大型客机后缘襟翼操纵与非对称控制

针对大型客机后缘襟翼操纵与非对称控制的复杂结构及运动机构动力学仿真问题,通过零部件模态综合法建立刚柔混合多体动力学模型，替代传统的有限元法，综合考虑结构柔性、关节轴承摩擦、滑轮架摩擦、机翼盒段变形协调支持边界影响，实现了大型客机后缘襟翼在空中多状态/多工况载荷综合作用下的仿真分析．总体上看，仿真计算的各作动器驱动载荷变化规律与试飞结果一致，驱动载荷最大值误差小于10 %．受内襟翼靠近机身部分的翼面风洞测压数据及机身变形支持边界等不确定因素影响，初始启动和襟翼小偏度时各作动器操纵载荷仿真结果与试飞结果相对误差偏大．通过数值仿真，进行后缘襟翼单作动器脱开故障的非对称控制需求及其交联装置动态冲击过程分析，仿真结果表明内外襟翼交联装置可以有效减小后缘襟翼单作动器脱开故障非对称变形影响．

Trailing-Edge Flap Operation and Asymmetric Control for Large Passenger Aircraft

Aiming at the simulation problems of operation and asymmetric control of trailing-edge flap with complex structure and mechanism dynamics for large passenger aircraft, the rigid-flexible hybrid multi-body dynamic model is developed through the modal synthesis method, to replace the traditional finite element method. An effective simulation is realized for the trailing edge flap under multiple loads considering the comprehensive influences of structural flexibility, mechanism friction and wing box deformation. On the whole, the variety of actuator loads in the simulation is consistent with that in the flight test results, with the maximum relative error less than 10 %. Because of uncertainty from the wind tunnel pressure data and the fuselage deformation boundary etc., the errors at the initial startup and the small flap deflection state are relatively larger. Through the numerical simulations, the asymmetric control requirements of the single actuator disconnecting are determined and the dynamic impact of cross-linking device are analyzed. The simulation results show that the cross-linking device could effectively reduce the influence of the trailing-edge flap asymmetry after the single actuator disconnecting.