Tiltrotor vectored long endurance unmanned aerial vehicle

Abstract

The application discloses a long-endurance unmanned aerial vehicle with tilting vector, which comprises a body, a propulsion system and a control system. The body comprises a frame and a power device for driving the frame to fly. The power device is rotationally arranged on the frame. The body is internally provided with a cargo compartment for placing goods. The power device can be driven to reciprocatingly rotate within a set angle range. The propulsion system is used for providing a power source for the power device. The control system is used for controlling the power device, a driving member and the propulsion system. The power device can be driven to reciprocatingly rotate within the set angle range, so that the unmanned aerial vehicle has excellent short-distance take-off and landing capability and excellent endurance capability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of a long-endurance unmanned aerial vehicle with a tilting vector. BACKGROUND

[0002] An unmanned aerial vehicle, commonly known as a drone, is an unmanned aircraft that is controlled by radio control equipment and self-provided program control device, or is operated by a vehicle-mounted computer completely or intermittently. Unmanned aerial vehicles can be divided into fixed-wing unmanned aerial vehicles and rotary-wing unmanned aerial vehicles.

[0003] Some islands are guarded by people and need to be regularly supplied with goods. Aircraft have the advantage of quick arrival and are the first choice for supplying goods. However, some islands are small in area and do not have the conditions to build runways for manned aircraft and medium-to-large fixed-wing unmanned aerial vehicles to take off and land. Although rotary-wing unmanned aerial vehicles can take off and land vertically, they have weak endurance and low load capacity, and are not suitable for supplying islands, so there is an urgent need for an unmanned aerial vehicle with a short taxiing and landing distance. SUMMARY

[0004] To solve the above technical problems, the present application provides a long-endurance unmanned aerial vehicle with a tilting vector.

[0005] The long-endurance unmanned aerial vehicle with a tilting vector provided by the present application adopts the following technical scheme:

[0006] A long-endurance unmanned aerial vehicle with a tilting vector comprises:

[0007] A body comprising a frame and a power device for driving the frame to fly, the power device being rotationally fitted on the frame, the body being internally provided with a cargo compartment for placing goods, and the power device being able to be driven to reciprocally rotate within a set angle range;

[0008] A propulsion system for providing a power source for the power device;

[0009] A control system for controlling the power device, the driving member and the propulsion system.

[0010] Optionally, the power device comprises a propeller, a motor for driving the propeller to rotate, and a tilting rudder, the frame being provided with a support frame, the tilting rudder being arranged on the support frame, the output end of the tilting rudder being fixedly provided with a rotating frame, the motor being fixedly arranged on the rotating frame, the tilting rudder driving the motor arranged on the rotating frame to rotate within a set angle range during rotation, and the control system being used to control the rotation angle of the tilting rudder and the start-stop of the motor.

[0011] Optionally, the fuselage comprises a body, wings arranged on both sides of the body, and a tail arranged at the tail of the body, the body comprises a front body section and a reinforced body section, the cargo compartment is arranged on the front body section, and the reinforced body section is used for bearing the force transmission between the wings on both sides, bearing the load of the cargo compartment, and connecting the tail and the front body section.

[0012] Optionally, the wings comprise an inner section wing, a middle section wing and an outer section wing arranged in sequence from inside to outside, the number of the main beams of the wings gradually decreases from the wing root to the wing tip, and the inner section wing, the middle section wing and the outer section wing are detachably connected.

[0013] Optionally, a reinforcing bulkhead is arranged between the front body section and the reinforced body section, and the reinforcing bulkhead comprises two bulkheads and a connecting portion arranged between the two bulkheads.

[0014] Optionally, the connecting portion comprises a first connecting portion and a second connecting portion, the two bulkheads are connected through the first connecting portion and the second connecting portion, the first connecting portion is provided with a limiting slot, and the second connecting portion is provided with a limiting block clamped into the limiting slot.

[0015] Optionally, support beams are arranged on both sides of the first connecting portion and the second connecting portion, and the two bulkheads are connected through the support beams.

