Launching and recycling integrated electromagnetic short-distance take-off and landing system suitable for fixed-wing unmanned aerial vehicle

Abstract

The invention relates to a launching and recycling integrated electromagnetic short-distance take-off and landing system suitable for a fixed-wing unmanned aerial vehicle, and belongs to the technical field of take-off and landing systems. Part of the mechanical transmission system is arranged on the vehicle system, and part of the mechanical transmission system is pre-arranged on the ground; the power system is arranged on the vehicle system and is connected with the mechanical transmission system; wherein by controlling the output direction of the power system, the mechanical transmission system selectively applies traction force the same as the movement direction to the fixed-wing unmanned aerial vehicle to achieve catapult-assisted take-off, or applies braking force opposite to the movement direction to achieve arresting recovery. The short-distance take-off and landing function of the fixed-wing unmanned aerial vehicle can be achieved, and take-off and landing flexibility of the unmanned aerial vehicle is improved; the construction difficulty and cost of the take-off and landing infrastructure are reduced, and the deployment efficiency is improved; meanwhile, the take-off and landing energy consumption of the unmanned aerial vehicle is reduced, the take-off and landing frequency of the unmanned aerial vehicle is improved, and the bearing capacity and the cruising range of the fixed-wing unmanned aerial vehicle are

Description

Technical Field

[0001] This application relates to the field of take-off and landing systems, and in particular to an integrated launch and recovery electromagnetic short take-off and landing system suitable for fixed-wing unmanned aerial vehicles. Background Technology

[0002] Fixed-wing unmanned aerial vehicles (UAVs), as an important type of unmanned aerial vehicle, have been widely used in both military and civilian fields due to their advantages such as high aerodynamic efficiency, long flight time, and relatively strong payload capacity. However, their traditional take-off and landing methods heavily rely on fixed runways that are hundreds of meters or even kilometers long, which greatly limits their application flexibility in areas with weak infrastructure or at the forefront. To overcome this limitation, short take-off and landing (STOL) technology has become crucial, the core of which lies in achieving short-distance catapult take-off and arrested recovery of UAVs.

[0003] Currently, mature short takeoff and landing (STOVL) technologies are mainly based on the takeoff and landing systems of aircraft carrier-based aircraft. For takeoff, steam catapults or electromagnetic catapults are primarily used. Steam catapults use stored high-pressure steam to drive pistons, propelling the aircraft along the deck track for acceleration; electromagnetic catapults utilize the principle of linear motors to convert stored electrical energy into the aircraft's kinetic energy. For recovery, hydraulic arresting gear or turbine-electric arresting gear are commonly used. Hydraulic arresting systems convert the aircraft's kinetic energy into the thermal and pressure energy of the liquid through hydraulic cylinders; turbine-electric arresting gear uses hydraulic turbines and motors to absorb the enormous energy generated during landing.

[0004] Although the aforementioned technologies have been successfully applied on medium and large aircraft carriers, their direct application to the highly maneuverable take-off and landing scenarios of UAVs reveals significant shortcomings. These systems require pre-installed fixed tracks up to 100 meters long and a large amount of supporting energy and buffer equipment, resulting in enormous overall weight and space occupation. This makes effective vehicle-mounted transportation and rapid deployment impossible, and fails to meet the high mobility requirements of take-off and landing systems in field or emergency conditions, thus limiting the expansion of the application scope of fixed-wing UAVs. Summary of the Invention

[0005] To improve the take-off and landing flexibility and deployment efficiency of fixed-wing UAVs, this application provides an integrated launch and recovery electromagnetic short take-off and landing system suitable for fixed-wing UAVs.

[0006] This application provides a launch-and-recovery integrated electromagnetic short takeoff and landing system suitable for fixed-wing unmanned aerial vehicles, which adopts the following technical solution: An integrated launch and recovery electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) includes: a vehicle system; a mechanical transmission system, partly mounted on the vehicle system and partly pre-positioned on the ground; and a power system, mounted on the vehicle system and connected to the mechanical transmission system, configured to provide bidirectional force output; wherein, by controlling the output direction of the power system, the mechanical transmission system selectively applies a traction force in the same direction of motion as the fixed-wing UAV to achieve catapult takeoff, or applies a braking force in the opposite direction of motion to achieve arresting recovery.

