An aeroelastic model for maneuver loads alleviation of the flexible aircraft including rigid- elastic coupling modes is developed by using subsonic unsteady aerodynamic theory and analytical mechanics. Based on this model,the effects of the structural elasticity on the airframe state of a whole aircraft in longitudinal maneuver are analyzed. The numerical results show that the influences of structural elasticity on the longitudinal maneuver flight can not be ignored. Afterwards, an optimal control law implemented with multi - control surfaces is designed to alleviate the longitudinal maneuver loads. It is demonstrated that the maneuver loads can be availably alleviated with this optimal control law.%针对飞行器刚体/弹性模态耦合作用下的机动载荷减缓问题,运用亚音速非定常空气动力学理论以及分析力学原理,建立了柔性飞机机动载荷分析及控制的气动弹性模型,分析了飞机作纵向机动飞行时结构弹性对机动飞行参数的影响.数值分析结果表明,结构弹性模态对飞机机动过程的影响不容忽视.为了有效减缓机动载荷,运用最优控制理论,采用多组控制面联合偏转的作动方案,设计机动载荷减缓最优控制律,实现了对飞机纵向机动载荷的控制.研究结果表明,提出的机动载荷减缓控制方案是有效的.
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