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分析了静不稳定高超声速飞行器弹性振动与飞行控制系统之间的耦合机理,进而研究机体弹性振动抑制方法。建立弹性高超声速飞行器耦合模型,针对静不稳定特性设计角速率稳定回路,并从时域和频域研究弹性振动与角速度稳定回路的耦合机理;提出一种新型综合相位稳定方法,该方法在达到传统弹性振动相位稳定要求同时保证弹性模态最大能控性指标,得到一种新的敏感元件位置配置准则。仿真结果表明,该方法能够保证飞行器的稳定性,与采用增益稳定和普通相位稳定方法相比,能更好地快速抑制弹性振动。
The coupling mechanism between the elastic vibration of the unstable unstable hypersonic vehicle and the flight control system is analyzed, and then the method of suppressing the elastic vibration of the aircraft body is studied. The coupled model of hypersonic hypersonic vehicle was established, the angular velocity stabilized loop was designed for the static instability, and the coupling mechanism between the elastic vibration and the angular velocity stabilized loop was studied in time and frequency domain. A new integrated phase stabilizing method was proposed, The traditional elastic vibration phase stability requirements at the same time to ensure the maximum elastic modal controllability index, get a new sensor configuration guidelines. The simulation results show that this method can ensure the stability of the aircraft, and can suppress the elastic vibration more quickly than the method of gain stabilization and ordinary phase stabilization.