[0007] Optionally, the mechanical transmission system includes a drum, a steel cable, a hydraulic buffer device, and a pulley block; the drum and the hydraulic buffer device are mounted on the vehicle system, and the pulley block is pre-positioned on the ground; the steel cable is wound around the drum and passes through the pulley block to change the direction of force transmission, and its free end is used to form a detachable connection with the fixed-wing UAV; the hydraulic buffer device is located on the force transmission path of the steel cable and is used to reduce the impact tension generated when the fixed-wing UAV docks.

[0008] Optionally, it also includes a track groove pre-installed on the ground, a track disposed in the track groove, and a trolley device slidably disposed on the track; the trolley device is used to connect with the landing gear of the fixed-wing UAV during catapult takeoff and to transmit the traction force of the steel cable to the fixed-wing UAV.

[0009] Optionally, the pulley system includes a ground-mounted pre-installed pulley assembly, an underground pre-installed pulley, and an intermediate pre-installed pulley; the vehicle system, mechanical transmission system, and power system are each provided in two sets, and are respectively located on both sides of the track groove; there are two underground pre-installed pulleys, located on both sides of the track centerline; an underground connecting cable is threaded through each of the underground pre-installed pulleys, and one end of the underground connecting cable is fixedly connected to the trolley device; there are two intermediate pre-installed pulleys, located on both sides of the track centerline, used to lead the end of the corresponding underground connecting cable away from the trolley device to the ground, so that the underground connecting cable can be detachably connected to the steel cable passing through the ground-mounted pre-installed pulley assembly during catapult launch.

[0010] Optionally, the trolley device includes a front trolley section and a rear trolley section, the front trolley section being detachably connected to a fixed-wing UAV, and the rear trolley section being fixedly connected to one end of an underground connecting cable.

[0011] Optionally, it also includes an arresting cable that is in a taut state during arresting recovery, with both ends of the arresting cable being used to connect to the free ends of two steel cables to form an arresting area for attaching a fixed-wing UAV.

[0012] Optionally, the power system includes a motor, an energy storage device, and a converter; the energy storage device is used to store and supply the required electrical energy to the motor; the converter is electrically connected between the energy storage device and the motor, and is used to control the current input to the motor, so as to control the magnitude and direction of the output torque of the motor.

[0013] Optionally, the motor is an integrated motor, with its outer rotor directly forming the drum.

[0014] Optionally, the vehicle system includes a loading vehicle and a container mounted on the loading vehicle.

[0015] In summary, this application includes at least one of the following beneficial technical effects: 1. This application integrates the vehicle system, mechanical transmission system, and power system with bidirectional force output capability, enabling the sequential or alternating completion of catapult launch and arrested recovery operations for fixed-wing UAVs. Compared to the existing technology that uses separate launch and recovery devices, this significantly reduces the overall complexity and footprint of the take-off and landing system, achieving rapid mobile transport and deployment capabilities, improving deployment and withdrawal efficiency, and facilitating the flexible and rapid response of fixed-wing UAVs to take-off and landing needs in various scenarios. Furthermore, the vehicle-mounted nature of the main equipment enhances the stealth and safety of the take-off and landing system in field environments.

[0016] 2. This application enables short take-off and landing (STOVL) functionality for fixed-wing UAVs, reducing the difficulty and cost of constructing STOVL infrastructure, while also reducing the energy consumption of STOVL and increasing the frequency of STOVL take-off and landing, thereby increasing the carrying capacity and cruising range of fixed-wing UAVs.

[0017] 3. The motor of the power system in this application adopts an integrated motor design, integrating the function of the drum onto the outer rotor of the motor. This allows the motor to act as a drive source to output strong traction torque during launch, and as a generator to apply adjustable braking torque during arrest. This eliminates the need for numerous intermediate transmission components such as independent drums and couplings required in traditional takeoff and landing systems, significantly saving space and overall weight, achieving high-density integration of the equipment. Furthermore, the precise control of the motor torque through the converter allows this application to flexibly adapt to fixed-wing UAVs with different weights and takeoff speed requirements, improving the equipment's versatility and mission adaptability.

[0018] 4. Regarding the safety of catapult launch, this application employs a design where the front trolley is detachably connected to the landing gear of the fixed-wing UAV, while the rear trolley remains connected to the underground connecting cable. Combined with the pre-installed braking distance on the drum, this effectively solves the problem of residual kinetic energy dissipation due to inertia after the fixed-wing UAV detaches from the cable and drum, ensuring the stability of the launch and landing system itself. After one catapult launch, the rear trolley can be pushed back to its initial position using a traction device, allowing the cable to quickly return to a ready-to-launch state, making the preparation process simple and efficient.

