WO2008073069A2

WO2008073069A2 - Unmanned aerial vehicle

Info

Publication number: WO2008073069A2
Application number: PCT/US2006/032280
Authority: WO
Inventors: James Alman
Original assignee: CYBER DEFENSE SYSTEMS Inc
Current assignee: CYBER DEFENSE SYSTEMS Inc
Priority date: 2006-08-18
Filing date: 2006-08-18
Publication date: 2008-06-19
Anticipated expiration: 2009-02-18
Also published as: WO2008073069A3

Abstract

An unmanned aerial vehicle includes a fuselage, a horizontal stabilizer assembly, a wing assembly, a forward propulsion device, and at least one rear propulsion device. The fuselage has a forward end portion and a rearward portion. The horizontal stabilizer assembly has a left wing and a right wing. The wing assembly has a wing substantially aligned with and parallel to the horizontal stabilizer assembly. Upon activation, the forward propulsion device operates to provide thrust to assist in lifting the unmanned aerial vehicle. Upon activation, the at least one rear propulsion device is selectively rotatable ninety degrees so as to direct the thrust from the at least one rear propulsion device in one of a downward direction and a rearward direction. The forward propulsion device and the at least one rear propulsion device cooperate to provide a downward thrust resulting in the lifting of the unmanned aerial vehicle.

Description

UNMANNED AERIAL VEHICLE

CROSS-REFERENCE TO RELATED APPLICATIONS

[0001] The present application claims the benefit under 35 U. S. C. 119(e) of U.S. Provisional Application Serial No. 60/709,210, filed August 18, 2005. The entire content of which is hereby expressly incorporated herein by reference.

BACKGROUND OF THE INVENTION [0002] Field of the Invention

[0003] The present invention relates generally to aerial vehicles and more particularly, but not by way of limitation, to an improved unmanned aerial vehicle capable of vertical take-off and landing.

[0004] Description of the Related Art

[0005] Unmanned aerial vehicles (UAVs) are well known in the art. Unmanned aerial vehicles are commonly used for a variety of purposes such as for aerial surveillance and reconnaissance, combat, convoy protection, coastal surveillance, law enforcement, traffic and border control, search and rescue and other such activities.

[0006] It has long been an objective in the design of aerial vehicles to provide vertical take-off and landing (VTOL) aircraft that are capable of performing within an extended operational flight envelope, such as speed, distance and altitude ranges. Further, it is desirable for such vehicles to have the capability of effectively and efficiently transitioning from one flight mode to another flight mode (e.g. hover, slow flight, high-speed flight).

[0007] To this end, although UAVs of the existing art are operable, further improvements are desirable to enhance the VTOL capabilities of UAVs and provide such unnamed aerial vehicles with the ability to hover and perform high-speed forward flight. It is to such an UAV that the present invention is directed.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS [0008] Fig. 1 is a perspective view of an unmanned aerial vehicle constructed in accordance with the present invention.

[0009] Fig. 2 is a front elevational view of the unmanned aerial vehicle of Fig. 1. [0010] Fig. 3 is a top plan view of the unmanned aerial vehicle of Fig. 1. [0011] Fig. 4 is a side elevational view of the unmanned aerial vehicle of Fig. 1. [0012] Fig. 5 is a fragmental, elevational view of a rearward propulsion device rotatably mounted to the unmanned aerial vehicle of Fig. 1.

DETAILED DESCRIPTION OF THE INVENTION

[0013] Referring now to the drawings, and more particularly to Fig. 1 , shown therein is an unmanned aerial vehicle (UAV) 10 constructed in accordance with the present invention. The UAV 10 may be constructed of any material having sufficient strength and durability to enable the UAV 10 to function in the manner described herein. Suitable materials include metals such as aluminum, steel, titanium, magnesium or alloys containing these metals. Other suitable materials for construction include plastics, polymeric materials, and lightweight, high-strength composite materials. The UAV 10 is sized to be hand carried to desired locations. However, the UAV 10 may be any size provided that the UAV 10 functions in the manner described herein.

[0014] As shown in Figs. 1-4, the UAV 10 includes a fuselage 12, a horizontal stabilizer assembly 14, and a wing assembly 16. The fuselage 12 has a forward end portion 18, a forward or first bay 20 and a rearward portion 22. A camera or other such piece of surveillance equipment may be mounted in the forward end portion 18 of the fuselage 12. The forward bay 20 is formed between the forward end portion 18 and the horizontal stabilizer assembly 14 to adaptingly receive a forward propulsion device 24 in the forward bay 20. The forward propulsion device 24 is mounted in the forward bay 20 to cooperate with rearward propulsion devices to provide lift and hovering capabilities as well be described hereinafter. The angle at which the forward propulsion device 24 is disposed in the forward bay 20 can vary depending on the configuration of the UAV 10. However, desirable results have been obtained when the forward propulsion device 24 is mounted in the forward bay 20 at a downward and rearward substantially forty-five degree (45°) angle. The forward propulsion device 24 operates to provide thrust in a substantially vertical and rearward downward direction. [0015] As shown in Figs. 2-4, a yaw vane 28 is mounted in the forward bay 20 to provide yaw control. Additionally, a thrust deflector 30 is operably connected to the fuselage 12 to redirect the thrust from the forward propulsion device 24 so that the thrust is directed vertically downward.

