Airborne launcher and unmanned aerial vehicle system

Abstract

The present invention relates to an airborne launcher and an unmanned aerial vehicle system. The airborne launcher comprises: a guide rail device, a launch preload providing device and a switch device spaced apart along the length direction of the guide rail device, a first connector and a second connector for connecting a load; the first connector and the second connector are respectively slidably connected to the guide rail device; the launch preload providing device is used to locate the initial position of the first connector and to increase the initial launch velocity of the load; the switch device is used to locate the initial position of the second connector. The present invention can effectively mount a small payload device for an unmanned aerial vehicle. When mounted, the launcher has the function of reliably locking the payload. During launch, an ignition signal can be sent from the ground or the unmanned aerial vehicle up and down to complete the automatic unlocking and payload engine ignition functions in a timely manner. While having the advantages of simple structure and high positioning accuracy, it also has comprehensive control functions.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles (UAVs), and in particular to an airborne launcher and a UAV system. Background Art

[0002] A drone is an unmanned aerial vehicle controlled by a wireless remote control device and its own control devices. Examples include unmanned helicopters, fixed-wing drones, and unmanned paragliders. Over the past decade or so, drones have been widely used in aerial photography, power inspections, environmental monitoring, forest fire prevention, disaster inspections, anti-terrorism and life-saving rescue, military reconnaissance, and battlefield assessments.

[0003] Due to their low cost and ease of operation, drones are suitable for research institutes and other private companies that need to launch small rockets and missiles, eliminating the need for traditional aircraft platforms. However, existing mounts for attaching small rockets and missiles to drones often suffer from complex structures, heavy weight, inconvenient operation, difficult maintenance, and limited reliability, resulting in low mounting efficiency. Summary of the Invention

[0004] The purpose of the present invention is to provide an airborne launcher and an unmanned aerial vehicle system.

[0005] To achieve the above-mentioned object of the invention, the present invention provides an airborne launcher, comprising: a guide rail device, a launch preload force providing device and a switch device arranged at intervals along the length direction of the guide rail device, and a first connecting member and a second connecting member for connecting a load;

[0006] The first connecting member and the second connecting member are respectively slidably connected to the guide rail device;

[0007] The launch preload providing device is used to locate the initial position of the first connecting member and to increase the initial launch velocity of the load;

[0008] The switch device is used to locate the initial position of the second connecting member.

[0009] According to one aspect of the present invention, the guide rail device comprises: a plate-shaped guide rail support, a guide support fixedly connected to the track support;

[0010] The guide support is a plate-shaped body, and is provided with a stepped guide groove penetrating the body thereof;

[0011] The guide groove is freely extended along the length direction of the guide support.

[0012] According to one aspect of the present invention, the launch preload force providing device comprises: a mounting seat, a first elastic member and a spherical positioning movable member;

[0013] The positioning end of the mounting seat is embedded in the guide rail support;

[0014] The positioning end is provided with a mounting groove for mounting the first elastic member;

[0015] The spherical positioning movable member is arranged to abut against the first elastic member and can slide freely along the installation groove.

[0016] According to one aspect of the present invention, the switch device includes: a switch base, an opening and closing controller provided on the switch base, a locking structure, a travel switch and a linkage member;

[0017] The opening and closing controller, the locking structure and the travel switch are arranged side by side on the switch seat, and the locking structure is located between the opening and closing controller and the travel switch;

[0018] The linkage member is in the form of an elongated strip, one end of which is hinged to the switch seat, and the other end of which is an opening and closing connection end that rotates at the hinged position of the linkage member and the switch seat;

[0019] The opening and closing controller is used to control the locking and release of the opening and closing connection end;

[0020] A control protrusion for controlling the switching action of the travel switch is provided at the hinged position between the linkage member and the switch seat;

[0021] The portion between the two opposite ends of the linkage member can be in contact with the locking structure to control the extension and retraction of the locking structure, so as to lock and release the second connecting member;

[0022] The travel switch is electrically connected to the propeller of the load.

