Guidance Laws Based on Optimal Feedback Linearization Pseudocontrol with Time-to-Go Estimation

摘要

The planar nonlinear (NL) problem of an ideal aerial interceptor pursuing an evasive target is studied. New closed-loop analytical optimal-feedback linearization-based guidance laws (OFL-GLs) are proposed using feedback linearization (FL) and OC theory, with zero-effort time-to-go estimation. The first is range OFL-GL (R-OFL-GL) and the second is parallel OFL-GL (P-OFL-GL). The resulting strategies are discussed with respect to the obtained optimal FL pseudocontrollers. In addition, the roles of the fictitious forces (i.e., Coriolis and centrifugal) are discussed and related to the obtained singularities of the resulting guidance strategies. Simulation results (shown in Appendix C) indicate that R-OFL-GL is less efficient in terms of control effort in comparison with P-OFL-GL, when the pursuit scenario starts with a collision course geometry. When starting on that geometry and when linearity is violated, R-OFL-GL strategy applies an extensive guidance effort to leave this geometry, whereas P-OFL-GL applies less effort to stay on it. When initial heading errors are considered for the bearing angle, using R-OFL-GL results with singular behavior, whereas using P-OFL-GL does not. When large heading errors are considered, P-OFL-GL does not guarantee capture.