Numerical Analysis On Response Characteristic Of Space Propulsion System For Attitude And Orbit Control

This paper designs a propulsion system for attitude and orbit control,establishes a dynamic model of system components,and builds a system simulation model based on AMESim Modular Simulation software.The influence factors of attitude control engine response characteristics for starting process,the influence of system operation time on response characteristics,and the transfer characteristics of pressure oscillation in combustion chamber are studied.The main contents of the thesis are as follows:Based on the orthogonal experimental design method,the factors affecting the response characteristics of attitude control engine during starting process are analyzed.The combustion delay,injection pressure drop and valve timing are determined as the main influencing factors by comparing the chamber pressure overshoot and response time.The simulation analysis is carried out to determine the influencing law.The simulation model of the system is established,and the effects of starting and shutting down time sequence on response characteristics and water hammer are analyzed.The flow matching characteristics of the system are analyzed.The pressure oscillation transfer model of the combustion chamber is established,and the influence of the oscillation combustion on the response characteristics of the system components is analyzed.The research content of this paper can satisfy the engineering requirements of quick response and reliable operation of the propulsion system for attitude and orbit control,and the obtained research rules are in line with the actual situation,which can be used as the guidance for the optimization design of the next generation of propulsion system for attitude and orbit control.