N_2O单组元微推进系统及其喷管流场的初步研究  

Preliminary study on a N_2O micro propulsion system and its nozzle flow field

作　　者：方杰[1] 田辉[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2005年第6期495-498,共4页Journal of Propulsion Technology

摘　　要：针对利用N2O单组元催化分解产生热气、用于精确控制飞行器姿态的微推进系统,提出了初步的系统方案和主要设计参数。通过数值仿真,对设计推力为1N的微推进器喷管在高空工况的内流场和真空羽流场进行了研究。计算得到喷管的推力为1.041N,比冲为1922.7N.s/kg,从而验证了喷管相关设计参数的合理性。理论分析为后续的地面试验件的设计加工及其热试车提供了有益的参考。Preliminary scheme＇and primary design parameters were described for a micro propulsion system used for the attitude control of the spacecraft, which is based on the monopropellant catalytic decomposition of nitrous oxide. The numerical simulation was used to analyze the flow field of inner nozzle and its vacuum plume for 1 N thruster in a vacuum. Results show that the nozzle thrust is 1. 041 N, and specific impulse is 1922.7N. s/kg, which fulfills the requirement and validates the feasibility of design parameters. Theoretical analysis is helpful for the design and manufacture of the test system, as well as the hot-fire test in future.

关 键 词：微推进系统^+ 喷管 数值仿真 优化 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]