Landing buffer device for rocket recovery

Abstract

The utility model relates to a landing buffer device for rocket recovery. The rocket has the advantages of being good in buffering effect and stable in landing and comprises a rocket body, at least three outer supports are hinged to the side wall of the rocket body, an inner support is arranged on the lower portion of each outer support in a sliding mode, a bottom table is fixed to the bottom of each inner support, a first damper is arranged in each outer support, and a second damper is arranged in each outer support. The upper portions of the first dampers are fixed into the outer supports, the lower portions of the first dampers are fixed to the upper portions of the inner supports, a limiting assembly is arranged on the side, close to the rocket body, of each outer support, and an auxiliary supporting assembly used for assisting landing supporting of the rocket body is arranged on the side, close to the rocket body, of each inner support. The multiple auxiliary supporting assemblies are rotationally connected with the outer side wall of the supporting annular plate.

Description

Technical Field

[0001] This utility model belongs to the field of aerospace technology, specifically relating to a landing buffer device for rocket recovery. Background Technology

[0002] With the development of aerospace technology, reducing the launch cost of launch vehicles has become one of the main problems facing the entire aerospace industry. Reusable launch vehicles are different from ordinary launch vehicles, which are discarded after launch. They are new types of launch vehicles that can be launched multiple times and reused. Therefore, reusable launch vehicles are an effective way to reduce the launch cost of launch vehicles and have extremely high military and civilian value. Reusable rockets adopt a vertical landing method with engine deceleration and control. This method has good deceleration effect and high control precision, but the landing impact is large and the stability of attitude maintenance at the moment of landing is poor. The rocket body is easily damaged by impact loads and overturning. Therefore, a landing buffer device for rocket recovery needs to be designed. Utility Model Content

[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide a rocket recovery device with good buffering effect and stable landing.

[0004] The technical solution of this utility model is as follows:

[0005] A landing buffer device for rocket recovery includes a rocket body. At least three outer supports are hinged to the side wall of the rocket body. An inner support is slidably disposed at the lower part of each outer support. A base is fixed at the bottom of each inner support. A first damper is disposed inside the outer support. The upper part of the first damper is fixed to the inside of the outer support, and the lower part of the first damper is fixed to the upper part of the inner support. A limit assembly is disposed on the side of each outer support near the rocket body. An auxiliary support assembly for assisting the rocket body in landing is disposed on the side of each inner support near the rocket body. Multiple auxiliary support assemblies are rotatably connected to the outer wall of a support ring plate.

[0006] Furthermore, the limiting component includes a first link hinged to the rocket body, a second link slidably disposed within the first link, and the second link hinged to the outer support near the rocket body.

[0007] Furthermore, the auxiliary support assembly includes a cylinder hinged to the outer support near the rocket body. The output end of the cylinder is hinged to a mating block, which is slidably disposed on a support plate. One end of the support plate is inserted into a support plate, which is rotatably connected to the lower part of the inner support. The other end of the support plate is rotatably connected to the outer wall of the support ring plate.

[0008] Furthermore, the other end of each of the multiple support plates is rotatably connected to the outer wall of the support ring plate.

[0009] Furthermore, a placement groove is provided in the middle of the support plate, the mating block is slidably disposed in the placement groove, a second damper is disposed in the placement groove, one end of the second damper is fixed to the side of the mating block away from the inner support, and the other end of the second damper is fixed in the placement groove.

[0010] Compared with the prior art, the beneficial effects of this utility model are:

[0011] 1. This utility model can buffer the impact force of the rocket during landing by using an outer support, an inner support, a first damper, and an auxiliary support assembly, thereby preventing the rocket from being damaged by excessive impact force. The auxiliary support assembly can also share the temporary pressure of the first damper, preventing the first damper from being damaged by excessive temporary pressure, thereby extending the service life of the first damper and making the rocket landing more stable.

[0012] 2. This utility model can increase the landing contact area through the base platform, auxiliary support components and support ring plate, thereby making the rocket landing more stable.

[0013] In summary, this invention has the advantages of good buffering effect and stable landing. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0015] Figure 2 This is a front sectional view of the structure of this utility model.

[0016] In the diagram, 1. Rocket body; 2. Outer support; 3. Inner support; 4. Base platform; 5. First damper; 6. First connecting rod; 7. Second connecting rod; 8. Cylinder; 9. Fitting block; 10. Support plate; 11. Support ring plate; 12. Support plate; 14. Placement slot; 15. Second damper. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0018] like Figures 1 to 2As shown, a landing buffer device for rocket recovery includes a rocket body 1. At least three outer supports 2 are hinged to the side wall of the rocket body 1. An inner support 3 is slidably arranged at the lower part of each outer support 2. A base platform 4 is fixed at the bottom of each inner support 3. A first damper 5 is arranged inside the outer support 2. The upper part of the first damper 5 is fixed to the inside of the outer support 2, and the lower part of the first damper 5 is fixed to the upper part of the inner support 3. A limit component is provided on the side of each outer support 2 near the rocket body 1. An auxiliary support component for assisting the landing support of the rocket body 1 is provided on the side of each inner support 3 near the rocket body 1. Multiple auxiliary support components are rotatably connected to the outer wall of the support ring plate 11.

