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System of attitude and orbit control actuator for all-electric propulsion satellite platform

A technology for actuators and satellite platforms, applied to space navigation equipment, space navigation vehicles, aircraft, etc., can solve problems such as inability to output expected torque, improve maneuverability, reduce launch and on-orbit mass, and satellite position Accurate hold effect

Active Publication Date: 2017-12-19
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there is a singularity problem in the control moment gyro system. When the system enters a singular state, it cannot output the desired torque

Method used

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  • System of attitude and orbit control actuator for all-electric propulsion satellite platform
  • System of attitude and orbit control actuator for all-electric propulsion satellite platform
  • System of attitude and orbit control actuator for all-electric propulsion satellite platform

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Experimental program
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Embodiment Construction

[0057] Such as figure 1 and 2 As shown, an all-electric propulsion satellite platform attitude control actuator system includes: satellite orbit control system, satellite attitude control system, electric propulsion system, control moment gyro system, reaction flywheel system and satellite measurement and feedback system; The propulsion system, the control moment gyro system and the reaction flywheel system are the actuators for the satellite attitude and orbit control, and they execute the corresponding thrust and torque output commands under the control of the satellite attitude control system and the satellite orbit control system; the actuators are respectively composed of the following parts Composition: 4 sets of electric thrusters, 4 control moment gyros and 2 reaction flywheels; its working modes include orbit transfer mode, CEO position maintenance mode and attitude adjustment / maneuvering mode.

[0058] The electric propulsion system includes 4 sets of electric thrus...

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Abstract

The invention discloses a system of an attitude and orbit control actuator for an all-electric propulsion satellite platform. The system of the attitude and orbit control actuator for the all-electric propulsion satellite platform comprises a satellite orbit control system, a satellite attitude control system, an electric propulsion system, a control torque gyroscope system, a reaction flywheel system and a satellite measurement and feedback system. In view of the working characteristics of a GEO satellite, the system of the attitude and orbit control actuator for the all-electric propulsion satellite platform provides an actuator system which adopts the control torque gyroscope, the reaction flywheel and the electric propulsion system, and aims at providing technical assurance for orbit transfer, orbit keeping and agile maneuvering of the GEO satellite; and through cooperation of the system, the following objectives on GEO satellite that the launch and orbit quality are reduced, the launch cost is reduced, the satellite position maintains accurate, the maneuverability and agility of the satellite attitude are improved, and the service life of the satellite is prolonged are achieved.

Description

technical field [0001] The invention relates to the technical field of satellite attitude and orbit control, in particular to a system of an all-electric propulsion satellite platform attitude and orbit control executive mechanism. Background technique [0002] Satellite quality is one of the key issues affecting space missions. The reduction in mass can not only save costs, but also greatly improve efficiency, and solve the problem of affecting the life of satellites because chemical fuel cannot be replenished in orbit. Boeing launched the world's first all-electric propulsion satellite 702SP in 2015. Compared with the same type of satellite, its mass has been reduced by half, nearly 2000kg. Studies have shown that the specific impulse of the electric propulsion system is much greater than that of the traditional chemical propulsion system, and the work efficiency is extremely high. However, the thrust of the electric propulsion platform is small, which will prolong the p...

Claims

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Application Information

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IPC IPC(8): B64G1/28
CPCB64G1/283B64G1/286
Inventor 吴云华韩锋郑墨泓华冰陈志明张泽中葛林林
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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