液体火箭推进剂
具有最高比冲的化学火箭使用液体推进剂,称为液体火箭。可分为单组元推进剂(如液化气体),双组元推进剂(进一步分为自燃推进剂与非自燃需要点火的推进剂[1])。此外,还有三组元推进剂。
大约有170种不同的推进剂被研发过,不含对推进剂的小的改型如添加剂、抗腐蚀物质、稳定剂等。美国对至少25种推进剂做过燃烧试验。[2] 近30年来没有新的类型推进剂被使用。[3]影响选择推进剂的最主要因素是易用性、成本、危险/环境与性能指标。
参考文献[编辑]
- ^ Larson, W.J.; Wertz, J. R. Space Mission Analysis and Design. Boston: Kluver Academic Publishers. 1992.
- ^ Sutton, G. P. History of liquid propellant rocket engines in the united states. Journal of Propulsion and Power. 2003, 19 (6): 978–1007.
- ^ Sutton, E.P; Biblarz, O. Rocket Propulsion Elements. New York: Wiley. 2010.
外部链接[编辑]
- Cpropep-Web an online computer program to calculate propellant performance in rocket engines
- Design Tool for Liquid Rocket Engine Thermodynamic Analysis is a computer program to predict the performance of the liquid-propellant rocket engines.
- Clark, John D. Ignition! An Informal History of Liquid Rocket Propellants (PDF). Rutgers University Press. 1972: 214 [2017-09-23]. ISBN 0-8135-0725-1. (原始内容 (PDF)存档于2020-05-15). for a history of liquid rocket propellants in the US by a pioneering rocket propellant developer.