- 作者: Lu-Ping TSAO and Ching-Show LIN
- 中文摘要: It is assumed that precise knowledge of a target? motion is available to a missile. Using the exact nonlinear equations of motion in the plane, a new optimal guidance law (OPG) for short-range homing missiles, based on minimizing the interception time, is presented. Unlike the conventional optimal guidance approach where the commanded lateral acceleration of the missile is considered to be the control variable, this study directly exploits the flight-path angle as the control variable to derive analytically the optimal missile trajectory needed to intercept the target. Numerical simulation has been used to evaluate the performance of the proposed guidance law and to make a comparison with the performance of the true proportional navigation (TPN) and augmented proportional navigation law (APN). It is verified that the performance of the proposed guidance law, in terms of the interception time and miss distance is superior to that of the other two schemes. Use of the APN leads to the smallest control energy expenditure among the three schemes.
- 英文摘要: --
- 中文關鍵字: homing missiles, optimal guidance, proportional navigation law
- 英文關鍵字: --