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为了支持民兵导弹第三级产品质量保证试验计划,1973年3月5日在火箭研制试验台(J-5)发动机试验装置(ETF)上对LGM-30G第三级固体推进剂火箭发动机PQA-103进行了点火试验。发动机的内弹道特性、液体喷射推力矢量控制系统、滚控系统和推力终止系统的性能都满足型号技术规范的要求。在压力高度为102000英尺的条件下,于发动机点火之前2.5秒,按预定的程序进行了滚控燃气发生器与液体喷射推力矢量控制隔离点火器的点火,发动机是在压力高度为101000英尺的条件下点火的。发动机点火延迟时间为89毫秒,点火后59秒,在燃烧室压力为75.3磅/英寸~2绝压下发动机推力终止。在59.93秒长的开车时间内,发动机产生的未增强的真空总冲量为2083103磅·秒。未增强的真空比冲是284.96磅·秒/磅。推力终止时的最大级间压力满足技术规范的要求。发动机点火后,其结构的完整性符合要求。
In support of the third-stage product quality assurance pilot program of the Militant Missile, the LGM-30G third-stage solid propellant rocket engine PQA-30G was commissioned on March 5, 1973 at the Rocket Test Bench (J-5) Engine Test Facility (ETF) 103 carried out the ignition test. The internal ballistic characteristics of the engine, the fluid injection thrust vector control system, the roll control system and the thrust termination system all meet the requirements of the model specifications. 2.5 seconds prior to engine ignition at a pressure of 102,000 feet and a predetermined procedure was followed. GAS GENERATOR AND LIQUID EJECTION Thrust Vector Control Isolated Ignition Ignition. The engine is operated at a pressure of 101,000 feet Under the ignition. The engine ignition delay is 89 milliseconds, 59 seconds after ignition, and the engine thrust is terminated at a combustor pressure of 75.3 lbs / in2. At 59.93 seconds long driving time, the engine produced an unreinforced total vacuum impulse of 2,083,103 lbs. The unreinforced vacuum impulse was 284.96 lbs./bs. The maximum interstage pressure at the end of thrust meets the requirements of the technical specifications. After the engine is ignited, its structural integrity meets the requirements.