大型旋转飞行器在非线性不对称支承条件下的发射特性分析

LAUNCHING BEHAVIOR OF A LARGE SPINNING VEHICLE WITH NONLINEAR AND NONSYMMETRIC SUPPORTS

以大型、远程旋转火箭为例 ,将飞行器仿真为具有多个非线性、不对称支承的 Euler-Bernoulli旋转梁 ,根据有限元方法和 Hamilton原理建立飞行器的运动控制方程 ,利用分段线性化方法近似弹性支承的非线性刚度 ,数值仿真并分析了推力偏心、质量偏心、结构柔性和支承非线性等因素对飞行器动力响应的影响 ,可望为新一代。

Taking a large, long range spinning rocket as an example, the launching behavior of the vehicle is studied The vehicle is modeled as a Euler Bernoulli rotor with multi nonlinear and nonsymmetric supports Coupled motion equations describing the dynamic characteristics are established by the finite element and Hamilton methods A numerical solution is developed, and the influence of thrust misalignment, dynamic unbalance, structural flexibility and nonlinear characteristics of the support on the vehicle's launching attitude is analyzed This research will provide a useful theoretical reference in the design of new types of large spinning vehicles