Study On Satellite Actuator Scheme For Large-angle Maneuver

With the vigorous development of modern aerospace industry,the advantages and disadvantages of space technology has become an important symbol to measure a country's comprehensive strength and scientific and technological strength.In our country,there is still a large space for the research of large-angle maneuver in the field of satellite,and the development and design of modern satellite with higher accuracy and reliability has become the goal of all the astronauts.At the same time,because of the increasing demand,the requirement of flexible large-angle attitude maneuver for satellites is still increasing.When satellite is maneuvering in large angle attitude,if the actuator only selects reaction wheels,although the cost can be reduced,the time of work will be very long because that the torque of reaction wheel is limited.In order to explore the control method of large-angle maneuver and compare the characteristics of various maneuver control schemes,the paper takes the satellite large-angle control system as the research object.According to the control requirements of large-angle maneuver,the control law of attitude is designed using the attitude model described by quaternion,and four kinds of attitude are studied respectively,The dynamic maneuver schemes are single reaction flywheel control,double reaction flywheel control,single reaction flywheel + air-jet actuator control and double reaction flywheel + air-jet actuator control.The effectiveness of the control law is verified by mathematical simulation and hardware in the loop simulation experiment.The main tasks are as follows:1)Using quaternion to describe the attitude model of space products,not only the kinematics equation and dynamics equation of satellite space attitude are established,but also a relatively complete simulation model of satellite space motion is built.2)A PID control law for satellite large-angle maneuver using reaction flywheel system and air-jet actuator as actuators is designed.3)The advantages and disadvantages of four attitude maneuvering schemes: single reaction flywheel control,double reaction flywheel control,single reaction flywheel + air-jet actuator control and double reaction flywheel + air-jet actuator control,are fully compared by simulation.4)The semi-physical simulation test platform of attitude and orbit control system is built by using star sensor and flywheel subsystem to verify the correctness and validity of the research scheme in this paper.