System and method for tracking and controlling gestures of spacecraft

Abstract

The invention discloses a system and a method for tracking and controlling gestures of a spacecraft. The system comprises a gesture measurement component, a gesture controller and a control executive component, wherein the gesture measurement component is used for acquiring gesture information of the spacecraft and outputting a signal having a functional relation with gesture parameters; the gesture controller is used for performing operation, correction and amplification in accordance with a set control law according to the information acquired by the gesture measurement component and a guidance command, and outputting a control signal to the control executive component; the control executive component comprises a magnetic torquer, a bias momentum wheel and a tilt switch control unit; and the tilt switch control unit is used for controlling the rotating speed control quantity of the bias momentum wheel. The system and the method skillfully achieve the fast control ability of a star pitch axis and simultaneously a high-precision complex gyroscopic instrument is not required in use, thus the dependence on angular speed information of the system is remarkably reduced.

Description

technical field [0001] The invention belongs to the research field of spacecraft control technology, and relates to a spacecraft attitude tracking control system and method, in particular to a novel attitude tracking control system and method suitable for offset momentum small satellites. Background technique [0002] Since the 1990s, micro-miniature application satellites have become a research hotspot in aerospace technology, showing broad application prospects in many fields. [0003] The satellite attitude control system is the core component of the satellite system, and its technical level directly determines the application tasks and on-orbit functions that the satellite can undertake, such as communication, imaging, detection, space formation, accompanying flight, etc. In order to complete these tasks correctly, efficiently, and reliably, it is required to orient the satellite attitude correctly in a given space direction, or to ensure that the payload on the satellit...

AI Technical Summary

Problems solved by technology

The control system implemented by this scheme is simple in composition, low in quality and power consumption, but the disadvantages are: the bias momentum wheel only plays a stabilizing role, and its internal usually has an infinite current link, and the characteristics of speed regulation and torque output are short-term spikes, which are difficult to control. To achieve effective attitude adjustment, the application efficiency is low, and the attitude stability accuracy is not high; the control torque of the magnetic torque device system is small, the attitude stability and maneuvering control capabilities are weak, and it cannot meet the needs of large-scale rapid attitude tracking applications

On the other hand, the dynamic torque output range of the reaction wheel itself is also required to be very high, which can take into account the rapidity of control under large attitude deviations and the pointing accuracy during steady-state control. However, the quality, power consumption, and development of such reaction wheels quite high cost

Based on the above reasons, it is not the optimal solution to realize the reaction wheel control on the small satellite platform under the existing technical conditions, and consumes more system resources

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