小型固体火箭发动机尾部点火设计与实验

根据固体火箭发动机点火器设计经验，选用赛璐珞为点火器盒体材料、黑火药为点火药，并以点火压强作为发动机装药可靠点燃的判据。采用头部点火设计经验公式对端面一侧面燃烧、尾部点火的小型固体火箭发动机点火药量进行了初步估算。为获得点火器的点火压强、点火延迟时间等性能参数，设计、加工了模拟发动机尾部点火空间的试验容器，研究了电点火头、电点火管点火方案在不同条件下的试验情况。结果表明，虽然点火药量相同，但两种点火方案的点火压强、点火延迟时间、喷管堵片的打开方式却存在较大差异，基于发动机可靠性、维修性考虑，将电发火管点火方案作为优选方案，并通过发动机点火试验的成功考核。

Design and Experiments of Aft-ignition for Small Solid Rocket Motor

According to the igniter design of similar solid rocket motors, celluloid was adopted as the igniter case and black powder as the amorce. Ignition pressure was chosen as a criterion of igniting the propellant. Based on the experimental formula of fore-ignition design ,the initial amorce mass of a small solid rocket motor with end-and- lateral burning grain and aft-ignition manner was estimated firstly. A simulation combustion container was made to obtain the ignition characteristics of the igniter, such as the ignition peak, the delay time, and the opening manner of the nozzle closure. The ignition tests of the primers ignition manner and electric-squib ignition manner at different conditions were studied respectively. The results indicated that, though the amorce mass was the same, the ignition pressure, the ignition delay and opened manner of the nozzle closure were different. Finally, the electric-squib ignition manner was regarded as the suitable choice due to the thought of reliability and maintainability for the solid rocket motor and checked in a lot of motor ignition successfully.