Unmanned aerial vehicle ejection equipment

Abstract

The utility model discloses unmanned aerial vehicle ejection equipment which is used for improving the deployment efficiency of the ejection equipment and improving the take-off efficiency of an unmanned aerial vehicle. The catapulting device comprises a catapulting track, an elastic piece, a track sliding block, a support, a supporting frame and a catapulting releasing mechanism. The ejection track is provided with a release end and an ejection end, and the support is arranged at the ejection end. The rail sliding block is arranged in the ejection rail, the rail sliding block can move in the ejection rail, the supporting frame is connected with the rail sliding block, and the supporting frame is used for supporting and hooking an unmanned aerial vehicle; the ejection release mechanism is arranged at the release end, one end of the elastic piece is connected with the ejection end, the other end of the elastic piece is connected with the rail sliding block, and the elastic piece is matched with the ejection release mechanism to be used for ejecting the rail sliding block from the release end to the ejection end.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle equipment, and particularly relates to an unmanned aerial vehicle launching device. BACKGROUND

[0002] With the rapid development of unmanned aerial vehicle technology, small unmanned aerial vehicles have been increasingly widely applied in many fields such as military reconnaissance, environmental monitoring, agricultural plant protection, logistics distribution and emergency rescue due to their small size, high flexibility and low cost.

[0003] At present, the take-off modes of small unmanned aerial vehicles mainly include taxiing take-off, vertical take-off, launching take-off and manual hand-throwing take-off. Among them, the launching take-off can make the unmanned aerial vehicle quickly obtain sufficient initial speed in a short distance, significantly prolong the endurance time and operation range, and thus becomes a popular mainstream unmanned aerial vehicle take-off mode.

[0004] However, in the existing launching device, a heavy launching frame structure is generally used, and the existing launching frame structure is bulky and heavy, which leads to difficulty in rapid carrying, transportation and on-site deployment, especially in some narrow spaces, a special area for deploying the launching frame structure needs to be specially opened, and the deployment efficiency is low, thereby affecting the take-off efficiency of the unmanned aerial vehicle.

[0005] Based on this, the present application provides an unmanned aerial vehicle launching device to solve the above technical problems. CONTENT OF THE UTILITY MODEL

[0006] In order to solve the above technical problems, the present application provides an unmanned aerial vehicle launching device, which can improve the deployment efficiency of the launching device and improve the take-off efficiency of the unmanned aerial vehicle.

[0007] The unmanned aerial vehicle launching device provided by the present application comprises:

[0008] a launching track, an elastic member, a track slider, a support, a support frame and a launching release mechanism;

[0009] The launching track is provided with a release end and a shooting end, and the support is arranged on the shooting end.

[0010] The track slider is arranged in the launching track and is movable in the launching track, the support frame is connected with the track slider, and the support frame is used for supporting and hooking the unmanned aerial vehicle.

[0011] The launching release mechanism is arranged at the release end, one end of the elastic member is connected with the shooting end, and the other end is connected with the track slider, and the elastic member cooperates with the launching release mechanism to launch the track slider from the release end to the shooting end.

[0012] Optionally, the ejection release mechanism comprises a release frame, a release rudder and a self-locking lock buckle arranged on the release frame.

[0013] The self-locking lock buckle is connected in the ejection track and is used for locking the track slider; the release rudder is connected with the self-locking lock buckle and is used for controlling the self-locking lock buckle to be unlocked.

[0014] Optionally, the release rudder is provided with a rudder swing arm, and the rudder swing arm is connected with an unlocking ring on the self-locking lock buckle through a steel wire rope.

[0015] Optionally, the ejection release mechanism further comprises a battery and a remote control receiver, the battery is electrically connected with the remote control receiver and the release rudder respectively, and the remote control receiver is electrically connected with the release rudder.

[0016] Optionally, a bumper is arranged in the ejection end and faces the track slider.

[0017] Optionally, the number of the elastic members is two, and one elastic member is arranged on each side of the ejection track.

