Chip star attitude orbit control system and method based on hybrid action of internal and external power

Abstract

The invention discloses a chip satellite attitude orbit control system under action of internal and external force mixing. A control system comprises a chip satellite, a flexible rod member made of flexible drivable materials, and an external force moment generator. After the external force moment generator is connected with the flexible rod member, the flexible rod member is connected with the main body of the chip satellite, and the flexible rod member is combined with the external force moment generator to act on chip satellite attitude orbit control. By adopting cooperation of two ways, the attitude orbit adjustment of the chip satellite is realized, and two different attitude adjusting mechanisms are serially connected together. By adopting the cooperation of the two ways, the attitude orbit adjustment of the chip satellite is realized, and the adjustment of the chip satellite attitude is carried out effectively by using the external force moment, and the capability of the attitude adjustment is maintained anytime, and therefore the consumption of the own energy of the chip satellite is reduced, the structural layout of the attitude orbit control is simplified, a control theory is simplified, and the efficiency of the attitude adjustment is improved.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a chip star attitude orbit control system and method with internal and external power hybrid effects. Background technique [0002] As a kind of microsatellite, chip star has attracted wide attention in the aerospace industry once it was proposed. Thanks to the development of chip technology, some missions that could only be performed by large spacecraft in the past can now be replaced by only one or a few small chip stars; It has a great advantage in launch cost. Due to the limitations of its own size and mass, traditional attitude determination and adjustment methods (such as momentum wheels, etc.) cannot be applied or are subject to considerable restrictions on chip stars. [0003] At present, for the problem of attitude adjustment of the chip star, there are two different methods of external environment torque and internal torque, both of which have a certain degree...

AI Technical Summary

Problems solved by technology

Compared with the external torque, the internal torque attitude orbit control method has the advantage of not being affected by the external environment. However, the internal torque attitude orbit adjustment method also has some unavoidable defects.

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

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; In addition, it is very difficult to ensure that all components of the satellite maintain a reasonable attitude layout, and complex and cumbersome control and optimization are required.

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