A fixed-wing unmanned aerial vehicle take-off and landing auxiliary device

Abstract

The application relates to the field of fixed-wing unmanned plane taking-off and landing technology, in particular to a fixed-wing unmanned plane taking-off and landing auxiliary device, which comprises a fixed-wing unmanned plane and a multi-rotor unmanned plane, a main lock and a vice lock are arranged between the fixed-wing unmanned plane and the multi-rotor unmanned plane, and the main lock and the vice lock are used for connecting the front and rear ends of the fixed-wing unmanned plane to the multi-rotor unmanned plane. The fixed-wing unmanned plane is taken off and landed by the multi-rotor unmanned plane, on one hand, the multi-rotor unmanned plane has almost no requirement for a taking-off site, can execute the unmanned plane taking-off and landing task on a narrow space and rugged terrain, on the other hand, the taking-off and landing process of the fixed-wing unmanned plane does not need to consume fuel, and the voyage and the flight time of the fixed-wing unmanned plane are increased.

Description

Technical Field

[0001] This invention relates to the field of fixed-wing unmanned aerial vehicle (UAV) take-off and landing technology, specifically to a fixed-wing UAV take-off and landing auxiliary device. Background Technology

[0002] Currently, the main takeoff methods for fixed-wing UAVs include runway takeoff, vehicle-mounted takeoff, catapult takeoff, rocket-assisted takeoff, and launch vehicle takeoff.

[0003] Takeoff is achieved by accelerating to a certain speed on the ground, which allows the aircraft to gain enough lift to leave the ground and begin flight.

[0004] Vehicle-mounted takeoff involves the aircraft being fixed to a launch vehicle. During takeoff, the aircraft's engine is started, propelling the launch vehicle to begin its runway roll. Once the runway speed is high enough, the aircraft has sufficient lift to take off. At this point, the aircraft detaches from the launch vehicle and begins its ascent.

[0005] Both runway takeoff and vehicle-mounted takeoff require a sufficiently long runway, which is obviously not suitable for drone takeoff in confined spaces. In addition, both of these takeoff methods require the drone to consume some energy during the takeoff phase, and wheeled drones must also be equipped with landing gear, which increases the structural weight and takeoff weight of the drone and shortens the endurance of fixed-wing drones.

[0006] Catapult takeoff is a takeoff method that uses a catapult to rapidly accelerate an aircraft and lift it off the ground. Rocket-assisted takeoff for drones utilizes rockets or rocket engines to provide additional thrust, aiding in takeoff. While both catapult and rocket-assisted takeoffs do not consume fuel, the acceleration of the drone during these processes is significant, subjecting the fuselage to substantial impact loads. This necessitates higher structural strength and toughness for the drone, inevitably increasing its weight to prevent structural failure. It also addresses the limitation of fixed-wing drones' short endurance. Furthermore, catapults are typically disposable, requiring maintenance after each use, increasing preparation time and cost, and limiting the maximum number of consecutive takeoffs within a given period. Additionally, catapult takeoff requires the installation of a catapult, which may be unsuitable for confined spaces, as it occupies considerable space. In addition, when fixed-wing UAVs need to take off from small ships or other vessels with limited space, the aircraft are constantly rolling and pitching while sailing on these small ships. Furthermore, the wind speed and direction on the sea surface are unstable, and the angle of attack changes greatly during the takeoff run, which seriously affects takeoff safety. Therefore, only large ships such as aircraft carriers and amphibious assault ships can stably launch and land fixed-wing UAVs. However, these large ships are high-value targets and are easily detected by the enemy in naval warfare, making them unsuitable as launch platforms for small fixed-wing UAVs.

