Combined Control Method of Solid Micro-Propeller Array and Magnetic Torque Device

Abstract

The invention discloses a joint control method of a solid micro-propulsion array and a magnetic torque device. An optimized ignition model of the solid micro-propulsion array is designed, and the solid micro-thrust array is controlled by the optimized ignition model to perform large-angle velocity damping control on the satellite until the satellite The angular velocity of the satellite is controlled jointly with small-angle damping through the magnetic torque device and the solid micro-propulsion array until the angular velocity of the satellite is less than or equal to the joint attitude acquisition control of the satellite through the magnetic torque device and the solid micro-propeller array; by designing the MSPT ignition model design , can optimize the ignition of the solid micro-thruster, and give the optimal ignition combination. According to the task requirements, the solid micro-thruster array and the magnetic torquer are combined for joint control, and the algorithm is proved by theoretical derivation and simulation experiments. Effectiveness can reduce the attitude control cycle of the satellite, improve control accuracy, and reduce control energy consumption.

Description

【Technical field】 [0001] The invention belongs to the technical field of micro-satellite attitude control, and in particular relates to a combined control method of a solid micro-propeller array and a magnetic torquer. 【Background technique】 [0002] In units and enterprises, micro-satellites are used in emergency communication, space networking and other fields due to their low cost of implementation and quick response capabilities such as short design time periods. In college education, its low-cost and high-integration features enable Pina Satellite to be well integrated into innovation and learning, which is very helpful for the development of students, so it is valued by many universities. At present, many universities have successfully launched small satellites. Attitude Determination and Control System (ADCS for short) of Pina satellite provides attitude control capability for small satellites, which is composed of attitude sensor, attitude control actuator and attit...

AI Technical Summary

Problems solved by technology

When the thrust of a single thruster is large, the accuracy of attitude control cannot be guaranteed; while when the thrust of the thruster is small, the scale of the thrusters required to complete large-angle maneuvers or multiple maneuvers is difficult to achieve in terms of power consumption and volume. limits

Therefore, attitude control using solid micro-propeller arrays alone cannot meet the needs of many actual flight missions. In order to make full use of the advantages of micro-solid micro-propellers, it is still necessary to explore a better combined attitude control method.

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