[0016] Referring to Figs. 1 , 3 and 4, the rearward portion 22 of the fuselage 12 tapers inwardly to form a frustoconical portion 32 which is operably connected to the wing assembly 16. The fuselage 12 can be field configured with a wide variety of cameras, weapons and instruments. [0017] As shown in Figs. 1-3, the horizontal stabilizer assembly 14 includes a left wing 40 and a right wing 42. The left wing 40 of the horizontal stabilizer assembly 14 has a proximal end 43, a distal end 44, a front edge 45 and a rear edge 46. The proximal end 43 is operably connected to the fuselage 12. An aileron 47 is pivotally connected to the rear edge 46 of the left wing 40 for controlling the rolling and banking movements of the UAV 10 and to assist in providing lift to the UAV 10. The right wing 42 of the horizontal stabilizer assembly 14 has a proximal end 48, a distal end 50, a front edge 52, and a rear edge 54. The proximal end 48 is operably connected to the fuselage 12. An aileron 55 is pivotally connected to the rear edge 54 of the right wing 42 for controlling the rolling and banking movements of the UAV 10 and to assist in providing lift to the UAV 10.

[0018] Referring now again to Figs. 1-5, the wing assembly 16 includes a wing 60 spatially disposed from the horizontal stabilizer assembly 14 such that the wing 60 is substantially aligned with and substantially parallel to the horizontal stabilizer assembly 14. The wing 60 includes a forward portion 62 and a tail portion 64. The tail portion 64 has a pair of spatially disposed rear flaps 66 and 68 operably connected to the tail portion 64 so as to assist in providing lift to the UAV 10. Further, the tail portion 62 of the wing 60 has a pair of vertical stabilizers 70 and 72 centrally disposed near a rear end 74 of the tail portion 64 of the wing 60. The vertical stabilizers 70 and 72 cooperate with the tail portion 64 and the spatially disposed rear flaps 66 and 68 to form a recess 76 which functions as a rearward or second bay 78. The rearward bay 78 is adapted to receive and support a pair of rearward propulsion devices 80 and 82. The pair of rearward propulsion devices 80 and 82 are rotatably mounted to the vertical stabilizers 70 and 72 (Fig. 5); and the pair of rearward propulsion devices 80 and 82 are connected via a connector 84 so as to move dependent of one another. Although only the rearward propulsion device 82 is shown being rotatable in Fig. 5, it should be understood that both the rearward propulsion devices 80 and 82 are rotatable ninety degrees (90°) so as to direct the thrust from the rearward propulsion devices 80 and 82 in a downward direction and a rearward direction. When directed downward, the rearward propulsion devices 80 and 82 cooperate with the forward propulsion device 24 to lift the UAV upward. However, when directed rearward, as illustrated in Figs. 1-4 (and Fig. 5 in phantom), the rearward propulsion devices 80 and 82 propel the UAV 10 in a forward direction so long as the forward propulsion device 24 is shut down. It should be understood that any type and size of propulsion device known in the art may be used in the UAV 10.

[0019] The propulsion devices 24, 80 and 82 are controlled by an integrated onboard stability augmentation or gyro stabilized control system 84. As shown in Fig. 1 , the control system 84 includes a transmitter 86 and a receiver 88. The receiver 88 is positioned in the fuselage 12 and configured to receive a signal for controlling the propulsion devices 24, 80 and 82 as well as other onboard devices, such as cameras, sensors, and other equipment from the transmitter 86 which is positioned in a remote location. A portion of the control system 84 operates in a conventional manner similar to that of an autopilot in a helicopter. The operation of an helicopter autopilot is known to one of ordinary skill in the art, thus no further description of the control system 84 is believed necessary. Further, it should be understood that the cameras, weapons, sensors and other equipment may be controlled by the control system 84 remotely from the UAV 10 in a conventional manner.

[0020] In one embodiment, the UAV 10 and its payload are operated via radio frequency from a remote location. However, it should be understood that any known method of communication may be utilized in accordance with the present invention. Altitude, air speed, measure of fuel, video and other such information may be communicated to the user of the UAV 10. Each of the propulsion devices 24, 80 and 82 are equipped with an electronic on board starter that allows for a selected propulsion device to be shut down during flight. This allows the UAV 10 to conserve fuel by only operating the engines which are necessary thereby providing additional loiter time for the UAV 10 in long-range use. Further, it should be understood that the UAV 10 may be powered by gas, heavy fuel, electrical or any other such means known in the art for providing power to the UAV 10.

