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A posture correcting device for a Mars landing module

A landing module and attitude technology, which is applied to the landing device of the aerospace vehicle, the system for the aerospace vehicle to return to the earth's atmosphere, etc., can solve the problem of the volume, weight, and energy constraints of the built-in cylindrical landing module, and the unsatisfactory initial landing attitude of the landing module. Attitude requirements and other issues, to achieve the effect of light weight, small volume, simple structure

Active Publication Date: 2016-04-20
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

[0003] Due to the constraints of the launch window and the existing carrying capacity, the weight of the lander in the Mars global remote sensing probe is only 60kg, and the volume, weight, and energy of the built-in cylindrical landing capsule are strictly limited; at the same time, due to the topographical characteristics of the landing site And the landing process is uncertain, the initial landing attitude of the landing module may not meet the attitude requirements of the specified face-up attitude, and later adjustments are required

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  • A posture correcting device for a Mars landing module
  • A posture correcting device for a Mars landing module
  • A posture correcting device for a Mars landing module

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Embodiment Construction

[0027] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0028] The invention proposes an attitude righting device suitable for the landing module of my country's first Mars soft landing detection. The posture righting device is mainly composed of a base plate 1, a support 2, a connecting shaft 3, a torsion spring 4, a centralizing ring 5 and a compression release device 6; the compression release device releases the compressed torsion spring through the pyrotechnics, thereby The centering ring is driven to realize the posture centering function of the ...

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Abstract

The invention provides a device for centering postures of a Mars landing capsule. The device comprises a base plate (1), a support (2), a connecting shaft (3), a torsional spring (4), a centering ring (5) and a compressing and releasing device (6). Under the conditions that the size, the weight and the energy supply of the device are limited strictly, an initiating explosive device acts to release the compacted torsional spring, and therefore the centering ring is driven to center the postures of the Mars landing capsule. The device for centering the postures of the Mars landing capsule has the advantages of being simple in structure, safe, reliable, small in size and light in weight. As the effective means for guaranteeing the correct postures of the landing capsule on the Mars, the device for centering the postures of the Mars landing capsule can be directly applied to development for a landing capsule in the first Chinese Mars landing detecting task, and can also provide reference for design of Chinese follow-up small-scale planet landing capsules.

Description

technical field [0001] The invention relates to a Mars landing system, in particular to a posture correcting device for a Mars landing module. Background technique [0002] my country plans to launch a Mars global remote sensing probe in December 2015 to realize Mars orbiting and carry out Mars global remote sensing exploration; at the same time, it will carry out Mars landing verification missions to verify Mars entering deceleration landing related technologies. [0003] Due to the constraints of the launch window and the existing carrying capacity, the weight of the lander in the Mars global remote sensing probe is only 60kg, and the volume, weight, and energy of the built-in cylindrical landing capsule are strictly limited; at the same time, due to the topographical characteristics of the landing site And the landing process is uncertain, the initial landing attitude of the landing module may not meet the specified face-up attitude requirements, and later adjustments are...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/62
Inventor 侯建文陆希徐亮
Owner SHANGHAI SATELLITE ENG INST
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