大质量比滚控式变质心飞行器动力学特性分析

Dynamics Characteristics Analysis of a Flight Vehicle with a High-mass-ratio Moving-mass Roll Control System

针对大质量比滚控式变质心再入飞行器结构参数设计问题,建立了包含活动体偏转运动的完整飞行器姿态伺服动力学模型,进而对活动体参数设计对姿态动力学耦合特性的影响展开分析研究。首先根据Routh准则给出了飞行器的纵向静稳定区域,并讨论了配平攻角与活动体配置参数间的关系。对飞行器系统的动力学耦合分析结果表明,活动体偏转在控制滚转姿态的同时会对偏航姿态产生影响,进而造成控制精度的下降,甚至导致不稳定的飞行状态。为了在飞行器结构参数的优化设计中提高飞行器的控制性能、最小化飞行器滚转机动对偏航通道的影响,采用多尺度法对活动体偏转与飞行器偏航姿态运动构成的耦合非线性动力学系统在不同构型参数下的稳态解析解进行幅频响应特性分析,并给出考虑滚转偏航耦合约束下的大质量比滚控式变质心飞行器构型设计方案。

A complete attitude-servo dynamics model,including the deflection motion of the slider,is established to address the structural parameter design problem for a class of high-mass-ratio moving-mass reentry vehicles(MMRV)with roll control system and further analyse the impact of slider parameter on the coupling characteristics of attitude dynamics of MMRV.Firstly,the longitudinal static stability region of the vehicle is given based on the Routh criterion,and the relationship between the trim angle of attack and the configuration parameters of the slider is discussed.The dynamics coupling analysis of the vehicle system shows that the deflection of the slider can affect the yaw attitude while controlling the roll attitude,resulting in a decrease in control accuracy and even instability of attitude control.In order to reduce the influence of roll maneuver on yaw channel and improve the control performance by optimizing the vehicle structure,the multiple scales method is used to analyze the amplitude-frequency response characteristics of the coupled nonlinear dynamic system composed of slider deflection and vehicle’s yaw attitude motion under different slider design parameters,and a configuration design scheme for a class of high-mass-ratio MMRV with roll control system considering roll-yaw coupling constraints is provided to improve the system performance.