[0016] Optionally, pins are arranged at the connecting portions of the inner section wing, the middle section wing and the outer section wing, and connecting slots are arranged at the connecting portions of the inner section wing, the middle section wing and the outer section wing, the pins are arranged at the connecting portions between the inner section wing and the middle section wing or the middle section wing and the outer section wing and clamped into the connecting slots.

[0017] Optionally, the propulsion system adopts an oil-electric hybrid double-engine propulsion system, the oil-electric hybrid double-engine propulsion system comprises a kerosene generator and a storage battery, the kerosene generator is used for supplying power to the storage battery, and the storage battery is used for supplying power to the power device.

[0018] Optionally, the tail adopts a V-tail design, and the wings adopt a large-aspect-ratio upper single wing.

[0019] In summary, the present application has at least one of the following beneficial technical effects:

[0020] 1. The power device can be driven to reciprocate within a set angle range, so that the unmanned aerial vehicle has excellent short take-off and landing capability and excellent endurance capability.

[0021] 2. In order to achieve the best economy, the design scheme adopts a V-tail body integrated overall aerodynamic layout scheme with high lift-drag ratio. The aerodynamic layout reduces the fuel consumption of the unmanned aerial vehicle and improves the use economy. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a schematic diagram of the overall structure of an embodiment of the application.

[0023] Figure 2 is an exploded schematic diagram of the front fuselage section, cargo hold and bulkhead of an embodiment of the application.

[0024] Figure 3 is a schematic diagram of the bulkhead structure of an embodiment of the application.

[0025] Figure 4 is a schematic diagram of the wing structure of an embodiment of the application.

[0026] Figure 5 is a schematic diagram of the power plant structure of an embodiment of the application.

[0027] Figure 6 is a flow chart of an embodiment of the application.

[0028] Figure 7 is a schematic diagram of the aerodynamic layout of an embodiment of the application.

[0029] Figure 8 is a graph of the relationship between take-off distance, motor tilt angle and take-off weight of an embodiment of the application.

[0030] BRIEF DESCRIPTION OF THE DRAWINGS: 1. airframe; 11. airframe; 111. fuselage; 1111. front fuselage section; 1112. reinforced fuselage section; 112. wing; 1121. inner wing section; 1122. middle wing section; 1123. outer wing section; 113. tail; 12. power plant; 121. propeller; 122. motor; 123. tilt actuator; 13. cargo hold; 2. propulsion system; 3. control system; 4. support strut; 5. swivel mount; 6. reinforced bulkhead; 61. bulkhead; 62. connecting portion; 621. first connecting portion; 622. second connecting portion; 7. support beam; 8. pin. DETAILED DESCRIPTION

[0031] The following description is made in connection with the accompanying drawings. Figures 1-8 The application is described in further detail.

[0032] An embodiment of the application discloses a tilt vector long-endurance unmanned aerial vehicle.

[0033] Reference is made to Figures 1-8The application discloses a long-endurance unmanned aerial vehicle with a tilting vector, which comprises a body 1, a propulsion system 2 and a control system 3, the body 1 comprises a frame 11 and a power device 12 for driving the frame 11 to fly, the power device 12 is rotationally arranged on the frame 11, the body 1 is internally provided with a cargo compartment 13 for placing goods, and the power device 12 can be driven to reciprocatingly rotate within a set angle range; the propulsion system 2 is used for providing a power source for the power device 12; and the control system 3 is used for controlling the power device 12, a driving member and the propulsion system 2.

[0034] The frame 11 comprises a fuselage 111, wings 112 located on both sides of the fuselage 111 and a tail 113 arranged at the tail of the fuselage 111, the fuselage 111 comprises a front fuselage section 1111 and a reinforced fuselage section 1112, the front fuselage 111 is responsible for placing electronic equipment required by the unmanned aerial vehicle, such as electronic equipment required by a data transmission, a GPS and a flight control, and in addition, the cargo compartment 13 is also arranged in the front fuselage section 1111, and a hatch communicating with the cargo compartment 13 is arranged on the front fuselage section 1111, so that goods can be conveniently taken and placed.

