Unmanned aerial vehicle ejection device
By combining the design of built-in elastic components and track components, the problem of the difficulty in deploying traditional UAV catapults in complex terrain is solved, enabling UAVs to be deployed flexibly and take off efficiently in complex terrain.
Patent Information
- Application Number
- CN202520822541.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-27
- Publication Date
- 2026-02-24
- Estimated Expiration
- 2035-04-27
AI Technical Summary
Existing catapult launch technology for small fixed-wing UAVs relies on external anchor points, which makes deployment in complex terrain difficult, costly, and inflexible, limiting their application in complex scenarios.
By employing a collaborative design of built-in elastic components and track assemblies, the power is provided through the energy storage and release of the elastic components, enabling the drone to take off quickly and eliminating the reliance on external anchor points.
It enables flexible deployment in complex terrains. The drone catapult device can quickly and stably adapt to various scenarios, reducing deployment difficulty and cost, and improving operational efficiency.
Smart Images
Figure CN223934995U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a UAV catapult device. Background Technology
[0002] With the rapid development of drone technology, small fixed-wing drones, with their unique advantages, have shown extremely broad application prospects in many fields such as environmental monitoring and disaster relief. Catapult takeoff, as an efficient and convenient takeoff method, has significant advantages for small fixed-wing drones. It enables rapid takeoff in limited space, greatly improving mission execution efficiency and providing strong support for the application of drones in various complex scenarios.
[0003] However, current catapult launch technology for small fixed-wing UAVs generally employs a power release mode combining a single catapult frame with external anchor points. This traditional catapult device mainly consists of a single guide rail, and its power release mechanism relies on external anchor points located far from the catapult frame to secure the catapult power components. In actual operation, this mode has revealed numerous problems. The deployment of external anchor points requires a large amount of planar space and places extremely stringent requirements on ground conditions. In complex terrain (such as mountains and hills) or limited spaces (such as narrow urban streets and ship decks), the deployment of external anchor points faces significant challenges and is difficult to complete quickly and effectively. This not only limits the applicability of the catapult launch system but also reduces its deployment flexibility, restricting the application of UAVs in certain special scenarios. Utility Model Content
[0004] This application provides a drone ejection device, which solves the problems mentioned in the background art.
[0005] This application provides a drone ejection device, including:
[0006] The catapult includes a support base, at least two support rods spaced apart along the width direction of the support base, and at least one crossbeam spaced apart along the height direction of the support rods; wherein the two ends of the crossbeam are connected to the two support rods.
[0007] At least one set of track components is inclined at a preset elevation angle toward the launch direction of the UAV on the two support rods, and each set of track components includes at least two parallel guide rails for placing the UAV;
[0008] At least one elastic element has its two ends connected to the side of the corresponding two guide rails away from the support rod, and its middle part forms a traction section for hooking the hook on the belly of the UAV;
[0009] At least one actuator is mounted on top of the corresponding crossbeam; and
[0010] At least one locking element, one end of which is connected to a hanging ring on the belly of the drone, and the other end of which is detachably connected to the output end of the corresponding actuator, for locking the drone to the guide rail;
[0011] When the drone is launched, the traction section of the elastic element is stretched and stores energy after being hooked onto the hook on the belly of the drone. The actuator releases the constraint on the locking element, allowing the drone to break free of the lock and take off along the guide rail.
[0012] In one possible implementation, the drone launch device further includes at least one release mechanism; the release mechanism is mounted on the bottom of the corresponding crossbeam and connected to the output end of the corresponding actuator; the end of the locking member away from the drone launch direction is detachably connected to the release mechanism.
[0013] In one possible implementation, the release mechanism includes a pin and a frame; the frame is disposed at the bottom of the corresponding crossbeam, and a guide hole is provided at its center; the pin is slidably disposed in the guide hole, and one end of it is hinged to the output end of the actuator, and realizes linear reciprocating motion under the drive of the actuator; when the UAV is not ejected, the end of the locking member away from the launch direction of the UAV is sleeved on the outer wall of the pin and located within the frame.
