A rear support point release mechanism of a UAV launching rack

Abstract

The utility model relates to a unmanned plane launching rack rear fulcrum release mechanism, including setting in the slide rail of the rear part of side beam of launching rack, this slide rail is used for supporting the rear fulcrum of guiding in the side part of unmanned plane fuselage, and the side beam of its launching rack is provided with rear fulcrum clamping plate, and the upper edge of rear fulcrum clamping plate is made with rear fulcrum clamping groove, and the rear end of rear fulcrum clamping plate is hinged to the side beam of support frame through pin shaft, and the side beam of launching rack is jointly installed with safety pin between rear fulcrum clamping plate, and the lower part of rear fulcrum clamping plate is made with handle, and the side beam of launching rack is installed between the lower end of handle and the side beam of launching rack and installs the tension spring, and the lower end of handle and the side beam of launching rack are further connected with the limit rope of the further connection. The utility model adopts tension spring and pull rope structure to jointly realize the clamping and release of rear fulcrum, thereby improving the convenience and reliability of unmanned plane launching operation.

Description

Technical Field

[0001] This utility model relates to the technical field of rocket-assisted takeoff unmanned aerial vehicle (UAV) launch devices, specifically a UAV launcher rear fulcrum release mechanism. Background Technology

[0002] Currently, the launch method for drone target drones is as follows: Before takeoff, the engine starts the main engine, followed by rocket ignition. The drone accelerates to above stall speed under the rocket's force, and the engine then takes over, providing the main power for the drone to continue stable flight. This launch method is a zero-length launch. Before launch, the target drone is typically mounted on a launch pad. A front support and front locking point at the front of the launch pad provide support, positioning, and release control for the front of the target drone's fuselage; a rear pivot point at the rear of the launch pad provides positioning and release control for the rear of the target drone's fuselage. Existing rear pivot release mechanisms typically require shear pins, which are complex and prone to damage to the shear pins before launch due to factors such as the machining precision of the shear mechanism and the installation method of the shear pins. Inconsistent shear pin supply conditions can also lead to inconsistent target drone launch conditions, affecting launch safety. Summary of the Invention

[0003] The present invention aims to overcome the shortcomings of the prior art and provide a release mechanism for the rear pivot point of a UAV launcher. It adopts a tension spring and a pull rope structure to achieve the locking and releasing of the rear pivot point, thereby improving the convenience and reliability of UAV launch operation.

[0004] The technical problem solved by this utility model is achieved through the following technical solution: A drone launcher rear support release mechanism includes a slide rail located at the rear of the side beam of the launcher. The slide rail supports and guides the rear support located on the side of the drone fuselage. The mechanism is characterized by: a rear support plate on the side beam of the launcher, with a rear support groove along its upper edge; the rear end of the rear support plate is hinged to the side beam of the support frame via a pin; a safety pin is installed between the rear support plate and the side beam of the launcher; a handle is provided at the lower part of the rear support plate; a tension spring is installed between the lower end of the handle and the side beam of the launcher; and a restraining rope is further connected between the lower end of the handle and the side beam of the launcher.

[0005] Furthermore, after the restraining rope passes through the side threading hole made in the side beam of the launcher, it is further tied and fixed to the first rear threading hole made in the longitudinal beam on the same side of the rear of the launcher.

[0006] Furthermore, a second rear threading hole is formed on the opposing longitudinal beam at the rear of the support frame, and a fixed cylinder is installed on the opposing longitudinal beam. The upper end of the fixed cylinder has a winding and fixing hole through which the limiting rope passes, and the root of the fixed cylinder has a winding groove for the limiting rope to be wound. The limiting rope passes through the side threading hole, the first rear threading hole, the second rear threading hole and the winding and fixing hole in sequence and then winds around the fixed cylinder. The limiting rope is wound and fixed to the winding groove of the fixed cylinder by friction.

[0007] The beneficial effects of this utility model are as follows: 1. In the UAV launcher rear fulcrum release mechanism of this utility model, after the engine trolley, the tension of the tension spring is insufficient to hold the rear fulcrum plate. At this time, the UAV is not released. Instead, the rear fulcrum plate is held by a restraining rope, which passes through the hole on the rear longitudinal beam. The restraining rope is brought as close as possible to the tail nozzle of the booster rocket. After the rocket is ignited, the restraining rope burns out, releasing the UAV. The UAV then takes off smoothly.

[0008] 2. The UAV launcher rear fulcrum release mechanism of this utility model has a limiting rope that passes through the side threading hole made by the side beam of the launcher and is further tied and fixed to the first rear threading hole made by the longitudinal beam on the same side of the rear of the launcher. The limiting rope then passes through the second rear threading hole and the winding and fixing hole and is wound around the fixing cylinder. The limiting rope is wound and fixed to the winding groove of the fixing cylinder by friction. The winding rope is easy to operate and not easy to slip off, further improving the convenience and stability of the limiting rope winding and installation. Attached Figure Description

[0009] Figure 1 This is a schematic diagram of the structure of this utility model in conjunction with the Flying Phoenix Target Launcher; Figure 2 This is a schematic diagram of the structure of this utility model; Figure 3 This is a schematic diagram of the structure of the rear support plate of this utility model; Figure 4 This is a structural schematic diagram of the present invention from another angle; Figure 5 This is a schematic diagram of the structure of the fixed cylindrical part of this utility model.