[0019] 5. In this application, the vehicle system carrying the core equipment does not need to move when switching between catapult takeoff and arrested recovery operations. Operators only need to change the connection object at the free end of the steel cable to quickly switch the operating state of the takeoff and landing system. Specifically, during catapult takeoff, the steel cable is connected to an underground connecting cable and then detachably connected to the fixed-wing UAV via a pulley device; during arrested recovery, the fixed-wing UAV is arrested by connecting the arresting cable. This "vehicle stationary, cable change" design facilitates rapid switching of operating modes, helps shorten mission preparation time, and thus improves the working efficiency and rapid response capability of the takeoff and landing system. Attached Figure Description

[0020] Figure 1 This is a block diagram of a launch and recovery integrated electromagnetic short take-off and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to an embodiment of this application.

[0021] Figure 2 This is a schematic diagram illustrating the structure of the vehicle system in the embodiments of this application.

[0022] Figure 3 This is a schematic diagram illustrating the structure of the mechanical transmission system in the embodiments of this application.

[0023] Figure 4 This is a layout diagram illustrating the catapult operation in the embodiments of this application.

[0024] Figure 5 This is a schematic diagram illustrating the structure of the trolley device in the embodiments of this application.

[0025] Figure 6 This is a layout diagram illustrating the blocking operation performed according to the embodiments of this application.

[0026] Explanation of reference numerals in the attached drawings: 1. Vehicle system; 11. Loading vehicle; 12. Container; 2. Mechanical transmission system; 21. Drum; 22. Steel cable; 23. Hydraulic buffer device; 24. Pulley block; 241. Ground pre-installed pulley assembly; 242. Underground pre-installed pulley; 243. Intermediate pre-installed pulley; 3. Power system; 31. Motor; 32. Energy storage device; 33. Converter device; 4. Rail groove; 41. Baffle; 5. Pulley device; 51. Front trolley section; 511. Fastening unit; 52. Rear trolley section; 6. Underground structural groove; 61. Underground connecting cable; 7. Barrier cable. Detailed Implementation

[0027] The following combination Figures 1-6 This application will be described in further detail below.

[0028] Example: This application discloses an integrated launch and recovery electromagnetic short takeoff and landing system suitable for fixed-wing unmanned aerial vehicles (UAVs). (Refer to...) Figure 1 An integrated launch and recovery electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) includes a vehicle system 1, a mechanical transmission system 2, and a power system 3. The mechanical transmission system 2 is partially mounted on the vehicle system 1 and partially pre-positioned on the ground. The power system 3 is mounted on the vehicle system 1 and connected to the mechanical transmission system 2, and is configured to provide bidirectional force output. By controlling the output direction of the power system 3, the mechanical transmission system 2 can selectively apply a traction force in the same direction of motion as the fixed-wing UAV to achieve catapult takeoff, or apply a braking force in the opposite direction of motion to achieve arresting recovery.

[0029] Reference Figure 1 and Figure 2 The vehicle system 1 includes a loading vehicle 11 and a container 12 fixed on the loading vehicle 11. In this embodiment, the loading vehicle 11 is a multi-axle loading vehicle 11, which is the transportation tool for the entire lifting and landing system; the container 12 provides loading space for the entire lifting and landing system.

[0030] Reference Figures 1-3 The mechanical transmission system 2 includes a drum 21, a steel cable 22, a hydraulic buffer device 23, and a pulley block 24. The drum 21 and the hydraulic buffer device 23 are installed in the container 12 of the vehicle system 1. The steel cable 22 is wound on the drum 21 and serves as a power connection unit. The drum 21 can quickly reel in and unload the cable and tension the cable 22. The pulley block 24 is used to change the direction of force transmission. The hydraulic buffer device 23 is located on the force transmission path of the steel cable 22 and is used to reduce the impact tension generated during docking of the fixed-wing UAV.

