Guidance Law Design: Sliding Mode Control Approach

• Main Authors: Hao-Ting Chiang, 江浩霆
• Other Authors: Chieh-Li Chen
• Format: Others
• Language: zh-TW
• Published: 2006
• Online Access: http://ndltd.ncl.edu.tw/handle/85795984026601012063

碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 94 === In the previous time, most guidance law designs were chosen to be according to the line of sight rate, which is known as PNG law. The required missile maneuver command is calculated by means of the outer guidance loop alongside with the target information, which is transferred to the inner autopilot loop to change the control surface signal. The ideal performance may not be achieved since the real missile mathematical model is not anticipated in the outer loop in this framework, and the maneuver command may diverge as the line of sight rate changes suddenly when the target is very close. Based on ZEM obtained by means of integrated with missile mathematical model and integral-type sliding mode control, an integrated guidance law with smooth control signal and relatively low miss distance is proposed; the proposed guidance law neither has the chattering phenomena comparing with the conventional sliding mode design.