论文部分内容阅读
针对一种适用于整体式固体火箭冲压发动机的泄流式进气道堵盖方案,作了详细方案设计,对工作原理和设计要点作了阐述。采用简化模型,考虑进气道堵盖泄流板前气流参数、泄流板长度及其抬升高度等关键参数,进行了流场数值仿真,得到了泄流板在不同工作状态下的载荷分布情况,仿真结果表明该堵盖具备实现自动开启的可行性,且表明在助推阶段该方案与不安装进气道堵盖方案相比可有效减阻50%。最后,开展了泄流式堵盖方案地面吹试实验,作动装置启动后,进气道堵盖在气流作用下顺利开启,进一步验证了该方案的有效性和可行性。
Aiming at a kind of plugging scheme of a bleed-type inlet which is suitable for an integrated solid rocket ramjet engine, a detailed scheme design is made, and the working principle and design points are elaborated. A simplified model was used to simulate the flow field and the load distribution under different operating conditions with the key parameters such as the airflow parameters in front of the exhaust block, the length of the drain plate and its lifting height. The simulation results show that the cover has the feasibility of automatic opening, and shows that the program can reduce drag effectively by 50% in the boost stage compared with the non-installation of the inlet cover. Finally, a blow-off test was conducted on the surface of the discharge plugging cover. After the actuating device was activated, the inlet plugging cover was opened smoothly under the action of airflow, which further validated the effectiveness and feasibility of the solution.