基于干法缠绕的固体火箭发动机壳体补强工艺研究

Research on reinforcement scheme of solid rocket motor case based on prepreg winding

本文开展了基于干法缠绕成型工艺固体火箭发动机复合材料壳体样件的力学特性研究。通过建立基于三次样条厚度预测方法的封头精细化数值模型,利用Hashin失效判据对壳体爆破压强进行预测,并结合试验结果,分析了固体火箭发动机壳体的水压爆破失效行为。基于该数值模型,探究了补强角度、补强厚度和补强区域对壳体爆破行为的影响。结果表明:封头精细化补强对壳体的承载性能有较大提升,通过40°补强层进行封头补强,壳体爆破压强提升了约50%;在一定范围内,壳体的爆压压强随着补强层的增加而增加;针对破坏位置的局部补强对壳体水压爆破强度有一定的提升,但壳体封头处未补强的区域会因为强度不足而发生破坏。研究成果对基于干法缠绕工艺的固体火箭发动机壳体的研制具有重要参考意义。

In this paper,a study on the mechanical properties of solid rocket motor composite shell samples was carried out using prepreg winding process.The mechanical behavior of composite shells was investigated and a refined numerical model of the composite dome using cubic-spline thickness prediction method was established.The burst pressure was predicted using Hashin failure criterion.With the aid of the test results,the failure mechanism of the composite shell was revealed.The influence of various reinforcement methods on the burst behavior of the composite shell was evaluated.The results show that the fine reinforcement of the dome can greatly improve the load carrying capacity of the shell.The burst pressure of the shell is increased by 50%with the reinforcement layup angle of 40°.The burst pressure increases with the increase of the reinforcement layer in a certain range.The local reinforcement for the damaged position will increase the hydraulic burst pressure of the shell to a certain extent.However,the unreinforced area at the dome of the shell will be damaged due to insufficient strength.This paper provides an important reference for design and production of composite solid rocket motor shell fabricated using prepreg winding.