针对高柔性飞机全机静力试验中结构突发破坏易诱发系统失稳及二次损伤的问题，首先对含作动器的刚柔耦合系统加载控制仿真方法进行了研究：基于部件物理力学特征，构建了包含机翼非线性单元与机身线性超单元的全机刚柔耦合有限元模型，在兼顾计算效率的同时实现了对关键构件从屈曲到断裂过程的高保真模拟；开发了基于ABAQUS用户子程序的嵌入式控制框架，在隐式求解器内集成了增量式比例-积分-微分（PID）控制律与虚拟作动器动力学模型，解决了结构突变引发的计算收敛难题。在此基础上，复现了极限载荷下的突发断裂工况，对比了位移锁定、被动泄压等卸载策略的力学响应特征，并提出了一种基于力反馈的作动器协调卸载控制策略。研究结果表明：非闭环策略会因残余内力保持或冲击诱发严重的二次损伤；闭环力控卸载策略能够自适应由受损结构动力特性决定的最小卸载时间；在不增生额外塑性损伤的前提下，该策略将动能比控制在1.02 %，成功实现了全机在突发损伤后动力学响应的平缓衰减与姿态平稳恢复，为高风险全机静力试验控制设计提供了可行的方法。
To address the problem that sudden structural damage during full-scale static tests of highly flexible aircraft easily induces system instability and secondary damage, the loading control simulation method for a rigid-flexible coupled system containing actuators is investigated. First, based on the physical and mechanical characteristics of the components, a full-scale rigid-flexible coupled finite element model comprising nonlinear wing elements and a linear fuselage super-element is constructed. This model achieves high-fidelity simulation of key components from buckling to fracture while balancing computational efficiency. Second, an embedded control framework based on ABAQUS user subroutines is developed. Incremental proportional-integral-derivative (PID) control laws and virtual actuator dynamic models are integrated into the implicit solver, which successfully resolves the computational convergence difficulties caused by abrupt structural changes. On this basis, the sudden fracture condition under ultimate loads is reproduced, and the mechanical response characteristics of unloading strategies, such as displacement locking and passive pressure relief, are compared. An actuator coordinated unloading control strategy based on force feedback is then proposed. The research results indicate that non-closed-loop strategies will induce severe secondary damage due to residual internal force retention or impacts. In contrast, the closed-loop force-controlled unloading strategy can self-adapt to the minimum unloading time determined by the dynamic characteristics of the damaged structure. Under the premise of not generating additional plastic damage, this strategy controls the kinetic energy ratio at 1.02 %, successfully achieving a smooth attenuation of the dynamic response and stable attitude recovery of the full aircraft after sudden damage, providing a feasible method for the control design of high-risk full-scale static tests.
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