[0023] According to one aspect of the present invention, the linkage member completes the opening action of the travel switch while completing the release control of the second connecting member; or, the linkage member completes the opening action of the travel switch after completing the release control of the second connecting member.

[0024] According to one aspect of the present invention, the locking structure includes: a locking rod and a second elastic member sleeved on the locking rod;

[0025] The opposite ends of the second elastic member are respectively arranged to abut against the upper end of the locking rod and the switch seat.

[0026] According to one aspect of the present invention, the opening and closing controller is a power-off type electromagnet.

[0027] According to one aspect of the present invention, the first connecting member includes: a first connecting portion and a second connecting portion that are perpendicular to each other;

[0028] The upper end of the first connecting portion is provided with a first positioning groove for cooperating with the spherical positioning movable member;

[0029] The second connecting member includes: a third connecting portion and a fourth connecting portion perpendicular to each other;

[0030] The upper end of the third connecting portion is provided with a second positioning groove for matching with the lower end of the locking rod.

[0031] According to one aspect of the present invention, it further comprises: a lifting connector;

[0032] The lifting connector includes: a lifting seat and a fastening member detachably connected to the lifting seat;

[0033] The hanging seat and the guide rail support are fixedly connected to each other.

[0034] To achieve the above-mentioned object of the invention, the present invention provides a UAV system using the aforementioned airborne launcher, comprising: a UAV, an airborne launcher connected to the UAV, and a payload connected to the airborne launcher;

[0035] The airborne launcher is fixedly connected to the UAV by a lifting connector;

[0036] The payload is hoisted below the airborne launcher by being fixedly connected to the first connecting member and the second connecting member;

[0037] The opening and closing controller in the switch device of the airborne launcher is connected to the control unit of the UAV;

[0038] The travel switch of the airborne launcher is electrically connected to the propulsion device of the payload.

[0039] According to one solution of the present invention, the present invention can effectively mount small payload devices (such as small missile rockets) for unmanned aerial vehicles. When mounted, the launcher has the function of reliably locking the payload. During launch, an ignition signal can be sent from the ground or up and down the unmanned aerial vehicle to complete the automatic unlocking and payload engine ignition functions in a timed sequence. While having the advantages of simple structure and high positioning accuracy, it also has comprehensive control functions.

[0040] According to one solution of the present invention, through the linkage mechanical structure design, it is reliable to ensure that the drone platform will be unlocked first when a transmission signal is transmitted, and the rocket engine will be ignited after the unlocking is completed, realizing the one-button launch function with timely and fast response.

[0041] According to one solution of the present invention, through mechanical structure design and the application of torque-related principles, the present invention can reliably realize the locking and unlocking functions through a small actuator, and ignition and launch can be completed at the moment of unlocking, which greatly reduces the power supply requirements for the launcher and improves reliability.

[0042] According to one embodiment of the present invention, by employing a launch preload providing device to initially position the rear end of the payload, it is effectively ensured that the payload, after reaching a sufficient velocity, overcomes the preload of the launch preload providing device, thereby enabling the payload to escape from the launch preload providing device upon reaching a certain initial velocity. This demonstrates that this embodiment achieves the effect of increasing the initial launch preload of the payload with a simple structure, thereby further increasing the payload's launch velocity at low elevation angles. Furthermore, while effectively increasing the payload's initial launch velocity, it can also effectively reduce the length of the guide rail assembly, thereby improving the launch reliability of this embodiment.

[0043] According to one solution of the present invention, the launcher of the present invention has no recoil, which greatly improves the adaptability of the UAV to high-altitude launch.

