Dept. of Electr. Eng., National Taiwan Univ.Yeh, Fu-KuangFu-KuangYehChien, Hsiuan-HauHsiuan-HauChienLI-CHEN FU2007-04-192018-07-062007-04-192018-07-06200107431619http://ntur.lib.ntu.edu.tw/bitstream/246246/2007041910021279/1/00946104.pdfhttps://www.scopus.com/inward/record.uri?eid=2-s2.0-0034842073&doi=10.1109%2fACC.2001.946104&partnerID=40&md5=38a976488f21b14f1bbc5edcf900433cA nonlinear missile guidance controller with Thrust Vector Control (TVC) inputs for the interception of a theater ballistic missile is presented. In this paper, the midcourse phase of the missile is investigated, during which many non-ideal conditions must be considered, such as variation of the inertia of the missile and existence of the aerodynamic force, and an effect controller is designed take into account the properties of TVC. Specifically, a 3 DOF optimal midcourse guidance law is designed to minimize the control effort and the distance between the missile and the target. The asymptotic stability of the overall system is proved by Lyapunov theory. Extensive simulations are conducted to validate the effectiveness of the proposed guidance law for TVC.application/pdf313876 bytesapplication/pdfen-USNonlinear system; Optimal control; Quaternion; Sliding mode; Target tracking[SDGs]SDG16Computer simulation; Lyapunov methods; Missiles; Nonlinear systems; Optimal control systems; Sliding mode control; System stability; Tracking (position); Vectors; Optimal midcourse guidance law; Quaternion; Theater ballistic missile; Thrust vector control; Electronic guidance systemsjournal article10.1109/ACC.2001.9461042-s2.0-0034842073http://ntur.lib.ntu.edu.tw/bitstream/246246/2007041910021279/1/00946104.pdf