A fixed-wing drone catapult

Abstract

The application relates to the technical field of unmanned aerial vehicles, in particular to a fixed-wing unmanned aerial vehicle ejector. The ejector comprises a first fixing base, a second fixing base, a slide rail and a load slide carriage; the second fixing base is arranged at intervals from the first fixing base, and the second fixing base is provided with a first lock catch assembly; the slide rail is connected with the first fixing base and the second fixing base at two ends respectively; the load slide carriage is in sliding cooperation with the slide rail, the load slide carriage is provided with a second lock catch assembly, the second lock catch assembly is connected with the first fixing base and the second fixing base through first elastic elements and second elastic elements respectively, and the load slide carriage is used for placing an unmanned aerial vehicle; wherein the load slide carriage can be locked with the second lock catch assembly, the first elastic elements can enable the unmanned aerial vehicle to be limited by the second lock catch assembly, and the second elastic elements can elastically release the limitation of the second lock catch assembly on the unmanned aerial vehicle. The application can realize stable ejection of the unmanned aerial vehicle and can be suitable for unmanned aerial vehicles of various models.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a catapult for a fixed-wing UAV. Background Technology

[0002] A drone catapult is a device that replaces hand-launching or runway takeoff, specifically designed for the rapid and reliable launch of drones in confined spaces or under specific conditions.

[0003] A drone catapult typically includes a launch track, a slider, an energy storage device, an energy release and drive mechanism, a control system, and a support structure. The drone is carried by the slider and gains a large initial velocity under its influence. Before the drone is launched, the slider needs to be fixed. During launch, the energy release and drive mechanism drives the slider to slide rapidly on the launch track, thus giving the drone a large initial velocity. When the slider reaches its endpoint, it needs to be braked and the drone unlocked to release it. Usually, a fork and impact braking structure are set on the slider. However, the timing of the drone unlocking and braking processes is difficult to control. For example, early unlocking and late braking, or early braking and late unlocking, may prevent the drone from gaining the expected initial velocity. Utility Model Content

[0004] This application aims to solve at least one of the technical problems mentioned in the background art by providing a catapult for a fixed-wing unmanned aerial vehicle.

[0005] This application is achieved through the following technical solution:

[0006] A catapult for a fixed-wing unmanned aerial vehicle, comprising:

[0007] First fixed seat;

[0008] The second fixing seat is arranged at a distance from the first fixing seat, and the second fixing seat is provided with a first locking assembly;

[0009] A slide rail, the two ends of which are respectively connected to the first fixed base and the second fixed base;

[0010] A load carriage is provided, which slides in conjunction with the slide rail. A second locking assembly is provided on the load carriage. The second locking assembly is connected to the first fixed seat and the second fixed seat through a first elastic member and a second elastic member, respectively. The load carriage is used to place a drone.

[0011] Specifically, when the load carriage approaches the second fixed base, it can lock with the second locking assembly to fix the load carriage relative to the second fixed base, and the first elastic member acts elastically on the second locking assembly to limit the drone by the second locking assembly; when the load carriage approaches the first fixed base, the second elastic member acts elastically on the second locking assembly to release the second locking assembly from limiting the drone.

[0012] In some alternative embodiments, the slide rail is configured as a slide bar, and the number of slide rails is configured to be no less than three, wherein the slide rails move through the load carriage.

[0013] In some alternative embodiments, the first fixing seat and / or the second fixing seat are provided with anti-slip shovels.

[0014] In some alternative embodiments, the first elastic element and / or the second elastic element are configured as elastic cords.

[0015] In some alternative embodiments, the first locking assembly includes:

[0016] Connecting seat, the connecting seat being connected to the second fixed seat;

[0017] The buckle is rotatably connected to the connecting seat, wherein an elastic element is disposed between one end of the buckle and the connecting seat, and the other end of the buckle is configured as a hook-shaped structure, and a hook groove adapted to the hook-shaped structure is provided on the load carriage;

[0018] An unlocking component is movably connected to the connecting seat, wherein when the unlocking component is movable relative to the connecting seat, it can contact the buckle and overcome the elastic force of the elastic element to drive the buckle to rotate.

