CN114802711A - Unmanned aerial vehicle with single duct at tail part - Google Patents

Abstract

The invention provides a tail single-duct propulsion unmanned aerial vehicle, relates to the technical field of unmanned aerial vehicles, and solves the technical problem that the unmanned aerial vehicle in the prior art is single in movement mode. The device comprises a fuselage, a tail duct device, wings and a driving device, wherein the tail duct device is connected with the tail of the fuselage, the side wall of the fuselage is detachably connected with the wings, the wings are close to the tail duct device, the driving device is arranged in the fuselage, and an output shaft of the driving device is connected with the tail duct device; the tail duct device comprises a variable pitch propeller mechanism, a steering mechanism and a shell, the shell is connected with the machine body, the variable pitch propeller mechanism is located in the shell, an output shaft of a driving device is connected with the variable pitch propeller mechanism, the driving device can drive the variable pitch propeller mechanism to rotate, the steering mechanism is installed in the shell, the steering mechanism and the machine body are respectively located on two sides of the variable pitch propeller mechanism, and the steering mechanism can swing.

Description

Unmanned aerial vehicle with single duct at tail part

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a tail single-duct propelling unmanned aerial vehicle.

Background

The unmanned aircraft is widely applied to the military and civil field since birth as an unmanned aircraft with high flexibility, wide application scene and simple operation, and plays an important role in aspects such as reconnaissance, positioning, transportation, routing inspection, aerial photography and the like. The existing unmanned aerial vehicle can be divided into a running and landing type unmanned aerial vehicle and a vertical landing type unmanned aerial vehicle, the former adopts a fixed wing layout, needs to be launched and landed through ground running, hand throwing or a special launching device, and the latter can realize vertical landing and horizontal flight through a special layout form, so that the application range is wider.

The vertical take-off and landing unmanned aerial vehicle put into use at the present stage can be divided into two types, one type is a thrust directional type, the flight speed direction of the aircraft is perpendicular to the rotary shaft of the rotor, and the thrust generated by the blades is fixedly used as lift force or pulling force, such as the layout of a traditional helicopter, the layout of a fixed-wing rotor combined type, the layout of multiple rotors and the like. The other type is the thrust switching-over type, and the flying speed direction of this type of aircraft is parallel with the rotor rotation axis, and the thrust that the rotor produced both can be used as lift, also can act as the pulling force, and the effect of power effect can interconversion, for example tilt rotor overall arrangement, tilt duct overall arrangement, tailstock formula overall arrangement etc.. The ducted aircraft with the slipstream control surface as a thrust reversing type vertical take-off and landing unmanned aerial vehicle has the advantages of good safety and concealment, capability of taking off and executing tasks in non-aircraft carrier ships, border zones and urban complex environments, capability of vertically taking off and landing, hovering and flying, and becoming one of the hotspots for research and development of the existing unmanned aerial vehicle.

The applicant has found that the prior art has at least the following technical problems:

in the prior art, the existing unmanned aerial vehicle for vertical take-off and landing has the problems of single movement mode, complicated take-off and landing process and the like.

Disclosure of Invention

The invention aims to provide a tail single-duct propelling unmanned aerial vehicle, which aims to solve the technical problem that the unmanned aerial vehicle in the prior art has a single motion mode. The technical effects that can be produced by the preferred technical scheme in the technical schemes provided by the invention are described in detail in the following.

In order to achieve the purpose, the invention provides the following technical scheme:

the invention provides a tail single-duct propelling unmanned aerial vehicle which comprises a body, a tail duct device, wings and a driving device, wherein the tail duct device is connected with the tail of the body;

the tail duct device comprises a variable pitch propeller mechanism, a steering mechanism and a shell, the shell is connected with the machine body, the variable pitch propeller mechanism is located in the shell, an output shaft of the driving device is connected with the variable pitch propeller mechanism, the driving device can drive the variable pitch propeller mechanism to rotate, the steering mechanism is installed in the shell, the steering mechanism and the machine body are located on two sides of the variable pitch propeller mechanism respectively, and the steering mechanism can do swing motion.

