Record number :
2230644
Title of article :
Roll-pitch-yaw integrated μ-synthesis for high angle-of-attack missiles
Author/Authors :
Choi، نويسنده , , Byunghun and Kang، نويسنده , , Seonhyeok and Kim، نويسنده , , H. Jin and Jun، نويسنده , , Byung-Eul and Lee، نويسنده , , Jin-Ik and Tahk، نويسنده , , Min-Jea and Park، نويسنده , , Changhan، نويسنده ,
Issue Information :
روزنامه با شماره پیاپی سال 2012
Pages :
10
From page :
270
To page :
279
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.
Keywords :
Robust control , ? synthesis , Aerodynamic coupling , Multivariable system , Skid-to-turn missile
Journal title :
Aerospace Science and Technology
Journal title :
Aerospace Science and Technology
Serial Year :
2012
Link To Document :
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