Investigation of Robust Combination Control for Elastic Vehicle Based on Reduced-Order Model

Abstract:

Putting forward with an integrated flight and aeroelasticity control method of elastic air vehicle and aiming at the reduction errors introduced during combination dynamic model reduction, the paper adopts mixed sensitivity H_∞ control to design low-order combination control law that satisfies its robustness based on reduced-order model. Against to the wide reduced-order error bounds that may influence control performance, the two-circuit design method is used, and combined with inner-circuit suboptimal feedback design, error bounds of equivalent model are greatly narrowed. Without any orders extra added to the controllers, the outer-circuit robust controller designed on that basis will effectively improve the performance of the system, significantly superior to the single circuit design method. It is shown in simulation results that such low-order combination law will not only provide satisfactory robustness and performance, but will also effectively suppress the occurrence of servo flutter, while the greatly-reduced orders will be helpful for the realization of projects.

• Periodical: Applied Mechanics and Materials (Volume 378)
• Pages: 3-12
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.378.3
• Online since: August 2013
• Authors: Zi Jian Zhang, Bin Liu
• Keywords: Aero-Servo-Elasticity, Elastic Vehicle, Model Reduction, Robust H_∞ Control

References

[1] Kapsecong Ro, Jewel B. Barlow, Gyunghyun Bae. Integrated flight control law synthesis for an aeroelastic forward-swept wing aircraft. AIAA 1992-0046.

DOI: 10.2514/6.1992-46

[2] Peper Y. Cheng, Timothy J. Hirner. Automated procedures for aircraft aeroservoelastic compensation. AIAA 1992-4606.

DOI: 10.2514/6.1992-4606

[3] David K. Schmidt. On the integrated control of flexible supersonic transport aircraft. AIAA 1995-3200.

[4] Ed Pendleton, Denis Bessette, Pete Field, Gerry Miller, Kenneth Griffin. The Active Aeroelastic Wing Flight Research Program - Technical program and model analytical development. AIAA 1998-(1972).

DOI: 10.2514/6.1998-1972

[5] Gertjan Looye. Integrated flight mechanics and aeroelastic aircraft modeling using object-oriented modeling techniques. AIAA 1999-4192.

DOI: 10.2514/6.1999-4192

[6] T. Jackson, E. Livne. Integrated Aeroservoelastic Design Optimization of Actively-Controlled Strain-Actuated Flight Vehicles. AIAA 2005-2170.

DOI: 10.2514/6.2005-2170

[7] Dario H. Baldelli, P.C. Chen. Unified Rational Function Approximation Formulation For Aeroelastic And Flight Dynamics Analyses. AIAA 2006-(2025).

DOI: 10.2514/6.2006-2025

[8] F. Kubica, T. Livet. Flight control law synthesis for a flexible aircraft. AIAA 1994-3630.

[9] M. Hanel. Integrated flight and aeroelastic control of a flexible transport aircraft. AIAA 1998-4297.

[10] Boris Moulin, Moshe Ldan, Mordechay Karpel. Aeroservoelastic structural and control optimization using classical and modern robust design schemes. AIAA 2000-1453.

DOI: 10.2514/6.2000-1453

[11] M. Goman, M. Sidoryuk, A. Ustinov. Control law design for flexible aircraft - Comparison of the H-infinity-based and classical methods. AIAA 2005-6265.

DOI: 10.2514/6.2005-6265

[12] Zames G. Feedback and Optimal Sensitivity: Model Reference Transformations, Multi plicative Seminorms, and Approximate Inverse. IEEE Trans., 1981, AC-26: 301-320.

DOI: 10.1109/tac.1981.1102603