推力矢量型V/STOL飞行器短距降落控制策略设计

Design of short landing control strategy for thrust-vectored V/STOL aircraft

针对推力矢量型垂直/短距起降(V/STOL)飞行的短距降落(SRVL)过程,进行了纵向动力学建模。基于飞机的减速性能与轨迹、速度稳定性,采用可达平衡集方法,构建了策略参数的边界,制定了参数选取标准,设计一种制定短距降落策略的方法。根据降落策略,分段进行了相应的控制框架建立,内环采用动态逆控制律,并引用一种基于频域尺度的效能分配准则进行控制分配设计。基于蒙特卡洛仿真法,对降落策略的鲁棒性进行了仿真验证,结果表明:针对不同降落阶段的策略参数边界制定方法能够满足该阶段的任务需求,且这些参数边界对短距降落策略制定有着明确的参考意义。以L1自适应控制器作为内环增稳控制器,所设计的短距降落策略使得飞行器在着陆过程中有着良好的轨迹鲁棒性。

A method to design the landing strategy for vertical/short takeoff and landing vehicles(V/STOL)was established for the shipborne rolling vertical landing(SRVL)process.A longitudinal dynamic model of the protype V/STOL aircraft was established,and then the boundaries of the strategy parameters were determined using attainable balance set methods,on the basis of the deceleration performance,trajectory stability and airspeed stability.The criterion of the strategy parameters specification was also given.Then the control scheme of the strategy was piecewise constructed,where the dynamic inverse methods were applied to the inner loop.A frequency-domain-based control allocation criterion was introduced into this architecture to design the control allocator.Finally,this strategy was verified by Monte Carlo simulations for its robustness performance.The results showed that:the formulation method for strategy parameter boundaries of each landing stages satisfied their requirements respectively,and these parameter boundaries had explicit reference significance to the landing strategy formulation.The landing strategy using L1 adaptive theory for inner loop stability augmentation enables the aircrafts to have excellent trajectory robustness performance.