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Integrated control system of landing and rising spacecraft

A control system and spacecraft technology, which is applied to aerospace vehicles, aerospace vehicle guidance devices, aircraft, etc., can solve problems such as poor technical reliability and outdated product technology level, to avoid common cause effects and ensure real-time uninterrupted , The effect of reducing fuel consumption

Active Publication Date: 2020-12-04
BEIJING INST OF CONTROL ENG
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem to be solved by the present invention is: aiming at the problems of poor technical reliability and obsolete product technical level of the existing landing and ascent mission control system, combined with new requirements such as unmanned landing needs to independently identify safety zones, a landing and ascent space flight control system is proposed. integrated control system

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  • Integrated control system of landing and rising spacecraft

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Embodiment Construction

[0029] An integrated control system for landing and ascending spacecraft, suitable for unmanned landing and ascending missions of extraterrestrial celestial bodies, specifically including a master controller, a slave controller, a landing image sensor, a distance measurement sensor, a speed measurement sensor, a star sensor The landing and ascending spacecraft control system adopts a layered structure. The top layer is equipped with a master controller, and the bottom layer is equipped with a slave controller. The master controller is set in the ascender part, and the slave controller is set in the lander part. Among them:

[0030] The spacecraft includes an ascender and a lander. The main controller, star sensor and inertial measurement components are installed on the ascender, and the slave controller and other sensors are installed on the lander. Specifically:

[0031] The master controller conducts navigation, guidance and control for the whole flight process of the spacecr...

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Abstract

The invention relates to an integrated control system of a landing and rising spacecraft. The system is provided with a hierarchical control structure of a master controller and a slave controller, issuitable for executing a landing and rising task of unmanned autonomous obstacle avoidance of an extraterrestrial celestial body, and specifically comprises the master controller, the slave controller, a topographic survey sensor, a distance measurement sensor, a speed measurement sensor and a star sensor. High-reliability control can be achieved in the ascending and landing process of the spacecraft, part of products can be discarded in the ascending process, the weight of the system is reduced, the problems that a traditional spacecraft control framework is poor in reliability and large inweight are solved, and the reliability requirement and the weight constraint are both considered.

Description

technical field [0001] The invention relates to an integrated control system for landing and ascending spacecraft, which belongs to the technical field of spacecraft control. Background technique [0002] With the continuous development of unmanned deep space exploration space missions, it is necessary to complete the landing and ascent control of extraterrestrial celestial bodies simultaneously in one mission. For example, the "landing and ascent assembly" spacecraft of my country's Chang'e-5 mission needs to complete the lunar landing and ascent into orbit tasks. [0003] Both the ascent and landing missions consume a lot of fuel. The landing process needs to reduce the speed of the spacecraft around the moon from about 1.7km / s to 0, while the ascent mission needs to increase the speed of the spacecraft from 0 to about 1.7km / s. Compared with conventional spacecraft, the landing and ascent mission spacecraft must reduce the dry weight of the system in order to meet the s...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/36
CPCB64G1/24B64G1/36B64G1/361
Inventor 于萍张洪华杨洁王佳王华强赵宇杨巍于洁王志文
Owner BEIJING INST OF CONTROL ENG
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