[0007] In general, each traditional drone takeoff method has its own drawbacks. Runway takeoff requires a long and straight runway, and the takeoff process consumes the drone's energy; catapult takeoff requires a lot of space and a certain amount of preparation time; rocket-assisted takeoff has a large acceleration, which places high demands on the structural strength of the drone; in terms of recovery, parachute recovery has a slow landing speed, the landing point is greatly affected by wind, and it cannot be recovered on small areas (such as small ships); runway landing requires the design of landing gear, which increases the structural weight; and net-based recovery has many limitations on the drone's weight, overload, and speed.

[0008] Therefore, a take-off and landing auxiliary device for fixed-wing UAVs was designed. Summary of the Invention

[0009] The purpose of this invention is to provide a fixed-wing unmanned aerial vehicle (UAV) take-off and landing assistance device to solve the problems mentioned in the background art.

[0010] To achieve the above objectives, the present invention provides the following technical solution: a fixed-wing UAV take-off and landing auxiliary device, comprising a fixed-wing UAV and a multi-rotor UAV, wherein a main lock and a secondary lock are provided between the fixed-wing UAV and the multi-rotor UAV, and the main lock and the secondary lock are used to connect the front and rear ends of the fixed-wing UAV to the multi-rotor UAV.

[0011] Preferably, the main lock includes a locking sleeve mounted on a fixed-wing UAV and a locking tongue mechanism mounted on a multi-rotor UAV, wherein the locking tongue mechanism is detachably connected to the locking sleeve by a plug-in locking method.

[0012] Preferably, the locking sleeve has a stored state that is housed inside the fixed-wing UAV and an external state that is released outside the fixed-wing UAV.

[0013] Preferably, the locking sleeve can rotate between a retracted state and an external state;

[0014] The front end of the locking sleeve is rotatably connected to the fixed-wing UAV;

[0015] The locking tongue mechanism is inserted into the locking sleeve from back to front.

[0016] Preferably, the locking sleeve is a four-sided pyramid shape with a pointed front and a wider rear, and the rear end of the locking sleeve is provided with two locking protrusions;

[0017] The locking mechanism includes a slide rod, a top cone and an electromagnet fixed at the front and rear ends of the slide rod, and two wing plates. The two wing plates are horizontally opposite each other on both sides of the axial direction of the slide rod with the front being narrower and the rear being wider. The front end of the wing plate is hinged to the top cone. A spring and a slider are sleeved on the slide rod. The slider is connected to the electromagnet through the spring. A first connecting rod is provided between the slider and the two wing plates. The slide rod is mounted on a multi-rotor UAV by a bracket.

[0018] When the locking tongue mechanism is inserted and locked inside the locking sleeve, the rear end of the wing plate abuts against the locking protrusion.

[0019] Preferably, the secondary lock includes a base mounted on the multi-rotor UAV and a clamping mechanism for fixing the tail support of the fixed-wing UAV to the base;

[0020] After the locking tongue mechanism is inserted and locked inside the locking sleeve, the tail support falls onto the base.

[0021] Preferably, the clamping mechanism includes a clamping part and a driving part, wherein the driving part drives the clamping part to clamp the tail support onto the base.

[0022] Preferably, the clamping part includes two flaps;

[0023] The drive unit includes two servo motors that correspond one-to-one with the two valves;

[0024] A second link connects the output shaft of the servo motor and the corresponding flap door of the servo motor.

[0025] The servo motor drives the valve to open or close.

[0026] Preferably, when the valves are closed, the base cooperates with the two valves to form a channel that matches the shape of the tail support.

[0027] Preferably, the inner surface of the channel is provided with a plurality of elastic rollers, and the rolling direction of the elastic rollers is consistent with the extension direction of the channel.

