Landing buffer device of reusable launch vehicle

A buffer device and carrier technology, applied in the field of aerospace vehicles, can solve problems such as landing instability and large ground impact load, and achieve the effects of improving absorption capacity, avoiding matrix damage, and improving outrigger handling and stability.

Active Publication Date: 2018-05-01
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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Problems solved by technology

[0004] During the landing process of the existing reusable vehicle, the complex aerodynamic environment under different meteorological conditions and the influence of the geographical environment conditions of the lar

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  • Landing buffer device of reusable launch vehicle
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  • Landing buffer device of reusable launch vehicle

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Embodiment Construction

[0026] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0027] The present invention aims at the requirements of reusable carrier's landing action and environmental adaptability, and designs and provides a reusable carrier's landing buffer device, which has four-leg deformation support, centralized control, independent drive, joint attitude adjustment, parallel It has the characteristics of quadrilateral connecting rod deformation and high cushioning, and has many advantages such as repeated folding and folding deformation of four legs, and preparation for supporting the landing of the carrier.

[0028] A landing buffer device for a reusable carrier, comprising an arrow body 1 and four outriggers 2; wherein, the arrow body 1 is a column structure placed vertically; On the side wall at the bottom end of the shaft; the four outriggers 2 move at the same time, and rotate along the connection between the...

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Abstract

A landing buffer device of a reusable launch vehicle relates to the field of space launch vehicles and comprises a rocket body and four support legs, wherein the rocket body is of a vertically-arranged cylinder structure; the four support legs are symmetrically fixedly mounted to the side wall of the axial bottom end of the rocket body in a mutually perpendicular manner; the four support legs actsimultaneously and rotate along the joint between the support legs and the side wall of the rocket body to achieve the folding or unfolding of the four support legs; the diameter of the rocket body is120-140 mm; the height of the rocket body is 510-530 mm; the total mass of the rocket body is 1.2-1.3 kg; and the included angle between the rocket body and the vertical direction after the landing of the rocket body is no more than 10 degrees. The landing buffer device of the reusable launch vehicle is capable of realizing the repeated folding, unfolding and deformation by the four-legged motionto make support preparation for the landing of the launch vehicle, and is of great significance to the fields of adaptation to a landing motion sequence, self-adaptive attitude adjustment, stable landing achievement, efficient buffer against ground impact and so forth of the landing device for the reusable launch vehicle.

Description

technical field [0001] The invention relates to the field of aerospace vehicles, in particular to a landing buffer device for a reusable vehicle. Background technique [0002] The reusable vehicle can not only realize the large-scale recovery of multi-sub-level systems, reduce the hardware cost of space vehicles, but also greatly simplify the ground support and equipment, significantly reduce the cost of ground operations, and then achieve fast response, high density, and high maneuverability. , is an ideal space vehicle for space vehicles such as weapons and satellites to meet the needs of aerospace emergency operations, emergency disaster monitoring, and information support for emergency rescue and disaster relief. The landing buffer device is an important part of the reusable vehicle, which puts forward high requirements on the law of movement, buffer design and outrigger control. [0003] After completing the flight mission, the reusable vehicle relies on aerodynamic se...

Claims

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Application Information

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IPC IPC(8): B64G1/62F42B15/00
CPCB64G1/62F42B15/00
Inventor 张雪峰季宝锋李雄魁闫冰张希王婧超张宏剑王世勋郭岳孟德浩闫路林川张超颖匡格平高艺航
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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