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固体火箭发动机主要由推进剂和推进剂燃烧用的高压容器(即发动机壳体)及喷管组成。现在使用的发功机壳体由铬钼钢等金属制成,这种材料重量大,所以迫切要求减轻重量。本研究以减轻壳体重量为目的,开发了机械性能好的碳纤维增强塑料火箭发动机壳体。考虑了壳体形状、高温、高压等条件,用有限元法进行了应力分析,确定了最佳缠绕层数和缠绕角度。探讨了利用长纤维缠绕法的制造技术,并试制了小型碳纤维增强塑料发动机壳体,装填高能固体推进剂,进行了燃烧试验。燃烧试验证明,试制的碳纤维增强塑料火箭发动机工作良好,发动机壳体的重量比现用金属壳体轻40％,完全可以满足火箭发动机所要求的耐高压、耐高温和燃烧特性。
The solid rocket motor is mainly composed of a high-pressure vessel for burning propellants and propellants (ie, an engine housing) and a nozzle. The generator housing now used is made of a metal such as chromium-molybdenum steel, which weighs heavily, so there is an urgent need to reduce weight. In order to reduce the weight of the shell, this study developed a carbon fiber reinforced plastic rocket motor shell with good mechanical properties. Considering the shell shape, high temperature, high pressure and other conditions, the finite element method was used to analyze the stress and determine the best winding layer and winding angle. The manufacturing technology using long filament winding method was discussed, and a small carbon fiber reinforced plastic engine case was trial fabricated, filled with high energy solid propellant, and the combustion test was carried out. The combustion test proves that the trial carbon fiber reinforced plastic rocket engine works well and the weight of the engine case is 40% lighter than the current metal case, which can fully meet the requirements of high pressure resistance, high temperature resistance and combustion characteristics required by the rocket engine.