The purpose of increasing the aerodynamic efficiency and enhancing the supermaneuverability for the selected supersonic aircraft is presented. Aerodynamic characteristics, the surface pressure distribution and the max...The purpose of increasing the aerodynamic efficiency and enhancing the supermaneuverability for the selected supersonic aircraft is presented. Aerodynamic characteristics, the surface pressure distribution and the maximum lift are estimated for the baseline configuration for different Mach numbers and attack angles in subson- ic and supersonic potential flows, using a low-order three-dimensional panel method supported with the semi-empirical formulas of the data compendium （DATCOM）. Total nose-up and nose-down pitching moments about the center of gravity of the complete aircraft in the subsonic region depending on flight conditions and aircraft performance limitations are estimated. A software package is developed to implement the two-dimensional thrust vectoring flight control technique （pitch vectoring up and down） controlled by the advanced aerodynamic and control surface （the foreplane or the canard）. Results show that the canard with the thrust vectoring produces enough nose-down moment and can support the stabilizer at high maneuvers. The suggested surface can increase the aerodynamic efficiency （lift-to-drag ratio） of the baseline configuration by 5%-6% in subsonic and supersonic flight regimes.展开更多
单边直线感应电机(single-sided linear induction motor,SLIM)的法向力和牵引力可以通过初级和次级磁链的幅值和夹角表示。通过选择PWM变频器最优电压矢量、改变磁链的瞬态幅值及夹角,可以实现单边直线感应电机法向力和牵引力的解耦控...单边直线感应电机(single-sided linear induction motor,SLIM)的法向力和牵引力可以通过初级和次级磁链的幅值和夹角表示。通过选择PWM变频器最优电压矢量、改变磁链的瞬态幅值及夹角,可以实现单边直线感应电机法向力和牵引力的解耦控制。由此可以将单边直线感应电机的法向力和牵引力分别用于直线电机车辆的悬浮及牵引控制,实现不设悬浮电磁铁的直线感应电机车辆的悬浮牵引同时运行。实验结果表明,在整个运行期间,悬浮牵引兼用直线电机车辆的悬浮气隙及运行速度均能快速的跟踪给定值,体现了良好的精度和稳定性能。提出的力解耦控制方案得到了较好的验证。展开更多
文摘The purpose of increasing the aerodynamic efficiency and enhancing the supermaneuverability for the selected supersonic aircraft is presented. Aerodynamic characteristics, the surface pressure distribution and the maximum lift are estimated for the baseline configuration for different Mach numbers and attack angles in subson- ic and supersonic potential flows, using a low-order three-dimensional panel method supported with the semi-empirical formulas of the data compendium （DATCOM）. Total nose-up and nose-down pitching moments about the center of gravity of the complete aircraft in the subsonic region depending on flight conditions and aircraft performance limitations are estimated. A software package is developed to implement the two-dimensional thrust vectoring flight control technique （pitch vectoring up and down） controlled by the advanced aerodynamic and control surface （the foreplane or the canard）. Results show that the canard with the thrust vectoring produces enough nose-down moment and can support the stabilizer at high maneuvers. The suggested surface can increase the aerodynamic efficiency （lift-to-drag ratio） of the baseline configuration by 5%-6% in subsonic and supersonic flight regimes.
文摘单边直线感应电机(single-sided linear induction motor,SLIM)的法向力和牵引力可以通过初级和次级磁链的幅值和夹角表示。通过选择PWM变频器最优电压矢量、改变磁链的瞬态幅值及夹角,可以实现单边直线感应电机法向力和牵引力的解耦控制。由此可以将单边直线感应电机的法向力和牵引力分别用于直线电机车辆的悬浮及牵引控制,实现不设悬浮电磁铁的直线感应电机车辆的悬浮牵引同时运行。实验结果表明,在整个运行期间,悬浮牵引兼用直线电机车辆的悬浮气隙及运行速度均能快速的跟踪给定值,体现了良好的精度和稳定性能。提出的力解耦控制方案得到了较好的验证。