[0028] Compared with the prior art, the beneficial effects of the present invention are:

[0029] This invention utilizes a multi-rotor UAV to achieve the takeoff and landing of a fixed-wing UAV. On the one hand, since multi-rotor UAVs have almost no requirements for takeoff sites, they can perform UAV takeoff and landing missions in confined spaces and rugged terrain, thus enabling fixed-wing UAVs to take off and land flexibly in special scenarios such as small ships and mountains. On the other hand, the takeoff and landing process of fixed-wing UAVs does not consume fuel (or electricity), increasing the combat radius of fixed-wing UAVs. Furthermore, fixed-wing UAVs do not require landing gear, and the acceleration during takeoff and landing is not large, which can reduce structural strength and thus reduce weight, thereby increasing range and flight time. Finally, the takeoff preparation process of fixed-wing UAVs is simple and the takeoff preparation time is short, which can greatly improve the takeoff and landing efficiency of fixed-wing UAVs, thereby increasing combat intensity. Moreover, by setting a main lock and a secondary lock to connect the front and rear ends of the fixed-wing UAV to the multi-rotor UAV, a stable connection between the fixed-wing UAV and the multi-rotor UAV is achieved, ensuring that the multi-rotor UAV can safely and stably transport the fixed-wing UAV to a suitable location. Attached Figure Description

[0030] Figure 1 This is a side view of the structure of the present invention;

[0031] Figure 2 This is a schematic diagram of the isometric side view structure of the present invention;

[0032] Figure 3 This is a schematic diagram of the main lock structure of the present invention;

[0033] Figure 4 This is a schematic diagram of the secondary lock structure of the present invention.

[0034] In the diagram: 1. Fixed-wing UAV; 11. Tail support; 2. Multi-rotor UAV; 3. Main lock; 31. Locking sleeve; 311. Locking boss; 32. Locking tongue mechanism; 321. Slide bar; 322. Top cone; 323. Electromagnet; 324. Wing plate; 325. Spring; 326. Slider; 327. First connecting rod; 328. Bracket; 4. Secondary lock; 41. Base; 42. Clamping mechanism; 421. Pressing part; 4211. Door; 422. Drive part; 4221. Servo motor; 423. Second connecting rod; 424. Elastic roller. Detailed Implementation

[0035] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0036] Please see Figure 1-4The present invention provides a technical solution:

[0037] A fixed-wing UAV take-off and landing assistance device includes a fixed-wing UAV 1 and a multi-rotor UAV 2. A main lock 3 and a secondary lock 4 are provided between the fixed-wing UAV 1 and the multi-rotor UAV 2. The main lock 3 and the secondary lock 4 are used to connect the front and rear ends of the fixed-wing UAV 1 to the multi-rotor UAV 2. In this embodiment, the multi-rotor UAV 2 can be a quadcopter UAV, and the multi-rotor UAV 2 is connected to the bottom of the fixed-wing UAV 1. During actual take-off, the multi-rotor UAV 2 can be used to transport the fixed-wing UAV 1 to a suitable altitude, and then the multi-rotor UAV 2 can be detached from the fixed-wing UAV 1. The purpose of connecting the multi-rotor UAV 2 to the bottom of the fixed-wing UAV 1 in this invention is to facilitate the engagement and disengagement of the fixed-wing UAV 1 and the multi-rotor UAV 2. During actual landing, the multi-rotor UAV 2 is first connected and fixed to the bottom of the fixed-wing UAV 1, and then the multi-rotor UAV 2 transports the fixed-wing UAV 1 to the designated position.

[0038] In the above scheme, a multi-rotor UAV 2 is used to complete the takeoff and landing of a fixed-wing UAV 1. On the one hand, since the multi-rotor UAV 2 has almost no requirements for the takeoff site, it can perform UAV takeoff and landing missions in confined spaces and rugged terrain, thus enabling the fixed-wing UAV 1 to take off and land flexibly in special scenarios such as small ships and mountains. On the other hand, the fixed-wing UAV 1 does not consume fuel (or electricity) during takeoff, increasing its combat radius. Furthermore, the fixed-wing UAV 1 does not need to be equipped with landing gear, and its takeoff and landing acceleration is not large, which can reduce structural strength and thus reduce weight, thereby increasing range and flight time. Finally, the takeoff preparation process of the fixed-wing UAV 1 is simple and the takeoff preparation time is short, which can greatly improve the takeoff and landing efficiency of the fixed-wing UAV 1, thereby increasing combat intensity. Moreover, by setting the main lock 3 and the secondary lock 4 to connect the front and rear ends of the fixed-wing UAV 1 to the multi-rotor UAV 2, a stable connection between the fixed-wing UAV 1 and the multi-rotor UAV 2 is achieved, ensuring that the multi-rotor UAV 2 can safely and stably transport the fixed-wing UAV 1 to a suitable location.