Optionally, the steering mechanism includes a deflection plate, a diversion plate, a connecting shaft, and a driver, one end of the diversion plate is connected to the side wall of the connecting shaft, the other end of the diversion plate is connected to the inner wall of the housing, the diversion plate is connected to the deflection plate through the driver, and the driver can drive the deflection plate to swing.

Optionally, the number of the deflection plates, the number of the shunt plates and the number of the drivers are all multiple and consistent, all the deflection plates are distributed along the circumferential direction of the connecting shaft, all the shunt plates are distributed along the circumferential direction of the connecting shaft, and all the drivers are distributed along the circumferential direction of the connecting shaft.

Optionally, the interior of the flow distribution plate is a hollow structure.

Optionally, the deflector plate has an airfoil shaped cross-section.

Optionally, the tail duct device further comprises a landing gear, the landing gear being connected to an outer wall of the housing;

the casing adopts the wing section, the casing is provided with the back taper angle, the casing pass through the link with the fuselage is connected.

Optionally, the pitch-variable propeller mechanism includes propeller hub, central column, fixed pressing plate, speed governing spring, removal clamp plate, pitch-variable pull rod, paddle and centrifugal hammer, the one end of central column with the center department fixed connection of propeller hub, the other end of central column passes fixed pressing plate just central column with fixed pressing plate is connected, it is located to remove the clamp plate the fixed pressing plate top just remove the clamp plate with fixed pressing plate passes through speed governing spring is connected, the one end of pitch-variable pull rod with it is connected to remove the clamp plate, the free end of pitch-variable pull rod passes fixed pressing plate and with the tip of paddle is connected, the tip of paddle with the lateral wall of propeller hub is connected through spacing portion, the tip of centrifugal hammer with the lateral wall fixed connection of paddle.

Optionally, the number of the variable pitch pull rod, the paddle and the centrifugal hammer is two.

Optionally, the aircraft further comprises an aileron and a driving device, wherein the aileron is hinged to the outer trailing edge of the wing, the driving device is connected with the aileron, and the driving device can drive the aileron to rotate.

Optionally, the tail duct device is connected with the tail duct device through a communication connection, and the tail duct device is connected with the tail duct device through a communication connection.

According to the tail single-duct propulsion unmanned aerial vehicle provided by the invention, the driving device can be used for driving the variable pitch propeller mechanism to rotate, so that the body of the unmanned aerial vehicle obtains thrust, and the tail single-duct propulsion unmanned aerial vehicle can fly.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic structural diagram of a tail single-duct propulsion unmanned aerial vehicle provided by an embodiment of the invention;

FIG. 2 is a main schematic view of a trailing single duct propelled UAV provided by an embodiment of the present invention;

FIG. 3 is a side schematic view of a trailing single duct propelled UAV provided by an embodiment of the present invention;

FIG. 4 is a schematic structural view of another angle of the tail single-duct propulsion unmanned aerial vehicle provided by the embodiment of the invention;

FIG. 5 is a schematic illustration of the internal structure of a caudal ducted device of a caudal single-ducted propulsive unmanned aerial vehicle according to an embodiment of the present invention;

FIG. 6 is a schematic structural diagram of a variable pitch propeller mechanism of a tail single-duct propulsion unmanned aerial vehicle provided by the embodiment of the invention;

FIG. 7 is a schematic view of a flight mode transition process of a tail single-duct propulsion unmanned aerial vehicle provided by an embodiment of the invention;

in the figure 1, a fuselage; 2. a tail duct device; 21. a variable pitch propeller mechanism; 211. a hub; 212. a central column; 213. fixing the pressing plate; 214. a speed regulating spring; 215. moving the pressing plate; 216. a variable-pitch pull rod; 217. a paddle; 218. a centrifugal hammer; 219. a limiting part; 22. a steering mechanism; 221. a deflection plate; 222. a flow distribution plate; 223. a connecting shaft; 224. a driver; 23. a housing; 24. a landing gear; 25. a connecting frame; 3. an airfoil; 4. an aileron.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.

