Short-range air-to-air missile guidance for all-aspect target interception

Abstract

This thesis proposes the look-angle based guidance law for all-aspect target interception. The guidance problem is formulated as a look-angle tracking problem and the desired look-angle is generated using collision geometry reflecting the time-varying missile velocity. Considering the characteristics of short-range air-to-air missiles, the guidance phase is divided into two phases. The first phase is the agile turn phase, which rapidly reduces look-angle error through large maneuvers. The second phase is the correction phase, which continuously compensates for the residual look-angle error. Guidance command in the agile turn phase is generated by error dynamics of look-angle error, and guidance command in the correction phase is generated by utilizing the condition for decrease in Lyapunov function. The characteristics of the proposed guidance are analyzed through comparison with PN guidance. Numerical simulation verifies that the proposed guidance effectively intercepts the maneuvering target, and robustly performs interception even under the missile parameter uncertainties. Finally, the feasible initial launch conditions and reachable area are estimated through the proposed guidance and capture region analysis.