[0044] According to one solution of the present invention, the launcher of the present invention is easy to maintain, reusable, and has a light structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 is a perspective view schematically showing an airborne launcher according to one embodiment of the present invention;

[0046] Figure 2 is a diagram schematically showing a locked state of an airborne launcher and a payload according to an embodiment of the present invention;

[0047] Figure 3 is a schematic diagram showing an end structure of a guide rail device according to an embodiment of the present invention;

[0048] Figure 4 is a structural diagram schematically showing a launch preload force providing device according to an embodiment of the present invention;

[0049] Figure 5 is a diagram schematically showing a locked state of a switch device according to an embodiment of the present invention;

[0050] Figure 6 is a diagram schematically showing a launch state of an airborne launcher and a payload according to an embodiment of the present invention;

[0051] Figure 7 is a diagram schematically showing an unlocked state of a switch device according to an embodiment of the present invention;

[0052] Figure 8is a structural diagram schematically showing a first connector or a second connector according to an embodiment of the present invention;

[0053] Figure 9 Schematically shows the structure of a drone system according to one embodiment of the present invention. DETAILED DESCRIPTION

[0054] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be derived from these drawings without inventive effort.

[0055] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

[0056] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not limited to the following embodiments.

[0057] Combine Figure 1 and Figure 2 As shown, according to one embodiment of the present invention, an airborne launcher of the present invention comprises: a guide rail device 1, a launch preload providing device 2 and a switch device 3 spaced apart along the length direction of the guide rail device 1, and a first connector 4 and a second connector 5 for connecting a load. In this embodiment, the first connector 4 and the second connector 5 are used to hoist and guide the load, and then they are respectively slidably connected to the guide rail device 1 to achieve a directional and stable launch of the load along the guide rail device 1. In this embodiment, the launch preload providing device 2 is used to locate the initial position of the first connector 4; the switch device 3 is used to locate the initial position of the second connector 5. In order to achieve a stable and reliable connection of the load before launch, it is necessary to lock the load through the launch preload providing device 2 and the switch device 3. During launch, the subsequent directional launch of the load can be achieved by unlocking the switch device 3.

[0058] Through the above configuration, the airborne launcher of the present invention has a simple structure and is lightweight, allowing for convenient and flexible installation on small vehicles such as drones to achieve stable lifting of payloads (such as small missiles and fire extinguishing bombs). Furthermore, the airborne launcher of the present invention can also securely lock and release the payload via a built-in switch device, greatly enhancing the safety of the present invention.

[0059] In addition, the launch preload providing device provided in the present invention can achieve stable positioning of the rear end of the load in the length direction of the guide rail device, thereby effectively avoiding disordered swinging of the load during the flight of the vehicle, which is beneficial to ensuring the accurate launch of the load.

[0060] Combine Figure 1 、 Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the guide rail device 1 includes: a plate-shaped guide rail support 11, and a guide support 12 fixedly connected to the rail support 11. In this embodiment, the guide support 12 is a plate-shaped body, and a stepped guide groove 121 is provided on the guide support 12 and passes through its body. In this embodiment, the guide groove 121 includes: a first guide groove portion 1211 and a second guide groove portion 1212, wherein the first guide groove portion 1211 is located above the second guide groove portion 1212, and the width of the first guide groove portion 1211 is greater than the width of the second guide groove portion 1212. In this embodiment, the guide support 12 is provided with one end of the first guide groove portion 1211 fixedly connected to the guide rail support 11, so that one end of the guide groove 121 is closed. In this embodiment, the guide groove 121 is freely extended along the length direction of the guide support 12.

[0061] In this embodiment, the cross-sectional area of ​​the guide groove 121 is constant along the length direction of the guide groove 121 .

[0062] Combine Figure 2 and Figure 4As shown, according to one embodiment of the present invention, a launch preload force providing device 2 includes a mounting seat 21, a first elastic member 22, and a spherical positioning movable member 23. In this embodiment, the positioning end of the mounting seat 21 is embedded in the guide rail support 11; the positioning end is provided with a mounting groove 211 for mounting the first elastic member 22. In this embodiment, the spherical positioning movable member 23 is arranged to abut against the first elastic member 22 and can slide freely along the mounting groove 211. In this embodiment, a mounting hole is provided through the guide rail support 11, so that the positioning end of the mounting seat 21 can be embedded in the mounting hole in a shape-fitting manner. By providing the elastic combination structure of the first elastic member 22 and the spherical positioning movable member 23 on the positioning end, the elastic force can always keep the portion of the spherical positioning movable member 23 protruding from the end surface of the positioning end. Thus, by providing a corresponding groove structure on the first connecting member 4 that cooperates with the protruding portion of the spherical positioning movable member 23, the first connecting member 4 can be positioned in the initial position.

