Wing end parallel combination aircraft multi-condition air decomposition test device

Abstract

The application discloses a wing-end parallel combined aircraft multi-working-condition air decomposition test device, and belongs to the technical field of aircrafts, which comprises a hanging truss, the upper end of the hanging truss is connected with a rotor unmanned aerial vehicle, the lower end of the hanging truss is connected with attack angle preset toolings on both sides, the attack angle preset toolings are connected with an aircraft simulation part on one side, and the aircraft simulation part is connected with a locking and separating mechanism. The wing-end parallel combined aircraft multi-working-condition air decomposition test device can accurately reproduce the initial separation state of the aircraft under different attack angles and flight speeds on the ground and in the air through the attack angle preset toolings, and can completely simulate the whole process task of combined stable flight, controllable separation triggering and autonomous flight of a single aircraft through the locking and separating mechanism.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a multi-condition aerial disassembly test device for wingtip parallel combined aircraft. Background Technology

[0002] As the demands of modern aerospace missions become increasingly complex, the limitations of traditional single-configuration aircraft are becoming increasingly apparent. While fixed-wing UAVs possess excellent cruise efficiency and range advantages, they suffer from insufficient maneuverability, demanding takeoff and landing conditions, and vulnerability to detection. Rotary-wing UAVs, despite their vertical takeoff and landing and hovering capabilities, exhibit significant shortcomings in range, speed, and payload. To overcome this technological bottleneck, the concept of modular aircraft has emerged. This technology combines multiple independently flightable units into a more aerodynamically efficient whole during the cruise phase, significantly improving range and economy. Upon arrival at the mission area, the individual units can be orderly separated according to predetermined instructions, forming a distributed intelligent swarm to achieve diverse functions such as collaborative reconnaissance, three-dimensional jamming, precision strikes, or data relay. This integrated "cruise-separation-coordination" working mode can effectively counter modern battlefield anti-access / area denial (A2 / AD) defense systems in the military field, and provides innovative solutions for large-scale geographic mapping, forest fire monitoring, and emergency communication support in the civilian field. It has now become a strategic frontier and development focus of international aerospace technology research. Summary of the Invention

[0003] The purpose of this invention is to provide a multi-condition aerial disassembly test device for wingtip parallel combined aircraft. By using angle-of-attack preset fixtures, the initial separation state of the aircraft under different angles of attack and flight speeds can be accurately reproduced on the ground and in the air. By using a locking separation mechanism, the entire process of combined stable flight, controllable separation triggering, and autonomous flight of the single aircraft can be fully simulated.

[0004] To achieve the above objectives, the present invention provides a multi-condition aerial disassembly test device for a wingtip parallel combined aircraft, including a suspension truss. The upper end of the suspension truss is connected to a rotary-wing UAV. The lower end of the suspension truss is connected to two sides of an angle-of-attack preset fixture for presetting and locking the pitch angle of attack of the aircraft. One side of the angle-of-attack preset fixture is connected to an aircraft simulator for simulating the aerodynamic shape of the main body of the combined aircraft. The aircraft simulator is connected to a locking and separation mechanism for realizing the connection and separation of the individual wings in the combined aircraft.

[0005] Preferably, the suspended truss includes an upper chord horizontal member, an upper chord vertical member, a lower chord horizontal member, and a lower chord vertical member. The upper chord horizontal members and the upper chord vertical members are interconnected, and the lower chord horizontal members and the lower chord vertical members are interconnected. Vertical members are connected to both ends of the bottom surface of the upper chord horizontal member, and the bottom ends of the vertical members are connected to the top surface of the lower chord horizontal member. A support is connected to the bottom surface of the lower chord horizontal member, and a ground beam is connected to the bottom end of the support. Diagonal members are connected to both ends of the upper chord horizontal member, and the bottom ends of the diagonal members are connected to the top surface of the lower chord horizontal member. A connector is connected to the diagonal member, and the connector is connected to the rotary-wing UAV. An angle-of-attack preset fixture is set on the lower chord horizontal member.

[0006] Preferably, the connector includes a square tube sleeve and a round tube sleeve, with a tube sleeve connecting block connecting the square tube sleeve and the round tube sleeve. The square tube sleeve is connected to the diagonal rod, and the round tube sleeve is connected to the rotary-wing UAV.

