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## Continuous Robust Control for Two-Dimensional Airfoils with Leading- and Trailing-Edge Flaps

Citations: | 1 - 1 self |

### Citations

866 |
Nonlinear and Adaptive Control Design
- Krstic, Kanellakopoulos, et al.
- 1995
(Show Context)
Citation Context ...rix S such that GS is positive-definite and symmetric. Based on the assumption that the HFG matrix was known, an adaptive backstepping technique was proposed for parametric strict feedback systems in =-=[27]-=-. In [28], a Lyapunov-based adaptive output feedback control was designed for a general class of MIMO systemwith unknown constant parameters, but susceptible to singularities owing to the existence of... |

433 |
Sliding Modes in Control Optimization.
- Utkin
- 1992
(Show Context)
Citation Context ... design. Some other examples relating to NN applications inMIMO control can be found in [32]. A summary of the theory and application of robust and sliding mode control in MIMO system can be found in =-=[33]-=-. In this paper, a novelMIMO continuous robust controller (i.e., C0) is designed to asymptotically stabilize the MIMO aeroelastic system with unstructured nonlinear uncertainties and bounded unknown e... |

369 |
Robust Adaptive Control
- Ioanno, Sun
- 1996
(Show Context)
Citation Context ...design for this kind ofMIMO systemswith uncertainty based on a variety of techniques and assumptions. In [25], the highfrequency gain (HFG) matrix G was assumed to be known for the control design. In =-=[26]-=-, a control law was proposed that required the existence of a matrix S such that GS is positive-definite and symmetric. Based on the assumption that the HFG matrix was known, an adaptive backstepping ... |

58 | A SemiEmpirical Model for Dynamic Stall,” - Leishman, Beddoes - 1989 |

53 |
Nonlinear Systems. Prentice-Hall, Upper Saddle River
- Khalil
- 2000
(Show Context)
Citation Context ...s4 or, equivalently, z t 2 D ≜ fzjkzk < 11 2 K 3 s4 p g This ensures that the first parenthesized term in Eq. (37) is nonnegative. Motivated by Theorem 8.4 in =-=[40]-=- and the definition of y and D, the region D can be explicitly given as D ≜ fyjkyk < 11 2 K 3 s4 p g Since K≜Kp diagfKd1; 0g, it is clear to see that K22 is det... |

51 | A continuous asymptotic tracking control strategy for uncertain nonlinear systems,”
- Xian, Dawson, et al.
- 2004
(Show Context)
Citation Context ...he MIMO aeroelastic system with unstructured nonlinear uncertainties and bounded unknown external disturbance. The result in this paper is motivated by a singleinput/single-output result presented in =-=[34]-=-. The challenge in extending this result to the MIMO system presented in this paper is due to the coupling of the control inputs, which causes the leadingedge flap displacement to appear as a disturba... |

14 |
Robust Aeroservoelastic Stability Analysis
- Lind, Brenner
- 1999
(Show Context)
Citation Context ... [1–6]. Among the latest active control methodologies, adaptive and robust control of nonlinear aeroelastic models was presented in [5], the -method for robust aeroservoelastic stability analysis in =-=[7]-=-, gain scheduled controllers in [8], and neural and adaptive control in [9]. Linear control theory, feedback linearizing techniques, and adaptive control strategies have been derived to account for th... |

14 |
Output Feedback Variable Structure Adaptive Control of a Flexible Spacecraft,”
- Zeng, Araujo, et al.
- 1999
(Show Context)
Citation Context ...nonlinear structural stiffness [10]. A model reference variable structure adaptive control system for plunge-displacement and pitch-angle control has been designed using bounds on uncertain functions =-=[11]-=-. This approach yields a high-gain feedback discontinuous control system. In [12–14], an adaptive design method for flutter suppression has been adopted while using measurements of either or both of t... |

13 |
Output feedback control for a class of uncertain mimo nonlinear systems with non-symmetric input gain matrix
- Zhang, Behal, et al.
- 2005
(Show Context)
Citation Context ...rities owing to the existence of an algebraic loop in the controller. Later, in [29], this problem was solved by designing a singularity-free output feedback controller with parameter uncertainty. In =-=[30]-=-, the proposed controller yields semiglobal uniformly ultimately bounded tracking result while compensating for unstructured uncertainty in both the drift vector and the input matrix. Later, in [31], ... |

