Aircraft rotary launch device and system

Abstract

The present application belongs to the field of aircraft launching technology, and particularly relates to a rotating launching device and system for aircraft, which comprises a support body, at least one rotating body rotating around the axis of the support body, and a driving device for providing power for the rotation of the rotating body; the rotating body is provided with at least one attitude adjusting device for adjusting the attitude of the aircraft in real time during the rotation acceleration and launching; the attitude adjusting device is provided with a launching frame for holding and releasing the aircraft; the bottom of the support body is provided with a base for providing stable support for the whole launching device. The present application can control and adjust the attitude of the aircraft through the attitude adjusting device, so that the relative air line speed of the left and right wings of the aircraft, especially the fixed-wing aircraft, is the same at the launching moment, thereby avoiding the potential take-off safety caused by the lift difference of the left and right wings.

Description

Technical Field

[0001] This invention belongs to the field of aircraft launch technology, specifically relating to an aircraft rotary launch device and system. Background Technology

[0002] Fixed-wing aircraft and rotorcraft are designed to meet specific mission objectives, offering advantages such as high speed, long endurance, and large payload. However, these aircraft require reaching and maintaining a certain speed for takeoff and landing, typically necessitating specially constructed runways for acceleration to takeoff speed and deceleration from landing speed to a stop. Fixed-wing aircraft struggle to take off and land in uneven terrain, such as in the wild, forests, and urban areas, severely limiting their operational flexibility. To enable fixed-wing aircraft to take off smoothly in environments without runways, auxiliary equipment is usually required to provide initial velocity, thus enabling takeoff without a runway.

[0003] Existing assisted takeoff and landing (ALT) systems mostly employ linear guidance-assisted takeoff, utilizing energy storage devices or actuators to generate thrust / pull forces to provide the initial velocity required for takeoff for fixed-wing aircraft within the size range of the linear guidance device. However, there are constraints between the structural dimensions of such ALT systems, the maximum output force of the actuators, and the overload capacity of the fixed aircraft, resulting in these systems often being bulky and providing very limited initial velocity. Furthermore, these devices are often large, making deployment and retraction cumbersome and time-consuming, and inconvenient to install on a vehicle for catapult launch during motion.

[0004] Chinese patent CN101327846A discloses a small UAV rotating catapult, which includes a launcher base, a rotating rocker arm, and a torsion spring. The launcher base consists of a tripod, a support rod, a fixed disc, and a limiting block. The upper end of the torsion spring is fixedly connected to the rotating rocker arm, and the lower end of the torsion spring is fixedly connected to the fixed disc on the base. This solution can provide a large initial velocity for the aircraft with a relatively small size. However, this solution uses a torsion spring as an energy storage element, which limits the range of initial velocities it can provide to the aircraft. Furthermore, because this solution uses a fixed-direction clamping frame, a fixed-length arm, and an uncontrolled torque drive, it cannot effectively control the aircraft's linear velocity and attitude based on the current angular velocity during the main shaft rotation to reduce the load on the arm. Most importantly, when releasing aircraft such as fixed-wing aircraft, the different distances of the left and right wings relative to the rotation center will generate a large lift difference, thus threatening the aircraft's safety.

[0005] Chinese patent CN101294782A discloses a launching device, including: a power system, a transmission system, a rotator, and a launched object; the power system is connected to the rotator through the transmission system, enabling the rotator to rotate, and the launched object is placed on the rotator. While this patent solves the power problem, it cannot effectively control the aircraft's linear velocity and attitude based on the current angular velocity during the rotator's rotation, thus failing to reduce the load on the rotator from the aircraft. This solution also fails to address the problem of a large lift difference caused by the different distances of the left and right wings relative to the rotation center, which threatens the aircraft's takeoff safety during release. Furthermore, the proposed solution cannot provide the aircraft with a complex and flexible initial launch state based on current advanced aircraft trajectory planning and control methods. Summary of the Invention

[0006] One aspect of this disclosure provides a rotating launch device and system for an aircraft. This launch device adjusts the attitude of the aircraft in real time during rotational acceleration and launch through an attitude adjustment device, so that the aircraft is in a safer or more advantageous initial state at launch. During the rotational acceleration process, it reduces or counteracts the centrifugal force generated by rotation. It can also launch in a more flexible launch state obtained by a planning control method.

