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为实现吸气式高超声速飞行器的姿态控制,需要对其复杂的气动特性进行分析,并完成控制系统的设计.通过研究高超声速飞行器风洞实验数据,分析其气动特性,即升力系数、升阻比和纵向总力矩系数在不同Ma时随攻角变化的规律进而进一步计算出纵向动力系数,研究其纵向动态稳定性.最后,基于气动分析设计了攻角反馈控制和法向过载控制两种不同的控制回路,分别计算出其时域和频域特性.实验结果表明:吸气式高超声速飞行器既能满足纵向动态稳定性,又具有良好的控制性能.
In order to realize the attitude control of the aspirated hypersonic vehicle, it is necessary to analyze its complex aerodynamic characteristics and complete the design of the control system.By studying the experimental data of the wind tunnel of the hypersonic vehicle, the aerodynamic characteristics of the aerodynamic vehicle are analyzed, that is, the lift coefficient, Longitudinal and longitudinal moment coefficients at different Ma angle of attack with the angle of attack and then further calculated the longitudinal dynamic coefficient to study its longitudinal dynamic stability.Finally, based on the aerodynamic analysis of the design of the angle of attack feedback control and normal overload control two different The control loop is used to calculate the time-domain and frequency-domain characteristics respectively.The experimental results show that the aspirated hypersonic vehicle can not only satisfy the longitudinal dynamic stability but also have good control performance.