[0010] In the picture 1-Flying Phoenix Target Drone, 2-Launch Mount, 3-Side Beam, 4-Side Cable Hole, 5-Slide Rail, 6-Rear Support Point Plate, 7-Rear Support Point Slot, 8-Pin Shaft, 9-Handle, 10-Restriction Rope, 11-Tension Spring, 12-Safety Pin, 13-Rear Support Point, 14-First Rear Cable Hole, 15-Second Rear Cable Hole, 16-Fixing Cylinder, 17-Wrapping Fixing Hole. Detailed Implementation

[0011] The present invention will now be described in more detail through specific embodiments. These embodiments are intended to provide a further understanding and explanation of the present invention, and are for descriptive purposes only, and do not constitute any limitation on the scope of protection of the present invention.

[0012] A drone launcher rear support release mechanism includes a slide rail 5 located at the rear of the side beam 3 of the launcher 2. The slide rail is used to support and guide the rear support 13 located on the side of the drone fuselage. The slide rail has a U-shaped cross section. The rear support has an L-shaped groove and a support plate. The rear support is guided and clamped onto the U-shaped slide rail through the L-shaped groove.

[0013] The innovation of this utility model lies in the following: a rear support plate 6 is provided on the side beam of the launcher. A rear support groove 7 is formed along the upper edge of the rear support plate, allowing the support plate of the rear support to be locked into the groove, thus limiting the locking and positioning of the rear support. To enable the rear support plate to disengage from the rear support, it is designed as a rotating structure. The rear end of the rear support plate is hinged to the side beam of the support frame via a pin 8. A safety pin 12 is installed between the rear support plate and the side beam of the launcher, allowing the engine trolley to pull out the safety pin. A handle 9 is provided at the lower part of the rear support plate. A tension spring 11 is installed between the lower end of the handle and the side beam of the launcher, and a restraining rope 10 is further connected between the lower end of the handle and the side beam of the launcher. The tension spring and the restraining rope tighten the rear support plate, thereby providing a limiting effect for the target drone by limiting the rear support.

[0014] The restraining rope passes through the side threading hole 4 on the side beam of the launcher and is then further secured to the first rear threading hole 14 on the longitudinal beam on the same side of the rear of the launcher. A second rear threading hole 15 is formed on the opposing longitudinal beam at the rear of the support frame. A fixed cylinder 16 is installed on this opposing longitudinal beam. The upper end of the fixed cylinder has a winding and fixing hole 17 through which the restraining rope passes, and the base of the fixed cylinder has a winding groove 18 for winding the restraining rope. The restraining rope passes sequentially through the side threading hole, the first rear threading hole, the second rear threading hole, and the winding and fixing hole before winding around the fixed cylinder. The restraining rope is secured to the winding groove of the fixed cylinder by friction. The winding rope is easy to operate and does not easily slip off, further improving the convenience and stability of the restraining rope winding installation.

[0015] After the engine is pulled back, the tension of the tension spring is insufficient to hold the rear support plate. At this time, the Flying Phoenix Target Drone 1 is not released. Instead, a restraining rope is introduced to hold the rear support plate and passes through the hole on the rear longitudinal beam. The restraining rope is brought as close as possible to the tail nozzle of the booster rocket. After the rocket is ignited, the restraining rope burns out, releasing the Flying Phoenix Target Drone, which then takes off smoothly.

[0016] Although the embodiments and drawings of this utility model have been disclosed for illustrative purposes, those skilled in the art will understand that various substitutions, variations and modifications are possible without departing from the spirit and scope of this utility model and the appended claims. Therefore, the scope of this utility model is not limited to the contents disclosed in the embodiments and drawings.

Claims

1. A release mechanism for the rear support point of a UAV launcher, comprising a slide rail (5) disposed at the rear of a side beam (3) of the launcher (2), the slide rail (5) being used to support and guide the rear support point (13) on the side of the UAV fuselage, characterized in that: A rear support plate (6) is provided on the side beam (3) of the launcher (2). The upper edge of the rear support plate (6) is provided with a rear support groove (7). The rear end of the rear support plate (6) is hinged to the side beam (3) of the support frame by a pin (8). A safety pin (12) is installed between the rear support plate (6) and the side beam (3) of the launcher (2). A handle (9) is provided at the lower part of the rear support plate (6). A tension spring (11) is installed between the lower end of the handle (9) and the side beam (3) of the launcher (2). A restraining rope (10) is further connected between the lower end of the handle (9) and the side beam (3) of the launcher (2).

2. The UAV launcher rear pivot release mechanism according to claim 1, characterized in that: The restraint rope (10) passes through the side threading hole (4) made by the side beam (3) of the launcher and is then tied and fixed to the first rear threading hole (14) made by the longitudinal beam on the same side of the rear of the launcher (2).

3. The UAV launcher rear pivot release mechanism according to claim 1, characterized in that: The support frame has a second rear threading hole (15) on the opposing longitudinal beam at the rear. A fixed cylinder (16) is installed on the opposing longitudinal beam. The upper end of the fixed cylinder (16) has a winding fixing hole (17) through which the limiting rope (10) passes. The root of the fixed cylinder (16) has a winding groove for the limiting rope (10) to be wound. The limiting rope (10) passes through the side threading hole (4), the first rear threading hole (14), the second rear threading hole (15) and the winding fixing hole (17) in sequence and then winds around the fixed cylinder (16). The limiting rope (10) is wound and fixed to the winding groove of the fixed cylinder (16) by friction.

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