[0018] Optionally, the elastic member comprises a rubber tube and first and second connecting heads connected to two ends of the rubber tube respectively.

[0019] The ejection end is externally provided with a first connecting rod, the track slider is externally provided with a second connecting rod, the first connecting head is connected with the first connecting rod, and the second connecting head is connected with the second connecting rod.

[0020] Optionally, the track slider comprises a frame, a pulley and a slider body, the slider body is fixed in the frame, the pulley is arranged on both sides of the slider body, and the pulley is used for abutting against the inner wall of the ejection track.

[0021] Optionally, the support frame comprises a support body, support rods and a cross rod, the support body is connected with the track slider, the support rods are arranged at two ends of the support body respectively, the cross rod is arranged on the support body, and the support rods are perpendicular to the ejection track, and the cross rod is used for abutting against the hook at the bottom of the unmanned aerial vehicle.

[0022] Optionally, the support frame comprises first and second supporting legs, and the angle between the first supporting leg and the second supporting leg ranges from 30 degrees to 120 degrees.

[0023] From the above technical solutions, the present application has the following effects:

[0024] The application sets the elastic member, sets the track slider in the ejection track, and the track slider is movable in the ejection track, connects the two ends of the elastic member with the ejection end and the track slider of the ejection track, sets the ejection release mechanism at the release end of the ejection track, and sets the support frame on the track slider, supports and hooks the unmanned aerial vehicle through the support frame, the elastic member provides the force for the track slider to move to the ejection end, the track slider is ejected from the release end to the ejection end through the cooperation of the elastic member and the ejection release mechanism, the track slider drives the support frame to move, so that the unmanned aerial vehicle is ejected quickly, compared with the ejection structure of the prior art, the volume and weight of the ejection device are reduced, the ejection device is miniaturized, the portability is improved, the requirements for the environment and space are reduced, the deployment efficiency is improved, and the take-off efficiency of the unmanned aerial vehicle is improved. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the application, the drawings needed in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0026] Figure 1 It is a schematic view of the unmanned aerial vehicle ejection device of the application.

[0027] Figure 2 It is a schematic view of the ejection track in the unmanned aerial vehicle ejection device of the application.

[0028] Figure 3 It is another schematic view of the ejection track in the unmanned aerial vehicle ejection device of the application.

[0029] Figure 4 It is a schematic view of the track slider in the unmanned aerial vehicle ejection device of the application.

[0030] Figure 5 It is a schematic view of the self-locking lock catch in the unmanned aerial vehicle ejection device of the application.

[0031] Figure 6 It is a schematic view of the support frame in the unmanned aerial vehicle ejection device of the application.

[0032] Figure 7 It is a schematic view of the steering engine swing arm in the unmanned aerial vehicle ejection device of the application.

[0033] Figure 8 It is another schematic view of the track slider in the unmanned aerial vehicle ejection device of the application.

[0034] Figure 9 It is another schematic view of the unmanned aerial vehicle ejection device of the application.

[0035] In the figure: Ejection track 01, elastic member 02, track slider 03, support 04, support frame 05, unmanned aerial vehicle 06, release frame 07, release servo 08, self-locking lock 09, servo swing arm 10, steel wire rope 11, first supporting leg 12, second supporting leg 13, bumper 14, rubber tube 15, first connecting head 16, second connecting head 17, first connecting rod 18, second connecting rod 19, frame 20, pulley 21, slider body 22, support body 23, support rod 24, crossbar 25. DETAILED DESCRIPTION

[0036] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "transverse", "longitudinal" and the like indicate the orientation or positional relationship shown in the drawings, and are used only to illustrate the relative positional relationship between the components or constituent parts, and do not particularly limit the specific installation orientation of the components or constituent parts.

[0037] In addition, in addition to being used to indicate the orientation or positional relationship, the above-mentioned terms can also be used to indicate other meanings, for example, the term "upper" can also be used to indicate a certain dependent relationship or connection relationship in some cases. For those skilled in the art, the specific meaning of these terms in the present application can be understood according to the specific circumstances.

