Roll-Pitch-Yaw Integrated Robust Autopilot Design for a High Angle-of-Attack Missile

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This paper explores the feasibility of roll-pitch-yaw integrated autopilots for a high angle-of-attack missile. Investigation of the aerodynamic characteristics indicates strong cross-coupling effects between the motions in longitudinal and lateral directions. Robust control techniques based on H(infinity) synthesis are employed to design roll-pitch-yaw integrated autopilots. The performance of the proposed roll-pitch-yaw integrated controller is tested in high-fidelity nonlinear 5-degree-of-freedom simulations. The proposed controllers are scheduled as a function of total angle of attack in a linear parameter varying framework with proportional navigation guidance laws. The integrated controller demonstrates satisfactory performance that cannot be achieved by the controller designed in a decoupled manner.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
2009-09
Language
English
Article Type
Article
Keywords

PARAMETER; AIRCRAFT; IMPACT

Citation

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, v.32, no.5, pp.1622 - 1628

ISSN
0731-5090
DOI
10.2514/1.39812
URI
http://hdl.handle.net/10203/99659
Appears in Collection
AE-Journal Papers(저널논문)
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