[0039] like Figure 3 As shown, the main lock 3 includes a locking sleeve 31 mounted on the fixed-wing UAV 1 and a locking tongue mechanism 32 mounted on the multi-rotor UAV 2. The locking tongue mechanism 32 is detachably connected to the locking sleeve 31 via a plug-in locking method. When the locking tongue mechanism 32 is plugged into and locked inside the locking sleeve 31, the fixed-wing UAV 1 and the multi-rotor UAV 2 are fixedly connected together; conversely, when the locking tongue mechanism 32 is separated from the locking sleeve 31, the fixed-wing UAV 1 and the multi-rotor UAV 2 are separated.

[0040] By setting the main lock 3 into two parts, namely the locking sleeve 31 connected to the fixed-wing UAV 1 and the locking tongue mechanism 32 connected to the multi-rotor UAV 2, and by making the locking tongue mechanism 32 detachably connected to the locking sleeve 31 by means of plug-in locking, the connection, fixation and disassembly of the locking sleeve 31 and the locking tongue mechanism 32 are facilitated, which also facilitates the combination and separation of the fixed-wing UAV 1 and the multi-rotor UAV 2.

[0041] Furthermore, the locking sleeve 31 has a retracted state inside the fixed-wing drone 1 and an external state outside the fixed-wing drone 1. Specifically, the fixed-wing drone 1 has an openable and closable hatch at its bottom. During the flight of the fixed-wing drone 1, the locking sleeve 31 is retracted inside the fixed-wing drone 1, that is, the locking sleeve 31 is in the retracted state; when the fixed-wing drone 1 needs to engage with the multi-rotor drone 2, the hatch at the bottom of the fixed-wing drone 1 will open, and then the locking sleeve 31 will move out from the open hatch, waiting for the locking tongue mechanism 32 to engage and lock.

[0042] The retractable design of the locking sleeve 31 allows it to be stored inside the fixed-wing UAV 1 during flight, thereby reducing the air resistance of the entire fixed-wing UAV 1 during flight and further increasing its range and flight time.

[0043] Furthermore, in this embodiment, the locking sleeve 31 can rotate between a retracted state and an external state. That is, when the locking sleeve 31 is in the retracted state, it can be rotated downwards by a certain angle to change the locking sleeve 31 from the retracted state to the external state.

[0044] For ease of description in this embodiment, the forward direction of the fixed-wing UAV 1 during flight is defined as forward. The front end of the locking sleeve 31 is rotatably connected to the fixed-wing UAV 1; the locking tongue mechanism 32 is inserted into the locking sleeve 31 from back to front. Therefore, when the locking sleeve 31 is in the external position, the locking sleeve 31 has a certain tilt angle. The existence of this tilt angle facilitates the locking of the secondary lock 4 onto the tail support 11. The specific principle will be described in detail below.

[0045] like Figure 3 As shown, the locking sleeve 31 is a four-sided pyramid shape with a pointed front and a wide rear. It is hollow inside and has an opening at the rear end for the locking tongue mechanism 32 to be inserted. The rear end of the locking sleeve 31 is provided with two locking protrusions 311, which are fixed at the left and right edges of the opening.

