A long-endurance high payload ratio combined vertical take-off and landing unmanned aerial vehicle

Abstract

The application relates to the technical field of unmanned planes, and particularly discloses a long-haul-time large-load-ratio combined vertical take-off and landing unmanned plane, which comprises a fixed-wing task machine and a vertical take-off and landing propulsion machine; the vertical take-off and landing propulsion machine is used for assisting the fixed-wing task machine to take off and land, and a docking device is arranged on the vertical take-off and landing propulsion machine and used for docking with the fixed-wing task machine when the fixed-wing task machine takes off and lands; the fixed-wing task machine has a front fuselage and a rear fuselage, a hinged connecting piece is arranged between the front fuselage and the rear fuselage, and the front fuselage and the rear fuselage are connected through the hinged connecting piece; the front fuselage and the rear fuselage are respectively provided with first wings and second wings, and the first wings and the second wings are arranged in a tandem wing layout; the long-haul-time large-load-ratio combined vertical take-off and landing unmanned plane can realize autonomous take-off and landing in a small space, and the take-off and landing are not limited by a site, so that the unmanned plane has great significance for future development.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically to a combined vertical take-off and landing (VTOL) UAV with long endurance and high payload ratio. Background Technology

[0002] Fixed-wing vertical takeoff and landing (VTOL) drones possess both vertical takeoff and landing (VTOL) and high-speed flight capabilities, but their complex mode-switching mechanisms result in lower reliability and endurance. Because they employ two separate power systems for forward flight and VTOL, one power unit will inevitably fail to operate under different flight conditions, becoming obsolete. This necessitates more power during flight; however, the thrust provided by the power unit is limited, thus restricting the aircraft's overall weight and payload, leading to lower mass efficiency. The performance of VTOL fixed-wing drones is generally lower than that of comparable fixed-wing drones with normal takeoff and landing capabilities, failing to fully leverage the advantages of both fixed-wing and rotary-wing drones.

[0003] Due to limitations of the takeoff and landing platform, maritime UAVs often employ catapult launch and arresting cable recovery. This method is inefficient, making it difficult to complete multiple takeoffs and landings in a short period. Furthermore, the recovery process requires manual intervention, hindering mission-level automation and making it difficult to form effective swarms. Meanwhile, land-based vertical takeoff and landing (VTOL) UAVs are limited by their vertical takeoff and landing systems, significantly sacrificing their range and other performance characteristics, making it difficult to meet the requirements for long-range operations.

[0004] To address the aforementioned drawbacks, a novel long-endurance, high-payload-ratio combined vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) is proposed. Summary of the Invention

[0005] The technical problem to be solved by this invention is to provide a combined vertical take-off and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio, which enables autonomous take-off and landing in confined spaces, so that take-off and landing are not limited by the site, which is of great significance to the future development of UAVs.

[0006] To solve the above problems, the present invention adopts the following technical solution:

[0007] A combined vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) with long endurance and high payload ratio includes a fixed-wing mission aircraft and a VTOL propulsion unit. The VTOL propulsion unit assists the fixed-wing mission aircraft in takeoff and landing by leveraging its vertical takeoff and landing advantages. During takeoff, the VTOL propulsion unit lifts the fixed-wing mission aircraft into the air, and separates it after reaching level flight speed. During landing, the VTOL propulsion unit assists the fixed-wing mission aircraft in landing, freeing it from site restrictions for takeoff and landing, and avoiding the drawbacks of redundant devices in other VTOL systems, thus maximizing the performance advantages of the fixed-wing mission aircraft.

[0008] The vertical takeoff and landing propulsion motor is used to assist the fixed-wing mission aircraft in takeoff and landing. The vertical takeoff and landing propulsion motor is equipped with a docking device, which is used to dock with the fixed-wing mission aircraft during takeoff and landing.

[0009] The fixed-wing mission aircraft has a forward fuselage and a rear fuselage, and a hinged connector is provided between the forward fuselage and the rear fuselage. The forward fuselage and the rear fuselage are connected by the hinged connector so that the forward fuselage and the rear fuselage can be folded according to the hinged connector.

[0010] The forward fuselage and the aft fuselage are respectively equipped with a first wing and a second wing, and the first wing and the second wing are arranged in a tandem wing configuration.

