舰载机蒸汽弹射反馈线性控制系统研究

摘要

To study the states'change of accumulator and cylinder in steam catapult aircraft launch, aiming at the nonlinear coupling characteristics of the cylinder system, considering the flashing phenomenon in the steam accu⁃mulator, the pressure change of chamber with rod and without rod in the steam cylinder, and the relationship be⁃tween launching valve's core displacement and flow area, the steam accumulator and launching valve mathematical model, cylinder thermodynamic model and the aircraft six degrees of freedom dynamics model were established, and the launching valve controller of steam catapult system was accomplished. The simulation finds that the pres⁃sure⁃drop steam catapult system was extremely small, almost negligible in the catapult period; moreover, because of the nonlinear and coupling characteristics of the cylinder system, the traditional control method cannot accom⁃plish a stable launching valve, whose opening degree experiences strong mutations when opened and closed. Based on the feedback linearization theory, the steam cylinder model can be completely linearized and can decouple cylin⁃der state variables, contributing to the design of the launching valve controller. The simulation shows that using the feedback linearization method, the launching valve regulator can perform in a stable manner, achieving acceptable acceleration tracking effect during the catapult process.%为了研究舰载机蒸汽弹射过程中储汽筒与汽缸中各状态的变化，针对汽缸系统的非线性强耦合特点，考虑储汽筒内闪蒸现象、汽缸有杆腔与无杆腔压力变化以及发射阀芯位移与流通面积之间的关系，建立储汽筒、发射阀的数学模型，汽缸的热力学模型以及舰载机的六自由度运动模型，完成蒸汽弹射系统发射阀控制器设计。通过仿真研究发现，蒸汽弹射系统的储汽筒在弹射阶段压降很小，其影响可以忽略；并且，由于汽缸系统的各状态具有非线性强耦合的特点，经典控制方法难以使发射阀稳定工作，其开度会在阀开启和关闭时发生突变。基于反馈线性化理论，能对汽缸系统模型进行完全线性化，实现汽缸内各状态量解耦。仿真结果表明，利用反馈线性化方法设计的发射阀调节器在弹射过程中性能稳定，使舰载机对加速度指令有良好的跟踪能力。