[0031] Reference Figure 4 and Figure 5The short takeoff and landing (STOVL) system also includes a pre-installed track trough 4 on the ground, a track within the track trough 4, and a slidable trolley device 5 mounted on the track. The trolley device 5 is detachably connected to the landing gear of the fixed-wing UAV during catapult launch and transmits the traction force of the steel cable 22 to the fixed-wing UAV. In this way, the track ensures that the fixed-wing UAV moves in a straight line along a pre-set path during the catapult launch phase, effectively preventing the risk of yaw or roll. The trolley device 5, acting as a force transmission intermediary, smoothly transmits the traction force of the steel cable 22 to the landing gear of the fixed-wing UAV, ensuring the reliability and consistency of force transmission, thereby guaranteeing the successful implementation of short takeoff and launch.

[0032] Reference Figure 1 , Figure 4 and Figure 5 The pulley system 24 includes a ground-mounted pre-installed pulley assembly 241, an underground pre-installed pulley 242, and an intermediate pre-installed pulley 243. The ground-mounted pre-installed pulley assembly 241 includes at least two ground-mounted pulley bodies, with an installation height higher than the ground. Two sets are provided for the vehicle system 1, mechanical transmission system 2, and power system 3, respectively located on both sides of the track groove 4. One end of the track groove 4 is vertically connected to the underground structural groove 6, and the track groove 4 and the underground structural groove 6 together form a T-shaped groove. In this embodiment, the track groove 4 is approximately 100 meters long, and the underground structural groove 6 is approximately 20 meters long. Two underground pre-installed pulleys 242 are provided and rotatably installed in the underground structural groove 6, with an installation height lower than the ground, and are located on both sides of the track centerline. Underground connecting cables 61 are respectively threaded through the underground pre-installed pulleys 242. One end of the underground connecting cable 61 is fixedly connected to the trolley device 5. Two intermediate pre-installed pulleys 243 are set on both sides of the track center line. They are used to lead the end of the corresponding underground connecting cable 61 away from the trolley device 5 to the ground so that the end of the underground connecting cable 61 away from the trolley device 5 can be detachably connected to the steel cable 22 that passes through the ground pre-installed pulley assembly 241 when the catapult takes off.

[0033] Reference Figures 3-5The trolley device 5 includes a front trolley section 51 and a rear trolley section 52 fixedly connected. The front trolley section 51 is equipped with a movable fastening unit 511 for detachable connection with the landing gear of the fixed-wing UAV. A baffle 41 is pre-installed in the track groove 4 to provide precise mechanical stopping for the trolley device 5. At the end of the catapult launch operation, the front trolley section 51, which is detachably connected to the fixed-wing UAV, impacts the baffle 41. At the same time, the fastening unit 511 is released, and the fixed-wing UAV is disengaged from the front trolley section 51, ensuring that the fixed-wing UAV can take off smoothly. The rear trolley section 52 is fixedly connected to one end of the underground connecting cable 61. Specifically, during catapult launch, the drum 21 rotates, pulling the fixed-wing UAV to move linearly along the track via the steel cable 22. When the fixed-wing UAV reaches a certain speed, the front trolley section 51 of the trolley device 5 impacts the pre-installed baffle 41 in the track groove 4, and the front trolley section 51 is disengaged from the UAV. The baffle 41 is made of energy-absorbing material or the impact surface of the baffle 41 is integrated with energy-absorbing material. It can quickly absorb and dissipate the remaining kinetic energy of the front trolley 51 during the impact, so that it can stop smoothly within a very short distance, effectively preventing the trolley device 5 from causing impact damage to the end of the track.

[0034] Reference Figure 6 The short takeoff and landing system also includes an arresting cable 7 that is tensioned during arresting and recovery. Both ends of the arresting cable 7 are connected to the free ends of two steel cables 22 to form an arresting area for attaching the fixed-wing UAV. In this embodiment, the length of the arresting cable 7 is 20m to 25m. When the fixed-wing UAV is arresting, after landing and attaching to the cable, the UAV pulls the arresting cable 7 forward. This, in turn, causes the drum 21 on the loading vehicle 11 to rotate and release the cable, converting the linear motion of the fixed-wing UAV into the rotational motion of the drum 21. During this process, a reverse drag torque is applied by the power system 3 to absorb the kinetic energy of the fixed-wing UAV, enabling it to brake within a given distance.