[0019] In some alternative embodiments, the unlocking element is configured as a cam, which is rotatably connected to the connecting seat.

[0020] In some alternative embodiments, the elastic element is configured as a spring sheet.

[0021] In some optional embodiments, the second locking assembly includes:

[0022] A support base, which is connected to the load carriage, is used to support the wings of the UAV;

[0023] The first limiting member is connected to the bearing seat;

[0024] Mounting base, the mounting base being connected to the support base;

[0025] The second limiting member is rotatably connected to the mounting base. One end of the second limiting member forms an engagement gap with the first limiting member, and the other end of the second limiting member is connected to the first elastic member and the second elastic member.

[0026] In some alternative embodiments, the second limiting member is slidably connected to the mounting base.

[0027] In some alternative embodiments, the support base is movably connected to the load carriage.

[0028] Compared with the prior art, this application has the following advantages and beneficial effects:

[0029] The fixed-wing UAV catapult provided in this application achieves a mechanical linkage where the load carriage slides out and unlocks immediately by arranging a slide rail and a load carriage between a first fixed seat and a second fixed seat, and by setting a second locking assembly driven by dual elastic elements (i.e., a first elastic element and a second elastic element) on the load carriage: the load carriage is initially located on one side of the second fixed seat, and is fixed by the first locking assembly. The first elastic element is stretched and elastically deformed to store launch energy, while the second locking assembly locks the UAV under the elastic force of the first elastic element; the first locking assembly releases the load carriage... The load carriage slides towards the first fixed seat under the elastic force of the first elastic member. The second elastic member is gradually stretched, and the first elastic member gradually contracts. Just before the load carriage reaches the end point, the elastic force generated by the elastic deformation of the second elastic member drives the second locking assembly to release the constraint on the drone. At the same time, the load carriage can be pulled back to decelerate without the need for an additional damper. This precisely couples the unlocking and braking processes, avoiding early unlocking, late braking, or opposite failures, ensuring that the drone can smoothly derail at the predetermined position and speed. This simplifies the structure and reduces costs and operational complexity. Attached Figure Description

[0030] The accompanying drawings, which are included to provide a further understanding of the embodiments of this application and form part of this application, do not constitute a limitation on the embodiments of this application. In the drawings:

[0031] Figure 1 This is a schematic diagram of a fixed-wing UAV catapult structure provided in an embodiment of this application;

[0032] Figure 2 This is a side view of the fixed-wing UAV catapult structure provided in an embodiment of this application;

[0033] Figure 3 This is a schematic diagram of the structure of the first locking assembly provided in an embodiment of this application;

[0034] Figure 4 This is a schematic diagram of the structure of the second locking assembly provided in an embodiment of this application.

[0035] The attached diagram shows the markings and corresponding component names:

[0036] 1-First fixed seat, 2-Second fixed seat, 3-First locking assembly, 31-Connecting seat, 32-Snap fastener, 33-Unlocking component, 34-Elastic component, 4-Slide rail, 5-Load-bearing slide, 6-Second locking assembly, 61-Bearing seat, 62-First limiting component, 63-Mounting seat, 64-Second limiting component, 7-First elastic component, 8-Second elastic component, 9-Anti-slip shovel. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the embodiments and accompanying drawings. The illustrative embodiments and descriptions of this application are only for explaining this application and are not intended to limit this application.

[0038] like Figures 1-2 As shown in the figure, this application provides a fixed-wing UAV catapult, which includes a first fixed base 1, a second fixed base 2, a slide rail 4, and a load carriage 5. The second fixed base 2 is arranged at intervals from the first fixed base 1, and a first locking assembly 3 is provided on the second fixed base 2. The two ends of the slide rail 4 are respectively connected to the first fixed base 1 and the second fixed base 2. The load carriage 5 is slidably engaged with the slide rail 4, and a second locking assembly 6 is provided on the load carriage 5. The second locking assembly 6 is connected to the first fixed base 1 and the second fixed base 2 through a first elastic member 7 and a second elastic member 8. The load carriage 5 is used to place the UAV. When the load carriage 5 is close to the second fixed base 2, it can lock with the second locking assembly 6 to fix the load carriage 5 to the second fixed base 2, and the first elastic member 7 elastically acts on the second locking assembly 6 to limit the UAV by the second locking assembly 6. When the load carriage 5 is close to the first fixed base 1, the second elastic member 8 elastically acts on the second locking assembly 6 to release the second locking assembly 6 from limiting the UAV.