[0014] In one possible implementation, the actuator includes a servo motor and a magnetic control interface mounted on the tail of the UAV; the servo motor is mounted on the top of the corresponding crossbeam; the magnetic control interface is electrically connected to the servo motor to receive control signals and control the servo motor's movement; when the servo motor rocker arm is in the zero position, the pin is inserted into the guide hole to lock; when the magnetic control interface is powered, the servo motor drives the rocker arm to rotate, causing the pin to make a linear displacement and completely exit the guide hole, thus separating the locking element from the pin.
[0015] In one possible implementation, the track assembly is provided in multiple sets, and the multiple sets of track assemblies are spaced apart along the height direction of the support rod.
[0016] In one possible implementation, the drone launch device further includes a plurality of ground spikes; one end of each of the plurality of ground spikes is detachably connected to the bottom of the support base, and the other end of each spike is screwed into the ground to fix the launch frame.
[0017] In one possible implementation, the drone launch device further includes a plurality of casters; all of the casters are disposed circumferentially at the bottom of the support base.
[0018] In one possible implementation, the drone launch device further includes a plurality of rigid members; the plurality of rigid members are disposed on the traction section of the corresponding elastic member.
[0019] In one possible implementation, the UAV ejection device further includes multiple diagonal bracing reinforcing ribs; the two ends of the multiple diagonal bracing reinforcing ribs are respectively connected to the support rod and the corresponding guide rail on the side away from the support rod.
[0020] In one possible implementation, the drone launch device further includes multiple rubber band hooks; the multiple rubber band hooks are respectively disposed on the side of the corresponding guide rail away from the support rod; the two ends of the elastic element are respectively connected to the corresponding rubber band hooks.
[0021] One or more technical solutions provided in the embodiments of this application have at least the following technical effects:
[0022] The UAV catapult device provided in this application includes a catapult frame, at least one set of track components, at least one elastic element, at least one actuator, and at least one locking element. Its working principle is as follows: The UAV is placed on the track components and fixed to the locking element via a hanging ring on the UAV's belly. At this time, the traction section of the elastic element is hooked onto the hook on the UAV's belly and is in a pre-stretched state. When the UAV needs to be launched, the actuator receives the launch command and begins to work, releasing the constraint on the locking element and separating it from the UAV. Due to the instantaneous release of the elastic potential energy stored in the elastic element, a strong pulling force is generated. This pulling force acts on the UAV through the hook on the UAV's belly, propelling the UAV to accelerate rapidly along the guide rail, ultimately causing the UAV to detach from the guide rail and take off, entering flight mode. Traditional UAV catapult devices rely on external anchor points to fix the launch power components. In complex terrains such as mountains and hills, anchor point deployment is difficult, costly, and easily affected by terrain undulations. This device, through the collaborative design of the built-in elastic element and track components, eliminates the need for external anchor points, flexibly adapts to complex terrain, and reduces deployment difficulty. Attached Figure Description
[0023] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0024] Figure 1 This is a schematic diagram of the structure of the UAV catapult device provided in the embodiments of this application;
[0025] Figure 2 This is a front view of the UAV catapult device provided in an embodiment of this application;
[0026] Figure 3 Left view of the UAV catapult device provided in the embodiment of this application;
[0027] Figure 4 for Figure 1 Enlarged view of point A in the image;
[0028] Figure 5 for Figure 2 Enlarged view of point B in the image;
[0029] Figure 6 This is a top view of the drone catapult device provided in an embodiment of this application.
[0030] Figure 7 for Figure 1 Enlarged view of point C in the image.
[0031] Icons: 1-Ejection rack; 11-Support base; 12-Support rod; 13-Crossbeam; 2-Rail assembly; 21-Guide rail; 3-Actuator; 31-Servo motor; 4-Release mechanism; 41-Pin; 42-Frame; 5-Universal wheel; 6-Diagonal brace reinforcing rib; 7-Rubber band hook; 8-Hook on the belly of the drone; 9-Hanging ring on the belly of the drone. Detailed Implementation
[0032] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0033] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.