[0007] Another aspect of this disclosure is that, through the structured design of this device, it is made more portable and easier to store, and it is also easier to integrate with its carrier for design and use.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] A rotating launch device for an aircraft includes a support body, at least one rotating body that rotates about the axis of the support body, and a drive device that provides power for the rotation of the rotating body; the rotating body is provided with at least one attitude adjustment device, which is used to adjust the attitude of the aircraft in real time during rotation acceleration and during launch; the attitude adjustment device is provided with a launch rack for holding and releasing the aircraft; the bottom of the support body is provided with a base for providing stable support for the entire launch device.

[0010] The attitude adjustment device includes a robotic arm consisting of at least two rotating joints. Each rotating joint is driven by a servo or energy storage device or a combination of servo and energy storage device. The attitude of the aircraft is adjusted by adjusting the angles of multiple axes on the robotic arm.

[0011] Furthermore, the attitude adjustment device includes at least one or more rotating joints for adjusting the heading angle of the aircraft.

[0012] Furthermore, the attitude adjustment device includes at least one or more rotating joints for adjusting the pitch angle of the aircraft.

[0013] Furthermore, the attitude adjustment device includes at least one or more rotating joints for adjusting the roll angle of the aircraft.

[0014] Specifically, the attitude adjustment device comprises three links connected in sequence by rotating joints. The first link is connected to the rotating body through a first rotating joint, the axis of which is radially radiating from the center of the rotating body. The first link is connected to the second link through a second rotating joint, the axis of which is perpendicular to the axis of the first rotating joint. The second link is connected to the third link through a third rotating joint, the axis of which is perpendicular to the axis of the second rotating joint. The launcher is mounted on the third link. The first, second, and third rotating joints are all driven by servo drives, energy storage devices, or a combination of servo and energy storage devices.

[0015] Furthermore, in one embodiment, the attitude adjustment device includes three links connected in sequence. The first link is connected to the rotating body via a first revolute joint, the axis of which is perpendicular to both the axis of the rotating body and the radial direction of the center of the rotating body. The first link is connected to the second link via a second revolute joint, the axis of which is perpendicular to the axis of the first revolute joint. The second link is connected to the third link via a third revolute joint, the axis of which is perpendicular to both the axes of the first and second revolute joints. The launcher is mounted on the third link. The first, second, and third revolute joints are all driven by servo drives, energy storage devices, or a combination of servo and energy storage devices.

[0016] Furthermore, the attitude adjustment device can reciprocate radially along the rotation center of the rotating body.

[0017] Preferably, the rotating body is a rotating structure with at least one rotating arm, and the attitude adjustment device is disposed on the rotating arm.

[0018] Furthermore, the rotating arm is a single-stage or multi-stage telescopic mechanism, or a mechanical arm composed of two or more rotating joints, all of which are servo driven.

[0019] Furthermore, the rotating arm is provided with a connecting block, and the rotating arm is connected to the support body through the connecting block. The rotating arm and the connecting block are rotatably connected, and a rotation locking mechanism is provided at the connection point.

[0020] Preferably, in one embodiment, the rotating body is a rotary table, and the attitude adjustment device is disposed on the rotary table.

[0021] Furthermore, a linear guide rail is provided radially along the upper edge of the rotary table, and the attitude adjustment device is installed on the moving part of the linear guide rail.

[0022] The aforementioned driving device is the launched aircraft itself; or

[0023] The drive unit is an aerodynamic actuator mounted on a rotating body; or

[0024] The driving device is a driver located at the coupling point between the support and the rotating body. The driver is fixedly mounted on the support, and its power output end is connected to the rotating body; or

[0025] The driving device is a driver, which is mounted on the base. The support body and the rotating body are fixedly connected, and the support body and the base are rotatably connected. The power output end of the driver is connected to the support body and drives the support body to rotate, thereby driving the rotating body to rotate.

[0026] Furthermore, the rotating body can reciprocate along the length of the support.

[0027] Furthermore, an angle adjustment structure is provided between the support body and the base, and the angle adjustment structure is used to adjust the angle between the support body and the base.

