基于微分流形理论的结冰条件下飞机鲁棒动力学边界研究

基于微分流形理论构建了一种结冰条件下飞机鲁棒动力学边界保护系统设计方案。首先基于微分流形理论计算了飞机未结冰时的动力学边界，并用Monte Carlo法验证了其准确性和高效性;其次，以结冰因子影响模型为基础，研究了不同结冰程度下飞机动力学边界的变化规律;进而提出了飞机鲁棒动力学边界，并设计了结冰条件下飞机鲁棒动力学边界保护系统。当飞机遭遇结冰不利飞行环境时，相比于传统动力学边界，该鲁棒动力学边界不需获取准确的冰型信息和结冰严重程度。考虑当前结冰检测技术手段，提出的方法具有更加广泛的工程应用意义。在飞机超出动力学边界之前，边界保护系统作用使飞行状态保持在安全阈值范围内，从而保证飞机安全可控。

A Design Method in Robust Dynamic Boundary Protection System under Condition of Ice Formation on Aircraft by Differential Manifold Theory

Based on the differential manifold theory, a design method of robust dynamic boundary protection system for ice formation on aircraft is proposed. First, the dynamic boundary of pre ice formation on aircraft is calculated by the differential manifold theory, and its accuracy and efficiency are verified by Monte Carlo method. Secondly, taking the influence model of icing factor as foundation, the variation rule of aerodynamics boundary under different icing degree is studied and analyzed. Then a robust dynamics boundary of aircraft is proposed, and a robust dynamic boundary protection system for aircraft under ice condition is designed. Compared to the traditional dynamic boundary, it is not necessary to obtain accurate ice type information and ice severity when the aircraft encounters icing adverse flight environment. In consideration of the current ice detection technology, the method proposed in this paper has more extensive engineering application significance. Before the aircraft goes beyond the dynamic boundary, the boundary protection system can keep the flight state within the safety threshold, ensuring the safety and controllability of the aircraft.