N_2O单组元微推进系统贮箱自增压特性  

Tank self-pressurization process of N_2O monopropellant micro-propulsion system

作　　者：孙威[1] 方杰[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《北京航空航天大学学报》2009年第11期1290-1293,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：建立了氧化亚氮(N2O)贮箱自增压地面试验系统,针对亚牛级氧化亚氮单组元微推进系统的推进剂自增压供给过程开展了初步测试试验.基于三区域集总参数物理模型建立了氧化亚氮单组元微推进系统贮箱自增压数学模型,针对相同试验条件下的贮箱自增压过程开展了数值模拟,模拟结果与试验数据吻合较好,验证了仿真模型的准确性.仿真及试验结果均表明,为了确保推力器工作全过程中推进剂供应稳定,在亚牛级氧化亚氮单组元微推进系统的自增压过程中需要对氧化亚氮贮箱进行热量补偿来保证贮箱压力的稳定性,而贮箱压力下降速度分别随着贮箱初始充填率的减少、贮箱容积的减小及氧化亚氮质量流率的增加而增大.A ground experimental system was built to study the propellant-tank self-pressurization process of the sub-Newton-thrust N2O monopropellant propulsion system.Numerical simulation using a three-region lumped model was conducted to simulate the same process as well.Simulation results under adiabatic wall condition agree well with the experimental data,which preliminary testifies the validity of the three-region lumped model.Both experimental and simulation results show that the heat compensation for propellant-tank is necessary during the propellant self-pressurization supply process of the sub-Newton-thrust N2O monopropellant propulsion system,in order to keep stability of the tank pressure.It is also found that the initial filling factor,the volume of the tank and the propellant flowrate have great effects on the decline velocity of the propellant-tank pressure.

关 键 词：微推进系统 氧化亚氮(N2O) 推进剂贮箱 自增压 

分 类 号：V434.23[航空宇航科学与技术—航空宇航推进理论与工程]