In the description of the present invention, it is to be noted that "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing and simplifying the description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and thus are not to be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as appropriate to those of ordinary skill in the art.

Example 1:

the invention provides a tail single-duct propelling unmanned aerial vehicle which comprises a body 1, a tail duct device 2, wings 3 and a driving device, wherein the tail duct device 2 is connected with the tail of the body 1, the side walls of the body 1 are detachably connected with the wings 3, the wings 3 are close to the tail duct device 2, the driving device is arranged in the body 1, an output shaft of the driving device is connected with the tail duct device 2, and the driving device can be a motor;

the tail culvert device 2 comprises a variable-pitch propeller mechanism 21, a steering mechanism 22 and a shell 23, the shell 23 is connected with the machine body 1, the variable-pitch propeller mechanism 21 is located in the shell 23, an output shaft of a driving device is connected with the variable-pitch propeller mechanism 21, the shell 23 separates the variable-pitch propeller mechanism 21 from the external environment, the safety of ground operators can be well protected, noise propagation is reduced, the concealment of the unmanned aerial vehicle is improved, the driving device can drive the variable-pitch propeller mechanism 21 to rotate, the steering mechanism 22 is installed in the shell 23, the steering mechanism 22 and the machine body 1 are located on two sides of the variable-pitch propeller mechanism 21 respectively, and the steering mechanism 22 can swing. According to the tail single-duct propulsion unmanned aerial vehicle provided by the invention, the driving device can be used for driving the variable pitch propeller mechanism 21 to rotate, so that the body 1 obtains thrust, and the tail single-duct propulsion unmanned aerial vehicle can fly, and in the flying process of the tail single-duct propulsion unmanned aerial vehicle, the wind direction generated by the variable pitch propeller mechanism 21 is changed by changing the deflection angle of the steering mechanism 22, so that the flying mode of the tail single-duct propulsion unmanned aerial vehicle can be changed, the hovering mode and the flat flying mode can be switched, and the technical problem that the movement mode of the unmanned aerial vehicle is single in the prior art is solved.

Example 2:

as an alternative embodiment, the steering mechanism 22 includes a deflection plate 221, a diversion plate 222, a connecting shaft 223 and a driver 224, one end of the diversion plate 222 is connected to a side wall of the connecting shaft 223, the other end of the diversion plate 222 is connected to an inner wall of the housing 23, the diversion plate 222 is connected to the deflection plate 221 through the driver 224, the driver 224 may be a steering engine, and the driver 224 can drive the deflection plate 221 to perform a swinging motion. The side of the diverter plate 222 is provided with a recess in which the driver 224 is mounted, and the rotating end of the driver 224 is connected to the deflector plate 221.

As an optional embodiment, the number of the deflection plates 221, the diversion plates 222, and the drivers 224 is multiple and consistent, the deflection plates 221, the diversion plates 222, and the drivers 224 are in one-to-one correspondence, all the deflection plates 221 are distributed along the circumferential direction of the connecting shaft 223, all the diversion plates 222 are distributed along the circumferential direction of the connecting shaft 223, and all the drivers 224 are distributed along the circumferential direction of the connecting shaft 223. The change in the deflection angle of each deflector 221, in turn, may cause a change in the steering of the trailing single duct propelled unmanned aerial vehicle.

As an alternative embodiment, the interior of the diversion plate 222 may be a hollow structure. The cross-section of the deflector plate 221 may be an airfoil configuration.

As an optional embodiment, the tail ducted device 2 further includes landing gears 24, the landing gears 24 are connected to the outer wall of the housing 23, the number of the landing gears 24 is four, the landing gears 24 are circumferentially distributed on the outer wall of the housing 23 at intervals of 90 °, and the landing gears 24 are used for supporting the airframe structure during take-off and landing and protecting the components thereof from being damaged. The undercarriage 24 can be additionally provided with a spring damping mechanism made of special materials, so that the unmanned aircraft propelled by a single duct at the tail part is better prevented from being damaged when landing, and the landing fault tolerance rate is improved;

the shell 23 adopts a wing section, the formation of a propeller tip vortex can be inhibited, the energy loss of wake flow is reduced, meanwhile, a certain additional thrust can be generated at the opening of the shell, the shell 23 is provided with an inverted cone angle for improving the distribution of the streaming in the shell 23 and improving the effective lift area of the shell 23, and the shell 23 is connected with the machine body 1 through a connecting frame 25.