[0034] This application provides a drone catapult device, such as... Figures 1 to 7 As shown. The drone ejection device includes an ejection frame 1, at least one set of track assemblies 2, at least one elastic element, at least one actuator 3, and at least one locking element. The ejection frame 1 includes a support base 11, at least two support rods 12 spaced apart along the width direction of the support base 11, and at least one crossbeam 13 spaced apart along the height direction of the support rods 12. The two ends of the crossbeam 13 are connected to the two support rods 12. At least one set of track assemblies 2 is inclined at a preset elevation angle toward the drone launch direction on the two support rods 12. Each set of track assemblies 2 includes at least two parallel guide rails 21 for placing the drone. The two ends of at least one elastic element are connected to the side of the corresponding two guide rails 21 away from the support rods 12, and the middle forms a traction section for hooking the drone's underside with a hook 8. At least one actuator 3 is mounted on the top of the corresponding crossbeam 13. One end of at least one locking element is connected to a hanging ring 9 on the drone's underside, and the other end is detachably connected to the output end of the corresponding actuator 3, for locking the drone to the guide rail 21. When launching the drone, the traction section of the elastic element is attached to the hook 8 on the belly of the drone and is stretched to store energy. The actuator 3 releases the constraint on the locking element, allowing the drone to break free from the lock and take off along the guide rail 21.
[0035] In one embodiment of this application, the tensile force of the elastic element is 21 kg.
[0036] It should be noted that the working principle of the drone ejection device is as follows: The drone is placed on the track assembly 2 and fixed to the locking component via the hanging ring 9 on the drone's belly. At this time, the traction section of the elastic component is already hooked onto the hook 8 on the drone's belly and is in a pre-stretched state. When the drone needs to be ejected, the actuator 3 receives the ejection command and starts working, releasing the constraint on the locking component and separating it from the drone. Due to the instantaneous release of the elastic potential energy stored in the elastic component, a strong pulling force is generated. This pulling force acts on the drone through the hook 8 on the drone's belly, propelling the drone to accelerate rapidly along the guide rail 21, ultimately causing the drone to detach from the guide rail 21 and take off, entering flight mode. Traditional drone ejection devices rely on external anchor points to fix the ejection power components. In complex terrains such as mountains and hills, the deployment of anchor points is difficult and costly, and the stability is easily affected by terrain undulations. This device, through the collaborative design of the built-in elastic component and the track assembly 2, eliminates the need for external anchor points, can flexibly adapt to complex terrains, and reduces deployment difficulty.
[0037] In this embodiment, the drone launch device further includes at least one release mechanism 4. The release mechanism 4 is mounted on the bottom of the corresponding crossbeam 13 and connected to the output end of the corresponding actuator 3. The end of the locking member away from the drone launch direction is detachably connected to the release mechanism 4.
[0038] In this embodiment, the release mechanism 4 includes a pin 41 and a frame 42. The frame 42 is disposed at the bottom of the corresponding crossbeam 13, and has a guide hole at its center. The pin 41 is slidably disposed in the guide hole, and one end is hinged to the output end of the actuator 3, achieving linear reciprocating motion under the drive of the actuator 3. When the drone is not ejected, the end of the locking member away from the drone's launch direction is sleeved on the outer wall of the pin 41 and located within the frame 42.
[0039] It should be noted that the actuator 3 drives the pin 41 to achieve linear reciprocating motion. When the drone needs to be ejected, the actuator 3 moves the pin 41, causing the locking element to disengage from the pin 41, thus completing the release action. This mechanical release method has a simple structure and reliable operation, ensuring accurate and timely release of the drone in various environments and ensuring the smooth execution of the ejection mission. This application provides a stable and precise locking position for the drone by fitting the end of the locking element away from the drone's launch direction onto the outer wall of the pin 41 and placing it within the frame 42. The linear sliding design of the pin 41 within the guide hole ensures the consistency and accuracy of the locking position, avoiding locking failure due to positional deviation or drone wobbling before ejection, thus improving the stability of the drone before ejection.