[0063] Furthermore, by using a launch preload providing device to initially position the rear end of the payload, it is effectively ensured that the payload, once it reaches a sufficient velocity, overcomes the preload provided by the launch preload providing device, allowing the payload to be released from the launch preload providing device once it reaches a certain initial velocity. This demonstrates that this solution achieves the effect of increasing the initial launch preload on the payload with a simple structure, further increasing the payload's launch velocity at low elevation angles. Furthermore, while effectively increasing the payload's initial launch velocity, it also effectively reduces the length of the guide rail assembly, improving the launch reliability of this solution.

[0064] Combine Figure 2 、 Figure 5 、 Figure 6 and Figure 7 As shown, according to one embodiment of the present invention, the switch device 3 includes: a switch base 31, an opening and closing controller 32 mounted on the switch base 31, a locking structure 33, a limit switch 34, and a linkage 35. In this embodiment, the opening and closing controller 32, the locking structure 33, and the limit switch 34 are arranged side by side on the switch base 31, with the locking structure 33 positioned between the opening and closing controller 32 and the limit switch 34. In this embodiment, the linkage 35 is an elongated structure, one end of which is hinged to the switch base 31, and the other end is an opening and closing connection end that rotates at the hinged position of the linkage 35 and the switch base 31. The opening and closing controller 32 is used to control the locking and release of the opening and closing connection end. In this embodiment, a control protrusion 351 is provided at the hinged position of the linkage 35 and the switch base 31 for controlling the opening and closing of the limit switch 34. The portion between the opposite ends of the linkage 35 can abut against the locking structure 33, controlling the extension and contraction of the locking structure 33, thereby controlling the locking and release of the second connecting member 5. In this embodiment, the travel switch 34 is electrically connected to the propeller of the load.

[0065] In this embodiment, the linkage member 35 is configured as an elongated strip. One end of the linkage member 35 is rotatable, while the other end (i.e., the opening and closing connection end) is freely movable. This allows the linkage member 35 to synchronize its lengthwise ends and the middle portion of the linkage member 35 during synchronous operation, thereby enabling simultaneous or sequential control of multiple structures. This configuration enables the switch device of the present invention to achieve the beneficial effects of multiple controls with a simple structure. This not only provides a simple structure and high reliability, but also provides accurate, stable, and precise control sequences. Furthermore, this configuration of the switch device ensures a simple structure while effectively reducing production costs.

[0066] In this embodiment, the switch base 31 is an overall rectangular structure, with a corresponding hollow interior to form corresponding mounting locations for the opening and closing controller 32, the locking structure 33, the limit switch 34, and the linkage member 35. Along the length of the linkage member 35, the opening and closing controller 32, the locking structure 33, and the limit switch 34 are sequentially mounted within the switch base 31. The limit switch 34 is located directly below the hinged connection between the linkage member 35 and the switch base 31, while the opening and closing controller 32 is located below the opening and closing connection end of the linkage member 35. Consequently, when the opening and closing connection end and the opening and closing controller 32 are engaged, the control protrusion 351 on the linkage member 35 precisely presses against the contact of the limit switch 34, ensuring that the limit switch is in the off state.

[0067] In this embodiment, when the opening and closing connection end of the linkage 35 is attracted to the opening and closing controller 32, the end of the locking structure 33 between the opening and closing controller 32 and the limit switch 34 is also pressed by the middle part of the linkage 35, so that the lower end of the locking structure 33 can extend in the direction of the guide groove 121 to achieve connection with the matching groove structure on the second connecting member 5, thereby locking the second connecting member 5.