[0035] The frame 11 is further provided with a landing device.

[0036] The reinforced fuselage section 1112 is used for bearing force transmission between the wings 112 on both sides, bearing the load of the cargo compartment 13 and connecting the tail 113 and the front fuselage section 1111.

[0037] The front fuselage section 1111 and the reinforced fuselage section 1112 are provided with a reinforced partition frame 6, and the reinforced partition frame 6 comprises two partition plates 61 and a connecting portion 62 arranged between the two partition plates 61.

[0038] The front fuselage section 1111 is provided with a sleeve rod, the connecting portion 62 comprises a first connecting portion 621 and a second connecting portion 622, the two partition plates 61 are connected through the first connecting portion 621 and the second connecting portion 622, the first connecting portion 621 is provided with a limiting groove, the second connecting portion 622 is provided with a limiting block clamped into the limiting groove, the first connecting portion 621 and the second connecting portion 622 are slidingly arranged on the sleeve rod, the second connecting portion 622 is slid to clamp the limiting block and the limiting groove, and the deflection between the two partition plates 61 is effectively avoided.

[0039] Support beams 7 are arranged on both sides of the first connecting portion 621 and the second connecting portion 622, and the two partition plates 61 transmit force through the support beams 7. The support beams 7 adopt ear pieces, the two partition plates 61 are both provided with the support beams 7 on a side close to each other, and in order to improve the stability of the connection, perforations are formed in the support beams 7, and the support beams 7 on both sides are fixed through bolts.

[0040] The front fuselage 111 is reinforced by aluminum alloy special reinforcing partition frame 6, which is connected at three positions; the first connecting part 621 and the second connecting part 622 in the middle ensure the correct position during docking, and the supporting beams 7 on the left and right sides ensure the effective force transmission between the connected fuselages 111.

[0041] The wing 112 comprises an inner wing section 1121, a middle wing section 1122 and an outer wing section 1123 arranged from inside to outside, and the number of main beams of the wing 112 gradually decreases from the wing root to the wing tip, and the inner wing section 1121, the middle wing section 1122 and the outer wing section 1123 are detachably connected.

[0042] In this embodiment, the outer wing section 1123 is provided with three main beams, the middle wing section 1122 is provided with two main beams, and the inner wing section 1121 is provided with one main beam, and the inner wing section 1121 is fixedly arranged on both sides of the reinforced fuselage section.

[0043] The connecting part of the inner wing section 1121, the middle wing section 1122 and the outer wing section 1123 is provided with a pin 8, and the head outer contour of the pin 8 is consistent with the outer contour curve of the wing 112. The main beams of the inner wing section 1121, the middle wing section 1122 and the outer wing section 1123 are provided with through holes for the pin 8 to pass through, and the connecting part of the inner wing section 1121, the middle wing section 1122 and the outer wing section 1123 is provided with a connecting groove for accommodating the pin 8, and the pin 8 is arranged in the connecting part between the inner wing section 1121 and the middle wing section 1122 or the middle wing section 1122 and the outer wing section 1123 and is clamped in the connecting groove.

[0044] The above connecting mode can be quickly and conveniently disassembled and assembled, and the overall weight of the unmanned aerial vehicle is reduced, and the take-off and landing distance is shortened.

[0045] In order to achieve the best economy, especially the manufacturing economy, the use economy and the maintenance economy, the tail 113 adopts a V-tail 113 design, and the wing 112 adopts a large-aspect-ratio upper wing. The above structure can increase the flight range of the unmanned aerial vehicle, and the tail support rod arranged at a lower position can reduce the force transmission of the partition frame and increase the volume of the fuselage 111.

[0046] The V-tail 113 has the functions of vertical tail and horizontal tail. The wing surface can be divided into fixed stabilizer and hinged rudder, or can be made into a full-motion type. The two tail surfaces in V shape have certain projection areas in the top view and side view, so they can simultaneously play the roles of longitudinal (pitching) and lateral direction stabilization. When the two rudders are deflected in the same direction, they play the role of elevator; when they are deflected in different directions (differential), they play the role of rudder.

