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A large-span, foldable and reusable rocket landing buffer structure

A buffer structure and large-span technology, which is applied to the landing device of aerospace vehicles and the system for spacecraft to return to the earth's atmosphere, etc., can solve the design content of no landing buffer mechanism, difficulty in providing large span and high folding deformation ratio, etc. problems, to achieve the effect of improving the operability and adaptability of installation and debugging, improving reusable performance, and small aerodynamic shape

Active Publication Date: 2021-07-13
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, most of the existing patents on the landing buffer structure of reusable launch vehicles are conceptual schemes or partial small structural designs. There is no detailed design content for the overall landing buffer mechanism, or it is difficult to provide large span and high folding deformation ratio. design content

Method used

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  • A large-span, foldable and reusable rocket landing buffer structure
  • A large-span, foldable and reusable rocket landing buffer structure
  • A large-span, foldable and reusable rocket landing buffer structure

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Embodiment Construction

[0037] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0038] The present invention is a large-span, foldable and reusable rocket landing buffer structure, comprising: a main leg 1, two auxiliary legs 2 and a landing plate 3; The upper joints are connected to the mounting seats of the rocket body through the joint bearings provided on them respectively, and the joint bearings are placed on the upper joints and the lower joints of the main leg 1 and the auxiliary leg 2; a rotating shaft is arranged on one side of the landing pad 3; The lower joint at the other end and the lower joint at the other end of each auxiliary leg 2 are connected to the same rotating shaft on the landing pad 3 through the joint bearings respectively provided on them. Such as Figure 9 As shown, the other side of the landing pad 3 is provided with a rubber cushion, which can be in contact with the ground cushion wh...

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Abstract

The present invention is a large-span, foldable and reusable rocket landing buffer structure, comprising: a main leg (1), two auxiliary legs (2) and a landing plate (3); an upper joint at one end of the main leg (1) The upper joint at one end of each auxiliary leg (2) is connected to the mounting seat of the rocket body through the joint bearing provided on each side, and joint bearings are placed on the upper joint and the lower joint of the main leg (1) and the auxiliary leg (2) One side of the landing pad (3) is provided with a rotating shaft; the lower joint at the other end of the main leg (1) and the lower joint at the other end of each auxiliary leg (2) are connected to the landing pad (3) ) on the same reel. The other side of the landing plate (3) is provided with a rubber buffer pad, which can be in contact with the ground buffer when the rocket lands slowly.

Description

technical field [0001] The invention relates to a large-span, foldable and reusable rocket landing buffer structure, which belongs to the technical field of mechanical combination load-bearing buffer devices with high light weight, high efficiency and good operability. Background technique [0002] The launch vehicle is the main tool for human beings to enter space. The high launch cost limits the development and utilization of space for human beings. The one-time use of the launch vehicle is the main reason for the high launch cost. Therefore, the reuse of launch vehicles is of great significance for reducing launch costs and improving the ability of humans to enter space. For the vertical round-trip reusable launch vehicle, the landing process is the last step of the return of the launch vehicle, and it is also the key to the overall plan of the rocket's vertical return technology. A large-span, foldable landing buffer structure for reusable rockets is designed, which can...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/62
CPCB64G1/62
Inventor 张宏剑张希章凌陈友伟王辰吴义田王雪梅邓新宇李长龙张雪峰闫冰
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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