[0068] In this embodiment, the control protrusion 351 on the linkage member 35 can be configured as an arc-shaped protrusion arranged axially along the hinge axis. The length of the control protrusion 351 is determined by the timing of the locking mechanism 33 controlling the locking and disengagement of the second connecting member 5. Specifically, when the opening and closing controller 32 releases the linkage member 35, the locking mechanism 33 activates the opening and closing connection end of the linkage member 35 to move away from the opening and closing controller 32. At this point, due to the loss of the restraint of the locking mechanism 33, the locking mechanism 33 disengages from the second connecting member 5, and the control protrusion 351 also rotates along the hinge axis. When the locking mechanism 33 is completely disengaged from the second connecting member 5, the control protrusion 351 also disengages from the contacts of the travel switch 34, which activates the load-generating device and enables the load to be launched. Of course, the length of the control protrusion 351 can be appropriately extended so that after the locking mechanism 33 is completely disengaged from the second connecting member 5, the control protrusion 351 continues to move a certain distance to disengage from the contacts of the travel switch 34, thereby achieving a delayed activation of the load-generating device.

[0069] In this embodiment, the opening and closing connection end of the linkage member 35 can be shaped accordingly based on the size of the engagement area of ​​the opening and closing controller 32, so as to achieve a stable connection between the opening and closing controller 32 and the linkage member 35. In this embodiment, the linkage member 35 can be configured as a metal material that engages with the opening and closing controller 32, or only the opening and closing connection end can be configured as a metal material that can engage with the opening and closing controller 32. The configuration can be adjusted according to actual needs.

[0070] Combine Figure 5 and Figure 7 As shown, according to one embodiment of the present invention, the locking structure 33 includes a locking rod 331 and a second elastic member 332 mounted on the locking rod 331. In this embodiment, the opposing ends of the second elastic member 332 are respectively disposed to abut against the upper end of the locking rod 331 and the switch base 31. In this embodiment, a boss is provided on the upper end of the locking rod 331 to ensure stable abutment against the second elastic member 332 and the linkage member 35. In this embodiment, the length of the second elastic member 332 in its free state is adjusted based on the linkage control requirements of the linkage member 35.

[0071] In this embodiment, in order to lock the lower end of the locking rod 331 with the second connecting member 5, a through hole needs to be set at a position corresponding to the locking rod 331 on the guide rail support 11 to achieve the extension and retraction of the lower end of the locking rod 331 during the extension and retraction process.

[0072] Combine Figure 5 and Figure 7 As shown, according to one embodiment of the present invention, the opening and closing controller 32 is a power-off type electromagnet.

[0073] Through the above configuration, by setting the opening and closing controller 32 as a power-off type electromagnet, it can lose its magnetism in the power-off state, so that the action response of the linkage part 35 is more timely and rapid, which is beneficial to improving the launch efficiency of the present invention.

[0074] Combine Figure 4 、 Figure 5 and Figure 8 As shown, according to one embodiment of the present invention, the first connecting member 4 includes: a first connecting portion 41 and a second connecting portion 42 that are perpendicular to each other. In this embodiment, the first connecting portion 41 is horizontally arranged, and its width is consistent with the width of the first guide groove portion 1211 in the guide groove 121, thereby being able to eliminate the shaking in the width direction of the guide groove 121 during the sliding process along the guide groove 121, which is beneficial to ensuring the guiding accuracy of the present invention. In this embodiment, the second connecting portion 42 is vertically arranged, and its width is inconsistent with the width of the second guide groove portion 1212 in the guide groove 121, that is, the width of the second connecting portion 42 is smaller than the width of the second guide groove portion 1212, which effectively reduces the contact area between the first connecting member 4 and the guide groove 121, which is beneficial to reducing the friction during the sliding process and effectively reducing the power loss during load launch.

