中文摘要：

质量矩控制可以有效解决飞行器在超高马赫数飞行时的舵面气动加热问题,建立了质量矩导弹通用数学模型,针对具有3个滑块的三轴稳定质量矩导弹,分析了惯性主轴变化、惯性力矩和气动力矩对导弹运动的影响,结合频域摄动法和数值分析方法对这一动力学模型进行了模型简化以及简化误差补偿方法的研究.研究结果表明经过误差补偿的简化模型与未简化模型的动力学特性基本一致,以动力学系数的形式对给出了质量矩导弹的控制系统方程,为质量矩导弹进行制导控制系统的设计与分析提供依据.

英文摘要：

A mass moment control can limit the aerodynamic heating of flight vehicles traveling at extreme Mach numbers. The general dynamic models were produced by theoretical study of a mass moment missile, and then, based on the models with three masses, the influence of principal axis.misalignment, inertia moment, and aerody- namic moment on missile movement was investigated. Based on the perturbation method for frequency response and numeration analysis, study and confirmation of rationality were completed for the simplified models and inversion error reconstruction of the dynamic models. The simulation results show that dynamic characteristics of simplified models with error reconstruction are consistent with those of the general dynamic models. Furthermore, the autopilot equations are built by dynamic coefficients for designing the guidance and control system of a missile.