Example 3:

as an alternative embodiment, the pitch propeller mechanism 21 includes a hub 211, a central upright 212, a fixed pressing plate 213, a speed regulating spring 214, a movable pressing plate 215, a pitch-changing pull rod 216, a blade 217 and a centrifugal hammer 218, one end of the central upright 212 is fixedly connected to the center of the hub 211, the other end of the central upright 212 passes through the fixed pressing plate 213 and the central upright 212 is connected to the fixed pressing plate 213, the movable pressing plate 215 is located above the fixed pressing plate 213 and the movable pressing plate 215 and the fixed pressing plate 213 are connected to the speed regulating spring 214, one end of the pitch-changing pull rod 216 is connected to the movable pressing plate 215, the free end of the pitch-changing pull rod 216 passes through the fixed pressing plate 213 and is connected to the end of the blade 217, the end of the blade 217 is connected to the sidewall of the hub 211 by a limiting portion 219, and the end of the centrifugal hammer 218 is fixedly connected to the sidewall of the blade 217.

In an alternative embodiment, the number of the pitch-changing pulling rod 216, the paddle 217 and the centrifugal hammer 218 is two. When the driving device drives the paddle 217 to rotate, the centrifugal hammer 218 can also rotate, but the centrifugal hammer 218 can drive the paddle 217 to rotate in a deviation manner, so that the variable-pitch pull rod 216 moves, the movable pressing plate 215 moves to deviate, meanwhile, the other variable-pitch pull rod 216 moves, the other paddle 217 rotates in a deviation manner, and then the two paddles 217 influence each other.

Example 4:

as an optional embodiment, the aircraft further comprises an aileron 4 and a driving device, wherein the aileron 4 is hinged with the outer rear edge of the wing 3, the driving device is connected with the aileron 4, and the driving device can drive the aileron 4 to rotate. Fuselage 1 and wing 3 all adopt combined material to make, and the quality is light, and wing 3 can be swift dismantles from fuselage 1 to this reduces unmanned vehicles's occupation of land space, and convenient transportation is carried. The wings 3 are in an upper single wing layout, and further in a high aspect ratio upper single wing layout, so that the high-speed cruising performance of the unmanned aerial vehicle is guaranteed during long-term navigation. The rotation of the ailerons 4 can realize the control of the rolling attitude during the level flight; the lower side of the wing 3 is provided with a micro missile which can hit a target accurately.

The fuselage 1 includes circular section organism and square section organism, and the tip rounding off of circular section organism and square section organism both connects, and this design appearance can increase fuselage 1 inner chamber space capacity under the prerequisite that keeps good aerodynamic shape, can hold more payload, and the free end of square section organism is connected with afterbody duct device 2. The head of the fuselage 1 may be connected with a head ducted device for providing thrust to the fuselage 1.

Example 5:

as an optional embodiment, the system further comprises an automatic driving system and a remote control device, the automatic driving system is installed on the fuselage 1, the automatic driving system can control the operation of the tail duct device 2, and the remote control device is in communication connection with the automatic driving system. The automatic piloting system comprises a sensor, an automatic pilot, an oil tank and a double-light pod, wherein the sensor, the automatic pilot and the oil tank are all arranged inside a fuselage 1, the double-light pod is connected to the outer wall of the fuselage 1, the sensor is electrically connected with the automatic pilot, a driving device, a driver 224 and driving equipment are electrically connected with the automatic pilot, the sensor is used for monitoring flight parameters of the tail single-duct propulsion unmanned aerial vehicle and transmitting the flight parameters to the automatic pilot, the flight parameters can comprise motion parameters such as the position, the ground speed, the airspeed, the altitude, the attitude and the like of the aircraft, the automatic pilot can receive the flight parameters and control the driving device, the driver 224 and the driving equipment to operate according to the flight parameters, the automatic pilot judges the current flight attitude and the target flight attitude according to the acquired flight parameters and makes a track command of the target attitude, thereby controlling the running states of the driving device, the driver 224 and the driving equipment, the oil tank is used for storing fuel oil, and the dual-light gondola is used for remote map transmission and tracking and positioning of the target. The ground operator can also operate the unmanned aerial vehicle through the remote control device.