[0039] In use, the drone is placed on the load carriage 5, and the load carriage 5 is pulled to bring it closer to the second fixed seat 2. The second elastic member 8 undergoes elastic deformation. Under the elastic force of the second elastic member 8, the second locking assembly 6 limits the fixed wings of the drone, and the drone and the load carriage 5 are relatively fixed. After the load carriage 5 is pulled to the initial position, the first locking assembly 3 on the second fixed seat 2 forms a sliding limit on the load carriage 5. At this time, the pulling force of the second elastic member 8 on the load carriage 5 reaches its maximum value. The sliding limit of the load carriage 5 by the first locking assembly 3 is released, and the load carriage 5 slides rapidly under the pulling force of the second elastic member 8. At this time, the drone also gains initial speed. As the load carriage 5 approaches the first fixed seat... 1. The elastic deformation of the second elastic member 8 decreases, while the first elastic member 7 is pulled by the load slide 5 and undergoes elastic deformation. When the elastic force of the first elastic member 7 is greater than the elastic force of the second elastic member 8, the first elastic member 7 will act on the second locking assembly 6 to release the restriction of the fixed wing of the drone by the second locking assembly 6, and the drone can be separated from the load slide 5. At the same time, the second locking assembly 6 can no longer be pulled in the unlocked state. At this time, the second elastic member 8 will pull the entire load slide 5, thereby achieving the braking of the load slide 5.

[0040] In some alternative embodiments, the slide rail 4 is configured as a slide bar, and the number of slide rails 4 is configured to be no less than three, wherein the slide rail 4 moves through the load carriage 5.

[0041] In this embodiment, the slide rail 4 is specifically defined as three or more slide rods, which can form multi-point, multi-directional constraints in a compact space. This improves the straightness and torsional stiffness of the load carriage 5 during movement, preventing swaying or jamming during high-speed ejection. Simultaneously, the multi-rod load-sharing structure disperses the impact force, reducing wear and deformation of individual slide rods, thus improving repeatability and extending the overall service life of the machine. In actual implementation, linear bearings can be configured between the load carriage 5 and the slide rods to achieve a tight fit, preventing the load carriage 5 from wobbling slightly on the slide rods.

[0042] In some optional embodiments, an anti-slip shovel 9 is provided on the first fixing seat 1 and / or the second fixing seat 2.

[0043] In this embodiment, the anti-slip shovel 9 facilitates the fixing of the first fixed seat 1 and the second fixed seat 2. The anti-slip shovel 9 is inserted into the soil to form a stable anchor point, which can prevent the entire device from tilting or leaning backward during the ejection process.

[0044] In some alternative embodiments, the first elastic element 7 and / or the second elastic element 8 are configured as elastic cords.

[0045] In this embodiment, the elastic cord is lightweight, has a large elongation, uniform rebound, and a built-in cushioning effect. This not only reduces the weight of the entire device but also provides a continuous and stable elasticity curve during launch and return, reducing instantaneous impact. At the same time, the elastic cord can be quickly disassembled, replaced, and its pretension adjusted, making it highly convenient to use.

