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Method for the production of a combustion chamber for solid propellant rocket motor
Method for the production of a combustion chamber for solid propellant rocket motor
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机译:用于固体推进剂火箭发动机的燃烧室的制造方法
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摘要
Sectors of tubes are adhesively fixed around a prefabricated propellant, the sectors being juxtaposed edge to edge to constitute a cylindrical tube, and a winding is formed around the tube at least in circumferential direction. The front and rear walls which are equipped with a seating and a tuyere, can be joined to the tubular structure formed by the tube sectors, by adhesive means on the inside of that structure, or as a variant, by means of a helical winding formed simultaneously on the wall and on the tubular structure.
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