[0007] Preferably, the angle-of-attack preset fixture includes a base, with mounting ears at both ends of the base. The mounting ears are connected to the lower chord crossbar. A positioning pad is provided inside the base, and a reducer is provided on the positioning pad. A pitch axis is connected to one side of the reducer, and the other end of the pitch axis passes through the base and the mounting ears in sequence and is connected to the aircraft simulator. An input shaft is provided on one side of the reducer, and the other end of the input shaft passes through the side wall of the base and is connected to a rotating component.

[0008] Preferably, the rotating assembly includes a washer and a rocker arm, with the washer fitted onto the input shaft and the rocker arm disposed at one end of the side wall of the washer.

[0009] Preferably, the aircraft simulator includes a main wing, with the other end of the pitch axis inserted into the main wing, a pitch pin provided between the main wing and the pitch axis, a cover plate embedded on the top surface of the main wing, a servo motor provided in the middle of the side wall of the main wing, positioning shafts inserted at both ends of the side wall of the main wing, and a locking and separating mechanism connected to the servo motor and the positioning shafts.

[0010] Preferably, the locking and separating mechanism includes a main connecting block, a locking and separating connecting block is provided on one side of the main connecting block, and a single connecting block is provided on one side of the locking and separating connecting block. The other end of the positioning shaft passes through the main connecting block and the locking and separating connecting block in sequence and is inserted into the single connecting block. A driving component and a driven component are provided inside the locking and separating connecting block. The driving component is connected to the output shaft of the servo motor. The driving component and the driven component are interconnected. One end of the driving component and the driven component is connected to the main connecting block, and the other end of the driven component is connected to the single connecting block.

[0011] Preferably, the drive assembly includes a drive shaft, a drive gear, and a rack. The drive shaft has first bearings at both ends, one of which is connected to the main body connecting block, and the other is connected to the locking and separating connecting block. One end of the drive shaft is connected to the output shaft of the servo motor. The drive gear is sleeved in the middle of the drive shaft, and the rack is located inside the locking and separating connecting block. The rack meshes with the drive gear, and the driven assembly contacts the rack.

[0012] Preferably, the driven component includes a driven shaft, a driven gear, and a separating cam. The driven shaft is provided with second bearings at both ends. One second bearing is connected to the main body connecting block, and the other second bearing is connected to the locking separating connecting block. The driven gear is sleeved in the middle of the driven shaft and meshes with a rack. One end of the separating cam is connected to the driven shaft, and the other end of the separating cam passes through the locking separating connecting block and is connected to the single-unit connecting block.

[0013] Preferably, the side wall of the single connecting block is provided with a cam hole, a separation pin is provided inside the cam hole, a cam groove is provided on the separation cam, the separation cam is inserted into the cam hole, and the cam groove and the separation pin are in contact.

[0014] Therefore, the present invention adopts the above-mentioned wingtip parallel combined aircraft multi-condition aerial disassembly test device. Through the angle of attack preset tooling, the initial separation state of the aircraft under different angles of attack and flight speeds can be accurately reproduced on the ground and in the air. Through the locking separation mechanism, the entire process of combined stable flight, controllable separation triggering, and autonomous flight of the single aircraft can be completely simulated.

[0015] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0016] Figure 1 This is a top view of the wingtip parallel combined aircraft multi-condition aerial disassembly test device of the present invention; Figure 2 This is a schematic diagram of the specific structure of the hanging truss in this invention; Figure 3 This is a schematic diagram of the specific structure of the connector in this invention; Figure 4 This is a schematic diagram of the specific structure of the angle-of-attack preset fixture in this invention; Figure 5 This is a schematic diagram of the specific structure of the reducer in this invention; Figure 6 This is a schematic diagram of the specific structure of the aircraft simulator in this invention; Figure 7 This is a schematic diagram of the specific structure of the locking and separating mechanism in this invention; Figure 8 This is a schematic diagram of the specific structure of the driving component and the driven component in this invention; Figure 9 This is a schematic diagram of the specific structure of the separating cam in this invention.