[0046] like Figure 3As shown, the locking tongue mechanism 32 matches the locking sleeve 31. The locking tongue mechanism 32 includes a slide rod 321, a top cone 322 and an electromagnet 323 fixed at the front and rear ends of the slide rod 321, and two wing plates 324. The slide rod 321 is cylindrical, the top cone 322 is a square pyramid, and the two wing plates 324 are horizontally opposed on both sides of the axial direction of the slide rod 321 in a way that is narrower at the front and wider at the rear. From the front end to the rear end of the slide rod 321, the distance between the wing plates 324 and the slide rod 321 gradually increases, and the front end of the wing plates 324 is hinged to the top cone 322. A spring 325 and a slider 326 are fitted on the slider 321. The slider 326 can slide along the axis of the slider 321. The slider 326 is connected to the electromagnet 323 through the spring 325. The distance between the slider 326 and the electromagnet 323 is such that the electromagnet 323 can attract the slider 326 after it is energized. A first connecting rod 327 is provided between the slider 326 and the two wing plates 324. The angle between the first connecting rod 327 and the wing plate 324 is an obtuse angle. The slider 321 is mounted on the multi-rotor UAV 2 through the bracket 328.

[0047] When the locking tongue mechanism 32 is inserted and locked inside the locking sleeve 31, the rear end of the wing plate 324 abuts against the locking boss 311, thereby locking the locking tongue mechanism 32 inside the locking sleeve 31.

[0048] The locking and releasing principle between the locking sleeve 31 and the locking tongue mechanism 32 is as follows: When the locking tongue mechanism 32 needs to be inserted and locked into the locking sleeve 31, that is, when the fixed-wing UAV 1 and the multi-rotor UAV 2 are joined, firstly, the hatch at the bottom of the fixed-wing UAV 1 is opened, and the locking sleeve 31 is rotated downwards at a certain angle, so that the locking sleeve 31 changes from the retracted state to the external state. At this time, the locking sleeve 31 has a certain downward tilt angle, and the electromagnet 323 is de-energized, and the slider 3... 26 moves forward along slide bar 321 under the action of spring 325 to the maximum extension of spring 325, thereby driving wing plate 324 to rotate to the maximum angle under the action of first link 327, that is, the included angle between the two wing plates 324 is maximized at this time. Then, locking tongue mechanism 32 moves together with multi-rotor UAV 2 and gradually approaches locking sleeve 31. Since the front end of locking tongue mechanism 32 is provided with top cone 322 and locking sleeve 31 is a four-sided pyramid shape with a pointed front and a wide rear, it gradually approaches the locking sleeve 31. The front end of the locking tongue mechanism 32 at the rear opening of the locking sleeve 31 can be easily inserted into the rear opening of the locking sleeve 31 via the top cone 322. Subsequently, as the multi-rotor UAV 2 continues to move forward, the locking tongue mechanism 32 gradually penetrates deeper into the interior of the locking sleeve 31. During this process, the two wing plates 324 are forced to rotate inward by the pressure of the two locking bosses 311 at the opening position. That is, the included angle between the two wing plates 324 gradually decreases under the pressure of the two locking bosses 311. The slider 326 moves backward, and the spring 32... 5. Retraction; When the wing plate 324 is fully inserted into the locking sleeve 31, the rear end of the wing plate 324 disengages from the locking boss 311, and the spring 325 quickly returns to its original length. At this time, the two wing plates 324 can rotate outward again under the action of the spring 325, that is, the included angle between the two wing plates 324 increases again until the rear end of the wing plate 324 abuts against the front side of the locking boss 311, thus completing the locking between the locking tongue mechanism 32 and the locking sleeve 31, and the main lock 3 enters the locked state. After that, the secondary lock 4 needs to enter the locked state to complete the fixation of the entire fixed-wing UAV 1, as follows.

[0049] like Figure 4 As shown, the secondary lock 4 includes a base 41 mounted on the multi-rotor drone 2 and a clamping mechanism 42 for fixing the tail support 11 of the fixed-wing drone 1 to the base 41; after the locking tongue mechanism 32 is inserted and locked inside the locking sleeve 31, the tail support 11 falls onto the base 41. The clamping mechanism 42 can clamp the tail support 11 onto the base 41 after it falls onto the base 41.

