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为了提高航天复合材料压力容器的性能因子,根据复合材料压力容器网络理论方法提出了“参数对应关系”结构设计方法,对一种卫星推进分系统复合材料氦气瓶进行了结构设计,确定了纤维复合层承载压力,得到了不同内衬壁厚情况下气瓶纤维预紧应力与内衬压缩应力、内衬工作应力、纤维工作应力的对应关系,获得了内衬最小壁厚和纤维预紧应力区间等参数,用有限元法对气瓶结构设计进行静力学分析校核,所设计气瓶完成了全部的鉴定试验,气瓶性能因子37km,爆破压力70MPa,纤维预紧应力区间为[120MPa,270MPa]。设计和验证结果表明:基于网络理论的“参数对应关系”结构设计方法可用于弹性工作金属内衬复合气瓶的研制,内衬最小壁厚的精确求解对提高复合材料气瓶性能因子是有效的。
In order to improve the performance factor of aerospace composite pressure vessel, according to the theory of composite pressure vessel network, a “parameter correspondence relationship” structure design method is proposed, and the structural design of a satellite propulsion subsystem composite helium cylinder is carried out. The bearing pressure of the fiber composite layer was obtained. Corresponding relations between the prestressed stress of the cylinder and the compressive stress of the liner, the working stress of the liner and the working stress of the fiber were obtained under different liner wall thicknesses. Tightness interval and other parameters, the finite element method of cylinder structure design for static analysis of the design, the design of cylinders to complete all the identification test, cylinder performance factor 37km, burst pressure of 70MPa, fiber preload stress interval [ 120MPa, 270MPa]. The results of design and verification show that the design method of “parameter correspondence” based on network theory can be used to develop elastic working metal lined composite gas cylinders. The exact solution of the minimum liner wall thickness can improve the performance of composite cylinder Effective.