[0017] Figure Labels 1. Suspension Truss; 101. Upper Chord Horizontal Member; 102. Upper Chord Longitudinal Member; 103. Lower Chord Horizontal Member; 104. Lower Chord Longitudinal Member; 105. Vertical Member; 106. Support; 107. Ground Beam; 108. Diagonal Member; 109. Square Tube Sleeve; 110. Round Tube Sleeve; 111. Tube Sleeve Connecting Block; 2. Angle of Attack Preset Fixture; 201. Base; 202. Mounting Ear Plate; 203. Positioning Pad; 204. Reducer; 205. Pitch Axis; 206. Input Axis; 207. Washer; 208. Crank Handle; 3. Aircraft Model Components: 301. Main wing; 302. Pitch pin; 303. Cover plate; 304. Servo; 305. Positioning shaft; 4. Locking and separating mechanism; 401. Main connecting block; 402. Locking and separating connecting block; 403. Single connecting block; 404. Drive shaft; 405. Drive gear; 406. Rack; 407. First bearing; 408. Driven shaft; 409. Driven gear; 410. Separating cam; 411. Second bearing; 412. Cam hole; 413. Separating pin; 414. Cam groove. Detailed Implementation

[0018] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0019] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0020] like Figures 1-9 As shown, a multi-condition aerial disassembly test device for a wingtip parallel combined aircraft is disclosed. The upper end of the suspension truss 1 is connected to a rotary-wing UAV. The lower end of the suspension truss 1 is equipped with angle-of-attack preset fixtures 2 on both sides. The angle-of-attack preset fixtures 2 can preset and lock the pitch angle of attack of the aircraft simulator 3 on the ground. The aircraft simulator 3 is installed on the side of the angle-of-attack preset fixtures 2 away from the suspension truss 1. The aircraft simulator 3 is used to simulate the aerodynamic shape of the main body in the combined aircraft and provide a real stress environment for the separation test. The aircraft simulator 3 is equipped with a locking separation mechanism 4, which is used to realize the connection and separation of the individual wings in the combined aircraft.

[0021] The suspended truss 1 includes two upper chord horizontal members 101, two upper chord vertical members 102, two lower chord horizontal members 103, and seven lower chord vertical members 104. The two upper chord vertical members 102 are installed between the two upper chord horizontal members 101, and the seven lower chord vertical members 104 are installed between the two lower chord horizontal members 103. Vertical members 105 are installed at both ends of the bottom surface of the upper chord horizontal members 101, and the bottom ends of the vertical members 105 are connected to the top surface of the lower chord horizontal members 103. Four supports 106 are evenly installed on the bottom surface of each lower chord horizontal member 103, and a ground beam 107 is installed between two supports 106. Diagonal members 108 are installed at both ends of the upper chord horizontal members 101, and the bottom ends of the diagonal members 108 are connected to the top surface of the lower chord horizontal members 103. Connectors are fitted on the diagonal members 108, and the connectors are connected to the rotary-wing UAV. Two angle-of-attack preset fixtures 2 are installed at both ends of the lower chord horizontal members 103.

[0022] The connector includes a square tube sleeve 109 and a round tube sleeve 110. A tube sleeve connecting block 111 is welded between the square tube sleeve 109 and the round tube sleeve 110. The square tube sleeve 109 is fitted onto the diagonal bar 108, and the round tube sleeve 110 is fitted onto the landing gear of a specified model of rotary-wing UAV and mates with the landing gear.

[0023] The angle-of-attack preset fixture 2 includes a base 201. Mounting holes are provided on both the left and right side walls of the base 201. Mounting ear plates 202 are fixed to the base 201 through the mounting holes. Mounting ear plates 202 are provided with mounting holes and are fixed between two lower chord crossbars 103 through the mounting holes. Mounting holes are provided on the inner bottom surface of the base 201. Positioning pads 203 are fixed inside the base 201 through the mounting holes. Positioning pads 203 are provided with mounting holes. Reducers 204 are fixed to positioning pads 203 through the mounting holes.

[0024] The reducer 204 is provided with an output shaft hole. The pitch shaft 205 is installed on the reducer 204 through the output shaft hole. The left and right side walls of the base 201 and the mounting ear plate 202 are provided with through holes. The other end of the pitch shaft 205 passes through the through hole in the side wall of the base 201 and the through hole in the mounting ear plate 202 in sequence. The part of the pitch shaft 205 that passes through is connected to the aircraft simulator 3. The front side wall of the reducer 204 is provided with an input shaft 206. The front side wall of the base 201 is provided with a through hole. The input shaft 206 passes through the through hole. The part of the input shaft 206 that passes through is provided with a rotating component.

