为降低霍尔推进系统产生的扭矩长期作用于航天器对姿态控制造成的干扰，对其扭矩特性进行分析和优化设计，通过对扭矩的产生机理进行模型化分析，得到了放电参数对扭矩大小及方向的影响关系。分析表明，1kW~5kW功率级霍尔推力器工作时,会产生量级为10^-4的扭矩，通过控制励磁电流方向可改变扭矩方向。针对典型的全电推进飞行任务，通过提出霍尔推进系统扭矩主动控制设计，实现了对系统产生的扭矩进行相互抵消或者叠加利用，降低了系统的应用风险。

In order to reduce the disruption caused by torques to the attitude and orbit control system of a spacecraft, the torque characteristics and optimize the design of the Hall propulsion system are theoretically analyzed. The effects of discharge parameters on the torque magnitude and direction are presented. Theoretical analysis indicates that a 1~5 kilowatt-class Hall thruster can generate torque in the order of 10^-4N?m when it works. Moreover, the design of active control torque direction by controlling the exciting currents direction of the Hall thruster is analyzed. Finally, based on the typical all electric propulsion missions, a torque active control design which can counteract the torques generated by different thrusters to zero or superpose them to a certain required direction is proposed.

V439+.2