A sliding mode observer is designed to estimate the Angle of attack and flight path Angle for a hypersonic vehicle.
对一个高超声速飞行器设计了滑动模态观测器来估计攻角和航迹倾角。
After adopting the correcting method of flight path Angle, flight path planned is further modified and ideal reference flight path is obtained.
航迹角修正法的采用，进一步修正了规划出的飞行轨迹，从而获得了理想的飞行参考轨迹。
The effects of the cocktail on overload, the level and vertical acceleration on flight path Angle, sinking velocity and extra required propulsion were analyzed during the glide of the aircraft.
着重分析了舰载飞机在下滑过程中，雄鸡尾流对过载以及雄鸡尾流水平加速度、铅垂加速度对航迹角、下沉率和附加需用推力的影响。
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