隐身飞机操纵面封严失效机理及优化设计方法研究

The design requirement of the stealth performance of modern aircraft raises great challenges for sealing design of the control surface of traditional aircrafts. Currently it has significant difficulty to solve the failure of traditional sheet sealing assemblies only by improving the materials. Therefore, based on the research of the failure mechanism, a structural variable thickness surface sealing design and an optimization method of sealing mechanism are put forward to the control surface of modern aircrafts, which will work out the difficult problem of the sealing design of modern aircraft. Three aspects are included into this research: (1) to obtain the failure mechanism of the traditional structural sealing design by integrating theory with experiment under complex loads and boundary condition, then come up with the optimization design methods of variable thickness surface sealing structure; (2) to determine the innovative design scheme of the follow-up sealing mechanism under multiple constrains boundary condition, and make sure the high reliability and long-life of the design scheme by integrated balancing the different kinds of scheme and the combining of the global optimization and the detail design. (3) to corroborate the design by the material object experiments. The research result can solve the problems of traditional sealing structure such as short life and high failure, and further more provide the reference to future sealing method on foldable wings of stealth carrier and the variant aircraft.

隐身飞机的高隐身性能设计要求，给传统飞机操纵面封严设计带来挑战，目前单纯从封严材料性能提升角度解决传统薄板式封严失效问题遇到了瓶颈。因此，本项目以隐身飞机操纵面封严为具体研究对象，主要研究重复弯曲载荷作用下封严结构失效机理模型，提出曲面变厚度结构式封严优化方法，探索研究机构式封严原理和优化设计方法。具体内容包括：1）考虑复杂载荷和边界条件，建立重复载荷作用下悬臂板结构自由端塑性变形和连接处疲劳裂纹失效物理模型；2）提出变厚度曲面封严结构构型设计原理，研究曲面变厚度结构式封严的优化设计方法；3）通过实物试验验证封严结构失效机理模型和变厚度曲面结构优化设计方法；4）进行多约束边界下的机构式随动隐身封严设计原理和优化方法探索研究。其研究成果不仅可以为解决隐身飞机操纵面封严失效难题奠定基础，同时对未来隐身舰载飞机的折叠机翼和未来变体飞机的封严设计有着重要的参考价值。

针对隐身飞机的高隐身性能设计要求给传统飞机操纵面封严设计带来的挑战，本项目以隐身飞机操纵面封严为具体研究对象，主要研究重复弯曲载荷作用下封严结构失效机理模型，提出曲面变厚度结构式封严优化方法，研究机构式封严原理和可靠性优化设计方法。具体内容包括：1）考虑复杂载荷和边界条件，建立重复载荷作用下悬臂板结构自由端塑性变形和连接处疲劳裂纹失效物理模型，获得封严结构塑性变形损伤发生规律，为封严板设计优化奠定了基础。同时针对封严机构往复运动下的磨损问题，提出了非规则磨损运动副的磨损损伤预测方法；2）提出变厚度曲面封严结构构型设计原理，并基于失效边界近似策略，提出了面向失效边界的自适应确定性优化方法和可靠性优化方法，保证了全局收敛性和优化效率，优化结果应用于型号动翼面和推力矢量机尾罩封严结构设计；3）开发了封严结构动态性能试验系统，实现了气动载荷模拟和动翼面偏转运动，试验系统完成了某重大型号封严结构十万次耐久性试验；4）提出了多约束边界下的机构式随动隐身封严设计原理方案10余种，成功应用于某型号飞机挂架封严口盖成品研发。依托本项目的资助，发表论文25余篇（其中SCI论文19篇），申请专利17项，获得授权8项，培养博士4名，硕士4名。部分成果已经成功应用于我国重大工程型号中。项目研究成果为解决隐身飞机操纵面封严失效难题奠定理论了基础，同时对未来隐身舰载飞机的折叠机翼和未来变体飞机的封严设计有着重要的参考价值。