When the unmanned aerial vehicle needs to adjust the flight attitude for maneuvering, the monitored flight parameters are transmitted to the autopilot through the sensor, the autopilot judges the current flight attitude and the target flight attitude through the flight parameters, the deflection quantity of the deflection plate 221 is calculated, the driver 224 is controlled to be started, the deflection plate 221 is controlled to rotate to a specified angle, and the attitude change of the unmanned aerial vehicle is achieved. When the deflection plate 221 deflects, a part of the deflection plate 221 deflects at a large angle, and the other part of the deflection plate 221 deflects at a small angle, so that the airflow in the housing 23 is guided to flow away, and the position and posture control with high precision and quick response is realized.

When the unmanned aerial vehicle is in a hovering mode, the thrust is basically parallel to the gravity direction, the normal moment required for maintaining flight is small, and the integral driving difficulty is small. When the unmanned aerial vehicle is in a fixed wing cruise mode, the ailerons 4 are involved in attitude control to provide main rolling torque, and when the unmanned aerial vehicle is subjected to pitching and yawing control, a yaw plate 221 is required to be added for driving control.

Example 6:

the transition process of the vertical take-off and landing mode of the unmanned aerial vehicle with single duct propulsion at the tail part is described as follows:

during taking off, the unmanned aerial vehicle is vertically placed on the ground, the main shaft of the aircraft body 1 is perpendicular to the ground, the aircraft body is supported through the undercarriage 24, and the variable pitch propeller mechanism 21 is driven to rotate by the driving device. The force generated by the variable pitch propeller mechanism 21 is used for overcoming the self gravity of the unmanned aerial vehicle during vertical takeoff and hovering, and the vertical takeoff and landing process is completed.

When the unmanned aerial vehicle ascends to a certain height, the command control driver 224 of the automatic driving system drives all the deflection plates 221 to deflect, the ailerons 4 are adjusted in the process, the fuselage 1 generates tilting head-lowering moment, the unmanned aerial vehicle rotates along a rotating shaft vertical to the main shaft of the fuselage 1, the nose gradually tilts forwards and pulls downwards, and at the moment, the unmanned aerial vehicle is converted into a flight mode transition stage from a hovering mode.

With the head of the unmanned aerial vehicle tilting forward continuously and the attack angle decreasing continuously, the force generated by the variable pitch propeller mechanism 21 is gradually changed into horizontal flight power, the wings 3 recover from stalling, the generated lift force is used for overcoming the full-aircraft gravity, the deflection plate 221 is reset at a deflection angle, and at the moment, the unmanned aerial vehicle enters a high-speed cruise stage.

When the task of the unmanned aerial vehicle is finished and the unmanned aerial vehicle arrives at a landing stage, the command control driver 224 of the automatic driving system drives the deflection plate 221 and the ailerons 4 to deflect, so that the unmanned aerial vehicle rotates along a transverse rotating shaft perpendicular to a main shaft of the vehicle body, climbs for a certain distance and is pulled upwards along with the vehicle head, finally, the direction of force generated by the variable-pitch propeller mechanism 21 is parallel to the gravity of the unmanned aerial vehicle, and when the rotating speed of the variable-pitch propeller mechanism 21 is reduced and the generated force is smaller than the self gravity of the unmanned aerial vehicle, the unmanned aerial vehicle can generate downward speed and slowly and vertically land.

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.