[0075] In this embodiment, the lower end of the second connecting portion 42 is connected to the load via a connecting member to achieve stable loading of the load.

[0076] In the present embodiment, the upper end of the first connecting portion 41 is provided with a first positioning groove 411 for cooperating with the spherical positioning movable member 23. In the present embodiment, the diameter of the first positioning groove 411 can be set accordingly according to the diameter of the protruding portion of the spherical positioning movable member 23, so as to meet the accurate positioning of the spherical positioning movable member 23 and eliminate the disordered shaking that exists in the case of a large gap, thereby improving the positioning accuracy of the present invention. By cooperating with the spherical positioning movable member 23, after the load is started, it is necessary to overcome the resistance of the spherical positioning movable member 23 through the action of the load's own power, so that the spherical positioning movable member 23 can be retracted along the mounting groove 211 to achieve the sliding flight of the load along the guide rail device. Through this setting method, it is effectively ensured that after the switch device is disengaged from the second connecting member 5, it can still provide a certain positioning effect through the launch preload providing device 2, effectively avoiding the load from falling off and sliding out after the lock is released, which is beneficial to ensuring the accurate launch of the load.

[0077] Combine Figure 4 、 Figure 5 and Figure 8As shown, according to one embodiment of the present invention, the second connecting member 5 includes: a third connecting portion 51 and a fourth connecting portion 52 that are perpendicular to each other. In this embodiment, the third connecting portion 51 is horizontally arranged, and its width is consistent with that of the first guide groove portion 1211 in the guide groove 121, thereby being able to eliminate shaking in the width direction of the guide groove 121 during sliding along the guide groove 121, which is beneficial to ensuring the guiding accuracy of the present invention. In this embodiment, the fourth connecting portion 52 is vertically arranged, and its width is inconsistent with that of the second guide groove portion 1212 in the guide groove 121, that is, the width of the fourth connecting portion 52 is smaller than the width of the second guide groove portion 1212, which effectively reduces the contact area between the second connecting member 5 and the guide groove 121, which is beneficial to reducing friction during sliding and effectively reducing power loss during load launch.

[0078] In this embodiment, the lower end of the fourth connecting portion 52 is connected to the load through a connecting member to achieve stable loading of the load.

[0079] In this embodiment, the upper end of the third connecting portion 51 is provided with a second positioning groove 511 for mating with the lower end of the locking rod 331. In this embodiment, the diameter of the second positioning groove 511 matches the diameter of the lower end of the locking rod 331 to ensure accurate positioning of the locking rod 331, eliminate positioning gaps, and improve the positioning accuracy of the present invention.

[0080] like Figure 9 As shown, according to one embodiment of the present invention, an airborne launcher further includes a lifting connector 6. In this embodiment, the lifting connector 6 includes a lifting seat 61 and a fastening member 62 detachably connected to the lifting seat 61. In this embodiment, the lifting seat 61 is fixedly connected to the guide rail support 11.

[0081] Combine Figure 9 、 Figure 4 and Figure 5 As shown, according to one embodiment of the present invention, a UAV system employing the aforementioned airborne launcher comprises: UAV a, airborne launcher b connected to UAV a, and payload c connected to airborne launcher b. In this embodiment, airborne launcher b is fixedly connected to UAV a using a hoisting connector 6; payload c is hoisted below airborne launcher b via a fixed connection between a first connector 4 and a second connector 5; the on / off controller 32 in the switch device 3 of airborne launcher b is connected to the control unit of UAV a; and the limit switch 34 of airborne launcher b is electrically connected to the propulsion device of payload c.

[0082] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail, it should be understood that they can be implemented by adopting general devices and methods available in the art.