[0035] Reference Figure 1 and Figure 2The power system 3 includes a motor 31, an energy storage device 32, and a converter 33. The energy storage device 32 stores and supplies the required electrical energy to the motor 31. The converter 33 is electrically connected between the energy storage device 32 and the motor 31, and is used to control the current input to the motor 31 to control the magnitude and direction of the output torque of the motor 31. The motor 31 is an integrated motor, with its outer rotor directly forming the drum 21 in the mechanical transmission system 2. This integrates the driving component of the motor 31 with the execution component of the mechanical transmission system 2, eliminating the complex transmission mechanisms such as couplings and reducers required between the motor 31 and the drum 21 in traditional solutions. This greatly simplifies the structure, reduces energy loss and potential failure points caused by mechanical connection points, improves transmission efficiency and system reliability, and significantly reduces the size and weight of the equipment, making it easier to meet the requirements of compactness, lightweighting, and high efficiency in short-distance take-off and landing systems.

[0036] The implementation principle of an integrated electromagnetic short take-off and landing system for fixed-wing UAVs according to an embodiment of this application is as follows: During the catapult operation, the drum 21 is pre-released and connected to the underground connecting cable 61 led from underground to the surface using a connector. During catapult launch, the control system sends a start signal, and the integrated motors 31 on both vehicle systems 1 start simultaneously. The outer rotor of the motor 31 (which is also the drum 21) rotates, pulling the fixed-wing UAV along the track in a straight line via the steel cable 22. After the fixed-wing UAV reaches a certain speed, the front trolley 51 strikes the baffle 41 in the track groove 4, and the front trolley 51 is unlocked from the fixed-wing UAV; the rear trolley 52 remains connected to the underground connecting cable 61 to keep the steel cable 22 taut, preventing the steel cable 22 from falling off the pulley block 24 and facilitating the reset of the steel cable 22 during the second catapult launch. The launch distance is approximately 100m. After the fixed-wing UAV separates from the front trolley section 51, the motor 31 switches to energy-consuming braking mode to decelerate and brake the drum 21. The horizontal distance required for the drum 21 to brake is approximately 50m. The connector at the point where the steel cable 22 connects to the underground connecting cable 61 does not pass through any pulleys during the entire movement. For subsequent launches, an external traction device (such as a tractor) is used to push the rear trolley section 52 back to the launch starting position to reset the steel cable 22.

[0037] During the arresting operation, the parking positions of the two loading vehicles 11 remain unchanged. The connection between the steel cable 22 and the underground connecting cable 61 is disconnected, and the underground connecting cable 61 and the aforementioned connection can be fixed to the ground nearby. The underground connecting cable 61 is kept taut and threaded onto the corresponding pulley, facilitating the transition to catapult operations. The steel cable 22 on the drum 21 is wound up to the pre-placed pulley assembly 241 on the ground. A steel plate is laid on the rail groove 4, flush with the ground, to prevent the landing gear tires of the fixed-wing UAV from getting stuck in it during the arresting operation. The arresting cable 7 is connected to the free ends of the steel cables 22 on both sides of the rail groove 4, and the arresting cable 7 is kept in a horizontally taut state, thus completing the arresting preparation work. During the arresting operation, after the fixed-wing UAV lands and attaches to the cable, it pulls the arresting cable 7 forward, which in turn drives the drum 21 on the loading vehicle 11 to rotate and release the cable through the arresting cable 7 and the steel cable 22, converting the linear motion of the fixed-wing UAV into the rotational motion of the integrated motor 31. During this process, the fixed-wing UAV is braked within a given distance by applying a reverse drag torque to the integrated motor 31 to absorb the kinetic energy of the UAV.

[0038] This application integrates the vehicle system 1, the mechanical transmission system 2, and the power system 3 with bidirectional force output capability, enabling the sequential or alternating completion of catapult launch and arrested recovery operations for fixed-wing UAVs. Compared to the existing technology that uses separate launch and recovery devices, this significantly reduces the overall complexity and footprint of the take-off and landing system, enabling rapid mobile transport and deployment, improving deployment and withdrawal efficiency, and facilitating the flexible and rapid response of fixed-wing UAVs to take-off and landing needs in various scenarios. Furthermore, the vehicle-mounted nature of the main equipment enhances the stealth and safety of the take-off and landing system in field environments.

[0039] This application enables short take-off and landing (STOVL) functionality for fixed-wing UAVs, reducing the difficulty and cost of constructing STOVL infrastructure, while also reducing energy consumption and increasing the frequency of STOVL take-off and landing, thereby enhancing the carrying capacity and cruising range of fixed-wing UAVs.

