Composite heat insulation structure for large-diameter engine charge combustion chamber

The invention provides a composite heat insulation structure for a large-diameter engine charge combustion chamber, which is suitable for the structural design of a heat protection structure of a large solid rocket engine and mainly solves the problem that the existing heat insulation layer design method cannot meet the requirement of a solid rocket on light weight of an engine. The composite material thermal protection structure for the large-caliber engine charge combustion chamber comprises a cylinder section thermal protection structure and a seal head thermal protection structure. The end socket thermal protection structure adopts a variable wall thickness design scheme; the invention solves the problem of ablation resistance of the inner molded surfaces of the front and rear ends of the engine combustion chamber, and has the outstanding advantages of light weight, simple structure and reliable work. 本发明提供了一种用于大口径发动机装药燃烧室的复合绝热结构，适用于大型固体火箭发动机热防护结构结构设计，主要解决现有绝热层设计方法无法满足固体火箭要求发动机重量轻的问题；一种用于大口径发动机装药燃烧室的复合材料热