[0011] In at least one embodiment of the combined vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, the VTOL propulsion mechanism includes a foldable support, control components, and a propulsion unit.

[0012] The foldable support is provided with a tilting mechanism, the thruster is mounted on the tilting mechanism, the tilting mechanism is configured to be electrically connected to the control component, and the tilting mechanism is used to tilt the thruster to adjust the overall heading and attitude.

[0013] When the foldable bracket is in the unfolded state, the foldable bracket has a socket in the middle, the control component partially passes through the socket, and the control component is configured to be detachably connected to the foldable bracket.

[0014] In at least one embodiment of the combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, the foldable support includes a first boom, a second boom, a first connecting beam, and a second connecting beam.

[0015] The first boom is rotatably connected to one end of the first connecting beam, and the first boom is rotatably connected to one end of the second connecting beam.

[0016] The second boom is rotatably connected to the other end of the second connecting beam, and the second boom is rotatably connected to the other end of the first connecting beam.

[0017] In at least one embodiment of the combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, the docking device includes a carrier plate, a connecting frame, an electric adsorber, a support frame, a measuring device, and an onboard computer.

[0018] The connecting frame, electric adsorber, support frame, measuring device, and onboard computer are all mounted on the carrier plate.

[0019] The carrier plate is fixedly connected to the control component.

[0020] The electric adsorber is used to adsorb onto the front body of the machine, and the electric adsorber is mounted on the connecting frame.

[0021] The support frame is used to abut against the bottom surface of the front fuselage and / or the rear fuselage.

[0022] Both the electric adsorber and the measuring device are electrically connected to the onboard computer.

[0023] In at least one embodiment of the combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, the support frame includes a backing plate, a telescopic support rod, and an electrically operated telescopic rod.

[0024] One end of each of the retractable support rod and the electric telescopic rod is connected to the carrier plate, and the other end of each of the retractable support rod and the electric telescopic rod is connected to the back of the abutment plate.

[0025] The electric telescopic pole is configured to be electrically connected to the onboard computer.

[0026] In at least one embodiment of the combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, the electric adsorber is an electromagnet, and the front fuselage is provided with a permanent magnet docking body or magnetic metal sheet that is paired with the electromagnet.

[0027] In at least one embodiment of the combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, both the front fuselage and the rear fuselage are lift fuselages.

[0028] In at least one embodiment of the combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, a buffer rubber pad is fixedly provided on the front side of the abutment plate.

[0029] In at least one embodiment of the combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio provided in this disclosure, both the first boom and the second boom are provided with support feet.

[0030] In at least one embodiment of the combined vertical takeoff and landing UAV with long endurance and high payload ratio provided in this disclosure, four tilting mechanisms and four thrusters are provided. The tilting mechanisms and thrusters are all rectangularly distributed, and the tilting mechanisms and thrusters are all misaligned with the first wing and the second wing.

[0031] The beneficial effects of this invention are as follows:

[0032] 1. The tandem wing configuration features long endurance and high maneuverability, while the lifting fuselage configuration achieves high lift and large payload capacity by providing lift to the fuselage, much like wings. Adopting a "tandem wing + lifting fuselage" configuration combines the advantages of both, giving fixed-wing mission aircraft long endurance, high maneuverability, and strong payload capacity. Simultaneously, it reduces wing span and area, enabling miniaturization of fixed-wing mission aircraft and providing a solid foundation for development towards intelligence and swarm capabilities. Furthermore, the innovative use of a twin-fuselage configuration significantly enhances the detachability of fixed-wing mission aircraft, providing greater convenience for the intelligentization of unmanned aerial vehicles (UAVs).

[0033] 2. By adopting a vertical takeoff and landing propulsion system to assist fixed-wing mission aircraft in takeoff and landing, it is possible to achieve takeoff and landing in confined spaces without affecting the performance of fixed-wing mission aircraft. This eliminates the limitations of the site for takeoff and landing, and also avoids the drawbacks of redundant devices in other vertical takeoff methods, thus maximizing the performance advantages of fixed-wing flight. Attached Figure Description

[0034] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0035] Figure 1 This is a top view of the combination of a fixed-wing mission aircraft and a vertical takeoff and landing propulsion system.

