襟翼是民用运输类飞机起飞和降落过程中重要的增生装置，襟翼系统的可靠性对飞行运行安全有着至关重要的作用。国内外开展了大量襟翼机构故障仿真分析工作，但针对物理试验相关技术的研究资料较少。研究了襟翼机构断裂故障模拟技术并设计了襟翼作动器脱开假件，实现了襟翼作动器正常状态和故障状态的功能切换。设计了满足试验要求的吸能元件和襟翼交联装置假件，通过落锤试验获得了吸能元件能量标定曲线。在全尺寸结构上开展了襟翼机构故障模拟和强度试验，真实模拟了襟翼在飞行过程中可能出现的单作动器断裂故障，获得了准确的故障后襟翼姿态和机构传力路径变化、襟翼交联装置自由行程和冲击能量，为交联装置设计参数优化提供了依据。

Flap is an important accretion device in the take-off and landing of civil transport aircraft. The reliability of flap system plays a vital role in flight safety， and airworthiness regulations explicitly require safe return capacities after flap failure. A significant amount of simulation and analysis work of flap mechanism fault has been carried out at home and abroad， but there is relatively little research data on physical test technologies. The simulation technology of flap mechanism fracture fault is studied and the flap actuator disengagement dummy is designed to realize the function switching between normal and fault state of flap actuator. The energy absorbing element and flap interconnect structure dummy were designed to meet the test requirements， and the energy calibration curve of the energy absorbing element was obtained through the drop hammer test. The flap mechanism fault simulation and strength test were carried out on the full-size structure， and the possible single actuator fracture fault of the flap during flight was simulated. Accurate flap attitude and mechanism force transfer path change， flap interconnect structure free travel， and impact energy were obtained after the fault， which provided foundation for optimizing the design parameters of the flap interconnect structure dummy.