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SINS-CNS.rar
- 弹道导弹SINS/CNS组合导航的程序，在发射点惯性坐标系下,Ballistic Missile SINS/CNS Integrated Navigation of the program, the launch point inertial coordinate system
LabVIEW-basedsimulationoftheopenspacesystemdesignb
- 基于LabVIEW的空地导弹弹道仿真系统设计-LabVIEW-based simulation of the open space system design ballistic missile
pingxing
- 采用平行接近法对导弹飞行制导过程进行弹道模拟-Parallel close to the method of ballistic missile flight guidance process simulation
ballistic_missile_inertial_navigation
- 弹道导弹从东经120北纬20高度30公里打目标东经150北纬30高度0的目标，关机点及飞行时间计算。还介绍了惯性导航的内容。 对于弹道式导弹：目标作为地球上的某一点，它是随地球一起在惯性空间运动的，因此需要迭代求解需要速度和自由飞行时间。按照给出的程序进行多次迭代解算即可得出考虑地球自转时的关机点参数解算和飞行时间计算。-20 ballistic missile from a high degree of north latitude and 120 east longitude hit tar
CNS
- 天文导航，弹道导弹SINS/CNS组合导航，轨迹发生器，卡尔曼滤波-Celestial navigation, ballistic missile SINS/CNS integrated navigation, trajectory generator, Kalman filtering
Missile-guidance-laws
- 关于导弹拦截的相关技术研究，比较了现有价值的追逃策略及相关算法-The increasing maneuverability potential of tactical ballistic missiles motivates the development of improved interceptor guidance laws. In this paper two guidance laws are compared, both based on a pursuit–evasion di0
gas-and-steam-launch
- 水下潜艇导弹燃气蒸汽式弹射时的内弹道方程和参数求解。-Solving interior ballistic equations and parameters when missile launched by gas and steam system on submarine.