[0028] Furthermore, the tilt adjustment structure comprises a rotating joint between the support body and the base, wherein the horizontal angle between the support body and the base is adjusted via the rotating joint, which is driven by a servo module support body tilt drive device; or

[0029] A servo-driven worm gear is used, with the worm gear output shaft connected to the rotating shaft between the support body and the base for driving; or

[0030] The base is equipped with a linear guide rail, and a connecting rod is provided between the moving part of the linear guide rail and the support body. The tilt angle between the support body and the base can be adjusted by adjusting the position of the moving part of the linear guide rail.

[0031] In addition, the rotating body is also provided with a balancing arm to reduce the torque on the base in the roll and pitch directions when the rotating body is stationary and during rotation. The balancing arm is provided with a counterweight block for counterweighting. The counterweight block can reciprocate radially along the rotation center of the balancing arm. Its distance from the rotation axis of the rotating body is adjustable in real time, and it can be quickly disengaged from the balancing arm.

[0032] A launch system for an aircraft includes the aforementioned rotating launch device and controller. The controller is a general-purpose computer or an embedded controller. It selects a corresponding program to control the operating state of the launch device based on the performance of the aircraft, so that the aircraft can be launched in a relatively good attitude.

[0033] Furthermore, the launch system is equipped with environmental sensing devices, which include at least one of an anemometer, an air volume meter, a lidar, and a visual sensor, and the environmental sensing devices are signal-connected to the controller.

[0034] Compared with the prior art, the present invention has the following advantages:

[0035] (1) By using an attitude adjustment device to specifically control and adjust the attitude of the aircraft, the relative linear velocity of the left and right wings of the aircraft, especially fixed-wing aircraft, can be the same at the time of launch, thereby avoiding the potential takeoff safety issues caused by the difference in lift between the left and right wings.

[0036] (2) Combining aircraft control technology, more flexible launch methods can be adopted. For example, when the aircraft takes off (catapult), the attitude of the aircraft can be adjusted by the attitude adjustment device and the tilt angle control of the support body, so that the aircraft attitude angle is larger or the initial velocity direction has a larger angle with the horizontal plane, or both.

[0037] (3) Introduce robot and aircraft control technology, and adjust the aircraft's attitude in real time during acceleration and launch through an attitude adjustment device. By controlling the aircraft's angle of attack and its attitude relative to the launcher, the load on the launcher is reduced by utilizing the aircraft's lift.

[0038] (4) This device is equipped with multiple kinematic pairs and widely adopts servo control. It has a high degree of automation, is easy to carry and deploy, and can be installed on a vehicle, making it easy to achieve the integration of aircraft and vehicle.

[0039] (5) Use environmental sensing equipment to realize the perception of the surrounding spatial environment and wind speed and direction, and provide data support for aircraft flight planning and take-off and landing planning. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the overall structure of one embodiment according to one aspect of this disclosure;

[0041] Figure 2 This is a schematic diagram of a structure of one embodiment of a support rod according to one aspect of this disclosure;

[0042] Figure 3 This is a schematic diagram of another embodiment of the support rod according to one aspect of this disclosure;

[0043] Figure 4 This is a schematic diagram of the structure of an embodiment of an attitude adjustment device according to one aspect of the present disclosure;

[0044] Figure 5 This is a schematic diagram of another embodiment of the attitude adjustment device according to one aspect of the present disclosure;

[0045] Figure 6 This is a structural schematic diagram of a support rod angle adjustment structure according to one aspect of this disclosure;

[0046] Figure 7 This is a schematic diagram of a rotating body with a connecting block according to one aspect of the present disclosure;

[0047] Figure 8 This is a schematic diagram of an overall structure with a counterweight arm according to one aspect of this disclosure;

[0048] Figure 9 This is a schematic diagram of the structure of an embodiment of a balance arm according to one aspect of this disclosure;

[0049] Figure 10 This is a schematic diagram of an overall structure having a rotary table according to one aspect of this disclosure;

[0050] Figure 11 This is a schematic diagram of the structure of a launch system according to one aspect of this disclosure;

[0051] In the diagram: 1-Support body, 101-Slider, 2-Rotating body, 201-Rotating arm, 202-Rotating table, 203-Connecting block, 204-Balancing arm, 205-Counterweight block, 3-Base, 301-Rotating pair, 4-Drive device, 5-Attitude adjustment device, 501, 504-First connecting rod, 502, 505-Second connecting rod, 503, 506-Third connecting rod, 6-Launcher, 7-Controller, 8-Environmental sensing device. Detailed Implementation

[0052] The present invention will be further explained below with reference to specific implementation schemes, but this explanation does not limit the invention. The structures, proportions, sizes, etc., shown in the accompanying drawings are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed in the specification, and are not intended to limit the conditions under which the present invention can be implemented. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportional relationships, or adjustments to the size, without affecting the effects and objectives that the present invention can produce, should still fall within the scope of the technical content disclosed in the present invention. At the same time, terms such as "upper," "lower," "front," "rear," and "middle" used in this specification are only for clarity of description and are not intended to limit the scope of the present invention. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of the present invention.

