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传统基于建模仿真的控制系统检验方法受建模质量的影响,在非定常效应较强时很难得出准确结果。为此,采用基于CFD的虚拟飞行数值模拟方法检验和优化控制系统。首先介绍了数值模拟方法,进行了纵向开环控制飞行模拟,结果与气动力建模仿真结果、风洞试验结果吻合较好,共同验证了计算方法和气动力模型。针对迎角拉起设计了PID控制器,阶跃响应仿真结果表明控制器具有良好的动态性能,然后进行了数值模拟验证,结果表明迎角超调量超过50%、调节时间1.7s。通过试探法对控制参数进行了优化改进,将超调量减小到14%,调节时间减小到1.18s,动态性能显著提高。分析表明,受控时尾舵角速度达到200°/s,非定常效应强,线性气动力模型不能精确描述这些过程,造成了仿真结果的差异;虚拟飞行数值模拟技术在控制律检验和优化上可以起到关键作用。
Traditional control methods based on modeling and simulation are affected by the quality of modeling, and it is very difficult to get accurate results when the unsteady effects are strong. To this end, CFD-based virtual flight numerical simulation method to test and optimize the control system. Firstly, the numerical simulation method is introduced and the longitudinal open-loop control flight simulation is carried out. The results are in good agreement with the aerodynamic modeling and simulation results and wind tunnel test results, which verify the calculation method and the aerodynamic model. The PID controller was designed to attack the angle of attack. The simulation results of the step response show that the controller has good dynamic performance and then verified by numerical simulation. The results show that the angle of attack overshoot exceeds 50% and the adjustment time is 1.7s. Through the heuristic method, the control parameters are optimized and improved, the overshoot is reduced to 14%, the adjustment time is reduced to 1.18s, the dynamic performance is significantly improved. The analysis shows that when the rudder angular velocity is controlled to 200 ° / s and the unsteady effect is strong, the linear aerodynamic model can not accurately describe these processes, resulting in the difference of the simulation results. The virtual flight numerical simulation can be used in the test and optimization of the control law Play a key role.