本文介绍了用于大型固体推进剂火箭发动机的组合式无喷管、无壳体点火器方案的设计、分析及试验结果。该点火方案的主要优点是可以把60%左右的点火器消极重量变成药柱有效载荷。点火系统的主装药由点火器周围的发动机前段装药所构成。这段装药又是发动机推进剂药柱的一部分,设计成象一个小的低压无喷管火箭发动机,给主发动机推进剂段提供足够的压力和热流输出以实现发动机点火。前段推进剂的点火由一个比较小的径向排气的BKNO_3烟火剂药片点火器来实现。试验计划需验证三个方面的设计问题: This paper presents the design, analysis and test results of a combined nozzleless and shellless igniter design for large solid propellant rocket motors. The main advantage of this ignition scheme is that it is possible to turn the negative weight of lighter about 60% into the column payload. The main charge of the ignition system is composed of the front charge of the engine around the igniter. This charge, in turn, forms part of the engine propulsion column designed as a small, low-pressure, nozzleless rocket engine that provides sufficient pressure and heat flow output to the main engine propellant section for engine ignition. The ignition of the front propellant is achieved by a relatively small radial exhaust BKNO 3 pyrotechnic tablet igniter. The test plan needs to verify three design issues: