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Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture
Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture
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机译:固体推进剂双脉冲火箭发动机装载壳体和点火系统及制造方法
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摘要
A solid propellant dual pulse rocket motor has a pressure vessel containing two pulse grains separated by a barrier insulator. An igniter assembly disposed at a fore end of the pressure vessel selectively ignites a first pulse grain from a central channel within the grain. The igniter assembly also ignites a second pulse grain by ejecting hot combustion gases onto the fore end of the grain. Using such an ignition arrangement, a dual pulse rocket motor may be constructed using standard off-the-shelf ignition components.
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