星用单元肼推力器工作性能分析及飞行验证

Performance Analysis and Flight Verification of the Hydrazine Monopropellant Thruster for Satellites

单元肼推力器被广泛应用于中低轨卫星推进系统,作为姿轨控喷气控制的执行部件,其工作性能直接影响卫星姿态控制和轨道控制的效果和精度。以单元肼5N推力器为例,对其在适应姿轨控需求的稳态及各品种脉冲控制程序下的工作性能进行分析,通过比对地面试验和在轨飞行试验的结果,给出推力器的输出性能特点、影响因素,并对脉冲小量轨控模式下的推力器性能进行分析,明确推力器的使用约束,为姿轨控喷气控制模式的进一步优化设计提供借鉴。

Hydrazine monopropellant thruster is extensively applied in LEO and MEO satellites’propulsion system.As the executive agency of attitude and orbit control system(AOCS),the thruster performance can directly affect the control accuracy and effect of AOCS.In this paper,takes the case of 5 Nthruster,analyze the performance of the thruster in the steady and various pulsed model.Through comparing of ground tests and flight tests,the thruster performance and influence factor are obtained.This paper also takes specialized analysis on the thruster performance at short-pulse orbit control,which proposes 5 Nthruster on-orbit working conditions.Therefore,review of these results can provide the reference for optimizing attitude and orbit control model.