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一、概述 固体火箭发动机的喷管一般是无冷却的。随着推进剂能量的提高,喷管受热很严重。一般含铝粉的CTPB推进剂,燃烧温度可达3500°K,燃气沿喷管膨胀加速产生推力,同时,炽热的燃气流使喷管受热,以临界截面处最为严重,因此,必须考虑特殊的耐烧蚀材料。另外,喷管作为固体火箭发动机的部件,还必须考虑其他要求,如重量、经济性、强度(结构完整性)等。所以产生了复合结构喷管的设计。 复合结构一般包含与燃气直接接触,构成燃气流动边界的内层,称为烧蚀层、中间绝热层及喷管结构本体。
First, an overview of the solid rocket engine nozzle is generally not cooling. As the propellant energy increases, the nozzle heat is very serious. CTPB propellants, typically containing aluminum powder, can burn at temperatures up to 3500 ° K. The gas accelerates along the nozzle to create thrust. At the same time, the hot gas stream heats the nozzle to the critical section. Therefore, special Ablative material. In addition, the nozzle as a solid rocket engine components, but also must consider other requirements, such as weight, economy, strength (structural integrity) and so on. Therefore, the design of the composite structure of the nozzle. The composite structure generally includes an inner layer that is in direct contact with the gas and forms a gas flow boundary, and is referred to as an ablation layer, an intermediate heat insulating layer, and a nozzle structure body.