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Mars exploration landing buffer device

A buffer device, the technology of Mars, is applied in the directions of the landing device of the spacecraft, the system of the spacecraft returning to the earth's atmosphere, etc. It can solve the problem of weak resistance to horizontal speed shock, and achieve improved motion stability, small impact overload, and resistance to impact. The effect of high impact velocity

Active Publication Date: 2015-05-20
BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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  • Description
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AI Technical Summary

Problems solved by technology

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, and solve the problem that the existing inverted triangle outrigger structure landing buffer device has weak resistance to horizontal velocity impact during the planetary landing detection mission in the atmosphere

Method used

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Embodiment Construction

[0014] The invention provides a solution to the buffer structure, unfolding and locking mode, folding and unfolding configuration of the Mars exploration and landing buffer device. The buffer adopts a cantilever structure based on aluminum honeycomb buffer; the deployment and locking of the landing buffer device are driven by the deployment frame. The main body of the lander is directly connected; the folding and unfolding configuration adopts the upturning type, that is, the main legs are turned outwards and upwards and fixed and installed through the pyrotechnic unlocker. After unlocking, the main legs are driven outwards and downwards by the deployment frame Release and lock, wherein the pyrotechnic unlocker includes an unlocking bolt, a pin puller, and a separation nut.

[0015] Such as figure 1 Shown is the landing buffer device for Mars exploration, which consists of three or four sets of symmetrically distributed landing legs, and each set of landing legs consists of a...

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Abstract

A Mars exploration landing buffer device comprises three or four sets of landing legs symmetrically distributed on the periphery of a Mars exploration lander body mechanism. Each set of landing legs is composed of a foot pad (1), a main leg (2), an auxiliary leg (3) and an unfolding locking mechanism (4), wherein the foot pad (1), the main leg (2), the auxiliary leg (3) and the unfolding locking mechanism (4) of the same set of landing legs are connected with one another through universal joints or rotating shafts, and the main leg (2), the auxiliary leg (3), the unfolding locking mechanism (4) of each set of landing legs and the lander body mechanism form a four-bar mechanism so that the landing buffer device can be overturned outwards up and down. The upturning folding structure enables the mass center of the lander to move forwards, the movement stability of the lander in an entering stage is improved, in addition, energy is absorbed through own movement deformation of buffer cellular structures in the main legs (2) and the auxiliary legs (3), soft landing of the lander is achieved, and the device can be applied to design of soft landing buffer mechanisms for landing detection on a planet or a satellite with atmosphere.

Description

technical field [0001] The invention belongs to the technical field of soft landing buffers for landing exploration missions on the surface of Mars, and relates to an overall configuration and layout scheme of a mechanical landing buffer mechanism device. Background technique [0002] With the development of my country's space technology, lunar exploration has achieved world-renowned achievements. The exploration of Mars and other planets and asteroids is becoming a research hotspot, and surface landing detection is the most effective way of detection. There have been successful cases of planetary landing detection on Mars and Venus abroad, and the United States has accumulated a lot of engineering experience in Mars landing detection. The landing buffer methods used in planetary surface landing exploration mainly include airbag buffer and mechanical landing buffer device. [0003] When performing landing detection on the surface of a planet with an atmosphere, the landing ...

Claims

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Application Information

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IPC IPC(8): B64G1/62
Inventor 蒋万松王永滨陈书通王磊
Owner BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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