Rocket-assisted drone launcher
By introducing rotary gears and adjustment components into the rocket-assisted UAV launch device, precise adjustment of 360° heading and 5° to 30° pitch angle is achieved. The use of a constant force release mechanism solves the flexibility and safety problems of existing devices, and improves the stability and safety of UAV launch.
Patent Information
- Application Number
- CN202521539759.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-23
- Publication Date
- 2026-08-04
- Estimated Expiration
- 2035-07-23
AI Technical Summary
Existing rocket-assisted UAV launchers have shortcomings in heading and pitch angle adjustment, making it difficult to achieve 360° flexible rotation and precise adjustment. They also lack a force release mechanism, which affects launch performance and safety.
A rocket-assisted UAV launcher was designed, comprising a base, a launch pad, and a force release mechanism. The UAV can be 360° yaw adjustment is achieved through a rotating gear, the pitch angle can be precisely adjusted by an adjustment component, and the UAV can be stably fixed and reliably released by an inverted T-shaped slide rail and a force release mechanism.
It enables rapid adaptation to the launch direction of the UAV and accuracy of the initial attitude, improves the safety and reliability of the launch, ensures the stable and reliable release of the UAV, and avoids potential damage and safety accidents.
Smart Images
Figure CN224589383U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) launch equipment technology, specifically to a rocket-assisted UAV launch device. Background Technology
[0002] Small drones can take off in various ways, including runway takeoff, airdrop, catapult launch, and boost-launch. In boost-launch, the thrust is provided by a rocket booster, which accelerates the drone from a standstill to the specified safe flight speed and altitude, achieving launch at zero altitude, zero speed, and zero distance.
[0003] Existing rocket-assisted UAV launch systems have several shortcomings. Regarding heading adjustment, most systems struggle to achieve 360° rotation, limiting the UAV's launch direction and hindering its ability to quickly adapt to different mission requirements. Pitch angle adjustment lacks precision, affecting the UAV's launch trajectory and initial attitude. Furthermore, existing UAVs are immediately propelled into launch after rocket booster ignition, lacking a thrust hold-out mechanism. This inaccurate and untimely release not only impacts launch performance but can also damage the UAV and even cause safety accidents. Therefore, there is an urgent need for a rocket-assisted UAV launch system that offers flexible heading adjustment, precise pitch angle control, and stable and reliable launch and release. Utility Model Content
[0004] To address the aforementioned shortcomings, this utility model aims to provide a rocket-assisted unmanned aerial vehicle (UAV) launch device. It aims to achieve 360° flexible heading adjustment of the launch device, precisely adjust the pitch angle of the launch pad, ensure stable coordination between the UAV and the launch pad, and simultaneously incorporate a constant force release mechanism to reliably release the UAV once the rocket thrust reaches the specified level.
[0005] To achieve the above technical objectives, the following technical solutions were adopted:
[0006] A rocket-assisted unmanned aerial vehicle (UAV) launch device includes a base, a launcher, and a force release mechanism. The lower end face of the base is provided with a rotating gear for meshing with a transport vehicle gear ring to achieve 360° heading adjustment of the launch device. The upper end face of the base is provided with a base support, which is hinged to the launcher. An adjustment component is provided at the center of its front end for adjusting the launcher's pitch angle α. Vertical columns are provided on the left and right rear sides of the launcher, and inverted T-shaped slide rails are provided on the columns for engaging with inverted T-shaped sliders on the UAV fuselage. U-shaped grooves are horizontally provided on the left and right sides of the front end of the launcher, and force release mechanisms are installed inside the U-shaped grooves on both sides. Each force release mechanism includes an L-shaped swing arm and a force pin. The L-shaped swing arm includes a vertical rod positioned in the U-shaped groove and a cutting edge at the bottom end of the rod, the bottom end of which is hinged to the U-shaped groove. The force pin passes laterally through the U-shaped groove and is fitted with the cutting edge.
[0007] Furthermore, a support ring is provided at the rear of the upper end face of the base for supporting the rocket booster.
[0008] Furthermore, the adjustment assembly includes an adjustment screw and an adjustment handwheel located at the end of the adjustment screw, and the pitch angle α of the launcher is adjusted by rotating the adjustment handwheel; the top of the adjustment screw is provided with a hinge point, and is hinged to the front end of the launcher through the hinge point.
[0009] Furthermore, the pitch angle α of the launcher can be adjusted from 5° to 30°.
[0010] Furthermore, the base support is provided with hinge points on the left and right sides of its rear end, which are respectively hinged to the left and right sides of the launcher.
[0011] Furthermore, the launcher is provided with a pitch angle dial on its side for indicating the adjustment of the pitch angle α.
[0012] Furthermore, the top of the upright of the L-shaped swing arm is provided with a groove for supporting the front support point of the drone fuselage.
[0013] Furthermore, a waist-shaped hole is provided on the side wall of the U-shaped groove, through which the force-holding pin passes.