[0036] Figure 2 This is a view of the vertical take-off and landing propulsion unit without the docking device installed.

[0037] Figure 3 This is a top view of a fixed-wing mission aircraft.

[0038] Figure 4 This is a 3D view of a fixed-wing mission aircraft.

[0039] Figure 5 This is a 3D view of a fixed-wing mission aircraft.

[0040] Figure 6 This is a diagram showing the positions of the thrusters distributed on the foldable support.

[0041] Figure 7 This is a schematic diagram showing the distribution of the first boom, the second boom, the first connecting beam, and the second connecting beam.

[0042] Figure 8 This is a three-dimensional view of the docking device.

[0043] Figure 9 This is a three-dimensional view of the docking device.

[0044] In the picture:

[0045] 10. Fixed-wing mission aircraft; 11. Forward fuselage; 12. Rear fuselage; 13. Articulated connector; 14. Engine; 111. First wing; 121. Second wing;

[0046] 20. Vertical take-off and landing propulsion unit; 21. Foldable support frame; 22. Control components; 23. Thruster; 24. Insertion port; 25. Tilting mechanism; 211. First boom; 212. Second boom; 213. First connecting beam; 214. Second connecting beam; 215. Support leg;

[0047] 30. Docking device; 31. Carrier plate; 32. Connecting frame; 33. Electric adsorber; 34. Support frame; 35. Measuring device; 36. Airborne computer; 341. Backing plate; 342. Telescopic support rod; 343. Electric telescopic rod. Detailed Implementation

[0048] The technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments, not all embodiments.

[0049] This invention proposes a novel combined vertical takeoff and landing (VTOL) UAV technology solution. It divides the commonly used "composite" VTOL UAV into a fixed-wing mission aircraft and a VTOL propulsion unit, each independently controlled. Their combination forms a "composite" VTOL UAV configuration. The VTOL propulsion unit carries the fixed-wing mission aircraft for takeoff. After takeoff, the fixed-wing mission aircraft accelerates, and the VTOL propulsion unit separates from it. The VTOL propulsion unit returns to the takeoff and landing platform under independent control, while the fixed-wing mission aircraft continues its mission. After the fixed-wing mission aircraft completes its mission and returns, the VTOL propulsion unit takes off from the takeoff and landing platform and autonomously docks with the fixed-wing mission aircraft, re-forming the "composite" configuration. Subsequently, the VTOL propulsion unit assists the fixed-wing mission aircraft in decelerating and carrying it to a designated location on the platform.

[0050] Example

[0051] like Figure 1 , 2 As shown in Figures 3, 4, 5, and 8, this embodiment provides a combined vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) with long endurance and high payload ratio, including a fixed-wing mission aircraft 10 and a VTOL propulsion aircraft 20.

[0052] Specifically, the vertical takeoff and landing propulsion unit 20 is used to assist the fixed-wing mission aircraft 10 in taking off and landing. The vertical takeoff and landing propulsion unit 20 is equipped with a docking device 30, which is used to dock with the fixed-wing mission aircraft 10 during takeoff and landing.

[0053] Specifically, the fixed-wing mission aircraft 10 has a forward fuselage 11 and a rear fuselage 12, with a hinged connector 13 between the forward fuselage 11 and the rear fuselage 12. The forward fuselage 11 and the rear fuselage 12 are connected by the hinged connector 13, so that the forward fuselage 11 and the rear fuselage 12 can be folded according to the hinged connector 13.

[0054] Furthermore, the engine 14 of the fixed-wing mission aircraft 10 is located on the rear fuselage 12, and the engine 14 is a fuel engine. The flight controller (not shown), battery (not shown), and fuel pump (not shown) of the fixed-wing mission aircraft 10 are all located in the forward fuselage 11.

[0055] Since fuel consumption during flight can cause a shift in the center of gravity, multiple fuel tanks (not shown) are distributed within the forward fuselage 11 and the aft fuselage 12. These tanks are connected by connecting pipes (not shown) to ensure that the center of gravity remains constant during fuel consumption. Preferably, four fuel tanks are provided.

