摘要
采用变燃面装药固体火箭发动机的"瞬时压强平衡法"和流量平衡的关系式,较准确地对涡轮喷嘴前火药燃气性能进行了计算,得到了涡轮喷嘴前火药燃气性能的各种参数,这些参数有助于对涡轮起动性能和发动机加速性的研究。
This article adopts the method of instantaneous pressure equilibrium of variational burning surface of powder in solid rocket engine and flow-rate equilibrium relation to calculate exactly the performance of powder gas in the front of the turbine nozzle. Various performance parameters of the powder gas in the front of the turbine nozzle were obtained. These parameters will be helpful to the research of turbine start and engine acceleration performances.
出处
《火箭推进》
CAS
2008年第6期14-18,共5页
Journal of Rocket Propulsion
