This paper studies the BTT missile's sliding mode flight controller. Firstly, the control model is established according to dynamic inverse method and the general dynamic equation of the missile flying in the atmosphere. Then, the sliding mode controller is designed and it adopts the time-varying sliding mode surface, the self-defined reaching law and the adaptive control parameters. Finally, three sets of simulation are carried out to prove the flight controller designed in this paper for BTT missile can follow the guidance instructions and meet operational needs.
A Specific Sliding Mode Control for Autopilot Design of Bank-to-Turn Missiles
2018
Aufsatz (Zeitschrift)
Elektronische Ressource
Unbekannt
Metadata by DOAJ is licensed under CC BY-SA 1.0
Bank-to-Turn Missiles and Autopilot Design
NTIS | 1990
|Adaptive sliding mode control for bank-to-turn missiles
Tema Archiv | 2009
|Autopilot Design for Bank-to-Turn Missiles Using Receding Horizon Predictive Control Scheme
Online Contents | 1997
|