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针对液体火箭发动机承力机架,开展复合材料机架的初步设计及探索应用研究。通过对原金属机架结构设计特点分析,提出了一种碳纤维增强复合材料机架的设计方案,并对其进行了力学性能预测及设计参数影响分析等方面研究工作;最后,采用有限元软件ANSYS的APDL语言开发了复合材料机架的计算程序,该程序基于损伤累积理论,包含结构应力分析、材料的失效判断及材料的性能退化3个主要循环过程,通过仿真手段模拟了在载荷增加过程中结构内部产生损伤,并逐渐累积直至破坏的整个过程。仿真分析结果表明:复合材料的应用可在满足原机架强度、刚度和稳定性等设计要求基础上,相对于原结构实现了50%的减重。
Aimed at the liquid rocket engine bearing frame, the preliminary design and exploration application research of the composite material frame was carried out. Through the analysis of the design characteristics of the original metal frame structure, a design scheme of the carbon fiber reinforced composite material frame was proposed, and the mechanical performance prediction and the influence analysis of the design parameters were carried out. Finally, the finite element software ANSYS APDL language, a program for calculating the composite frame is developed. The program is based on the theory of damage accumulation, including three main cyclic processes including structural stress analysis, material failure judgment and material performance degradation. Through simulation, Structure within the injury, and gradually accumulated until the destruction of the entire process. Simulation results show that the application of composite materials can achieve 50% weight reduction relative to the original structure based on the design requirements of the original frame, such as strength, stiffness and stability.