A kind of chip satellite group and its dispersing method

Abstract

The invention discloses a chip satellite group and a dispersing method thereof, comprising a plurality of chip satellites, the chip satellites are connected by a controllable rotation connection mechanism, and the head-end chip satellites in the chip satellite are connected with the chip satellites by the controllable rotation connection mechanism for dispersing The controllable rotation connection mechanism includes a controllable rotation mechanism, and both ends of the controllable rotation mechanism are provided with open and close jaws; the open and close jaws are used to connect the chip satellite or the chip satellite spreader. The initial attitude requirement of each chip satellite can be achieved after the dispersion is realized, and the initial attitude disturbance of each chip satellite is reduced, and the stability of the initial attitude after the dispersion of the chip satellite is realized.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, relates to a chip satellite group, and also relates to a method for dispersing the above-mentioned chip satellite group. Background technique [0002] As a kind of micro-satellite, the chip satellite has received wide attention from the aerospace industry once it was proposed. Thanks to the development of chip technology, some tasks that could only be performed by large spacecraft in the past can now be replaced by only one or a few small chip satellites; and compared with traditional large spacecraft, chip satellites are being manufactured And the launch cost has a great advantage. Due to the limitation of its own size and quality, the traditional attitude determination and adjustment methods cannot be applied or are subject to considerable restrictions on chip satellites. [0003] At present, for the attitude adjustment of chip satellites, there are two different methods: ...

AI Technical Summary

Problems solved by technology

However, the internal moment attitude orbit adjustment method also has some unavoidable defects of its own.

On the one hand, the internal torque attitude adjustment method will be limited by its own energy reserve. The energy carried by the chip satellite itself is often very limited, and it may be difficult to obtain a good recharging environment during the orbit. Therefore, using internal torque to adjust the attitude of the chip satellite will be difficult. The working life of the satellite is greatly reduced, and the frequency and magnitude may not be able to meet the attitude adjustment requirements

On the other hand, in the process of internal torque attitude orbit adjustment based on angular momentum, the attitude adjustment of the satellite body must be accompanied by changes in the relative structure of the satellite, and limited by the range of satellite structure changes, the space for attitude adjustment of the satellite body is often limited. Moreover, it is very difficult to ensure that all components of the satellite are kept in a reasonable attitude layout, and complex and cumbersome control and optimization are required.

[0005] To sum up, the attitude adjustment methods and capabilities of the chip satellite itself are very limited. The attitude adjustment method relying on external environmental torque is limited by the initial state conditions and may not be able to start at all; the attitude adjustment method relying on internal torque Limited by the range limitation and load energy limitation of satellite structure changes, it may not be able to meet the needs of attitude adjustment

Therefore, on the one hand, the randomly scattered chip satellites are likely to be unable to adjust their attitude to the initial attitude required for their work; on the other hand, when the initial attitude of the chip satellite is seriously deviated or disturbed, it is often impossible to achieve the stability of its own attitude.

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