为了减小再入段风干扰造成的误差，利用在Simulink中建立的数字打靶平台对它进行了研究。
To reduce the wind disturbance error, the wind disturbance regular pattern is studied using a missile simulation system based on the SIMULINK.
在现有再入段解析方法的基础上，考虑更为贴近实际的条件因素，求得一组新的弹道导弹再入弹道解析解。
A new analytic solution of the ballistic missiles reentry trajectory is presented by considering some more actual factors on the basis of the existing analytic solution.
文中在简化的大气模型下建立TBM的再入段方程，并采用龙格-库塔法来求解，通过仿真，可以看出模型符合仿真需要。
The paper has brought out functions of the reentry trajectory of TBM in case of the predigest model of atmosphere and solved them by the Runge-Kutta method.
针对于目前地磁传感器测量精度较低，将其信息直接用于飞行器再入段定高误差较大的问题，提出了一种在线预测进行定高的方法。
Against the big error of height determination for the reentry vehicle because of the information provided by low precision geomagnetic sensor, a novel real-time prediction method is proposed.
在配平迎角飞行的合理假设下，建立了描述载人飞船再入飞行段弹道的数学仿真模型。
On the reasonable assumption of match AOA (Angle of attack) flight, the mathematics simulation model of the reentry flight of a spaceship is formulated in this paper.
分析结果表明，反导系统红外探测器在再入飞行段的最佳工作波段是短波和中波。
The analysis results demonstrate that the infrared detector of the anti-missile system in the reentry can work well on short wave and medium wave.
研究了在降弧段进行高空机动的再入飞行器最优制导律。
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
将再入航迹分为助推加速段和无动力滑翔段分别优化，从而得到优化航迹。
The trajectory was divided into boost phase and glide phase, which were optimized respectively and the optimal trajectory was obtained.
将再入航迹分为助推加速段和无动力滑翔段分别优化，从而得到优化航迹。
The trajectory was divided into boost phase and glide phase, which were optimized respectively and the optimal trajectory was obtained.
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