[0053] Please see Figure 1The rotating launch device of the present invention includes a cylindrical support body 1 and a rotating body 2 that rotates around the axis of the support body. In this embodiment, the rotating body is provided with two rotating arms 201 and a drive device 4 that provides power for the rotation of the rotating body 2. The rotating arms 201 are provided with an attitude adjustment device 5, which is used to adjust the attitude of the aircraft in real time during rotation acceleration and launch. The attitude adjustment device 5 is provided with a launch rack 6 that docks with the aircraft. The launch rack 6 and the attitude adjustment device 5 can be integrated or separate designs. The launch rack 6 uses mechanical or electromagnetic means to achieve the connection and disconnection between the aircraft and the attitude adjustment device 5. For example, a U-shaped manipulator gripping method is used to clamp the mating parts on the aircraft to achieve the docking of the launch rack 6 with the aircraft. The connection and disconnection of the aircraft are achieved through the cooperation between the launch rack 6 and the aircraft. The bottom of the support body 1 is provided with a base 3 to provide stable support for the entire launch device.

[0054] The present invention provides four embodiments of the driving device 4. The four embodiments are mainly used to illustrate the position of the driving device 4. In practical applications, different implementation methods can be selected according to different needs and existing technologies.

[0055] In the first embodiment of the drive device 4, the support body 1 is rotatably connected to the rotating body 2, and the drive device 4 that provides rotational driving force for the rotating body 2 is the launched aircraft itself, that is, the flight power of the aircraft itself provides power for the rotation of the rotating body 2.

[0056] In a second embodiment of the drive device 4, the drive device 4 is mounted on the rotating body 2, the support body 1 is rotatably connected to the rotating body 2, and the rotating body 2 is provided with a drive that relies on aerodynamics. The common drive is a motor-driven propeller drive, which provides power for the rotation of the rotating body 2.

[0057] In a third embodiment of the drive device 4, the drive device 4 is located at the coupling point between the support body 1 and the rotating body 2. For example, a motor is fixedly installed on the support body 1, and the power output end of the motor is connected to the rotating body 2. The motor can also be replaced with other suitable drivers.

[0058] In a fourth embodiment of the drive device 4, the drive device 4 is mounted on the base 3, the support body 1 is fixedly connected to the rotating body 2, the support body 1 is rotatably connected to the base 3, a motor is mounted on the base 3, the power output end of the motor is connected to the support body 1 and drives the support body 1 to rotate, thereby driving the rotating body 2 to rotate. The motor can also be a steam turbine or a fuel engine.

[0059] In one embodiment, the rotating body 2 is fixedly connected to the support body 1 along the length of the support body 1, that is, the rotating body 2 is relatively stationary along the length of the support body 1.

[0060] More preferably, in another embodiment, the rotating body 2 can reciprocate along the length of the support body 1, as in embodiment one, such as... Figure 2 As shown, the support body 1 is equipped with a guide rail, and a slider 101 is mounted on the guide rail. The rotating body 2 is placed on the slider 101, and the reciprocating motion of the rotating body 2 is achieved by the sliding of the slider 101; Implementation scheme two, as shown... Figure 3 As shown, the support body 1 is a single-stage or multi-stage telescopic mechanism, and the rotating body 2 is set on the top of the support body 1. The reciprocating motion of the rotating body 2 is realized by the extension and retraction of the telescopic mechanism. In the third embodiment, the support body 1 is a double-legged or multi-legged or main-legged and auxiliary support structure. The height and angle of the rotating body 2 are changed by changing the length or position of each leg or auxiliary support, thereby realizing the reciprocating motion of the rotating body 2. This embodiment can also better control the attitude of the aircraft.