[0019] When the rocket lands, the auxiliary support assembly deploys, and the base platform 4 and the auxiliary support assembly contact the ground together. The impact force of the rocket landing is buffered by the first damper 5 and the auxiliary support assembly. Moreover, the auxiliary support assembly can share the pressure of the first damper 5, preventing the first damper 5 from being damaged by excessive pressure in a short period of time, which would cause the rocket's landing angle to deviate, thus making the rocket land stably. Furthermore, the auxiliary support assembly increases the support points and support area, making the rocket landing more stable.

[0020] In this embodiment, the limiting component includes a first link 6 hinged to the rocket body 1, a second link 7 slidably disposed inside the first link 6, and the second link 7 hinged to the side of the outer support 2 near the rocket body 1.

[0021] The second link 7 is designed to extend beyond the length of the first link 6, thereby limiting the maximum and minimum rotation angles of the outer support 2 and ensuring that the outer support 2 is in an extended state.

[0022] Preferably, the auxiliary support assembly includes a cylinder 8 hinged to the outer support 2 on the side near the rocket body 1. The output end of the cylinder 8 is hinged to a mating block 9, which is slidably disposed on the support plate 10. One end of the support plate 10 is inserted into a support plate 12, which is rotatably connected to the lower part of the inner support 3. The other end of the support plate 10 is rotatably connected to the outer wall of the support ring plate 11.

[0023] In this embodiment, the other ends of the plurality of support plates 10 are rotatably connected to the outer wall of the support ring plate 11.

[0024] In this embodiment, a placement groove 14 is provided in the middle of the support plate 10, and the mating block 9 is slidably disposed in the placement groove 14. A second damper 15 is provided in the placement groove 14. One end of the second damper 15 is fixed to the side of the mating block 9 away from the inner bracket 3, and the other end of the second damper 15 is fixed in the placement groove 14.

[0025] The operation of cylinder 8 can drive the movement of mating block 9, which in turn pushes support plate 10 to unfold. Support plate 10 then drives support ring plate 11 to unfold, increasing the force-bearing area and making rocket landing more stable. During rocket landing, the outer support 2 can simultaneously use the first damper 5 and the second damper 15 for buffering, effectively relieving the temporary pressure on the first damper 5 and ensuring the service life of the first damper 5 and the second damper 15. Support ring plate 11, together with support plate 10, connects multiple inner supports 3, which can support each other and thus strengthen the structural strength.

[0026] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A landing buffer device for rocket recovery, comprising the rocket body, characterized in that: At least three outer supports are hinged to the side wall of the rocket body. Each outer support has an inner support slidably mounted on its lower part. Each inner support has a base fixed to its bottom. A first damper is installed inside the outer support. The upper part of the first damper is fixed to the inside of the outer support, and the lower part of the first damper is fixed to the upper part of the inner support. Each outer support has a limit assembly on the side near the rocket body. Each inner support has an auxiliary support assembly on the side near the rocket body for assisting the rocket body in landing. Multiple auxiliary support assemblies are rotatably connected to the outer wall of the support ring plate.

2. A landing buffer device for rocket recovery according to claim 1, characterized in that: The limiting component includes a first link hinged to the rocket body, a second link slidably disposed within the first link, and the second link hinged to the outer support near the rocket body.

3. A landing buffer device for rocket recovery according to claim 1, characterized in that: The auxiliary support assembly includes a cylinder hinged to the outer support near the rocket body. The output end of the cylinder is hinged to a mating block, which is slidably disposed on a support plate. One end of the support plate is inserted into a support plate, which is rotatably connected to the lower part of the inner support. The other end of the support plate is rotatably connected to the outer wall of the support ring plate.

4. A landing buffer device for rocket recovery according to claim 3, characterized in that: The other end of each of the multiple support plates is rotatably connected to the outer wall of the support ring plate.

5. A landing buffer device for rocket recovery according to claim 3, characterized in that: The support plate has a placement groove in the middle, the mating block is slidably disposed in the placement groove, and a second damper is disposed in the placement groove. One end of the second damper is fixed to the side of the mating block away from the inner support, and the other end of the second damper is fixed in the placement groove.

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