吸气式高超声速飞行器控制系统设计

摘要

To achieve the attitude control of air-breathing hypersonic vehicle, it's necessary to analyze its complex aerodynamic characteristics, and complete the control system design. Aerodynamic characteristic of airbreathing hypersonic vehicle, namely, the variations of lift coefficient, lift-drag ratio and pitch-moment coefficient with that of attack angle at different Mach numbers, is explored by the data from wind tunnel test. The longitudinal dynamic coefficients are calculated to analyze its stability. Two different control strategies are designed based on aerodynamic analysis, one is attack angle feedback control and the other is normal overload control, and their time domain and frequency domain characteristics are calculated respectively. Experiment result shows that air-breathing hypersonic vehicle not only satisfies longitudinal dynamic stability, but also demonstrates good flight control performance.%为实现吸气式高超声速飞行器的姿态控制，需要对其复杂的气动特性进行分析，并完成控制系统的设计．通过研究高超声速飞行器风洞实验数据，分析其气动特性，即升力系数、升阻比和纵向总力矩系数在不同Mα时随攻角变化的规律进而进一步计算出纵向动力系数，研究其纵向动态稳定性．最后，基于气动分析设计了攻角反馈控制和法向过载控制两种不同的控制回路，分别计算出其时域和频域特性．实验结果表明：吸气式高超声速飞行器既能满足纵向动态稳定性，又具有良好的控制性能．