[0056] In operation, the fixed-wing mission aircraft 10 and the vertical takeoff and landing propulsion aircraft 20 form a "composite" unmanned aerial vehicle (UAV) that takes off vertically from the takeoff point together. After reaching a certain altitude, the fixed-wing mission aircraft 10 and the vertical takeoff and landing propulsion aircraft 20 begin to accelerate in level flight, moving away from the takeoff point.

[0057] Once accelerated to a certain speed, meeting the takeoff speed of the mission aircraft, the fixed-wing mission aircraft 10 and the vertical takeoff and landing propulsion aircraft 20 are separated via the docking device 30. After separation, the vertical takeoff and landing propulsion aircraft 20 begins its return journey, returning to the airspace above the takeoff point and slowly descending vertically; the mission aircraft then begins its acceleration and climb, reaching cruising speed before flying to the target location to perform its flight mission.

[0058] For example, the hinge connector 13 is provided with a locking screw hole (not shown) and a locking bolt (not shown). The locking bolt is screwed into the locking screw hole, thereby enabling the front fuselage 11 and the rear fuselage 12 to be positioned so that the front fuselage 11 and the rear fuselage 12 are in a horizontal state, and can ensure that the front fuselage 11 and the rear fuselage 12 have good stability during flight.

[0059] Specifically, the forward fuselage 11 and the aft fuselage 12 are respectively equipped with a first wing 111 and a second wing 121, which are arranged in a tandem wing configuration. Both the forward fuselage 11 and the aft fuselage 12 are lifting fuselages. The tandem wing configuration features long endurance and high maneuverability, while the lifting fuselage configuration achieves high lift and large payload capacity by providing lift to the fuselage, just like the wings.

[0060] By adopting a "tandem wing + lifting fuselage" layout, the advantages of both can be combined, giving the Fixed-wing Mission Aircraft 10 features such as long endurance, high maneuverability, and strong payload capacity. At the same time, it can reduce the wing span and area, realizing the miniaturization of the mission aircraft, which is conducive to providing a solid foundation for the development towards intelligence and clustering.

[0061] like Figure 2 , 6 As shown in Figure 7, in this embodiment, the vertical take-off and landing propulsion machine 20 includes a foldable support 21, a control assembly 22, and a propulsion unit 23.

[0062] Specifically, a tilting mechanism 25 is provided on the foldable support 21, and the thruster 23 is mounted on the tilting mechanism 25. The tilting mechanism 25 is configured to be electrically connected to the control component 22. The tilting mechanism 25 is used to tilt the thruster 23, thereby adjusting the heading and attitude of the vertical take-off and landing propulsion machine 20.

[0063] By tilting the thruster 23 forward and backward, its pitch position and attitude can be decoupled, meaning that it can accelerate or decelerate forward at any pitch angle within a certain range. This design allows the thruster to assist the fixed-wing mission aircraft 10 in acceleration and deceleration during combined flight, while maintaining the same pitch angle and speed as the fixed-wing mission aircraft 10 during docking.

[0064] For example, the tilting mechanism 25 is a servo motor, and the thruster 23 is fixedly connected to the output shaft of the servo motor. The thruster 23 is a turbojet engine and is equipped with a fuel supply system (not shown) that provides fuel to the turbojet engine. Both the turbojet engine and the fuel supply system are electrically connected to the control assembly 22.

[0065] When the foldable bracket 21 is in the unfolded state, the foldable bracket 21 has a socket 24 in the middle, the control component 22 partially passes through the socket 24, and the control component 22 is configured to be detachably connected to the foldable bracket 21.

[0066] like Figure 6 As shown, in this embodiment, the foldable bracket 21 includes a first arm 211, a second arm 212, a first connecting beam 213, and a second connecting beam 214. Support legs 215 are provided on both the first arm 211 and the second arm 212.

[0067] Specifically, the first boom 211 is rotatably connected to one end of the first connecting beam 213 through a rotating shaft and a rotating connecting seat, and the first boom 211 is also rotatably connected to one end of the second connecting beam 214 through a rotating shaft and a rotating connecting seat.

[0068] Specifically, the second boom 212 and the other end of the second connecting beam 214 are rotatably connected through a rotating shaft and a rotating connecting seat, and the second boom 212 and the other end of the first connecting beam 213 are rotatably connected through a rotating shaft and a rotating connecting seat.