[0061] In this invention, the attitude adjustment device 5 is used to adjust the attitude of the aircraft during its circular motion and when it detaches from the launch pad 6 for launch, making the aerodynamic forces acting on the aircraft more reasonable during these processes. Adjusting the aircraft's attitude helps to: firstly, reduce the aircraft's disturbance to the center of rotation during acceleration before takeoff; and secondly, ensure safer takeoff by providing a flexible initial flight state, allowing the aircraft to better adapt to the planned flight trajectory. The attitude adjustment device 5 is constructed using a multi-axis arbitrary combination method according to the type of aircraft to adjust the required pitch, roll, and yaw angles, controlling the aircraft to be in the optimal attitude. In particular, by combining environmental perception and planning control methods, the launch state can be planned very flexibly, adapting to very complex motion planning, thereby achieving launch capabilities that are impossible with existing technologies. The attitude adjustment device 5 is essentially a robotic arm composed of two or more revolute joints. By adjusting the angles of each axis on the robotic arm, the aircraft obtains the desired attitude. Two typical configurations are selected here for further explanation.

[0062] For a first embodiment of the attitude adjustment device 5 of the present invention, please refer to [link / reference]. Figure 4 It consists of three links connected in sequence by a rotating joint. The first link 501 is connected to the rotating body 2 through the first rotating joint. The axis of the first rotating joint is radially radiating from the center of the rotating body 2. The first link 501 is connected to the second link 502 through the second rotating joint. The axis of the second rotating joint is perpendicular to the axis of the first rotating joint. The second link 502 is connected to the third link 503 through the third rotating joint. The axis of the third rotating joint is perpendicular to the axis of the second rotating joint. The launcher 6 is mounted on the third link 503. The first, second, and third rotating joints are all driven by servo motors.

[0063] To optimize drive configuration, some key rotating joints can be driven by energy storage devices or a combination of servo drives and energy storage devices. For example, when the aircraft adopts a horizontal launch mode, the third rotating joint of the attitude adjuster can be driven by hydraulic, pneumatic, or spring energy storage devices to pre-store energy or temporarily store energy for the energy storage device during the acceleration of the rotating body 2 via servo drive. As the aircraft approaches launch, the energy stored in the energy storage device is released accordingly via the drive components based on the energy required to correct the aircraft's heading, ensuring that the aircraft's heading is at the expected value at launch.

[0064] When adjusting the aircraft's attitude, the first link 501 adjusts the pitch angle, the second link 502 adjusts the roll angle, and the third link 503 adjusts the yaw angle. Here, we will illustrate the application of this embodiment. For example, the plane of rotation of the rotating body 2 is parallel to the ground, and the angles of the first link 501 and the second link 502 of the attitude adjustment device 5 are initial angles, keeping the aircraft in a horizontal position. Here, the aircraft is an unmanned aerial vehicle (UAV). Before launch, the yaw angle is adjusted by rapidly adjusting the angle of the third link 503. The aircraft is launched simultaneously with the adjustment, ensuring that the left and right wings have the same ground velocity at the moment of ejection, thus avoiding flight safety issues caused by unbalanced lift between the left and right wings due to rotational motion. Furthermore, by adjusting the angle of the first link 501, the pitch angle can be adjusted, thereby adjusting the angle of attack, allowing the aircraft to obtain optimal lift that matches its linear velocity upon ejection.

[0065] For a second embodiment of the attitude adjustment device of the present invention, please refer to [link / reference]. Figure 5 It includes three links connected in sequence. The first link 504 is connected to the rotating body 2 through a first revolute joint. The axis of the first revolute joint is perpendicular to both the axis of the rotating body 2 and the radial direction of the center of the rotating body 2. The first link 504 is connected to the second link 505 through a second revolute joint. The axis of the second revolute joint is perpendicular to the axis of the first revolute joint. The second link 505 is connected to the third link 506 through a third revolute joint. The axis of the third revolute joint is perpendicular to both the axes of the first and second revolute joints. The launcher is mounted on the third link 506. The first, second, and third revolute joints are all driven by servo drives, energy storage devices, or a combination of servo drives and energy storage devices.