[0038] In addition, the terms "mounting", "setting", "provided with", "connected", "connected" should be broadly understood. For example, it can be fixedly connected, detachably connected, or integrally configured; it can be mechanically connected, or electrically connected; it can be directly connected, or indirectly connected through an intermediate medium, or it can be internal communication between two devices, elements or constituent parts. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0039] In addition, the structure, proportion, size, etc. shown in the drawings attached in the present application are only used to cooperate with the content disclosed in the specification, so that those skilled in the art can understand and read, and do not have technical significance. Any modification of the structure, change of the proportion relationship or adjustment of the size, without affecting the effect and purpose that can be achieved by the present application, should still fall within the scope of the technical content disclosed by the present application.

[0040] With reference to the drawings of the embodiments of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort belong to the scope of protection of the present application.

[0041] The present application provides a UAV launching device, which is used to improve the deployment efficiency of the launching device and the take-off efficiency of the UAV. The specific implementation process of the present application is described as follows.

[0042] Referring to Figures 1 to 9 The UAV launching device provided by the present application comprises:

[0043] The UAV launching device comprises a launching track 01, an elastic member 02, a track slider 03, a support 04, a support frame 05 and a launching release mechanism. The launching track 01 is provided with a release end and a launching end, and the support 04 is arranged on the launching end. The track slider 03 is arranged in the launching track 01 and is movable in the launching track 01. The support frame 05 is connected with the track slider 03 and is used to support and hook the UAV 06. The launching release mechanism is arranged at the release end. One end of the elastic member 02 is connected with the launching end, and the other end is connected with the track slider 03. The elastic member 02 cooperates with the launching release mechanism to push the track slider 03 from the release end to the launching end.

[0044] The launching track 01 provides a moving path for the track slider 03 and determines the moving direction and distance of the track slider 03. The launching track 01 is provided with a release end and a launching end. The release end is the starting position of the track slider 03, and the launching end is the terminal position of the track slider 03 (the position where the UAV 06 is launched).

[0045] The track slider 03 is arranged in the launching track 01 and is movable freely in the launching track 01. The track slider 03 is a moving component in the launching device and is connected with the support frame 05 and the elastic member 02. The track slider 03 is responsible for transmitting the energy of the elastic member 02 to the support frame 05 and the UAV 06.

[0046] The elastic member 02 is the power source of the present application and can store energy and push the track slider 03 to move rapidly to the launching end when released. One end of the elastic member 02 is connected with the launching end, and the other end is connected with the track slider 03. When the launching release mechanism unlocks the track slider 03, the elastic member 02 releases the stored energy and pushes the track slider 03 to move rapidly to the launching end along the launching track 01, so that the UAV 06 hooked on the support frame 05 is launched.

[0047] The support 04 is a support structure of the present application, which is arranged on the shooting end of the ejection track 01 and used for supporting and fixing the ejection track 01. The support frame 05 has a certain height to form a height difference between the shooting end and the release end, facilitating the ejection of the unmanned aerial vehicle 06 in the obliquely upward direction.

[0048] The ejection release mechanism is a component for controlling the locking and releasing of the track slider 03. When the track slider 03 moves to the release end, the ejection release mechanism first locks the track slider 03. After the unmanned aerial vehicle 06 is hooked on the support frame 05, the ejection release mechanism is controlled to unlock the track slider 03, so that the elastic member 02 can release energy and push the track slider 03 to move to the shooting end. The unlocking of the ejection release mechanism can be achieved by manual control or by electric control.

[0049] In the present embodiment, the track slider 03 is first moved to the release end by external force and locked by the ejection release mechanism. At this time, the elastic member 02 is in a stretched state and has a restoring force. Then, the unmanned aerial vehicle 06 is placed on the support frame 05 and hooked on the support frame 05. Next, the track slider 03 is released by the ejection release mechanism, so that the track slider 03 quickly moves to the shooting end under the action of the elastic member 02, and the support frame 05 and the unmanned aerial vehicle 06 also quickly move to the shooting end. The track slider 03 and the support frame 05 are limited at the shooting end, and the unmanned aerial vehicle 06 is ejected under the action of inertia.

