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Landing leg pressing, unfolding and locking device of lander

A technology for locking devices and landing legs, which is applied in the direction of aerospace vehicle landing devices, shock absorbers, and shock absorbers. The effect of low frictional resistance

Inactive Publication Date: 2013-07-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The structure of the mechanism is complex and the reliability is not high

Method used

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  • Landing leg pressing, unfolding and locking device of lander
  • Landing leg pressing, unfolding and locking device of lander

Examples

Experimental program
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Effect test

Embodiment Construction

[0013] as attached figure 1 Shown is the schematic structural view of the compression and deployment locking device of the present invention. The inner cylinder of the auxiliary pillar of the lander is installed in the outer cylinder 1 of the pillar, and the inner cylinder top cover 14 is installed on the inner pillar cylinder 6, and the turntable 15 chamber and the locking spring chamber 16 are formed between the pillar inner cylinder 6 and the inner cylinder top cover 14, and the pillar The wall of the outer cylinder 1 is machined with two circles of trumpet-shaped small holes along the axial direction, and each circle has four holes, which are respectively used for locking before deployment and locking after deployment. A stepper motor 12 is fixedly installed on the top cover 14 of the inner cylinder, and the motor shaft extends into the turntable chamber 15 to be connected with the shaft. The locking spring chamber 16 is equipped with a radial spring 4 and a latch 2. One e...

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Abstract

The invention relates to a landing leg pressing, unfolding and locking device of a lander, which belongs to the landing leg unfolding and locking mechanism. The device comprises an outer support cylinder (1) and an inner support cylinder (6); the top part of the inner support cylinder (6) is provided with a top inner cylinder cover (14), a mounting chamber is formed between the top part of the inner support cylinder (6) and the top inner cylinder cover (14); a stepper motor (12) is arranged above the top inner cylinder cover (14) and is connected with the top part of the outer support cylinder (1) through an axial spring (13); a turntable (11) is arranged on a motor shaft and is connected with a bolt (2) through a radial spring (4) which penetrates through a locking spring chamber (16); and the outer support cylinder (1) is also provided with an upper locking hole (3) which is matched with the bolt (2) and is used for locking the inner support cylinder before the landing leg is unfolded and a lower locking hole (7) which is matched with the bolt (2) and is used for locking the inner support cylinder after the landing leg is unfolded. The invention has the advantages of simple mechanism and high reliability.

Description

technical field [0001] The invention belongs to a mechanism for deploying and locking the landing legs of an interstellar lander landing device. technical background [0002] The landing legs are an important part of the lander, providing support for the lander to land stably on the interstellar surface. In order to ensure the stability of the lander, it is required to have a large support area after landing. However, due to the limitation of the vehicle, it is required that the landing legs can be folded and compressed in the launch section. After flying to a certain orbit, the compression device is unlocked, and the landing legs are unfolded and locked under the action of the expansion drive device. [0003] The systematic research and application of space unfolding and locking mechanism began in the late 1970s, but developed rapidly. Many novel and creative concepts of unfolding and locking mechanism have been proposed, and some have been applied. NASA of the United Sta...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/62B64C25/00F16F9/00
Inventor 聂宏陈金宝李立春张则梅万峻麟廖俊侠
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS