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Attitude-adjustable moon soft lander

A technology of soft lander and lander, which is applied to the landing device of aerospace vehicles, the system of spacecraft returning to the earth's atmosphere, etc., and can solve problems such as attitude adjustment and control of payloads that are not considered

Active Publication Date: 2013-10-16
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] This structure is mainly to solve the problem of attitude stability after landing, but still does not consider the problem of attitude adjustment and control of the payload

Method used

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  • Attitude-adjustable moon soft lander
  • Attitude-adjustable moon soft lander
  • Attitude-adjustable moon soft lander

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Embodiment Construction

[0029] The present invention will be further described below in conjunction with the accompanying drawings.

[0030] The lunar soft lander of the present invention, as figure 1 As shown, it includes the lander main body 1 and the buffer leg assembly 2; the lander main body 1 is a box structure, the bottom surface is closed, and the interior is installed such as image 3 The attitude adjustable payload is shown onboard platform 3 and is used to accommodate the payload. There are 24 sets of buffer leg assemblies, which are evenly installed on the peripheral side wall of the main body of the lander.

[0031] Each set of buffer leg assemblies 2 above is composed of a foot pad 201, a main buffer support leg 202 and two sets of auxiliary buffer legs 203, such as figure 2 As shown, the main buffer support leg 202 includes two parts, an upper strut 202a and a lower strut 202b. The upper strut 202a is made of aluminum alloy, and the interior is filled with a honeycomb buffer struct...

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Abstract

The invention discloses an attitude-adjustable moon soft lander which comprises a lander body and buffering leg components, wherein the buffering leg components are uniformly mounted on the circumferential side wall of the lander body and can realize stable landing. An attitude-adjustable effective load carrying platform is mounted inside the lander body and adopts a four-degree-of-freedom parallel connection platform which comprises an upper platform, a lower platform and five electric push rods connected with the upper platform and the lower platform, wherein displacement sensors which are used for acquiring a distance between the electric push rods and the upper and lower platforms in real time are mounted at body ends of the five electric push rods; a double-shaft tilt angle sensor used for acquiring attitude information of the upper platform is mounted on the upper platform; and the five electric push rods are controlled to realize attitude adjustment of the moon soft lander. Solar panels used for charging the soft lander are mounted on the side walls of the soft lander body through torsional springs, and the torsional springs and electromagnets mounted on the side walls of the soft lander body are used for unfolding and folding the solar panels. The attitude-adjustable moon soft lander has the benefits as follows: soft landing can be stably realized, and the attitude can be adjusted.

Description

technical field [0001] The invention relates to a lunar soft lander, specifically, a lunar soft lander with an attitude-adjustable carrying platform. Background technique [0002] There are two ways for lunar probes to land on the lunar surface: "hard landing" and "soft landing". "Hard landing" means that the probe flies to the surface of the moon at high speed and collides with the surface of the moon. Although this type of probe can detect the moon at close range, it has a short working time and can only do so in a short period before impacting the surface of the moon. To explore the moon in time; "soft landing" refers to the use of buffer rockets and other deceleration measures to reduce the landing speed of the probe when it is approaching the lunar surface, so that the probe lands on the lunar surface at a very low speed, and at the same time Using the landing buffer mechanism to absorb the landing impact energy, the probe can conduct scientific exploration activities ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/62
Inventor 李昭莹包泽宇
Owner BEIHANG UNIV
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