[0021] Additionally, as shown in Fig. 4, the UAV 10 includes a payload pod 90. The payload pod 90 is positioned under the wing 60 of the UAV 10 near the center of gravity of the UAV 10 thereby allowing a variety of payload weights to be carried by the UAV 10 without any vehicle reconfiguration. The payload pod 90 allows the UAV 10 to be adapted for various missions, such as being fitted for munitions and armaments or other such reconfiguration. Aerial surveillance equipment, radar jamming devices, and the like may be installed in the payload pod 90. In addition, it should be understood that the UAV 10 can be configured to incorporate additional systems and technologies by upgrading various system components. [0022] In use, the pair of rearward propulsion devices 80 and 82 are rotated so that the thrust is directed downward, as illustrated in Fig. 5. When the propulsion devices 24, 80 and 82 are activated, the forward propulsion device 24 cooperates with the pair of rearward propulsion devices 80 and 82 to provide thrust to lift the UAV 10 in an upward vertical direction. During take-off, the control system 84 adjusts the thrust provided by each of the propulsion devices to maintain the UAV 10 in a level position. Once the UAV 10 has obtained the desired altitude, the pair of rearward propulsion devices 80 and 82 are rotated 90° (as shown in Figs. 1-4 and in phantom in Fig. 5) so that the thrust is directed rearward from the UAV 10 which in turn propels the UAV 10 in a forward direction. At this point, the forward propulsion device 24 may be shut off. The wings 40 and 42 of the horizontal stabilizing assembly 14 and the wing 60 of the wing assembly 16 provide the lift necessary to maintain the UAV 10 in an airborne condition. [0023] While in flight, if a hovering position is desired for stationary observation or other such activity, the forward propulsion device 24 is activated, thus providing a downward and rearward thrust which slows the UAV 10. The pair of rearward propulsion devices 80 and 82 are rotated from the rearward direction to the downward direction (Fig. 5) such that the thrust is directed downward, thus cooperating with the forward propulsion device 24 to maintain the UAV 10 in the hovering position. The UAV 10 may land from the hovering position, however, it should be understood that the UAV 10 is also capable of taking-off and landing in a conventional manner. [0024] From the above description, it is clear that the present invention is well adapted to carry out the objects and to attain the advantages mentioned herein as well as those inherent in the invention. While presently preferred embodiments of the invention have been described for purposes of this disclosure, it will be understood that numerous changes may be made which will readily suggest themselves to those skilled in the art and which are accomplished within the spirit of the invention disclosed.

Claims

What is claimed is:

1. An unmanned aerial vehicle, comprising: a fuselage having a forward end portion, a rearward portion and a first bay positioned between the forward end portion and the rearward portion; a horizontal stabilizer assembly having a left wing and a right wing wherein each of the left wing and right wing have a proximal end and a distal end wherein each proximal end is operably connected to the fuselage; a wing assembly having a wing substantially aligned with and parallel to the horizontal stabilizer assembly, the wing having a forward portion and a tail portion wherein the forward portion is operably connected to the fuselage and wherein the tail portion having at least one spatially disposed rear flap and at least one vertical stabilizer near a rear end of the tail portion of the wing; a forward propulsion device wherein the first bay is configured to receive the forward propulsion device and wherein upon activation the forward propulsion device operates to provide thrust to assist in lifting the unmanned aerial vehicle; and at least one rear propulsion device wherein the tail portion is adapted to receive and support the at least one rotatably mounted rear propulsion device wherein upon activation the at least one rear propulsion device is selectively rotatable ninety degrees so as to direct the thrust from the at least one rear propulsion device in one of a downward direction and a rearward direction wherein the forward propulsion device and the at least one rear propulsion device cooperate to provide a downward thrust resulting in the lifting of the unmanned aerial vehicle and wherein the forward propulsion device is shut down, the at least one rear propulsion device is selectively rotated to a position for imparting forward movement to the unmanned aerial vehicle.

2. The unmanned aerial vehicle of claim 1 wherein surveillance equipment is mounted in the forward end portion of the fuselage.

3. The unmanned aerial vehicle of claims 1 or 2 wherein the forward propulsion device is mounted at a downward and rearward forty-five degree angle.

4. The unmanned aerial vehicle of claims 1-3 wherein an aileron is provided on a rear edge of each of the left and right wings of the horizontal stabilizer assembly for controlling the rolling and banking movements of the unmanned aerial vehicle.

5. The unmanned aerial vehicle of claims 1 -4 wherein the forward propulsion device operates to provide thrust in a vertically downward direction.

6. The unmanned aerial vehicle of claims 1-5 wherein a yaw vane is operably mounted in the forward end portion of the unmanned aerial vehicle, to provide yaw control.

7. The unmanned aerial vehicle of claims 1 -6 wherein a thrust deflector is operably connected to the fuselage to redirect thrust from the forward propulsion device so the thrust is directed vertically downward.

8. The unmanned aerial vehicle of claims 1-7 wherein the rearward portion of the fuselage tapers inwardly to form a frustoconical portion which is operably connected to the wing assembly.

9. The unmanned vehicle of claims 1-8 wherein the at least one vertical stabilizer cooperates with the tail portion and the at least one spatially disposed rear flap to form a recess which is adapted to receive and support the at least one rear propulsion device.