[0050] In the present embodiment, a more lightweight and flexible design is adopted, which has low manufacturing cost and is convenient for carrying and transporting. Due to the small size and light weight, the device can be quickly deployed and used in various scenes. The structure is simple and the overall structure weight is light, which can reduce the logistics pressure of the unmanned aerial vehicle 06 operation.

[0051] Please continue to refer to Figure 2 With Figure 7 In an optional embodiment, the ejection release mechanism includes a release frame 07, a release servo 08 arranged on the release frame 07, and a self-locking lock 09 connected in the ejection track 01. The self-locking lock 09 is used to lock the track slider 03. The release servo 08 is connected with the self-locking lock 09, and the release servo 08 is used to control the self-locking lock 09 to be unlocked.

[0052] The release frame 07 is made of high-strength and lightweight materials, such as aluminum alloy or carbon fiber composite materials, to reduce the overall weight and improve the structural strength. The shape and size of the release frame 07 are customized according to the specific needs of the ejection device to ensure that the release servo 08 and the self-locking lock 09 can be stably installed and adapt to the layout of the ejection track 01.

[0053] The self-locking lock 09 is responsible for locking the track slider 03 before ejection, preventing accidental movement; during ejection, the self-locking lock is unlocked according to the release of the steering engine 08 control, allowing the track slider 03 to move to the ejection end under the action of the elastic element 02. The self-locking lock 09 can be in the form of a mechanical lock or an electromagnetic lock, in this embodiment, the self-locking lock 09 is connected by bolts in the ejection track 01, the locking part is tightly matched with the track slider 03, ensuring that the track slider 03 cannot move in the locked state. When ejection is needed, the self-locking lock 09 is unlocked by the steering engine to allow the track slider 03 to move freely.

[0054] In this optional embodiment, the release steering engine 08 is provided with a steering engine swing arm 10, which is connected to the unlocking ring on the self-locking lock 09 through a steel wire rope 11. In this embodiment, the release steering engine 08 drives the self-locking lock 09 to perform the unlocking action through the steering engine swing arm 10 and the steel wire rope 11, and the release steering engine 08 can be selected as a high-precision and high-reliability servo motor.

[0055] The steering engine swing arm 10 is connected to the release steering engine 08, which can drive the steering engine swing arm 10 to rotate, and the end of the steering engine swing arm 10 is connected to the unlocking ring on the self-locking lock 09 through the steel wire rope 11. The steering engine swing arm 10 moves the unlocking ring, thereby unlocking the self-locking lock 09.

[0056] In this optional embodiment, the ejection release mechanism also includes a battery and a remote control receiver, the battery is electrically connected with the remote control receiver and the release steering engine 08, and the remote control receiver is electrically connected with the release steering engine 08.

[0057] In this embodiment, the battery provides power for the release steering engine 08 and the remote control receiver, and the remote control receiver is electrically connected with the release steering engine 08, so that the release steering engine 08 can be remotely controlled by an external remote controller to rotate, thereby remotely unlocking the self-locking lock 09, thereby improving safety.

[0058] Please continue to refer to Figure 3 In an optional embodiment, a bumper 14 is provided in the ejection end, facing the track slider 03. In this embodiment, the ejection track 01 is an internal track, the bumper 14 is arranged in the track and located in the ejection end, and the bumper 14 can absorb the impact force generated during the ejection of the track slider 03, thereby protecting the ejection track 01.

[0059] The bumper 14 is made of high-elasticity and high-damping materials, such as rubber or hydraulic bumper 14. The bumper 14 is arranged in the ejection end and faces the track slider 03, and when the track slider 03 carrying the unmanned aerial vehicle 06 slides to the ejection end, the bumper 14 will first contact the track slider 03, thereby playing a buffering role.

