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高超声速飞行器广泛采用升力体、乘波体等气动布局和轻质复合材料、薄壁结构等,导致结构振动与刚体运动频率非常接近,给飞行器制导控制系统设计带来了巨大挑战.针对该类飞行器的特点,考虑结构的横向位移,将机身前后体简化为于质心处固联的2根悬臂梁,并从统一的能量观点出发,基于拉格朗日方程与虚功原理,在纵向平面推导出适合高超声速飞行器的刚体/弹性体耦合动力学模型.通过对比耦合模型与传统刚体模型的极点分布情况,发现结构振动与刚体短周期模态紧密耦合,离心力的引入影响了高度与长周期模态,对高超声速飞行器航迹运动的作用不可忽视.最后分析了飞行速度与结构阻尼变化对耦合模型动态性能的影响.结果证明飞行速度对刚体运动模态影响显著,而结构阻尼的变化主要改变弹性模态.
Hypersonic vehicles are widely used aerodynamic layout such as lift body, wave body and light composite materials, thin-walled structures, etc., resulting in very close structural vibration and rigid body movement frequency, posing a huge challenge to the design of guidance control system for aircraft. Considering the transverse displacement of the structure, the fuselage front and rear bodies are simplified as two cantilever beams solidified at the center of mass. Based on the Lagrangian equation and virtual work principle, The rigid-body coupling dynamics model for hypersonic vehicle is deduced. By comparing the pole distribution between the coupled model and the traditional rigid-body model, it is found that the structural vibration is closely coupled with the short-period mode of rigid body. The introduction of centrifugal force affects the relationship between height and long period Modal effect on track motion of hypersonic vehicle can not be ignored.Finally, the influence of flight velocity and structural damping on the dynamic performance of the coupled model is analyzed.The results show that the flight velocity has a significant influence on the rigid body modal movement, while the change of structural damping mainly Change the elastic mode.