摘要
结合传统弹箭刚体飞行动力学理论,基于大运动弹性体浮动框架建模方法,采用混合坐标建立了飞行力学模型,该模型考虑了柔性弹箭惯量矩阵时变效应,通过小参数摄动法确定了柔性变形引起的空气动力变化.采用了合适的浮动框架———线性化Tisserand框架,使得浮动框架引出的约束方程自动满足,飞行力学求解由微分代数混合方程组化为微分方程组;通过分析变形运动方程,给出了在转速变化较慢的被动段时系统临界状态的条件和临界转速.
Based on the hybrid coordinate model and floati for the elastic body with large overall motion, the flight d rocket was developed by combining with the conventional and taking into account the influence of time-variant inerti ng frame of reference formulation ynamics model of the elastic shell/ rigid body flight dynamics model a matrix. The influence of aerodynamics caused by deformation of shell/rocket was described by using the perturbation method. Since the floating frame, which is linearized Tisserand frame, was reasonably selected, the constraint formulations caused by the floating frame of reference formulation can come into existence automatically. Then flight dynamics model of differential algebra equations was transferred into differential equations that will greatly simplify dynamics model. By analyzing the deformation motion equations of the shell/rocket, the critical characteristics and critical angular velocity of the system were given during the passive span when the rotational velocity changes slowly.
出处
《弹道学报》
CSCD
北大核心
2006年第1期22-24,29,共4页
Journal of Ballistics
关键词
柔性体
弹箭
气动弹性
飞行力学
摄动理论
flexible body
rocket
aeroelasticity
flight dynamics
perturbation theory