[0047] The power device 12 comprises a propeller 121, a motor 122 for driving the propeller 121 to rotate, and a tilting rudder 123, the support frame 4 is arranged on the frame 11, the support frame 4 is arranged with a wire hole, the tilting rudder 123 is arranged on the support frame 4, the output end of the tilting rudder 123 is fixedly provided with a rotating frame 5, the motor 122 is fixedly arranged on the rotating frame 5, and the motor 122 arranged on the rotating frame 5 is driven to rotate within a set angle range in the rotating process of the tilting rudder 123, and the control system 3 is used for controlling the rotating angle of the tilting rudder 123 and the start-stop of the motor 122.

[0048] In the embodiment, the motor 122 adopts a double-turbine GA2000R.

[0049] The motor 122 is vector controlled by the tilting rudder 123, and the motor 122 is tilted in a take-off stage to shorten the take-off distance.

[0050] It can be known that the take-off distance estimation formula can establish a curve of the ratio of the tilting angle of the motor 122 to the take-off sliding distance. It can be known that the take-off distance can be reduced to about 75% of the original under the optimal state. And within a certain take-off weight and motor 122 tilting angle range, the greater the take-off weight, the shorter the take-off distance.

[0051] At present, most of the small and medium-sized unmanned aerial vehicles on the market use the motor 122 as the power source, but due to the influence of the battery, the endurance time and flight distance of the motor 122 cannot meet the design requirements; the mass of the traditional small fuel engine 1 is large, and the use of double-fuel engines will cause the mass of the empty machine to exceed the expected range; another common power mode is to use an internal fuel engine, and then use mechanical transmission to output the power of the fuel engine to the rotating structure. This transmission mode is too complex, the transmission structure will bring additional mass to the machine 1, and structural failure is easy to occur during use and maintenance.

[0052] Therefore, in the embodiment, the propulsion system 2 adopts an oil-electric hybrid dual-engine propulsion system 2, the oil-electric hybrid dual-engine propulsion system 2 comprises a kerosene generator 122 and a storage battery, the kerosene generator 122 is used for supplying power to the storage battery, and the storage battery is used for supplying power to the power device 12.

[0053] The oil-electric hybrid propulsion system 2 uses the kerosene generator 122 to have large thrust and save oil, the kerosene generator 122 converts kerosene into electric energy of the storage battery, and then transmits the electric energy to the motor 122 and the tilting rudder 123 to work. Compared with the traditional working mode, the use of the kerosene engine solves the characteristics of insufficient endurance of the traditional motor 122 and large structure mass of the fuel engine, so that the cargo carrying capacity of the unmanned aerial vehicle is improved, and the take-off and landing distance is shorter.

[0054] Considering that the required altitude of the unmanned aerial vehicle flight is higher than the normal working altitude of most small piston engines, the working altitude of the kerosene generator 122 is higher than that of the piston engine used by the conventional unmanned aerial vehicle, and the oil-electric hybrid system with a battery has higher working efficiency, so that the aircraft can work at high altitude. The use of kerosene generator 122 and battery as power source also facilitates the arrangement of propulsion system 2. Not only can the flight envelope of the unmanned aerial vehicle be expanded, the flight performance and flight quality of the unmanned aerial vehicle can be improved, but also the safety of the unmanned aerial vehicle can be improved. The unique power device 12 and propulsion system 2 enable the unmanned aerial vehicle to quickly reach the maximum track inclination, the unmanned aerial vehicle climbs faster, and the take-off and landing distance will be greatly shortened.

[0055] The control system 3 adopts the prior art unmanned aerial vehicle control system 3, including a flight control system, a wireless transmission system and a central controller. The flight control system controls the start and stop and the rotating speed of the motor 122, the central controller adopts a single-chip microcomputer and its system, the central controller is electrically connected with the wireless transmission system, the ground remote controller electric signal is transmitted to the receiver on the unmanned aerial vehicle through the wireless transmission system by the control of the tilting rudder 123, the receiver transmits to the central controller, and the central controller controls the tilting rudder 123 to change the angle of the motor 122.