[0069] Specifically, there are two sets of tilting mechanisms 25, which are respectively mounted on the first boom 211 and the second boom 212.

[0070] Furthermore, there are four tilting mechanisms 25 and four thrusters 23. The tilting mechanisms 25 are arranged in groups of two, and similarly, the thrusters 23 are arranged in groups of two.

[0071] Furthermore, both the tilting mechanism 25 and the thruster 23 are rectangularly distributed, and both the tilting mechanism 25 and the thruster 23 are misaligned with the first wing 111 and the second wing 121.

[0072] For example, the control component, the first connecting beam, and the second connecting beam are all provided with screw holes (not shown), and quick-release bolts (not shown) are screwed into the screw holes to connect the control component and the foldable bracket.

[0073] like Figure 8 and 9 As shown, in this embodiment, the docking device 30 includes a carrier plate 31, a connecting frame 32, an electric suction device 33, a support frame 34, a measuring device 35, and an onboard computer 36.

[0074] Specifically, the connecting frame 32, support frame 34, measuring device 35, and onboard computer 36 are all mounted on the carrier plate 31. The carrier plate 31 is fixedly connected to the control assembly 22. The electric adsorber 33 is used to adsorb onto the front fuselage 11. Both the electric adsorber 33 and the measuring device are electrically connected to the onboard computer 36. The electric adsorber 33 is fixedly disposed on the connecting frame 32.

[0075] Considering that the three-support method is prone to collision and bounce during docking, the docking technology needs to be optimized. To this end, the support frame 34 is made retractable. Before docking begins, the support frame 34 is in a retracted state. After the docking position is calibrated, the electric adsorber 33 is first adsorbed and docked with the fixed-wing mission aircraft 10, and then the support frame 34 is extended and fixed for docking.

[0076] Specifically, the support frame 34 includes a backing plate 341, a telescopic support rod 342, and an electrically telescopic rod 343.

[0077] One end of the telescopic support rod 342 and the electric telescopic rod 343 are both connected to the carrier plate 31, and the other end of the telescopic support rod 342 and the electric telescopic rod 343 are both connected to the back of the abutment plate 341.

[0078] The electric telescopic mast 343 is configured to be electrically connected to the onboard computer 36.

[0079] In some embodiments, two support frames 34 are provided, and the two support frames 34 are respectively used to abut against the bottom surfaces of the front fuselage 11 and the rear fuselage 12.

[0080] In some embodiments, a support frame 34 is provided, which is used to abut against the bottom surface of the front fuselage 11.

[0081] In some embodiments, a support frame 34 is provided, which is used to abut against the bottom surface of the rear fuselage 12.

[0082] In some embodiments, the electric adsorber 33 uses an electromagnet, and the front body 11 is provided with a permanent magnet docking body (not shown) that matches the electromagnet. The permanent magnet docking body is a magnet.

[0083] For example, the measuring device 35 uses a vision camera. When the fixed-wing mission aircraft 10 and the vertical takeoff and landing propulsion aircraft 20 enter the pre-set electromagnetic field range, the vision camera is activated simultaneously with the positions of the fixed-wing mission aircraft 10 and the vertical takeoff and landing propulsion aircraft 20. The vision camera intervenes to assist in electromagnetic adsorption control, keeping the speeds of the two aircraft approximately the same during the docking process.

[0084] In another embodiment not shown, the electric adsorber uses an electromagnet, and a magnetic metal plate (not shown) paired with the electromagnet is disposed on the forward fuselage. Fixed-wing mission aircraft only need to add one set of electromagnets under the fuselage, thus greatly increasing the design flexibility of fixed-wing mission aircraft, which is key to achieving high payload ratios and long ranges.

[0085] In another embodiment not shown, the electric suction device employs a vacuum suction cup and a vacuum pump, with a smooth and flat suction surface on the front body for the vacuum suction cup to adsorb.

[0086] In another embodiment not shown, a first power source is provided on the carrier plate 31 to supply power to the electrical appliances in the docking device 30.

[0087] In another embodiment not shown, the vertical take-off and landing propulsion unit 20 further includes a second power source that supplies power to the various electrical appliances in the vertical take-off and landing propulsion unit 20.