[0083] The above description is merely one embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. An airborne launcher, characterized in that: include: A guide rail device (1), a launch preload force providing device (2) and a switch device (3) arranged at intervals along the length direction of the guide rail device (1), and a first connecting member (4) and a second connecting member (5) for connecting a load; The first connecting member (4) and the second connecting member (5) are respectively slidably connected to the guide rail device (1); The launch preload providing device (2) is used to locate the initial position of the first connecting member (4) and to increase the initial launch velocity of the load; The switch device (3) is used to locate the initial position of the second connecting member (5); The switch device (3) comprises: a switch base (31), an opening and closing controller (32) arranged on the switch base (31), a locking structure (33), a travel switch (34) and a linkage member (35); The opening and closing controller (32), the locking structure (33) and the travel switch (34) are arranged side by side on the switch seat (31), and the locking structure (33) is located between the opening and closing controller (32) and the travel switch (34); The linkage member (35) is in the form of a long strip, one end of which is hinged to the switch seat (31), and the other end of which is an opening and closing connection end that rotates at the hinged position of the linkage member (35) and the switch seat (31); The opening and closing controller (32) is used to control the locking and release of the opening and closing connection end; A control protrusion (351) for controlling the switching action of the travel switch (34) is provided at a hinged position between the linkage member (35) and the switch seat (31); The portion between the two opposite ends of the linkage member (35) can be in contact with the locking structure (33) to control the extension and contraction of the locking structure (33) so as to lock and release the second connecting member (5); The travel switch (34) is electrically connected to the propeller of the load.

2. The airborne launcher according to claim 1, characterized in that: The guide rail device (1) comprises: a guide rail support (11); The launch preload force providing device (2) comprises: a mounting seat (21), a first elastic member (22) and a spherical positioning movable member (23); The positioning end of the mounting seat (21) is embedded in the guide rail support (11); The positioning end is provided with a mounting groove (211) for mounting the first elastic member (22); The spherical positioning movable member (23) is arranged to abut against the first elastic member (22) and can slide freely along the installation groove (211).

3. The airborne launcher according to claim 2, characterized in that: The linkage member (35) completes the release control of the second connecting member (5) and simultaneously completes the opening action of the travel switch (34); or, after the linkage member (35) completes the release control of the second connecting member (5), it completes the opening action of the travel switch (34).

4. The airborne launcher according to claim 3, characterized in that: The locking structure (33) comprises: a locking rod (331) and a second elastic member (332) sleeved on the locking rod (331); The opposite ends of the second elastic member (332) are respectively arranged to abut against the upper end of the locking rod (331) and the switch seat (31).

5. The airborne launcher according to claim 4, characterized in that: The opening and closing controller (32) is a power-off type electromagnet.

6. The airborne launcher according to claim 5, characterized in that: The first connecting member (4) comprises a first connecting portion (41) and a second connecting portion (42) which are perpendicular to each other; The upper end of the first connecting portion (41) is provided with a first positioning groove (411) for cooperating with the spherical positioning movable member (23); The second connecting member (5) comprises a third connecting portion (51) and a fourth connecting portion (52) which are perpendicular to each other; The upper end of the third connecting portion (51) is provided with a second positioning groove (511) for cooperating with the lower end of the locking rod (331).

7. The airborne launcher according to claim 6, characterized in that: Also includes: Lifting connector (6); The hanging connection member (6) comprises a hanging seat (61) and a fastening member (62) detachably connected to the hanging seat (61); The hanging seat (61) and the guide rail support (11) are fixedly connected to each other.

8. An unmanned aerial vehicle system using the airborne launcher according to any one of claims 1 to 7, characterized in that: include: An unmanned aerial vehicle (a), an airborne launcher (b) connected to the unmanned aerial vehicle (a), and a payload (c) connected to the airborne launcher (b); The airborne launcher (b) is fixedly connected to the UAV (a) by a lifting connector (6); The load (c) is hoisted below the airborne launcher (b) by being fixedly connected to the first connecting member (4) and the second connecting member (5); The opening and closing controller (32) in the switch device (3) of the airborne launcher (b) is connected to the control unit of the unmanned aerial vehicle (a); The travel switch (34) of the airborne launcher (b) is electrically connected to the propulsion device of the payload (c).

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