Abstract In this research, we explore the feasibility of a roll-pitch-yaw integrated autopilot for a high angle-of-attack missile. Investigation of the aerodynamic characteristics of a surface-to-air missile is presented, which reveals the strong effects of aerodynamic cross-coupling between the longitudinal and lateral dynamics. Robust control techniques based on H and μ-synthesis are employed to design roll-pitch-yaw integrated autopilots. The performance of the proposed roll-pitch-yaw integrated controller is tested in nonlinear simulation accounting for cross-coupling effects between the lateral and longitudinal channels. In comparison of H and μ controllers, the performance of μ controller is slightly better in terms of rising time and settling time of the response. Using μ analysis, we identified the suitable structure and magnitude of the uncertainty block representing the nonlinear perturbations and cross coupling in the missile dynamics. The level of robustness obtained cannot be achieved by a controlled designed in a decoupled manner.


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    Titel :

    Roll-pitch-yaw integrated μ-synthesis for high angle-of-attack missiles


    Beteiligte:
    Choi, Byunghun (Autor:in) / Kang, Seonhyeok (Autor:in) / Kim, H. Jin (Autor:in) / Jun, Byung-Eul (Autor:in) / Lee, Jin-Ik (Autor:in) / Tahk, Min-Jea (Autor:in) / Park, Changhan (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2011-08-18


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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    Optimal Trajectory Analysis of High Angle of Attack Missiles

    Innocenti, M. / Nasuti, F. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 1996