[0046] In some alternative embodiments, see [reference]. Figure 3 The first locking assembly 3 includes a connecting seat 31, a buckle 32, and an unlocking element 33. The connecting seat 31 is connected to the second fixed seat 2, and the connecting seat 31 and the second fixed seat 2 can be connected by bolts for easy maintenance. The buckle 32 has a certain length, and the middle part of the buckle 32 can be rotatably connected to the connecting seat 31 by a pin. One end of the buckle 32 is provided with an elastic element 34 between it and the connecting seat 31, and the other end of the buckle 32 is set with a hook-shaped structure. The load carriage 5 has a hook groove adapted to the hook-shaped structure, that is, the hook-shaped structure can hook into the hook groove. The load carriage 5 and the second fixed seat 2 can be relatively fixed, and the elastic force of the elastic element 34 makes the buckle 32 have a rotation tendency, which can ensure that the hook structure is always in the hook groove; the unlocking element 33 is movably connected to the connecting seat 31. When the unlocking element 33 moves relative to the connecting seat 31, it can contact the buckle 32 and overcome the elastic force of the elastic element 34 to drive the buckle 32 to rotate. During the rotation, the hook structure and the groove are disengaged. The load carriage 5 slides on the slide rail 4 under the elastic force of the first elastic element 7.

[0047] In some optional embodiments, the unlocking element 33 is configured as a cam, which is rotatably connected to the connecting seat 31. The cam is specifically located on the connecting seat 31 between the pin and the other end of the buckle 32. During rotation, the cam can contact the buckle 32 and lift the other end of the buckle 32, thereby causing the hook-shaped structure on the buckle 32 to disengage from the hook groove. In actual implementation, an operating rope can be connected to the cam, and the cam can be made to contact the buckle 32 or disengage from the buckle 32 by pulling it to the left or right.

[0048] In some alternative embodiments, the elastic element 34 is configured as a spring sheet.

[0049] In some alternative embodiments, see [reference]. Figure 4The second locking assembly 6 includes a support seat 61, a first limiting member 62, a mounting seat 63, and a second limiting member 64. The support seat 61 is connected to the load carriage 5 and has a bearing surface. The support seat 61 supports the wings of the drone through the bearing surface. Since the drone usually has two wings (i.e., fixed wings), there are also two support seats 61 to correspond to the number of wings of the drone. The first limiting member 62 is connected to the bearing surface of the support seat 61. The first limiting member 62 can be set as a bending plate, so that the drone's wings can form a locking relationship with the first limiting member 62. The mounting seat 63 is connected to the support seat 61. The second limiting member 64 rotates with the mounting seat 63. The second limiting member 64 can be designed as a strip structure. One end of the second limiting member 64 in the length direction forms an engagement gap with the first limiting member 62, indicating that one end of the second limiting member 64 is above the bearing surface. The other end of the second limiting member 64 is connected to the first elastic member 7 and the second elastic member 8. Through the elastic force of the first elastic member 7 and the second elastic member 8, the second limiting member 64 can be pulled to rotate clockwise or counterclockwise, so that one end of the second limiting member 64 is above the bearing surface, below the bearing surface, or level with the bearing surface. When one end of the second limiting member 64 is below the bearing surface or level with the bearing surface, the restriction on the wings of the UAV can be released.

[0050] During the release of the drone, as the load carriage 5 moves further away from the second fixed seat 2, the second elastic member 8 gradually pulls the second limiting member 64. One end of the second limiting member 64 gradually approaches a state of being level with the bearing surface. During this process, the restriction of the second limiting member 64 on the drone becomes weaker and weaker. When the second limiting member 64 is level with the bearing surface, the second limiting member 64 completely releases its restriction on the drone, so that the drone can detach from the load carriage 5.

[0051] In some alternative embodiments, the second limiting member 64 is slidably connected to the mounting base 63; thus, the engagement gap between one end of the second limiting member 64 and the first limiting member 62 is adjustable, which can accommodate wings of different sizes and improve the overall adaptability of the aircraft.

[0052] In some optional embodiments, the support 61 and the load carriage 5 are movably connected. Specifically, the support 61 may have a slot, and the support 61 is bolted to the load carriage 5 through the slot. By adjusting the relative position of the support 61 and the load carriage 5, it can accommodate drones of different widths, thereby improving the overall adaptability of the drone.

[0053] The specific embodiments described above illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Although the description of this application is presented in conjunction with some embodiments, this does not mean that the features of this application are limited to this embodiment. On the contrary, the purpose of describing the application in conjunction with embodiments is to cover other options or modifications that may be derived based on the claims of this application. To provide a thorough understanding of this application, many specific details are included in the above description. This application may also be implemented without using these details. Furthermore, to avoid confusion or obscuring the focus of this application, some specific details will be omitted in the description. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other.