[0050] Furthermore, the clamping mechanism 42 includes a clamping part 421 and a driving part 422, the driving part 422 driving the clamping part 421 to clamp the tail support 11 onto the base 41.

[0051] Furthermore, the clamping part 421 includes two flaps 4211; the driving part 422 includes two servo motors 4221 corresponding to the two flaps 4211; a second connecting rod 423 is connected between the output shaft of the servo motor 4221 and the flap 4211 corresponding to the servo motor 4221; the servo motor 4221 drives the flaps 4211 to open or close.

[0052] When the valve gate 4211 is closed, the base 41 cooperates with the two valve gates 4211 to form a channel that matches the shape of the tail support 11. In this embodiment, the channel is cylindrical.

[0053] In this embodiment, the base 41 is semi-cylindrical with a semi-circular groove at the top. Two servo motors 4221 are symmetrically arranged on both sides of the axial direction of the base 41. Two flaps 4211 are hinged to the top of the base 41 and are quarter-cylindrical in shape. When closed, the two flaps 4211 can form a semi-cylindrical shape, which, together with the base 41, constitutes a complete cylinder to limit the tail support 11.

[0054] The locking process of the secondary lock 4 is as follows: After the main lock 3 enters the locked state, the tail boom 11 of the fixed-wing UAV 1 falls into the semi-circular groove of the base 41. Then, the servo motor 4221 is activated, and the output axis of the servo motor 4221 rotates in a direction that gradually approaches the base 41. Under the action of the second link 423, the two flaps 4211 are pushed to gradually close, and finally the position of the tail boom 11 is limited, and the secondary lock 4 enters the locked state.

[0055] In the above scheme, since the locking sleeve 31 has a certain downward tilt angle when it is in the external position, the multi-rotor UAV 2 is always in an upward tilt state during the process of the locking tongue mechanism 32 being inserted into the locking sleeve 31 until it is locked. Therefore, during the locking process of the main lock 3, the horizontal height of the tail support 11 is higher than the horizontal height of the highest point of the flap 4211 when it is in the open state, and the flap 4211 will not obstruct the tail support 11 from falling into the base 41. Moreover, since the locking of the main lock 3 is mainly achieved through the two wing plates in the middle and later stages, the locking process is mainly achieved through the two wing plates. The precise positioning achieved by the cooperation between the slide bar 324 and the two locking protrusions 311 ensures that the distance between the slide bar 321 and the two locking protrusions 311 remains approximately equal. Thus, during the locking process of the main lock 3, the cooperation between the wing plate 324 and the locking protrusions 311 provides a positioning basis for the locking of the tail support 11 by the auxiliary lock 4, ensuring that the tail support 11 is always above the base 41. This ensures that the tail support 11 can accurately fall into the base 41 after the main lock 3 is locked, facilitating the quick and precise locking of the tail support 11 by the auxiliary lock 4.

[0056] Furthermore, the inner surface of the channel formed by the base 41 and the two flaps 4211 is provided with multiple elastic rollers 424, and the rolling direction of the elastic rollers 424 is consistent with the extension direction of the channel. This prevents excessive friction between the secondary lock 4 and the tail support 11. In this embodiment, two sets of elastic rollers 424 are provided, each set containing 4-8 rollers arranged in a ring, with the two sets of elastic rollers 424 respectively located at the front and rear ends of the channel.

[0057] The elastic roller 424 includes a roller shaft and a spring. The roller shaft is connected to the inner surface of the channel through the spring, thereby realizing the floating of the roller and further reducing the contact pressure and friction. Furthermore, a groove is provided on the inner surface of the channel to accommodate the elastic roller 424, so that each elastic roller 424 protrudes less than half of itself from the inner surface of the channel under normal conditions.