[0060] In an alternative embodiment, the number of elastic members 02 is 2, and one elastic member 02 is arranged on each side of the launching track 01. In this embodiment, the elastic members 02 are located outside the launching track 01 and on both sides of the launching track 01 to form a symmetrical structure to launch the track slider 03.

[0061] Please continue to refer to Figure 3 In this alternative embodiment, the elastic member 02 includes a rubber tube 15 and first and second connecting heads 16 and 17 connected to both ends of the rubber tube 15, respectively. The first connecting rod 18 is arranged outside the launching end of the launching track 01, and the second connecting rod 19 is arranged outside the track slider 03. The first connecting head 16 is connected to the first connecting rod 18, and the second connecting head 17 is connected to the second connecting rod 19.

[0062] Outside the launching end of the launching track 01, the first connecting rod 18 is arranged on both sides. The first connecting rod 18 and the launching end can be connected by bolts, buckles, or integrally formed. The specific connection method is not limited here, and the actual implementation is acceptable. The second connecting rod 19 is on the same side as the first connecting rod 18, and the track slider 03 and the second connecting rod 19 are connected by bolts, buckles, or integrally formed.

[0063] One end of the rubber tube 15 is connected to the first connecting head 16, and the other end is connected to the second connecting head 17. The first connecting head 16 is connected to the first connecting rod 18 to achieve the fixed connection between the rubber tube 15 and the launching end. The second connecting head 17 is connected to the second connecting rod 19 to achieve the connection between the rubber tube 15 and the track slider 03. The length of the rubber tube 15 in the natural state (without stretching and shortening) is less than the length of the launching track 01. Therefore, when the self-locking lock 09 locks the track slider 03, the rubber tube 15 is in a stretched state, and there is a restoring force to restore it to its original state. This restoring force is used to move the track slider 03 to the launching end when the self-locking lock 09 is unlocked.

[0064] To facilitate the disassembly and replacement of the rubber tube 15, the first connecting head 16 and the second connecting head 17 can be provided as hooks.

[0065] In an alternative embodiment, the track slider 03 includes a frame 20, a pulley 21, and a slider body 22. The slider body 22 is fixed in the frame 20, and the pulley 21 is arranged on both sides of the slider body 22. The pulley 21 is used to abut the inner wall of the launching track 01.

[0066] Please continue to refer to Figure 4 、 Figures 6-8In the embodiment, the frame 20 is sleeved outside the ejection track 01, the second connecting rod 19 is connected to the two sides of the frame 20, a through slot is arranged on the upper surface of the ejection track 01, the frame 20 is fixedly connected with the slider body 22 inside the ejection track 01 through the through slot, and the frame 20 and the slider body 22 are integrated. The pulley 21 is arranged on the two sides of the slider body 22, the pulley 21 abuts against the inside of the ejection track 01, and the pulley 21 can reduce the friction between the slider body 22 and the ejection track 01 and reduce the loss of elastic force.

[0067] The slider body 22 is provided with a locking rod at one end close to the self-locking lock 09, when the slider body 22 hits the self-locking lock 09, the self-locking lock 09 locks the locking rod, so that the slider state is fixed in the release end.

[0068] Please continue to refer to Figure 6 In an optional embodiment, the support frame 05 includes a support body 23, a support rod 24 and a cross rod 25, the support body 23 is connected with the track slider 03, the support rod 24 is arranged at the two ends of the support body 23 respectively, the cross rod 25 is arranged on the support body 23, and the support rod 24 is perpendicular to the ejection track 01, and the cross rod 25 is used for abutting against the hook at the bottom of the unmanned aerial vehicle 06.

[0069] The support body 23 is connected with the frame 20 in the track slider 03, and the two are connected by bolts, buckles or the like. The two ends of the support body 23 extend upward, and each end is connected with a support rod 24, the support rods 24 at the two ends are arranged at the same height, and the support rods 24 at the two ends are used for supporting the lower surface of the unmanned aerial vehicle 06.