[0040] Furthermore, during the switching between catapult launch and arrested recovery operations, the vehicle system 1 carrying the core equipment does not need to move. Operators only need to change the connection object at the free end of the steel cable 22 to quickly switch the operating state of the takeoff and landing system. This "vehicle stationary, cable change" design facilitates rapid switching of operating modes, shortens mission preparation time, and thus improves the efficiency and rapid response capability of the takeoff and landing system.

[0041] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A launch-and-recovery integrated electromagnetic short takeoff and landing system suitable for fixed-wing unmanned aerial vehicles, characterized in that, include: Vehicle system (1); Mechanical transmission system (2), part of which is mounted on the vehicle system (1) and part of which is pre-positioned on the ground; as well as A power system (3) is mounted on the vehicle system (1) and connected to the mechanical transmission system (2), and is configured to provide bidirectional force output; In this process, by controlling the output direction of the power system (3), the mechanical transmission system (2) can selectively apply a traction force in the same direction of motion to the fixed-wing UAV to achieve catapult takeoff, or apply a braking force in the opposite direction of motion to achieve arresting recovery.

2. The electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to claim 1, characterized in that: The mechanical transmission system (2) includes a drum (21), a steel cable (22), a hydraulic buffer device (23), and a pulley block (24); the drum (21) and the hydraulic buffer device (23) are mounted on the vehicle system (1), and the pulley block (24) is pre-positioned on the ground; the steel cable (22) is wound around the drum (21) and passes through the pulley block (24) to change the direction of force transmission, and its free end is used to form a detachable connection with the fixed-wing UAV; the hydraulic buffer device (23) is located on the force transmission path of the steel cable (22) and is used to reduce the impact tension generated when the fixed-wing UAV docks.

3. The electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to claim 2, characterized in that: It also includes a track groove (4) pre-set on the ground, a track set in the track groove (4), and a trolley device (5) slidably set on the track; the trolley device (5) is used to connect with the landing gear of the fixed-wing UAV during catapult takeoff and to transmit the traction force of the steel cable (22) to the fixed-wing UAV.

4. The electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to claim 3, characterized in that: The pulley system (24) includes a ground-mounted pre-installed pulley assembly (241), an underground pre-installed pulley (242), and an intermediate pre-installed pulley (243); the vehicle system (1), the mechanical transmission system (2), and the power system (3) are each provided in two sets, and are respectively located on both sides of the track groove (4); there are two underground pre-installed pulleys (242), which are located on both sides of the track centerline; Each of the underground pre-installed pulleys (242) is provided with an underground connecting cable (61), one end of which is fixedly connected to the trolley device (5); there are two intermediate pre-installed pulleys (243), which are located on both sides of the center line of the track, and are used to lead the end of the corresponding underground connecting cable (61) away from the trolley device (5) to the ground so that the underground connecting cable (61) can be detachably connected to the steel cable (22) that passes through the ground pre-installed pulley assembly (241) when the catapult takes off.

5. The integrated launch and recovery electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles according to claim 4, characterized in that: The trolley device (5) includes a front trolley section (51) and a rear trolley section (52). The front trolley section (51) is used for detachable connection with a fixed-wing UAV, and the rear trolley section (52) is fixedly connected to one end of an underground connecting cable (61).

6. The electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to claim 4, characterized in that: It also includes an arresting cable (7) that is in a tensioned state during arresting and recovery, the two ends of which are respectively used to connect to the free ends of two steel cables (22) to form an arresting area for attaching a fixed-wing UAV.

7. The electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to claim 2, characterized in that: The power system (3) includes a motor (31), an energy storage device (32), and a converter (33); the energy storage device (32) is used to store and supply the required electrical energy to the motor (31); the converter (33) is electrically connected between the energy storage device (32) and the motor (31) and is used to control the current input to the motor (31) so as to control the magnitude and direction of the output torque of the motor (31).

8. The electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to claim 7, characterized in that: The motor (31) is an integrated motor (31), and its outer rotor directly forms the drum (21).

9. The electromagnetic short takeoff and landing system for fixed-wing unmanned aerial vehicles (UAVs) according to claim 1, characterized in that: The vehicle system (1) includes a loading vehicle (11) and a container (12) mounted on the loading vehicle (11).

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