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本文采用间隙单元处理组合机身弹性连接，由此对组合机身进行结构有限元分析，从而求得了不同载荷工况下机身各结合面之间的接触压力分布，并提出了考察接触点接触状态的方法。本文的计算方法和结论对弹性接触问题的处理及压力机组合机身的设计，具有一定的参考价值和指导意义。
In this paper, the gap element is used to deal with the elastic connection of the composite fuselage, and the structure of the composite fuselage is analyzed by finite element method. The contact pressure distribution between the fuselage joints under different load conditions is obtained. State of the method. The calculation method and conclusion of this article have certain reference value and guiding significance for dealing with the elastic contact problem and the design of press body.