[0025] The rotating assembly includes a washer 207 and a rocker arm 208. The washer 207 is sleeved on the input shaft 206, and the rocker arm 208 is mounted on one end of the side wall of the washer 207.

[0026] The aircraft simulator 3 includes a main wing 301. A shaft hole is provided on the side wall of the main wing 301 near the angle-of-attack preset fixture 2. The other end of a pitch axis 205 is inserted into the shaft hole of the main wing 301. Five evenly spaced pin holes are provided on the pitch axis 205, and pitch pins 302 pass through these pin holes. Cotter pin holes matching the pitch pins 302 are provided on the main wing 301. Both ends of the pitch pins 302 are placed inside the cotter pin holes, completing the positioning between the pitch axis 205 and the main wing 301. The top surface of the main body wing 301 is provided with a guide groove. The cover plate 303 is embedded in the main body wing 301 through the guide groove. The end of the main body wing 301 away from the angle of attack preset tooling 2 is provided with a mounting groove. The servo motor 304 is fixed inside the mounting groove by hot melt adhesive technology. The two ends of the side wall of the main body wing 301 away from the angle of attack preset tooling 2 are provided with shaft holes. The positioning shaft 305 is inserted into the shaft hole and fixed to the main body wing 301 by a pin. The locking separation mechanism 4 is connected to the output shaft of the servo motor 304 and the other end of the positioning shaft 305.

[0027] The specific implementation process of the preset aircraft simulator with a 3-angle of attack is as follows: Increasing Angle of Attack: Before the towed gantry 1 leaves the ground, the rotary-wing UAV controls the input shaft 206 to rotate by manually cranking the crank handle 208 clockwise. The output shaft hole of the reducer 204 rotates synchronously to the pitch axis 205. The main wing 301 is tightly engaged with the pitch axis 205 through the pitch pin 302. Thus, the main wing 301 rotates synchronously with the pitch axis 205, increasing the pitch angle and realizing the function of increasing the angle of attack of the aircraft simulator 3.

[0028] Process of reducing angle of attack: Before the towed gantry 1 leaves the ground, the rotorcraft UAV controls the input shaft 206 to rotate by manually cranking the crank handle 208 counterclockwise. The output shaft hole of the reducer 204 will rotate synchronously to the pitch axis 205. The main wing 301 is closely engaged with the pitch axis 205 through the pitch pin 302. Thus, the main wing 301 rotates synchronously with the pitch axis 205, and the pitch angle is reduced, realizing the function of reducing the angle of attack of the aircraft simulator 3.

[0029] The locking and separating mechanism 4 includes a main connecting block 401, a locking and separating connecting block 402 installed on one side of the main connecting block 401, and a single connecting block 403 installed on one side of the locking and separating connecting block 402. Both ends of the main connecting block 401, the locking and separating connecting block 402 and the single connecting block 403 are provided with shaft holes. The other end of the positioning shaft 305 passes through the shaft hole on the main connecting block 401 and the shaft hole on the locking and separating connecting block 402 in sequence, and is inserted into the shaft hole of the single connecting block 403. The main connecting block 401 and the locking and separating connecting block 402 are fixed to the positioning shaft 305 by pins. The single connecting block 403 and the positioning shaft 305 retain the axial direction of freedom of movement.

[0030] The locking separation connecting block 402 is internally equipped with a drive component and a driven component. The drive component is connected to the output shaft of the servo motor 304. The drive component and the driven component are interconnected. One end of the drive component and the driven component is connected to the main body connecting block 401, and the other end of the driven component is connected to the single unit connecting block 403.