[0056] The above are preferred embodiments of the present application, and are not intended to limit the protection scope of the present application, therefore: any equivalent changes made according to the structure, shape, principle of the present application should be covered within the protection scope of the present application.

Claims

1. A long endurance unmanned aerial vehicle with vectoring by tilting, characterised by: The utility model relates to a kind of unmanned aerial vehicle, including: Machine body (1), including frame (11) and drive frame (11) the power device (12) that flies, the power device (12) is rotatably matched to be arranged on frame (11), the machine body (1) inside is provided with the goods compartment (13) for placing goods, the power device (12) can be driven in the set angle range reciprocating rotation; Propulsion system (2) for providing power source to power device (12); Control system (3) for controlling power device (12), driving piece and propulsion system (2); The frame (11) includes fuselage (111), wing (112) located at both sides of fuselage (111) and tail fin (113) arranged at the tail of fuselage (111), the fuselage (111) includes front fuselage section (1111) and reinforced fuselage section (1112), the goods compartment (13) is arranged on front fuselage section (1111), and the reinforced fuselage section (1112) is used for bearing the force between two side wings (112), bearing the load of goods compartment (13) and tail fin (113) and front fuselage section (1111) connection; The wing (112) includes inner section wing (1121), middle section wing (1122) and outer section wing (1123) arranged in sequence from inside to outside, the number of main beam of the wing (112) gradually reduces from wing root to wing tip, and the inner section wing (1121), the middle section wing (1122) and the outer section wing (1123) are detachably connected;Reinforced bulkhead (6) is arranged between the front fuselage section (1111) and the reinforced fuselage section (1112), and the reinforced bulkhead (6) includes two bulkheads (61) and a connecting portion (62) arranged between the two bulkheads (61);The connecting portion (62) includes a first connecting portion (621) and a second connecting portion (622), the two bulkheads (61) are connected by the first connecting portion (621) and the second connecting portion (622), the first connecting portion (621) is provided with a limiting slot, and the second connecting portion (622) is provided with a limiting block clamped into the limiting slot; Supporting beam (7) is arranged on both sides of the first connecting portion (621) and the second connecting portion (622), and the two bulkheads (61) are connected by the supporting beam (7).

2. The long endurance unmanned aerial vehicle with yaw vectoring according to claim 1, characterized in that: The power device (12) includes propeller (121), motor (122) for driving propeller (121) to rotate and tilting rudder (123), supporting frame (4) is arranged on the frame (11), the tilting rudder (123) is arranged on the supporting frame (4), the output end of the tilting rudder (123) is fixedly provided with rotating frame (5), the motor (122) is fixedly arranged on the rotating frame (5), the tilting rudder (123) drives the motor (122) arranged on the rotating frame (5) to rotate in the set angle range during rotation process, and the control system (3) is used for controlling the rotation angle of the tilting rudder (123) and the start-stop of the motor (122).

3. The long endurance yaw vectoring UAV of claim 1, wherein: The connecting part of the inner wing (1121), the middle wing (1122) and the outer wing (1123) is provided with a pin (8), and a connecting groove is formed in the connecting part of the inner wing (1121), the middle wing (1122) and the outer wing (1123), the pin (8) is arranged in the connecting part between the inner wing (1121) and the middle wing (1122) or the middle wing (1122) and the outer wing (1123) and is clamped in the connecting groove.

4. The long endurance yaw vectoring UAV of claim 1, wherein: The propulsion system (2) adopts an oil-electric hybrid double-engine propulsion system (2), the oil-electric hybrid double-engine propulsion system (2) comprises a kerosene generator (122) and a storage battery, the kerosene generator (122) is used for supplying power to the storage battery, and the storage battery is used for supplying power to the power device (12).

5. The yaw vector long endurance unmanned aerial vehicle of claim 1, wherein: The tail wing (113) adopts a V-shaped tail wing (113) design, and the wing (112) adopts a large-aspect-ratio upper single wing.

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