[0066] The attitude adjustment device 5 can reciprocate radially along the rotation center of the rotating body 2. In one embodiment, the rotating arm 201 uses a single-stage or multi-stage telescopic mechanism to control the distance between the attitude adjustment device 5 and its rotation center, the purpose of which is to fully utilize the capability of the drive device 4. For example, during the initial acceleration rotation phase of the rotating body 2, the length of the telescopic mechanism is adjusted in real time according to the drive constraints of the drive device 4 and the mission's requirements for the angular velocity of the rotating body, thereby fully utilizing the drive capability of the drive device 4. More specifically, since the distance between the aircraft and the rotation center is proportional to the torque of the drive device 4, the distance between the attitude adjustment device 5 and the rotation center is set to the shortest during the initial startup of the rotating launch device. During the acceleration rotation process, the attitude adjustment device 5 gradually adjusts the length of the rotating body according to the type of aircraft to meet the takeoff requirements of the aircraft, while reducing the performance requirements of the drive device 4. For another example, when the driving force of the third link 503, 506 of the attitude adjustment device 5 cannot meet the requirements of a small-radius, high-speed launch mode, a long-link, low-speed launch mode can be used.

[0067] In one embodiment, please refer to Figure 6 A rotating joint 301 is provided between the support body 1 and the base 3. Its function is to adjust the normal direction of the rotation plane of the rotating body 2, thereby adjusting the velocity direction when the aircraft is launched. This rotating joint 301 is driven by a servo module support body 1 tilt drive device; alternatively, a servo-driven worm gear can be used, with the worm gear output shaft connected to the rotating shaft between the support body 1 and the base 3; or a linear guide rail can be provided on the base 3, with a connecting rod between the moving part of the linear guide rail and the support body 1. The tilt angle of the support body 1 can be adjusted by adjusting the position of the moving part of the linear guide rail. Specifically, the angle between the support body 1 and the ground can be set to α. When the angle between the aircraft's rotational velocity vector and the ground is α, the aircraft disengages from the launch arm, thus obtaining an initial velocity direction obliquely upwards at an angle α with the ground. The aircraft launched obliquely upwards has more adjustment time to enter normal flight mode, making takeoff more flexible and safer. Furthermore, this embodiment facilitates the folding and storage of the device.

[0068] Please see Figure 7To further facilitate the storage of the launching device, the rotating body 2 also includes a connecting block 204. The rotating arm 201 is connected to the support body 1 via the connecting block 203. The rotating arm 201 and the connecting block 203 are rotatably connected, and a rotation locking mechanism is provided at the connection point. In one embodiment, the rotation locking mechanism can be a worm gear, with the worm gear output shaft connected to the rotating shaft between the rotating arm 201 and the connecting block 203. The locking purpose is achieved through the self-locking property of the worm gear. The worm can be driven by a handwheel or a servo drive. In another embodiment, the rotating joint here can be driven by a linkage slider mechanism. The linkage is connected to one of the rotating arms or the support body 1 via a rotating joint, and the slider is connected to the other via a sliding joint. In another real-time solution, a positioning pin or method such as applying pressure to increase static friction is used to lock the device at a preset or desired position.

[0069] In one embodiment, please refer to Figure 8 and Figure 9 The rotating body 2 is also equipped with a balancing arm 204 to reduce the roll and pitch torque on the base 3 when the rotating body is stationary and during rotation. The balancing arm 204 has a counterweight block 205 for counterweighting, the distance between which is adjusted in real time by a servo motor to meet real-time balance requirements. When necessary, the counterweight block 205 can be quickly disengaged from the balancing arm 204 to prevent sudden changes in the system's force balance when the aircraft is ejected. For example, the balancing arm 204 can employ a single-stage or multi-stage telescopic mechanism or a guide rail slider mechanism; here, a telescopic mechanism is used for explanation. The counterweight block 205 is located at the end of the telescopic mechanism, and its position is controlled by the telescopic mechanism. The telescopic mechanism and the counterweight block 205 are electromagnetically fastened together. When the aircraft is ejected, the counterweight block 205 quickly retracts to near the center point. When necessary, the electromagnetic connection between the telescopic mechanism and the counterweight block 205 can be released, allowing the counterweight block 205 to quickly disengage from the balancing arm 204.

[0070] Another embodiment of the present invention, in conjunction with the above embodiments, please refer to... Figure 10 In this embodiment, the rotating body 2 is a rotating platform 202. The rotating platform 202 can be of any shape. Preferably, the rotating platform 202 is circular. At least one attitude adjustment device 5 is provided on the rotating platform 202.

