Control method for nano satellite magnetic torquer space temperature compensation attitude

Abstract

The invention discloses a control method for a nano satellite magnetic torquer space temperature compensation attitude. The control method specifically comprises the following steps that first, a system and an orbital coordinate system are built separately; second, in the despinning process, nano satellite attitude parameters and magnetic torquer parameters are obtained, and a despinning control law based on temperature compensation is built; third, in the capturing process, nano satellite attitude parameters and magnetic torquer parameters are obtained and subjected to optimizing treatment, and accordingly an attitude capturing control law based on temperature compensation is built; and fourth, a magnetic torquer is controlled by means of the despinning control law based on temperature compensation and the attitude capturing control law based on temperature compensation so as to control the satellite attitude. The control precision of the satellite attitude is improved by adopting a temperature compensation method, so that the control period is shortened, and validity is verified; and compared with a nano satellite system without temperature control, by using the method, good engineering application prospects are achieved, and wide ideas are supplied to low-cost microsatellite development.

Description

【Technical field】 [0001] The invention belongs to the technical field of satellite attitude control, and in particular relates to a space temperature compensation attitude control method of a magnetic moment device of a nanosatellite. 【Background technique】 [0002] Because microsatellites have a series of advantages such as light weight, small size, low cost, and short development cycle, they can play an important role in the fields of communication, remote sensing, military affairs, planetary exploration, engineering technology experiments, etc., and have potential strategic value and market prospects. The development of satellites is very hot in the world. At the same time, the development of micro-satellites does not require the support of large-scale system facilities, and can be carried out in laboratories of universities and scientific research institutes, which is conducive to reducing the cost of research and development as a whole. Micro-satellites are not only va...

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a nano-satellite magnetic torque device space temperature compensation attitude control method to solve the problem that the existing magnetic torque device is easily affected by temperature on satellite attitude control

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