[0040] In this embodiment, the actuator 3 includes a servo motor 31 and a magnetic control interface mounted on the tail of the UAV. The servo motor 31 is mounted on the top of the corresponding crossbeam 13. The magnetic control interface is electrically connected to the servo motor 31 and is used to receive control signals and control the movement of the servo motor 31. When the rocker arm of the servo motor 31 is in the zero position, the pin 41 is inserted into the guide hole to lock. When the magnetic control interface is powered, the servo motor 31 drives the rocker arm to rotate, causing the pin 41 to make a linear displacement and completely exit the guide hole, thus separating the locking element from the pin 41.
[0041] It should be noted that in one embodiment of this application, the servo motor 31 is a 10kg-class servo motor. The actuator 3 of this application greatly saves manpower and catapult takeoff time. Using the actuator 3, the UAV can be triggered to take off at a very small time interval through the flight control.
[0042] In this embodiment, multiple sets of track assemblies 2 are provided, and these multiple sets of track assemblies 2 are spaced apart along the height direction of the support rod 12. Specifically, five sets of track assemblies 2 are provided in this application.
[0043] It should be noted that, from a functional perspective, traditional catapults 1 are mostly single-drone catapults, with excessively large spacing between the catapult elastic band anchor points. This not only occupies a significant amount of space but also requires manual release of the drones, making it difficult to meet the needs of large-scale takeoffs of swarm drones. In contrast, the multi-layer track assembly 2 design of this application not only meets the actual needs of swarm drone catapult takeoffs but also allows for the deployment of a larger number of drones under the same site conditions. Once the personnel have completed the drone deployment, the device can automatically activate and take off, greatly improving operational convenience and efficiency.
[0044] From a technological perspective, the device's innovation lies in several aspects. First, the multi-layered track assembly 2 structure optimizes site space utilization, increasing the utilization rate of catapult launch sites for large-scale swarm drone launches, enabling limited space to accommodate more launch missions. Second, the autonomous release takeoff function completely eliminates the constraints of manual release, saving significant labor costs and avoiding operational delays and errors caused by human factors. Third, the overall design improves production efficiency, providing strong support for the large-scale application of swarm drones.
[0045] In this embodiment, the drone launch device also includes multiple ground spikes. One end of each ground spike is detachably connected to the bottom of the support base 11, and the other end is screwed into the ground to fix the launch frame 1.
[0046] In this embodiment, the drone launch device also includes multiple casters 5. All casters 5 are circumferentially located at the bottom of the support base 11. When the launch site needs to be changed, the convenient mobility of the casters 5 allows the drone launch device to be quickly and easily moved to a new location, shortening transportation time, improving transportation efficiency, and enabling the device to be deployed to new launch missions more quickly.
[0047] In this embodiment, the drone launch device further includes multiple rigid components. These rigid components are disposed on the traction section of a corresponding elastic component. The rigid components of this application can improve the service life of the elastic component.
[0048] In this embodiment, the UAV ejection device further includes multiple diagonal reinforcing ribs 6. The two ends of the multiple diagonal reinforcing ribs 6 are respectively connected to the support rod 12 and the corresponding guide rail 21 on the side away from the support rod 12, forming a stable triangular structure.
[0049] In this embodiment, the drone launch device further includes multiple rubber band hooks 7. The multiple rubber band hooks 7 are respectively disposed on the side of the corresponding guide rail 21 away from the support rod 12. Both ends of the elastic element are respectively connected to the corresponding rubber band hook 7.
[0050] It should be noted that the two ends of the elastic element in this application can be tied to the corresponding rubber band hook 7.
[0051] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.
[0052] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.
