整体式固体火箭冲压发动机飞行试验

Flight test investigation for an integrated ducted rocket

关键词:  整体式火箭冲压发动机  飞行试验  发动机试验  发动机性能参数

Key words:  Integral rocket ramjet  Flight test  Engine test  Motor performance parameter

摘要:

在地面试验基础上进行了整体式固体火箭冲压发动机飞行试验,以验证发动机的工作可靠性和飞行性能。飞行试验结果表明:试飞发动机和试飞器总体设计合理;发动机性能良好;主级在余气系数0.8~2.3范围内能够稳定工作;最大比冲为6.62 kN.s/kg。达到了试验的目的。

Abstract:

Flight tests for an integrated ducted rocket were carried out successfully following ground tests in order to investigate the performance of the ducted rocket.The data obtained have shown that the performance of the ducted rocket is satisfactory.The ducted rocket worked well with excess oxidizer coefficient ranging from 0.8 to 2.3.Its maximum specific impulse is 6.62 kN·s/kg.It demonstrated that the design for both the engine and vehicle is correct.