1, wherein the upper surface of the body, tail boom and tail reflect light diffusely.

6. (canceled)

7. The UAV according to claim 1, wherein the lower surface of the body, tail boom and tail reflect light.

8-11. (canceled)

12. The UAV according to claim 1, wherein the light sources are wide beam LEDs.

13-20. (canceled)

21. The UAV according to claim 1, wherein the wing configuration is selected to match an initial assessment of the amount of light expected to be required for an operation, wherein obtaining the initial assessment comprises the steps of: a ascertain the colouration of the terrain over which the operation is to take place, gain the angle of the sun at the latitude of the operation and the expected atmospheric conditions; b calculate the amount of ground reflectance; c divide the ground reflectance by the reflectance value for the underside of the aircraft and pi; d calculate the amount of light obscured by the aircraft; e the amount of light reflected by the aircraft is deducted from the amount of light obscured by the aircraft to give the net obscured light value; f the net obscured light value is then adjusted to obtain the amount of light that would be seen from an individual's viewpoint of the aircraft; and g where the solid angle subtended by the aircraft exceeds the solid angle resolvable by the human eye this value is multiplied by the result of the preceding step to give the amount of light needed to camouflage the aircraft to be emitted in the direction of the individual.

22. The UAV according to claim 1, wherein one light sensor is attached to the upper surface of the body and is capable of rotating horizontally by 360° and tilting vertically by 180°.

23. The UAV according to claim 22, wherein movement of the light sensor is undertaken by a gimbal

24. The UAV according to claim 1, wherein a light sensor is attached to the lower surface of the body in a fixed position pointing downwards.

25. The UAV according to claim 1, wherein a camera is attached to the lower surface of the aircraft body and is capable of rotating horizontally by 360° and tilting vertically by 180°.

26. The UAV according to claim 25, wherein movement of the camera is undertaken by a gimbal.

27. The UAV according to claim 25, wherein the camera can be manually controlled to focus on and follow an object or person at ground level.

28. (canceled)

29. The UAV according to claim 1, wherein the camera and the light sensor attached to the upper surface of the body are linked so as to maintain the orientation of the light sensor so that it points in the opposite direction by 180° to the centre of the camera's field of view.

30. The UAV according to claim 29, wherein the camera and upper light sensor are linked by a mechanical mechanism to maintain alignment.

31. The UAV according to claim 30, wherein the camera and upper light sensor are linked by a digital electronic mechanism to maintain alignment.

32. The UAV according to claim 1, wherein the controller is connected to the upper light sensor, the lower light sensor and the light sources, wherein the controller receives measurements of the amount of light incident on a surface from the upper and lower light sensors, the angle of the upper sensor calculates the amount of light to be emitted, and uses it to control the power to the light sources.

33. (canceled)

34. The UAV according to claim 32 wherein the controller is configured to calculate the amount of power required to actively illuminate the aircraft by: calculating the amount of light reflected by the aircraft from the ground reflection measured by the lower light sensor; deducting the amount of reflected light from the amount of background light obscured by the aircraft measured by the upper light sensor giving the net obscured light; multiplying the net obscured light by the surface area of the underside of the aircraft, the angle of the upper light sensor which is the angle of view of the aircraft by the individual and the solid angle of emitted light in the direction of the individual to give the emitted light; where the solid angle subtended by the aircraft exceeds the solid angle resolvable by the human eye, multiply the emitted light value by the solid angle subtended by the aircraft divided by the solid angle resolvable by the human eye; and converting the result of the calculation to a power value and set the power input to the light sources to this value.

35. (canceled)

36. (canceled)

Description

[0047] The invention is described by reference to the accompanying drawings and two embodiments:

[0048] FIG. 1 shows the physical illumination and reflectance paths modelled within the invention.

[0049] FIGS. 2a and 2b show the structural components of the UAV and the angular surface designed to reduce specular reflectance.

[0050] FIG. 3 shows a means of controlling the illumination emitted by the UAV to camouflage it from the viewpoint of an observer.

[0051] FIG. 4 show a cross section of a wing incorporating the illumination array where the upper wing surface is solid; and

[0052] FIG. 5 show a cross section of a wing incorporating the illumination array where the upper wing surface is transparent.

[0053] The first embodiment shown in FIGS. 2a and 2b is a UAV comprising of a body 201, removable wings 202, a tail boom 204 and twin tail fins 205. The body 201 is designed to have a flattened cross section comprising of several trapezoid surfaces 203. The cross section of the tail boom 204 is diamond shaped with two tail fin surfaces 205 angled downwards from the lower side. The surfaces' angles are designed to reduce specular reflection to a minimum when viewed side on at an angle of 45° at an altitude of 1000 m and a distance of 1000 m. In sunlight this ensures that glint from the edges is reduced.

[0054] A propeller and electric motor 206 are fitted to the body. These are chosen to be efficient and quiet in operation to reduce the auditory signature of the UAV. All upper surfaces of the fuselage are painted a matte grey and the propeller has a lighter matt grey coating.

[0055] FIG. 3 shows a cross section of one of the removable wings 302 attached to either side of the body 301. The wings are constructed with an upper 303 and lower 305 surface between which are a number of LEDs 304. The body 301 also hosts the equipment that controls the active camouflage aspects of the invention during flight.

[0056] The position and orientation of the camera 306 and background illuminance sensor 307 are shown in FIG. 3. Both upper sensor and the camera are attached to gimbals that allow them to rotate and tilt. These are linked 310 together so that a movement in the camera gimbal results in an equal but opposite movement in the sensor gimbal. The ground reflection sensor 308 is also attached to the body 301 in a position that does not obscure the field of view of the camera 306. It is angled downward towards the ground. The background illuminance sensor 307 and ground reflection sensor 308 are connected to microcontroller 309 which adjusts the power input to the LEDs 304 using the illuminance values measured by the sensors 307 & 308. The microcontroller implements the method described in the invention for active illumination to reduce the visual signature of the UAV in flight.

[0057] FIG. 3 references d, e, f, g show the path and direction of light illuminating and reflected by the UAV, previously described in relation to FIG. 1. FIG. 4 shows a cross section of the wing of the first embodiment comprising of an upper surface 401, a rib 402 and a lower surface 403. The UAV in this embodiment is intended to operate over highly reflective light-coloured terrain against a background of bright clouds. The upper surface 401 has a uniform matt grey covering and the lower surface 403 has a uniform translucent white surface. The inside of the upper surface is lined with a reflective layer 405 to which a strip of LED lights 404 are attached. The lower power, wide beam LEDs 404 are orientated downwards. The lower surface is made of two parts an outer translucent skin 403 and an inner mesh lining 406. The combination of the two parts diffuses the light from the LED so that they do not appear as point light sources but as a luminescent glow.

[0058] The second wing embodiment, shown in FIG. 5, is an alternate configuration of wing structure intended for use in dark overcast conditions. Both the upper 501 and lower 503 surfaces are made of a transparent, non-reflective material. This allows most of the sky luminescence to be seen through the UAV wing. The ribs 502 and spars are the only solid components that require visually camouflaged. The wing material changes the amount of blocked light used in step 2 of the method to compute the active illumination required. In this embodiment fewer light sources 504 are needed and they are attached vertically to each rib to disguise the solid structures within the wing. In all other respects the UAV is the same as that in the first embodiment.

[0059] It would be readily appreciated that in further embodiments, the aircraft comprises wings that are not removable but perform the same function as the removable wings 302 described above.