燃气流量可调固体火箭冲压发动机飞行性能分析

摘要

Based on ducted rocket operating principle, mathematical working model of air inlet, gas generator and secondary chamber was built. The altitude characteristics and velocity characteristics of variable flow ducted rocket were numerically studied.Increasing the flight mach or decreasing the flight altitude can not only help the engine work in a wide range of thrust, but also decrease the thrust coefficient. Decreasing the area of gas regulation valve ean increase thnust and thrust coefficient.%在建立燃气流量可调固体火箭冲压发动机工作过程仿真模型的基础上,对燃气流量调节过程中发动机飞行性能进行分析.结果表明,在低飞行高度或高飞行马赫数时,发动机有较宽的推力调节范围;随着飞行高度降低或飞行马赫数增加,发动机推力系数降低;随着燃气发生器喷喉面积变小,发动机推力和推力系数增加.