[0088] In another embodiment not shown, a cushioning rubber pad (not shown) is fixedly provided on the front side of the abutment plate.

[0089] Although embodiments of this application have been shown and described above, the scope of protection of this invention is not limited thereto. Any variations or substitutions that can be conceived without inventive effort should be covered within the scope of protection of this invention. Unless expressly stated otherwise, no element, action or instruction used herein should be construed as critical or necessary.

Claims

1. A combined vertical takeoff and landing unmanned aerial vehicle (UAV) with long endurance and high payload ratio, characterized in that, include: Fixed-wing mission aircraft and vertical takeoff and landing propulsion aircraft; The vertical takeoff and landing propulsion motor is used to assist the fixed-wing mission aircraft in takeoff and landing. The vertical takeoff and landing propulsion motor is equipped with a docking device, which is used to dock with the fixed-wing mission aircraft during takeoff and landing. The fixed-wing mission aircraft has a forward fuselage and a rear fuselage, and a hinged connector is provided between the forward fuselage and the rear fuselage. The forward fuselage and the rear fuselage are connected by the hinged connector so that the forward fuselage and the rear fuselage can be folded according to the hinged connector. The forward fuselage and the rear fuselage are respectively provided with a first wing and a second wing, and the first wing and the second wing are arranged in a tandem wing configuration; The vertical take-off and landing propulsion system includes a foldable support frame, control components, and a propulsion unit; The foldable support is provided with a tilting mechanism, the thruster is mounted on the tilting mechanism, the tilting mechanism is configured to be electrically connected to the control component, and the tilting mechanism is used to tilt the thruster to adjust the overall heading and attitude; When the foldable bracket is in the unfolded state, the foldable bracket has a socket in the middle, the control component partially passes through the socket, and the control component is configured to be detachably connected to the foldable bracket; The docking device includes a carrier plate, a connecting frame, an electric adsorber, a support frame, a measuring device, and an onboard computer. The connecting frame, electric adsorber, support frame, measuring device, and airborne computer are all mounted on the carrier plate; The carrier plate is fixedly connected to the control component; The electric adsorber is used to adsorb onto the front body of the machine, and the electric adsorber is mounted on the connecting frame; The support frame is used to abut against the bottom surface of the front fuselage and / or the rear fuselage; Both the electric adsorber and the measuring device are electrically connected to the onboard computer.

2. The combined vertical takeoff and landing UAV with long endurance and high payload ratio according to claim 1, characterized in that, The foldable support includes a first arm, a second arm, a first connecting beam, and a second connecting beam; The first boom is rotatably connected to one end of the first connecting beam, and the first boom is rotatably connected to one end of the second connecting beam; The second boom is rotatably connected to the other end of the second connecting beam, and the second boom is rotatably connected to the other end of the first connecting beam.

3. The combined vertical takeoff and landing UAV with long endurance and high payload ratio according to claim 2, characterized in that, The support frame includes a backing plate, a retractable support rod, and an electrically operated telescopic rod; One end of each of the retractable support rod and the electric telescopic rod is connected to the carrier plate, and the other end of each of the retractable support rod and the electric telescopic rod is connected to the back of the abutment plate. The electric telescopic pole is configured to be electrically connected to the onboard computer.

4. The combined vertical takeoff and landing UAV with long endurance and high payload ratio according to claim 3, characterized in that, The electric adsorber is an electromagnet, and the front body is provided with a permanent magnet docking body or magnetic metal sheet that matches the electromagnet.

5. A combined vertical takeoff and landing unmanned aerial vehicle with long endurance and high payload ratio according to claim 1, characterized in that, Both the forward and aft fuselages are lift fuselages.

6. A combined vertical takeoff and landing unmanned aerial vehicle with long endurance and high payload ratio according to claim 3, characterized in that, A cushioning rubber pad is fixedly provided on the front side of the abutment plate.

7. A combined vertical takeoff and landing unmanned aerial vehicle with long endurance and high payload ratio according to claim 3, characterized in that, Both the first boom and the second boom are equipped with support feet.

8. A combined vertical takeoff and landing unmanned aerial vehicle with long endurance and high payload ratio according to claim 3, characterized in that, There are four tilting mechanisms and four thrusters, all of which are rectangularly distributed and are offset from the first and second wings.

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