Claims (10)

1. The tail single-duct propelling unmanned aerial vehicle is characterized by comprising a vehicle body (1), a tail duct device (2), wings (3) and a driving device, wherein,

the tail duct device (2) is connected with the tail of the fuselage (1), the side wall of the fuselage (1) is detachably connected with the wings (3), the wings (3) are close to the tail duct device (2), the driving device is installed in the fuselage (1), and the output shaft of the driving device is connected with the tail duct device (2);

afterbody duct device (2) are including displacement screw mechanism (21), steering mechanism (22) and casing (23), casing (23) with fuselage (1) is connected, displacement screw mechanism (21) are located just in casing (23) drive arrangement's output shaft with displacement screw mechanism (21) are connected, drive arrangement can drive displacement screw mechanism (21) rotate, steering mechanism (22) are installed just in casing (23) steering mechanism (22) with fuselage (1) is located respectively the both sides of displacement screw mechanism (21), swing motion can be done in steering mechanism (22).

2. The aft single duct propelled unmanned aerial vehicle of claim 1, wherein the steering mechanism (22) comprises a deflector (221), a diverter plate (222), a connecting shaft (223), and a driver (224), wherein one end of the diverter plate (222) is connected to a side wall of the connecting shaft (223), the other end of the diverter plate (222) is connected to an inner wall of the housing (23), the diverter plate (222) is connected to the deflector (221) through the driver (224), and the driver (224) can drive the deflector (221) to perform a swinging motion.

3. The aft single duct propelled UAV according to claim 2 wherein the number of said deflector plates (221), said splitter plates (222), and said actuators (224) are all plural and uniform, all of said deflector plates (221) are distributed along the circumference of said connecting shaft (223), all of said splitter plates (222) are distributed along the circumference of said connecting shaft (223), and all of said actuators (224) are distributed along the circumference of said connecting shaft (223).

4. The aft single ducted propelled unmanned aerial vehicle of claim 2, wherein said diverter plate (222) is hollow internally.

5. The aft single ducted propelled unmanned aerial vehicle of claim 2, wherein a cross-section of said deflector plate (221) is an airfoil structure.

6. The aft single-duct propulsive unmanned aerial vehicle of claim 1, wherein the aft duct device (2) further comprises a landing gear (24), the landing gear (24) being coupled to an outer wall of the housing (23);

the shell (23) adopts a wing section, the shell (23) is provided with an inverted cone angle, and the shell (23) is connected with the machine body (1) through a connecting frame (25).

7. The aft single ducted propulsive unmanned aerial vehicle of claim 1, wherein the variable pitch propeller mechanism (21) comprises a hub (211), a central upright (212), a fixed platen (213), a speed control spring (214), a moving platen (215), a variable pitch tie rod (216), a blade (217), and a centrifugal hammer (218), one end of the central upright (212) is fixedly connected to the center of the hub (211), the other end of the central upright (212) passes through the fixed platen (213) and the central upright (212) is connected to the fixed platen (213), the moving platen (215) is located above the fixed platen (213) and the moving platen (215) and the fixed platen (213) are connected by the speed control spring (214), one end of the variable pitch tie rod (216) is connected to the moving platen (215), the free end of the variable pitch pull rod (216) penetrates through the fixed pressing plate (213) and is connected with the end of the blade (217), the end of the blade (217) is connected with the side wall of the hub (211) through a limiting part (219), and the end of the centrifugal hammer (218) is fixedly connected with the side wall of the blade (217).

8. The aft single duct propelled unmanned aerial vehicle of claim 7, wherein the number of pitch links (216), blades (217), and centrifugal hammers (218) is two.

9. The aft single ducted propulsive unmanned aerial vehicle of claim 1, further comprising an aileron (4) and a drive device, said aileron (4) being hingedly connected to an outboard trailing edge of said wing (3), said drive device being connected to said aileron (4) and said drive device being capable of driving the aileron (4) in rotation.

10. The aft single ducted propulsive unmanned aerial vehicle of claim 1, further comprising an autopilot system mounted to said fuselage (1), said autopilot system capable of controlling operation of said aft ducted device (2), and a remote control device in communicative connection with said autopilot system.

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