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

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.

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