建立了可用于现代火控计算机的火控弹道权函数法模型。
Presents a weighted function model for the flight traJectory of projectiles, oriented for applications with computers in modern fire control systems.
建立了再入机动弹道数学模型，给出了气动力系数为速度、迎角、高度的函数拟合式，进行了最佳再入机动弹道设计和仿真计算。
The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
弹道修正弹；灵敏度函数；辨识；最优控制；舵机。
Trajectory correction projectile; Sensitivity function; Identification; Optimal control; Actuator.
在现有定位模型的基础上，通过函数误差传递关系，推导了弹道参数的误差表达式。
The error equation of the trajectory parameters is developed by the relationship of the error transmission function based on the intersection model.
最后，运用样条函数表示弹道参数，解决了计算量问题。
Finally, a fusion method to represent trajectory parameter with spline function is used, which solve the problem of huge computational cost.
仿真结果表明换极后的球谐函数计算扰动引力能够满足精度要求，且在计算中弹道方程的解算速度也有很大的提高。
The result of simulation indicates that this method not only satisfies the precision but also enables us to enhance the calculation speed of the trajectory equations.
通过与三体弹道模型的比较，从关联函数提取了轻粒子的发射时间。
Emission time of light particles has been extracted from correlation functions using the three-body trajectory model.
对一般空舰导弹的纵向下滑弹道进行了设计研究，提出用样条函数作为导弹的纵向下滑基准弹道。
The longitudinal glide trajectory design for general air-to-ship missile is studied. Using spline function as glide standard trajectory of missile is presented.
对一般空舰导弹的纵向下滑弹道进行了设计研究，提出用样条函数作为导弹的纵向下滑基准弹道。
The longitudinal glide trajectory design for general air-to-ship missile is studied. Using spline function as glide standard trajectory of missile is presented.
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