[0014] Furthermore, the fixed pin is provided with a notch, the depth of which is designed according to the critical thrust of the rocket booster to ensure that it is cut off by the cutting edge when the thrust reaches the target.
[0015] The beneficial effects achieved by this utility model are:
[0016] This invention provides a rocket-assisted unmanned aerial vehicle (UAV) launch device. A rotating gear is located on the lower end face of the base, meshing with a gear ring on a transport vehicle to achieve 360° heading adjustment. This eliminates the tediousness of manual adjustment and shortens the UAV launch preparation time, enabling rapid and precise adjustment of the launch direction to adapt to different mission requirements. The pitch angle of the launch pad can be precisely adjusted via a handwheel and lead screw in the adjustment assembly. A pitch angle scale on the side of the launch pad clearly indicates the adjustment angle, ensuring the accuracy of the UAV's launch trajectory and initial attitude. The inverted T-shaped slide rail on the launch pad and the front-end force release mechanism support and limit the UAV to be launched. This design is not only simple in structure but also highly stable, effectively fixing the UAV to be launched and improving the positional accuracy of the UAV's attitude. The cutting edge of the L-shaped swing arm accurately cuts the force pin, ensuring a stable and reliable release of the UAV and improving the overall launch safety and reliability. Attached Figure Description
[0017] The present invention will now be described in conjunction with the accompanying drawings.
[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model.
[0019] Figure 2 This is a schematic diagram of the base structure described in this utility model.
[0020] Figure 3 This is a schematic diagram of the launcher structure described in this utility model.
[0021] Figure 4 This is a schematic diagram of the force release mechanism described in this utility model.
[0022] In the diagram: 1-base; 2-launcher; 3-force release mechanism; 4-rotating gear; 5-base bracket; 6-adjusting screw; 7-adjusting handwheel; 8-support ring; 9-U-shaped groove; 10-inverted T-shaped slide rail; 11-pitch angle dial; 12-L-shaped swing arm; 121-upright pole; 122-blade edge; 123-groove; 13-force pin; 14-waist-shaped hole; 15-column. Detailed Implementation
[0023] The following specific embodiments illustrate the implementation of this utility model. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification. The described embodiments are merely some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.
[0024] like Figure 1 As shown, the present invention provides a rocket drone launch device, which includes a base 1, a launcher 2, and a force release mechanism 3.
[0025] like Figure 2 As shown, the lower end face of the base 1 is provided with a rotating gear 4 for meshing with the gear ring of the transport vehicle to achieve 360° heading adjustment of the launch device; the upper end face of the base 1 is provided with a base bracket 5, and the front middle of the base bracket 5 is provided with an adjustment component. The adjustment component is used to adjust the pitch angle α of the launcher 2, which includes an adjustment screw 6 and an adjustment handwheel 7 located at the end of the adjustment screw 6. The pitch angle α of the launcher 2 is adjusted by rotating the adjustment handwheel 7. The adjustment range of the pitch angle α is 5° to 30°; the top end of the adjustment screw 6 is provided with a hinge point, which is hinged to the front end of the launcher 2; the rear left and right sides of the base bracket 5 are respectively provided with hinge points, which are hinged to the left and right sides of the launcher 2; a support ring 8 is provided at the rear of the upper end face of the base 1 for supporting the rocket booster.
[0026] like Figure 3As shown, the launcher 2 has vertical columns 15 on the left and right sides of its rear end. The columns 15 are equipped with inverted T-shaped slide rails 10 for cooperating with the inverted T-shaped sliders of the UAV body. A pitch angle dial 11 is provided on the side of the launcher 2 for indicating the adjustment of the pitch angle α. U-shaped grooves 9 are horizontally provided on the left and right sides of the front end of the launcher 2. A constant force release mechanism 3 is installed in the U-shaped grooves 9 on the left and right sides respectively.
[0027] like Figure 4 As shown, the constant force release mechanism 3 includes an L-shaped swing arm 12 and a constant force pin 13. The L-shaped swing arm 12 includes a vertical rod 121 disposed in the U-shaped groove 9 and a cutting edge 122 disposed at the bottom end of the rod 121. The bottom end of the rod 121 is hinged to the U-shaped groove 9, and its top end is provided with a groove 123 for supporting the front support point of the UAV fuselage. The constant force pin 13 passes through the waist-shaped hole 14 disposed in the side wall of the U-shaped groove 9 and fits with the cutting edge 122. It is provided with a notch. The depth of the notch is designed according to the critical thrust of the rocket booster to ensure that it is cut off by the cutting edge 122 when the thrust reaches the standard.
[0028] The working steps of this utility model are as follows:
[0029] (a) Launch adjustment stage: Adjust the launcher 2 to the launch heading by rotating the gear 4 on the lower end face of the base 1, and adjust the pitch angle of the launcher 2 by adjusting the handwheel 7. The angle is indicated by the pitch angle scale 11.