[0031] The drive assembly includes a drive shaft 404, a drive gear 405, and a rack 406. First bearings 407 are fitted at both ends of the drive shaft 404. Bearing grooves are formed on the sidewalls of the main connecting block 401 and the locking / separating connecting block 402, which are close to each other. The first bearing 407 at the front end of the drive shaft 404 connects to the bearing groove on the sidewall of the main connecting block 401, and the first bearing 407 at the rear end of the drive shaft 404 connects to the bearing groove on the sidewall of the locking / separating connecting block 402. The end of the drive shaft 404 closest to the main connecting block 401 is connected to the servo motor. The output shaft of 304 is fixed, the drive gear 405 is sleeved in the middle of the drive shaft 404, the side wall of the locking and separating connecting block 402 is provided with a sliding groove, the rack 406 is embedded in the inside of the sliding groove and slides along the sliding groove, the drive gear 405 and the rack 406 mesh with each other, the side wall of the main connecting block 401 is provided with a protrusion at the position corresponding to the sliding groove, the protrusion is inserted into the inside of the sliding groove and contacts the side wall of the rack 406, the driven components are symmetrically arranged at both ends of the locking and separating connecting block 402, and the driven components contact the rack 406.

[0032] The driven assembly includes a driven shaft 408, a driven gear 409, and a separating cam 410. Second bearings 411 are sleeved at both ends of the driven shaft 408. The second bearing 411 at the front end of the driven shaft 408 is connected to the bearing groove on the side wall of the main connecting block 401, and the second bearing 411 at the rear end of the driven shaft 408 is connected to the bearing groove on the side wall of the locking separating connecting block 402. The driven gear 409 is sleeved in the middle of the driven shaft 408 and meshes with the rack 406. One end of the driven shaft 408 near the individual connecting block 403 is threadedly connected to the separating cam 410, and the other end of the separating cam 410 passes through the bearing groove on the side wall of the locking separating connecting block 402 and is connected to the individual connecting block 403.

[0033] The side wall of the single connecting block 403 is provided with a cam hole 412. A separation pin 413 is installed inside the cam hole 412. During the locking process, the separation cam 410 and the cam hole 412 cooperate with each other. A cam groove 414 is provided on the separation cam 410. The two ends of the separation pin 413 are embedded in the cam groove 414 inside the separation cam 410, thereby realizing that when the separation cam 410 rotates, it drives the separation pin 413 to move axially, and finally realizes the axial movement of the single wing connecting block.

[0034] The specific implementation process of the locking and separating mechanism 4 is as follows: Locking process: The cam hole 412 on the unit connecting block 403 corresponds to the separating cam 410, the separating pin 413 contacts the cam groove 414, the servo motor 304 receives the locking signal, starts and rotates counterclockwise, the drive shaft 404 transmits synchronously to the driven shaft 408 and the separating cam 410 through the drive gear 405 and rack 406; the separating cam 410 rotates counterclockwise, the separating pin 413 slides relative to the inner wall of the cam groove 414, the bottom of the cam groove 414 gradually approaches the end of the separating pin 413 in the circumferential direction, the separating pin 413 is screwed in and pulled axially, realizing the tight constraint with the separating cam 410. At this time, the unit connecting block 403 and the locking separating connecting block 402 are tightly connected in the axial direction, realizing the locking function of the locking separating mechanism 4.

[0035] Separation process: When the servo motor 304 receives the separation signal, it starts and rotates clockwise. The drive shaft 404 transmits synchronously to the driven shaft 408 and the separation cam 410 through the drive gear 405 and rack 406. The separation cam 410 rotates clockwise, and the separation pin 413 slides relative to the inner wall of the cam groove 414. The groove opening of the cam groove 414 gradually approaches the end of the separation pin 413 in the circumferential direction. The separation pin 413 is rotated out and pushed out axially until the axial constraint of the separation pin 413 of the separation cam 410 is released. At this time, the axial constraint between the single connecting block 403 and the locking separation connecting block 402 is released, and the single connecting block 403 disengages from the locking separation connecting block 402, realizing the separation function of the locking separation mechanism 4.