[0058] The process of releasing the fixed-wing UAV 1 by the main lock 3 and the secondary lock 4 in this invention is as follows: First, the two servo motors 4221 in the secondary lock 4 are activated, causing the output axis of the servo motors 4221 to rotate outward. This, in conjunction with the second connecting rod 423, can pull the two flaps 4211 open. At this time, the tail support 11 can be separated from the base 41, and the secondary lock 4 enters the unlocked state. After that, the electromagnet 323 of the main lock 3 is energized, attracting the slider 326 to slide towards the electromagnet 323 against the elastic force of the spring 325. This causes the two wing plates 324 to rotate inward through the first connecting rod 327, that is, the included angle between the two wing plates 324 gradually decreases, causing the rear end of the wing plate 324 to slide out of the locking boss 311. Then, the locking tongue mechanism 32 exits from the inside of the locking sleeve 31, and the main lock 3 enters the unlocked state. At this time, the fixed-wing UAV 1 separates from the multi-rotor UAV 2.

[0059] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A take-off and landing auxiliary device for a fixed-wing unmanned aerial vehicle, characterized in that, It includes fixed-wing drones and multi-rotor drones, and a main lock and a secondary lock are provided between the fixed-wing drones and the multi-rotor drones. The main lock and the secondary lock are used to connect the front and rear ends of the fixed-wing drone to the multi-rotor drone. The main lock includes a locking sleeve mounted on a fixed-wing UAV and a locking tongue mechanism mounted on a multi-rotor UAV. The locking tongue mechanism is detachably connected to the locking sleeve by a plug-in locking method. The locking sleeve has a stored state that is housed inside the fixed-wing UAV and an external state that is released outside the fixed-wing UAV. The locking sleeve can rotate between a retracted state and an external state. The front end of the locking sleeve is rotatably connected to the fixed-wing UAV; The locking tongue mechanism is inserted into the locking sleeve from back to front; The locking sleeve is a four-sided pyramid shape with a pointed front and a wider rear, and the rear end of the locking sleeve is provided with two locking protrusions. The locking mechanism includes a slide rod, a top cone and an electromagnet fixed at the front and rear ends of the slide rod, and two wing plates. The two wing plates are horizontally opposite each other on both sides of the axial direction of the slide rod with the front being narrower and the rear being wider. The front end of the wing plate is hinged to the top cone. A spring and a slider are sleeved on the slide rod. The slider is connected to the electromagnet through the spring. A first connecting rod is provided between the slider and the two wing plates. The slide rod is mounted on a multi-rotor UAV by a bracket. When the locking tongue mechanism is inserted and locked inside the locking sleeve, the rear end of the wing plate abuts against the locking protrusion. The secondary lock includes a base mounted on the multi-rotor UAV and a clamping mechanism for fixing the tail support of the fixed-wing UAV to the base. After the locking tongue mechanism is inserted and locked inside the locking sleeve, the tail support falls onto the base; The clamping mechanism includes a clamping part and a driving part, wherein the driving part drives the clamping part to clamp the tail support onto the base. During unlocking, the secondary lock is first unlocked by controlling the clamping part to open and release the tail support through the drive unit, and then the main lock is unlocked by energizing the electromagnet to drive the bolt mechanism to exit the locking sleeve.

2. The fixed-wing unmanned aerial vehicle take-off and landing auxiliary device according to claim 1, characterized in that: The clamping part includes two valves; The drive unit includes two servo motors that correspond one-to-one with the two valves; A second link connects the output shaft of the servo motor and the corresponding flap door of the servo motor. The servo motor drives the valve to open or close.

3. The fixed-wing UAV take-off and landing auxiliary device according to claim 2, characterized in that: When the valves are closed, the base cooperates with the two valves to form a channel that matches the shape of the tail support.

4. The fixed-wing unmanned aerial vehicle take-off and landing auxiliary device according to claim 3, characterized in that: The inner surface of the channel is provided with a plurality of elastic rollers, and the rolling direction of the elastic rollers is consistent with the extension direction of the channel.

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