[0030] (II) Launch Process: During launch, the UAV performs a self-check and is placed on launcher 2, with its inverted T-shaped slider engaging with the inverted T-shaped rail 10 of launcher 2. The UAV's front fulcrum is placed in the groove 123 at the top of the upright 121 of the L-shaped swing arm 12. Simultaneously, the rocket booster is placed on the support ring 8 and connected to the UAV. Then, the engine is started. Upon receiving the launch command, the rocket booster ignites. When the thrust generated by the rocket booster reaches the critical value, the L-shaped swing arm 12 receives the thrust transmitted by the UAV. Its bottom edge 122 applies pressure to the notch of the retaining pin 13, cutting off the retaining pin 13. The L-shaped swing arm 12 rotates around its bottom hinge, releasing the UAV. Under the thrust of the rocket booster, the L-shaped swing arm 12 flips, and the UAV's front fulcrum and inverted T-shaped slider slide out from the L-shaped swing arm 12 and the inverted T-shaped rail 10, allowing the UAV to detach from launcher 2 and take off.
[0031] (III) Launch Completion Stage: After launch, when retracting the launcher, adjust the handwheel 7 to level the launcher 2 and return the rotating gear 4 to the "0" position.
[0032] Other aspects of this utility model that are not detailed herein are all conventional techniques known to those skilled in the art.
[0033] It should be noted that the terms “comprising,” “including,” or any other variations are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.
[0034] The scope of protection of this utility model is not limited to the technical solutions disclosed in the specific embodiments. Any modifications, equivalent substitutions, improvements, etc., made to the above embodiments based on the technical essence of this utility model shall fall within the scope of protection of this utility model.
Claims
1. A rocket-boosted unmanned aerial vehicle launcher, characterized in that: The device includes a base (1), a launcher (2), and a constant force release mechanism (3). The lower end face of the base (1) is provided with a rotating gear (4) for meshing with a transport vehicle gear ring to achieve 360° heading adjustment of the launch device. The upper end face of the base (1) is provided with a base support (5), which is hinged to the launcher (2). An adjustment component is provided at the center of its front end, used to adjust the pitch angle α of the launcher (2). Vertical columns (15) are provided on the left and right sides of the rear end of the launcher (2). Inverted T-shaped slide rails (10) are provided on the columns (15) for connecting with the UAV. The fuselage has a "⊥" shaped slider; U-shaped grooves (9) are horizontally provided on both the left and right sides of the front end of the launcher (2), and a constant force release mechanism (3) is installed in the U-shaped grooves (9) on both the left and right sides respectively; the constant force release mechanism (3) includes an L-shaped swing arm (12) and a constant force pin (13). The L-shaped swing arm (12) includes a vertical rod (121) set vertically in the U-shaped groove (9) and a cutting edge (122) set at the bottom end of the vertical rod (121). The bottom end of the vertical rod (121) is hinged to the U-shaped groove (9); the constant force pin (13) passes through the U-shaped groove (9) laterally and fits against the cutting edge (122).
2. The rocket boosted unmanned aerial vehicle launcher of claim 1, wherein: The base (1) has a support ring (8) at the rear of its upper end face for supporting the rocket booster.
3. The rocket boosted drone launch device of claim 1, wherein: The adjustment assembly includes an adjustment screw (6) and an adjustment handwheel (7) located at the end of the adjustment screw (6). The pitch angle α of the launcher (2) is adjusted by rotating the adjustment handwheel (7). The top of the adjustment screw (6) is provided with a hinge point, which is hinged to the front end of the launcher (2).
4. The rocket boosted drone launch device of claim 3, wherein: The pitch angle α of the launcher (2) can be adjusted from 5° to 30°.
5. The rocket-assisted unmanned aerial vehicle launching device according to claim 4, characterized in that: The base bracket (5) has hinge points on the left and right sides of its rear end, which are respectively hinged to the left and right sides of the launcher (2).
6. The rocket-assisted unmanned aerial vehicle launching device according to claim 5, characterized in that: The launcher (2) is provided with a pitch angle dial (11) on the side for indicating the adjustment of the pitch angle α.
7. The rocket-assisted unmanned aerial vehicle launching device according to claim 1, characterized in that: The top of the upright (121) of the L-shaped swing arm (12) is provided with a groove (123) for supporting the front support point of the UAV fuselage.
8. The rocket-assisted unmanned aerial vehicle launching device according to claim 1, characterized in that: A waist-shaped hole (14) is provided on the side wall of the U-shaped groove (9), and the fixed pin (13) passes through the waist-shaped hole (14).
9. The rocket-assisted unmanned aerial vehicle launching device according to claim 1, characterized in that: The fixed pin (13) has a notch, the depth of which is designed according to the critical thrust of the rocket booster to ensure that it is cut off by the cutting edge when the thrust reaches the target.