[0070] The cross rod 25 is connected to the support body 23, the cross rod 25 is arranged perpendicularly to the ejection track 01, a hook is arranged on the lower surface of the unmanned aerial vehicle 06, the hook can be hooked on the cross rod 25, when the cross rod 25 moves in the direction of the ejection end along with the track slider 03 during ejection, the hook and the unmanned aerial vehicle 06 also move in the direction of the ejection end, and when the track slider 03 hits the buffer 14, the unmanned aerial vehicle 06 flies out due to inertia.

[0071] In an optional embodiment, the support frame 04 includes a first support leg 26 and a second support leg 27, and the angle between the first support leg 26 and the second support leg 27 ranges from 30 degrees to 120 degrees. In the embodiment, the support frame 04 is connected with the ejection track 01 in a detachable manner, the support legs can be detached during transportation, so that the volume is further reduced and portability is improved. The angle between the first support leg 26 and the second support leg 27 can be fixed or adjustable, so as to adapt to the launch height of unmanned aerial vehicles of different specifications.

[0072] It is to be understood that the embodiments that have been described are merely illustrative of the principles of the application. Numerous modifications can be made to the application and alternative embodiments can be implemented by those skilled in the art without departing from the scope of the application. No limitation is intended by the description set forth in this patent other than that which is provided by the appended claims.

Claims

1. An unmanned aerial vehicle catapult apparatus, characterized by, The application relates to a launching track, an elastic member, a track slider, a support, a supporting frame and a launching release mechanism. The launching track is provided with a release end and a launching end, and the support is arranged on the launching end. The track slider is arranged in the launching track and is movable in the launching track, the supporting frame is connected with the track slider, and the supporting frame is used for supporting and hooking a UAV. The launching release mechanism is arranged on the release end, one end of the elastic member is connected with the launching end, the other end is connected with the track slider, and the elastic member cooperates with the launching release mechanism to launch the track slider from the release end to the launching end. The launching release mechanism comprises a release frame, a release steering engine arranged on the release frame and a self-locking lock.

2. The UAV catapult apparatus of claim 1, wherein, The self-locking lock is connected in the launching track and is used for locking the track slider. The release steering engine is connected with the self-locking lock and is used for controlling the self-locking lock to be unlocked.

3. The UAV catapult apparatus of claim 2, wherein, The release steering engine is provided with a steering engine swing arm connected with an unlocking ring on the self-locking lock through a steel wire rope.

4. The UAV catapult apparatus of claim 2 or 3, wherein, The launching release mechanism further comprises a storage battery and a remote control receiver.

5. The UAV catapult apparatus of any one of claims 1 to 3, wherein, The storage battery is electrically connected with the remote control receiver and the release steering engine.

6. The UAV catapult apparatus of any one of claims 1 to 3, wherein, The launching end is provided with a buffer towards the track slider.

7. The UAV catapult apparatus of claim 6, wherein, The number of the elastic members is two, and one elastic member is arranged on each side of the launching track. The elastic member comprises a rubber tube and first and second connecting heads connected on two ends of the rubber tube.

8. The UAV catapult apparatus of any one of claims 1-3, wherein, The launching end is provided with a first connecting rod, the track slider is provided with a second connecting rod, the first connecting head is connected with the first connecting rod, and the second connecting head is connected with the second connecting rod.

9. The UAV catapult apparatus of any one of claims 1-3, wherein, The track slider comprises a frame, a pulley and a slider body, the slider body is fixed in the frame, the pulley is arranged on both sides of the slider body, and the pulley is used for abutting against the inner wall of the launching track.

10. The UAV catapult apparatus of any one of claims 1-3, wherein, The supporting frame comprises a supporting body, supporting rods and a cross rod, the supporting body is connected with the track slider, the supporting rods are arranged on both ends of the supporting body, the cross rod is arranged on the supporting body, the supporting rods are perpendicular to the launching track, and the cross rod is used for abutting against a hook on the bottom of the UAV. The support comprises first and second supporting legs, and the angle between the first and second supporting legs ranges from 30 degrees to 120 degrees.

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