[0071] Please see Figure 11 The launch system of the present invention includes the aforementioned rotating launch device and controller 7. Controller 7 is a general-purpose computer or embedded controller. The rotating launch device and controller 7 are interconnected. Controller 7 obtains the status data of each node of the rotating launch device and the status data of the aircraft in real time. Based on the performance of the aircraft, it selects the appropriate program to control the working state of the launch device so that the aircraft can be launched in a relatively good attitude.

[0072] To better adapt to the environment, this system is equipped with an environmental sensing device 8, which includes at least one of the following: an anemometer, an airflow meter, a lidar sensor, and a visual sensor. The environmental sensing device 8 is connected to the controller 7. The environmental sensing device 8 and the controller 7 are used to sense surrounding environmental information and to control the various components of the rotating launcher in real time.

[0073] 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 rotating launch device for an aircraft, comprising a support body (1), characterized in that: And at least one rotating body (2) that rotates about the axis of the support (1), and a drive device (4) that provides power for the rotation of the rotating body (2); The rotating body (2) is provided with at least one attitude adjustment device (5), which is used to adjust the attitude of the aircraft in real time during rotation acceleration and launch. The attitude adjustment device (5) is equipped with a launcher (6) for holding and releasing the aircraft; The support body (1) is provided with a base (3) at its bottom, which is used to provide stable support for the entire launching device; The attitude adjustment device (5) is provided with a first rotating joint, and the launcher (6) is connected to the rotating body (2) through the first rotating joint. The first rotating joint is configured to be able to quickly rotate the launcher (6) before the launcher (6) releases the aircraft, so that the two wings of the aircraft have the same ground speed when the launcher (6) releases the aircraft.

2. The aircraft rotary launch device according to claim 1, characterized in that: The attitude adjustment device (5) includes a mechanical arm consisting of at least two rotating joints. Each rotating joint is driven by a servo or energy storage device or a combination of servo and energy storage device. The attitude of the aircraft is adjusted by adjusting the angles of multiple axes on the mechanical arm.

3. The aircraft rotating launch device according to claim 1, characterized in that: The attitude adjustment device (5) can reciprocate radially along the rotation center of the rotating body (2).

4. The aircraft rotating launch device according to claim 1, characterized in that: The rotating body (2) can reciprocate along the length of the support body (1).

5. The aircraft rotary launch device according to claim 1, characterized in that: An inclination adjustment structure is provided between the support (1) and the base (3), and the inclination adjustment structure is used to adjust the inclination angle between the support (1) and the base (3).

6. The aircraft rotary launch device according to any one of claims 1 to 5, characterized in that: The rotating body (2) is a rotating structure with at least one rotating arm (201), and the attitude adjustment device (5) is disposed on the rotating arm (201); or The rotating body (2) is a rotating platform (202), and the attitude adjustment device (5) is mounted on the rotating platform (202).

7. The aircraft rotary launch device according to claim 6, characterized in that: The rotating arm (201) is provided with a connecting block (203), and the rotating arm (201) is connected to the support body (1) through the connecting block (203). The rotating arm (201) and the connecting block (203) are rotatably connected and a rotation locking mechanism is provided at the connection.

8. The aircraft rotating launch device according to claim 6, characterized in that: The rotating body (2) is also provided with a balancing arm (204) to reduce the torque on the base (3) in the roll and pitch directions when the rotating body is stationary and during rotation. The balancing arm (204) is provided with a counterweight (205) for counterweighting. The counterweight (205) can reciprocate radially along the rotation center of the balancing arm (204). The distance between the counterweight (205) and the rotation axis of the rotating body (2) is adjustable in real time, and the counterweight (205) can be quickly disengaged from the balancing arm (204).

9. A launch system for an aircraft, characterized in that: The rotating launch device and controller (7) according to any one of claims 1 to 8, wherein the controller (7) is a general-purpose computer or an embedded controller, and the operating state of the launch device is controlled by a corresponding program selected according to the performance of the aircraft, so that the aircraft can launch in a relatively good attitude.

10. The launch system for an aircraft according to claim 9, characterized in that: The launching system is equipped with an environmental sensing device (8), which includes at least one of an anemometer, an air volume meter, a lidar, and a visual sensor. The environmental sensing device (8) is signal-connected to the controller (7).

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