N<sub>2</sub>O单组元微推进系统贮箱自增压特性

孙 威; 方 杰; 蔡国飙

N₂O单组元微推进系统贮箱自增压特性

北京航空航天大学宇航学院, 北京 100191

详细信息

作者简介:
孙威(1981-),男,博士生,湖南益阳人,sw@sa.buaa.edu.cn.

中图分类号: V 434⁺.23
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出版历程
- 收稿日期: 2008-10-31
- 网络出版日期: 2009-11-30

Tank self-pressurization process of N₂O monopropellant micro-propulsion system

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

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.
- 微推进系统 /
- 氧化亚氮(N₂O) /
- 推进剂贮箱 /
- 自增压
Abstract: 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.
- micro-propulsion system /
- nitrous oxide(N₂O) /
- propellant-tank /
- self-pressurization

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参考文献(1)

[1] Tiliakos N, Tyll J S, Herdy R, et al. Development and testing of a nitrous oxide/propane rocket engine .AIAA 2001-3258, 2001 [2] Gibbon D, Paul M, Smith M, et al. The use of liquefied gases in small satellite propulsion systems .AIAA 2001-3246, 2001 [3] Arves J P, Jones H S, Kline K, et al. Development of a N₂O/HTPB hybrid rocket motor .AIAA97-2803, 1997 [4] Gibbon D, Zakirov V, EIoirdi R, et al. Energetic green propulsion for small spacecraft .AIAA 2001-3247, 2001 [5] 方杰,田辉,蔡国飙. N₂O单组元微推进系统及其喷管流场的初步研究 [J].推进技术, 2005,26(6):495-498 Fang Jie, Tian Hui, Cai Guobiao. Preliminary study on a N₂O micro-propulsion system and its nozzle flow field [J]. Journal of Propulsion Technology, 2005,26(6): 495-498(in Chinese) [6] Cai Guobiao, Sun Wei, Fang Jie, et al. Initial results of BUAA nitrous oxide micro-thruster research 58th International Sstronautical Congress. Paris: International Astronautical Federation, 2007:5950-5956 [7] Casalino L, Pastrone D. Optimal design of hybrid rockets with self-pressurizing oxidizer .AIAA 2006-4501, 2006 [8] Zilliac G, Karabeyoglu M. Modeling of propellant tank pressurization .AIAA 2005-3549, 2005 [9] 唐铖,韦迪,李路明.小型航天器液化气推进系统的数值模拟[J].清华大学学报(自然科学版),2007, 47(5):730-733 Tang Cheng, Vadim Z, Li Luming. Numerical simulation of liquefied gas self-pressurization for small spacecraft propulsion systems[J].Journal of Tsinghua University (Science & Technology) ,2007, 47(5): 730-733(in Chinese) [10] 黄建彬.工业气体手册[M].北京:化学工业出版社,2002: 144-159 Huang Jianbin. Industrial gas data book[M]. Beijing:Chemical Industry Press, 2002:144-159(in Chinese)

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