In this article, a method to make the normal acceleration of medium angle of attack missile to track some desired trajectories is presented. The dynamics which describe a missile acceleration are known to be non-minimum phase, which makes it difficult to use a straightforward feedback linearization technique. This article aims at showing that this problem may be overcome by employing cascaded regulations in the non-linear area. First, inner loop controller by dynamical sliding mode control (SMC) method based on asymptotic output tracking is designed for angle of attack control which has a minimum phase characteristics. Also then, the problem that is addressed here is the completion of the global loop by designing an additional outer loop proportional-integral (PI) controller and angle of attack estimator. The performance and stability of proposed method are illustrated via computer simulations.
Missile acceleration controller design using proportional-integral and non-linear dynamic control design method
Entwurf eines Raketen-Beschleunigungs-Controllers mit Hilfe einer proportional-integralen und nichtlinear-dynamischen Steuerungsdesignmethode
2012
16 Seiten, 15 Bilder, 17 Quellen
Aufsatz (Zeitschrift)
Englisch
Beschleunigungsverhalten , Raketenantrieb , Steuerungs- und Regelungsverfahren , Steuerungs-Controller , Kaskadenregelung , nichtlineares dynamisches System , PI-Regler , Anstellwinkel (Tragflügel) , Schätzfunktion , Betriebsverhalten , Stabilität , rechnerunterstützte Simulation , Design (Entwurf) , asymptotische Näherung , Bahnverfolgung
Missile Acceleration in Proportional Navigation
IEEE | 1973
|BASE | 2021
|BASE | 2016
|