Claims
1. A catapult launcher for unmanned aerial vehicles (UAVs), characterized in that, include: The ejection frame (1) includes a support base (11), at least two support rods (12) spaced apart along the width direction of the support base (11), and at least one crossbeam (13) spaced apart along the height direction of the support rods (12); wherein the two ends of the crossbeam (13) are connected to the two support rods (12); At least one set of track components (2) are inclined at a preset elevation angle toward the launch direction of the UAV on the two support rods (12). Each set of track components (2) includes at least two parallel guide rails (21) for placing the UAV. At least one elastic element has its two ends connected to the side of the corresponding two guide rails (21) away from the support rod (12), and its middle part forms a traction section for attaching the hook (8) to the belly of the UAV; At least one actuator (3) is mounted on top of the corresponding crossbeam (13); and At least one locking element, one end of which is connected to the hanging ring (9) on the belly of the UAV, and the other end of which is detachably connected to the output end of the corresponding actuator (3), for locking the UAV to the guide rail (21); When the UAV is launched, the traction section of the elastic element is attached to the hook (8) on the belly of the UAV and is stretched to store energy. The actuator (3) releases the constraint on the locking element, so that the UAV is released from the lock and takes off along the guide rail (21).
2. The UAV ejection device according to claim 1, characterized in that, It also includes at least one release mechanism (4); The release mechanism (4) is installed at the bottom of the corresponding crossbeam (13) and connected to the output end of the corresponding actuator (3); The end of the locking member away from the launch direction of the UAV is detachably connected to the release mechanism (4).
3. The UAV ejection device according to claim 2, characterized in that, The release mechanism (4) includes a pin (41) and a frame (42); The frame (42) is disposed at the bottom of the corresponding crossbeam (13), and a guide hole is provided at its center; The pin (41) is slidably disposed in the guide hole, and one end of it is hinged to the output end of the actuator (3), and realizes linear reciprocating motion under the drive of the actuator (3); When the drone is not ejected, the end of the locking member away from the launch direction of the drone is fitted onto the outer wall of the pin (41) and located inside the frame (42).
4. The UAV ejection device according to claim 3, characterized in that, The actuator (3) includes a servo motor (31) and a magnetic control interface installed at the tail of the UAV; The servo motor (31) is mounted on the top of the corresponding crossbeam (13); The magnetic control interface is electrically connected to the servo motor (31) and is used to receive control signals and control the movement of the servo motor (31). When the rocker arm of the servo motor (31) is in the zero position, the pin (41) is inserted into the guide hole to lock; when the magnetic control interface is powered, the servo motor (31) drives the rocker arm to rotate, causing the pin (41) to make a linear displacement and completely exit the guide hole, so that the locking member is separated from the pin (41).
5. The UAV ejection device according to claim 1, characterized in that, The track assembly (2) is provided in multiple sets, and the multiple sets of track assemblies (2) are spaced apart along the height direction of the support rod (12).
6. The UAV catapult device according to claim 1, characterized in that, It also includes multiple ground stakes; One end of each of the multiple ground spikes can be detachably connected to the bottom of the support base (11), and the other end of each spike is screwed into the ground to fix the catapult (1).
7. The UAV catapult device according to claim 1, characterized in that, It also includes multiple casters (5); Multiple casters (5) are disposed circumferentially at the bottom of the support base (11).
8. The UAV catapult device according to claim 1, characterized in that, It also includes several rigid components; Multiple rigid members are disposed on the traction section of the corresponding elastic member.
9. The UAV catapult device according to claim 1, characterized in that, It also includes multiple diagonal bracing ribs (6); The two ends of the plurality of diagonal bracing reinforcing ribs (6) are respectively connected to the support rod (12) and the corresponding guide rail (21) on the side away from the support rod (12).
10. The UAV catapult device according to claim 1, characterized in that, It also includes multiple rubber band hooks (7); Multiple rubber band hooks (7) are respectively disposed on the side of the corresponding guide rail (21) away from the support rod (12); Both ends of the elastic element are respectively connected to the corresponding rubber band hooks (7).