Solar sail attitude orbit coupling control method based on model prediction control

Abstract

The invention provides a solar sail attitude orbit coupling control method based on model prediction control. The method comprises the following steps: step 1: establishing a control torque and a control force model of RCDs in solar sail attitude orbit control; step 2: establishing a relative kinematics and dynamics equation of solar sail orbit motion of an earth-moon system; step 3: establishinga relative kinematics and dynamics equation of solar sail attitude motion of the earth-moon system; step 4: establishing a solar sail relative motion coupling equation in combination with the equations of the step 2 and the step 3; and step 5: designing a control rate by using the coupling equation obtained in the step 4 and using a model prediction control method. According to the solar sail attitude orbit coupling control method provided by the invention, the RCDs is used as an attitude orbit drive of the active control of the solar sail, the control rate of the solar sail attitude orbit isdesigned by using the model prediction control method, so that the coupling and saturation of the driver and the output limit of a solar sail attitude angle in an attitude orbit coupling control process can be conveniently solved.

Description

technical field [0001] The invention belongs to the field of spacecraft flight control, in particular to a solar sail attitude-orbit coupling control method based on model predictive control, which optimizes the performance of reflectivity control devices (RCDs) as solar sail attitude-orbit controllers. Background technique [0002] Compared with traditional spacecraft, solar sails have the advantages of using solar light pressure to obtain continuous small thrust and high load ratio without fuel, and have great application potential in earth-moon space missions. At present, the theoretical research of solar sails in the Earth-Moon system mainly focuses on the design of the periodic orbit and suspension orbit of a single solar sail, and the formation flight research of multiple solar sails is still an open topic. Considering the instability of the mission orbit of the solar sail of the Earth-Moon system, the solar sail needs active orbit control, the magnitude and direction ...

AI Technical Summary

Problems solved by technology

At present, there are three key problems in RCDs in the attitude-orbit coupling control of solar sails: 1. The control torque generated by RCDs has a saturation effect and is closely related to the area ratio and distribution of RCDs and the attitude angle of the solar sail; 2. RCDs change the solar sail The reflectivity coefficient will change the sunlight pressure acting on the solar sail, and then affect the orbital characteristics of the solar sail, causing the coupling problem between attitude and orbit control; 3. Considering the power consumption of RCDs, it is necessary to design an appropriate switching rate

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