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A Pneumatically Driven Retrievable Rocket Landing Support Mechanism

A technology of pneumatic drive and supporting mechanism, which is applied in the field of aerospace and can solve problems such as poor stability and large launch air resistance

Active Publication Date: 2021-07-06
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem of poor stability of the traditional rocket support mechanism and large launching air resistance, the present invention further proposes a pneumatically driven recoverable rocket landing support mechanism

Method used

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  • A Pneumatically Driven Retrievable Rocket Landing Support Mechanism
  • A Pneumatically Driven Retrievable Rocket Landing Support Mechanism

Examples

Experimental program
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Effect test

specific Embodiment approach 1

[0012] Specific implementation mode one: combine figure 1 with figure 2 Describe this embodiment, a pneumatically driven recoverable rocket landing support mechanism described in this embodiment, which includes four foldable and foldable integrated expandable mechanisms with cushioning characteristics, and the four foldable and retractable integrated mechanisms with cushioning characteristics The fully deployable mechanism is uniformly arranged on the outer wall of the bottom of the rocket body 7 along the circumferential direction, and each of the foldable and retractable integrated deployable mechanisms with cushioning properties includes a landing leg 1, a buffer assembly, a pneumatic drive assembly and a locking Assembly, one end of the landing leg 1 is hinged to the side wall at the bottom of the rocket body 7, the upper surface of the other end of the landing leg 1 is connected to the rocket body 7 through the buffer assembly, and one end of the locking assembly is conn...

specific Embodiment approach 2

[0014] Specific implementation mode two: combination figure 1 with figure 2 Describe this embodiment, the buffer assembly of a pneumatically driven recoverable rocket landing support mechanism described in this embodiment includes a hydraulic buffer 2, a buffer support rod 3 and a rocket body support rod 4, the bottom of the hydraulic buffer 2 and the landing leg 1 The upper surface of the other end is hinged, one end of the buffer support rod 3 is fixedly connected to the piston of the hydraulic buffer 2, the other end of the buffer support rod 3 is hinged to one end of the arrow body support rod 4, and the other end of the arrow body support rod 4 One end is hinged with the outer wall of the rocket body 7 . The buffer support rod 3 reasonably distributes the structural strength by adopting a Y-shaped structure. Other components and connections are the same as those in the mechanism implementation mode 1.

specific Embodiment approach 3

[0015] Specific implementation mode three: combination figure 1 with figure 2 Describe this embodiment. The locking assembly of a pneumatically driven recoverable rocket landing support mechanism described in this embodiment includes a driving intermediate link 8, an auxiliary intermediate link 9 and a locker 10. One end of the driving intermediate link 8 is connected to the The bottom of the rocket body 7 is hinged, the other end of the driving intermediate link 8 is hinged with one end of the auxiliary intermediate link 9, the other end of the auxiliary intermediate link 9 is hinged with the other end of the buffer support rod 3, and the locking device 10 is installed on The connection between the driving intermediate link 8 and the auxiliary intermediate link 9. Other compositions and connections are the same as those in Embodiment 1 or 2.

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Abstract

A pneumatically driven recoverable rocket landing support mechanism relates to a rocket landing support mechanism, in particular to a pneumatically driven recoverable rocket landing support mechanism. The invention aims to solve the problems of poor stability of the traditional rocket support mechanism and large launching air resistance. Each of the folding-folding integrated deployable mechanisms with cushioning characteristics of the present invention includes landing legs, buffer components, pneumatic drive components and locking components. One end of the landing legs is hinged to the side wall at the bottom of the rocket body. The upper surface of the other end of the leg is connected to the rocket body through the buffer assembly, one end of the locking assembly is connected to the buffer assembly, the other end of the locking assembly is hinged to the outer wall of the bottom of the rocket body, and the pneumatic The driving assembly is connected with the locking assembly, and the pneumatic assembly is hinged with the outer wall of the rocket body. The invention belongs to the field of aerospace.

Description

technical field [0001] The invention relates to a rocket landing support mechanism, in particular to a pneumatically driven recoverable rocket landing support mechanism, which belongs to the field of aerospace. Background technique [0002] In recent years, recyclable rockets have developed rapidly. Since conventional rockets will not be recycled after completing the launch mission, the main parts of the rocket will be damaged when they fall to the ground and cannot be used here. The cost of rocket fuel only accounts for a small part of the cost of rocket launch. For recoverable rockets, the landing support mechanism is a key technology in the field of recyclability. The soft landing of the rocket is realized through the landing support mechanism, and through the ground Simple maintenance and refueling enable re-launch, thereby achieving rapid response of the rocket, improving launch efficiency and reducing launch costs. Contents of the invention [0003] In order to solv...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/62
CPCB64G1/62
Inventor 于海涛高海波田保林刘振李楠丁亮邓宗全
Owner HARBIN INST OF TECH
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