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A landing support mechanism of a pneumatic deployment and folding repeat vehicle

A technology of support mechanism and support legs, applied in the field of repeated carrier landing support mechanism, can solve problems such as instability and failure of recovery work, and achieve the effects of high reliability, multiple use, and high landing stability

Active Publication Date: 2019-01-25
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention solves the problem that the existing support mechanism used for the soft landing of the carrier may be in an unstable state due to the influence of the first-order vibration, resulting in the failure of the recovery work, and further provides a pneumatically deployed and folded repeat carrier landing support mechanism

Method used

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  • A landing support mechanism of a pneumatic deployment and folding repeat vehicle
  • A landing support mechanism of a pneumatic deployment and folding repeat vehicle
  • A landing support mechanism of a pneumatic deployment and folding repeat vehicle

Examples

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specific Embodiment approach 1

[0022] Specific implementation mode one: as figure 1 and figure 2 As shown, the pneumatic deployment, folding and repeating carrier landing support mechanism of this embodiment includes four sets of folding, locking, and buffering integrated mechanisms, and the four sets of folding, locking, and buffering integrated mechanisms are uniformly arranged on the lower part of the rocket body 6 along the circumferential direction. The integrated folding, locking and buffering mechanism includes the landing support leg 1, the hydraulic buffer 2, the buffer support link 3, the auxiliary support link 4, the cylinder drive link 5, the cylinder locking mechanism 7, the cylinder 8 and the foot pad 9 , the upper end of the landing support leg 1 is rotatably connected with the outer edge of the lower end of the rocket body 6, the lower end of the landing support leg 1 is provided with a foot pad 9, the hydraulic buffer 2 is installed on the lower part of the buffer support link 3, and the b...

specific Embodiment approach 2

[0026] Specific implementation mode two: as image 3 , Figure 4 and Figure 5 As shown, the cylinder locking mechanism 7 of this embodiment includes a locking mechanism support seat 7-1, a locking driving spring 7-3, a locking slider 7-5, a limit driving elastic element 7-6, two locking Drive rod 7-9 and two limit baffles 7-10; Cylinder 8 is installed on the locking mechanism support seat 7-1, and the lower end of cylinder 8 is rotationally connected with locking mechanism support seat 7-1, and two limit stops The baffle plate 7-10 is arranged on the outside of the two locking drive rods 7-9, the one end of the cylinder drive connecting rod 5 is provided with a connecting rod 7-8 perpendicular thereto, and one end of the two locking drive rods 7-9 Rotately connected with the connecting rod 7-8, the other end of the two locking drive rods 7-9 can slide in the inner guide groove 7-1-1 of the locking support seat 7-1 and be locked by the inner guide groove 7-1-1. 1, the two s...

specific Embodiment approach 3

[0028] Specific implementation mode three: as image 3 and Figure 5 As shown, the cylinder locking mechanism 7 of this embodiment also includes a cylinder pressure plate 7-2 and a screw 7-4; the cylinder 8 is fixed through the cylinder pressure plate 7-2 and the screw 7-4 arranged on the locking support seat 7-1 On the locking support seat 7-1. Designed in this way, it is convenient to install the cylinder 8 and be installed on the locking support seat 7-1. Other components and connections are the same as those in the second embodiment.

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Abstract

A landing support mechanism of a pneumatic deployment and folding repeat vehicle relates to a landing support mechanism. The invention solves the problem that the prior supporting mechanism used for the soft landing of the vehicle may be unstable due to the influence of the first-order vibration, which leads to the failure of the recovery work. The upper end of the landing support leg is rotatablyconnected with the lower end of the main body of the rocket, the hydraulic damper is mounted on the lower part of the damper support connecting rod, the lower end of the buffer support connecting rodis rotatably connected with the foot pad, the upper end of the damper support connecting rod is rotatably connected with the lower end of the auxiliary support connecting rod through a first rotatingshaft and a damper bearing, The upper end of the auxiliary support connecting rod is rotatably connected with the lower part of the rocket main body, the middle and lower parts of the auxiliary support connecting rod are connected with one end of the cylinder drive connecting rod through a cylindrical pin, the other end of the cylinder drive connecting rod is connected with one end of the cylinder through a cylinder locking mechanism, and the other end of the cylinder is rotatably connected with the lower end of the rocket main body. The present invention is used for aerodynamically deployinga stowed repeat vehicle for landing.

Description

technical field [0001] The invention relates to a landing support mechanism for a carrier, in particular to a landing support mechanism for a carrier that is deployed and folded repeatedly by pneumatic drive. Background technique [0002] At present, rockets are mainly used for one-time use. After the rocket mission is completed, it cannot be reused after it lands freely. However, the main components of the rocket are expensive and the fuel cost is relatively low. The resulting waste is a major factor hindering the rapid response of the rocket. Rocket recovery can greatly reduce launch costs. The support mechanism is a key technology in vertical take-off and landing carrier technology. The support legs and buffers in the support mechanism can achieve a soft landing of the vehicle, and it can be reused through subsequent maintenance and fuel replenishment. [0003] The existing support mechanism used for landing has a small support circle diameter and excessive air resistance...

Claims

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Application Information

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IPC IPC(8): B64G1/62
CPCB64G1/62
Inventor 高海波于海涛田保林刘振李楠丁亮邓宗全
Owner HARBIN INST OF TECH