[0036] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A multi-condition aerial disassembly test device for a wingtip parallel combined aircraft, characterized in that: The system includes a suspension truss, the upper end of which is connected to a rotary-wing UAV. The lower end of the suspension truss is connected to two sides with angle-of-attack preset fixtures for presetting and locking the pitch angle of attack of the aircraft. One side of the angle-of-attack preset fixture is connected to an aircraft simulator for simulating the aerodynamic shape of the main body in the combined aircraft. The aircraft simulator is connected to a locking and separation mechanism for realizing the connection and separation of the individual wings in the combined aircraft. The suspended truss includes an upper chord horizontal member, an upper chord vertical member, a lower chord horizontal member, and a lower chord vertical member. The upper chord horizontal members and the upper chord vertical members are interconnected, and the lower chord horizontal members and the lower chord vertical members are interconnected. Vertical members are connected to both ends of the bottom surface of the upper chord horizontal member, and the bottom ends of the vertical members are connected to the top surface of the lower chord horizontal member. A support is connected to the bottom surface of the lower chord horizontal member, and a ground beam is connected to the bottom end of the support. Diagonal members are connected to both ends of the upper chord horizontal member, and the bottom ends of the diagonal members are connected to the top surface of the lower chord horizontal member. A connector is connected to the diagonal member, and the connector is connected to the rotary-wing UAV. The angle-of-attack preset fixture is set on the lower chord horizontal member. The angle-of-attack preset fixture includes a base, with mounting lugs at both ends of the base. The mounting lugs are connected to the lower chord crossbar. A positioning pad is provided inside the base, and a reducer is provided on the positioning pad. A pitch axis is connected to one side of the reducer, and the other end of the pitch axis passes through the base and the mounting lugs in sequence and is connected to the aircraft simulator. An input shaft is provided on one side of the reducer, and the other end of the input shaft passes through the side wall of the base and is connected to a rotating component. The aircraft simulator includes a main wing, the other end of the pitch axis is inserted into the interior of the main wing, a pitch pin is provided between the main wing and the pitch axis, a cover plate is embedded on the top surface of the main wing, a servo is provided in the middle of the side wall of the main wing, and positioning shafts are inserted at both ends of the side wall of the main wing. The locking and separating mechanism is connected to the servo and the positioning shafts. The locking and separating mechanism includes a main connecting block, a locking and separating connecting block on one side of the main connecting block, and a single connecting block on the other side of the locking and separating connecting block. The other end of the positioning shaft passes through the main connecting block and the locking and separating connecting block in sequence and is inserted into the single connecting block. A driving component and a driven component are disposed inside the locking and separating connecting block. The driving component is connected to the output shaft of the servo motor. The driving component and the driven component are interconnected. One end of the driving component and the driven component is connected to the main connecting block, and the other end of the driven component is connected to the single connecting block. The drive assembly includes a drive shaft, a drive gear, and a rack. The drive shaft has first bearings at both ends. One first bearing is connected to the main body connecting block, and the other first bearing is connected to the locking and separating connecting block. One end of the drive shaft is connected to the output shaft of the servo motor. The drive gear is sleeved in the middle of the drive shaft. The rack is disposed inside the locking and separating connecting block and meshes with the drive gear. The driven assembly contacts the rack.

2. The multi-condition aerial disassembly test device for a wingtip parallel combined aircraft according to claim 1, characterized in that: The connector includes a square tube sleeve and a round tube sleeve, with a tube sleeve connecting block connecting the square tube sleeve and the round tube sleeve. The square tube sleeve is connected to the diagonal rod, and the round tube sleeve is connected to the rotary-wing UAV.

3. The multi-condition aerial disassembly test device for a wingtip parallel combined aircraft according to claim 2, characterized in that: The rotating assembly includes a washer and a rocker arm. The washer is fitted onto the input shaft, and the rocker arm is located at one end of the side wall of the washer.

4. The multi-condition aerial disassembly test device for a wingtip parallel combined aircraft according to claim 3, characterized in that: The driven assembly includes a driven shaft, a driven gear, and a separating cam. The driven shaft has second bearings at both ends. One second bearing is connected to the main body connecting block, and the other second bearing is connected to the locking separating connecting block. The driven gear is sleeved in the middle of the driven shaft and meshes with the rack. One end of the separating cam is connected to the driven shaft, and the other end of the separating cam passes through the locking separating connecting block and is connected to the single-unit connecting block.

5. The multi-condition aerial disassembly test device for a wingtip parallel combined aircraft according to claim 4, characterized in that: The single connecting block has a cam hole on its side wall, a separation pin is provided inside the cam hole, a cam groove is provided on the separation cam, the separation cam is inserted into the cam hole, and the cam groove is in contact with the separation pin.

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