Modified three‐dimensional true proportional navigation and its inverse optimal form

Abstract

AbstractA novel three‐dimensional modified true proportional navigation (MTPN) guidance and its inverse optimal form are proposed for the interception of the nonmaneuvering and maneuvering targets, and the nonlinear dynamic characteristics of pursuit situations and target maneuvers are taken into full account. The proposed approach is feasible without knowing any prior information or estimate of the target maneuvers, which are regarded as the unknown disturbance input. Therefore, the TPN‐type guidance is extended to intercept the maneuvering targets with bounded unknown accelerations. Moreover, the explicit physical significance is given for each component of the navigation gain expression of MTPN. The inverse optimal control approach and the input‐to‐state stability are introduced to the MTPN design. Using the MTPN, the homing missile can conduct the terminal homing guidance phase in any particular direction with respect to their nonmaneuvering or maneuvering targets through choosing an appropriate inertial reference coordinate system in practice. Using the proposed schemes, the line‐of‐sight (LOS) rate is globally exponentially stable for nonmaneuvering targets, and is input‐to‐state stability (ISS) for maneuvering targets with bounded unknown accelerations. Performed simulation results have confirmed the effectiveness of the proposed scheme.