摘要
实现了一种基于摄动制导的弹道导弹的发射诸元算法。给定发射点与瞄准点的地理位置,通过一种迭代方法求解发射方位角和标准关机时间,并以此确定自发射点到瞄准点的标准弹道。采用求差法解算摄动制导的关机方程与导引方程系数。最后给出诸元计算软件流程图。将该软件应用于某导弹六自由度飞行仿真系统的发射诸元计算,论证了该算法的可行性。
It is presented an effective approach for computing the basic firing data of missiles. If the launch position and aiming position are given, the launch orientation and shutoff time can be gotten by iterative method. Then the standard trajectory data is obtained by numerical integral algorithm. And the differential method is applied to compute coefficients of the shutoff equation and guidance equations. Finally the feasibility of this approach is proven by an application to a six-degree flight simulation of one type of missile.
出处
《系统仿真学报》
EI
CAS
CSCD
北大核心
2005年第5期1048-1051,共4页
Journal of System Simulation
关键词
发射诸元
弹道导弹
摄动制导
仿真
firing data
ballistic missile
disturbance guidance
simulation