[0054] It should be noted that in this specification, similar reference numerals and letters in the above figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. In the description 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 figures, and are only for the convenience of describing this application and 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, and therefore should not be construed as a limitation on this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In the description of this application, it should be noted that unless otherwise expressly specified and limited, 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; and they can refer to the internal communication between two elements. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0055] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A fixed-wing unmanned aerial vehicle catapult, characterized in that, The utility model relates to a kind of unmanned aerial vehicle storage device, including: First fixed seat (1); Second fixed seat (2), the second fixed seat (2) is arranged with interval with the first fixed seat (1), first lock catch assembly (3) is provided on the second fixed seat (2); Slide rail (4), the slide rail (4) both ends are connected with the first fixed seat (1) and second fixed seat (2) respectively; Load slide (5), the load slide (5) is slidably connected with the slide rail (4), second lock catch assembly (6) is provided on the load slide (5), and the second lock catch assembly (6) is connected with the first fixed seat (1) and second fixed seat (2) by first elastic member (7) and second elastic member (8) respectively, and the load slide (5) is used to place unmanned aerial vehicle; Wherein, when the load slide (5) is close to the second fixed seat (2), it can be locked with the second lock catch assembly (6) to make load slide (5) and second fixed seat (2) relative fixed, and first elastic member (7) is elastically acted on the second lock catch assembly (6) to make unmanned aerial vehicle be limited by second lock catch assembly (6);When the load slide (5) is close to the first fixed seat (1), second elastic member (8) is elastically acted on the second lock catch assembly (6) to release the limitation of second lock catch assembly (6) to the unmanned aerial vehicle.

2. The fixed-wing UAV catapult of claim 1, wherein, The slide rail (4) is configured as a slide rod, and the number of the slide rail (4) is configured to be not less than three, wherein the slide rail (4) is movably penetrated through the load slide (5).

3. The fixed-wing UAV catapult of claim 1, wherein, The first fixed seat (1) and / or the second fixed seat (2) are provided with an anti-skid shovel (9).

4. The fixed-wing UAV catapult of claim 1, wherein, The first elastic member (7) and / or the second elastic member (8) are configured as elastic thin ropes.

5. The fixed-wing UAV catapult of claim 1, wherein, The first lock catch assembly (3) comprises: A connecting seat (31) connected with the second fixed seat (2); A buckle (32) rotatably connected with the connecting seat (31), wherein one end of the buckle (32) and the connecting seat (31) are configured with an elastic member (34), the other end of the buckle (32) is provided as a hook-shaped structure, and a hook groove adapted to the hook-shaped structure is formed on the load slide (5); An unlocking member (33) movably connected with the connecting seat (31), wherein the unlocking member (33) can contact the buckle (32) and drive the buckle (32) to rotate against the elastic force of the elastic member (34) when the unlocking member (33) moves relative to the connecting seat (31).

6. The fixed-wing UAV catapult of claim 5, wherein, The unlocking member (33) is configured as a cam, and the unlocking member (33) is rotatably connected with the connecting seat (31).

7. The fixed-wing UAV catapult of claim 5, wherein, The elastic member (34) is configured as a spring sheet.

8. The fixed-wing UAV catapult of claim 1, wherein, The second lock catch assembly (6) comprises: A bearing seat (61) connected with the load slide (5), for supporting the wings of the unmanned aerial vehicle; A first limiting member (62) connected with the bearing seat (61); A mounting seat (63) connected with the bearing seat (61). A second limiting member (64) is rotationally connected with the mounting seat (63), a clamping gap is formed between one end of the second limiting member (64) and the first limiting member (62), and the other end of the second limiting member (64) is connected with the first elastic member (7) and the second elastic member (8).

9. The fixed-wing UAV catapult of claim 8, wherein, The second limiting member (64) is slidingly connected with the mounting seat (63).

10. The fixed-wing UAV catapult of claim 8, wherein, The bearing seat (61) is movably connected with the load carriage (5).

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