9 |
Pado, "Active control of wind-tunnel model aeroelastic response using neural networks
- RC, E
(Show Context)
Citation Context ...control of nonlinear aeroelastic models was presented in [5], the -method for robust aeroservoelastic stability analysis in [7], gain scheduled controllers in [8], and neural and adaptive control in =-=[9]-=-. Linear control theory, feedback linearizing techniques, and adaptive control strategies have been derived to account for the effect of nonlinear structural stiffness [10]. A model reference variable... |

9 | Adaptive output feedback control of a nonlinear aeroelastic structure - Xing, Singh - 2000 |

9 |
Multivariable high-authority control of plate-like active structures,”
- Lazarus, Crawley
- 1992
(Show Context)
Citation Context ...continuous control system. In [12–14], an adaptive design method for flutter suppression has been adopted while using measurements of either or both of the pitching and plunging variables. Results in =-=[15]-=- demonstrated that the proposed full state feedback active control mechanism with an estimator was efficient by using a typical section with leading- and trailing-edge flaps. Disturbance rejection, gu... |

8 | Comparing linear parameter-varying gain-scheduled control techniques for active flutter suppression
- Barker, Balas
- 2000
(Show Context)
Citation Context ...trol methodologies, adaptive and robust control of nonlinear aeroelastic models was presented in [5], the -method for robust aeroservoelastic stability analysis in [7], gain scheduled controllers in =-=[8]-=-, and neural and adaptive control in [9]. Linear control theory, feedback linearizing techniques, and adaptive control strategies have been derived to account for the effect of nonlinear structural st... |

8 | Control of a nonlinear wing section using leading-and trailing-edge surfaces.
- Platanitis, Strganac
- 2004
(Show Context)
Citation Context ...e performance through an extension to a wing section with both trailingedge control surface (TECS) and leading-edge control surface (LECS). An adaptive full state feedback control law was provided in =-=[21]-=-. However, only an inversion of a nominal input gain matrix was used to decouple the control inputs without considering the uncertainty. In [22], adaptive and radial basis function neural network cont... |

8 |
Multi-input/multioutput adaptive output feedback control design for Zhang and Behal 17 at
- KK, Chen, et al.
- 2007
(Show Context)
Citation Context ...ut considering the uncertainty. In [22], adaptive and radial basis function neural network controllers were provided in order to compensate for the system nonlinearity and compared via simulation. In =-=[23]-=-, an output feedback adaptive control algorithm was proposed by using a backstepping technique, and an SDU decomposition (symmetricdiagonal-upper triangular factorization) was applied on the input gai... |

7 | A gain matrix decomposition and some of its applications
- Morse
- 1993
(Show Context)
Citation Context ...sICl mwxb2Cmeff g21 U211bsmwxbCl mTbCmeff g22 U211bsmwxbCl mTbCmeff (6) where ≜ detGs mTI m2wx2b2 ≠ 0 Motivated by the matrix decomposition approach introduced in =-=[39]-=- and the facts that both the leading principal minors g11 and are nonzero, Gs can be decomposed as Gs SDU, where S is a symmetric positive-definite matrix, D is a diagonal matrix with diagonal ent... |

6 | Advances in the linear/nonlinear control of aeroelastic structural systems,” - Librescu, Marzocca - 2005 |

5 | Adaptive Control of Aeroelastic Instabilities in Transonic flow and Its Scaling,’ - Friedmann, Guillot, et al. - 1997 |

5 |
Adaptive Output Feedback Control of an Aeroelastic System with Unstructured Uncertainties
- Zhang, Singh
- 2001
(Show Context)
Citation Context ...ural and adaptive control in [9]. Linear control theory, feedback linearizing techniques, and adaptive control strategies have been derived to account for the effect of nonlinear structural stiffness =-=[10]-=-. A model reference variable structure adaptive control system for plunge-displacement and pitch-angle control has been designed using bounds on uncertain functions [11]. This approach yields a high-g... |

5 | Adaptive control for a nonlinear wing section with multiple flaps - Behal, Rao, et al. - 2006 |

5 |
2001 Aeroelastic response of 2-D lifting surfaces to gust and arbitrary explosive loading signature
- MARZOCCA, LIBRESCU, et al.
(Show Context)
Citation Context ...th LECS and TECS is illustrated in Fig. 1. The classical aeroelastic governing equations for the sectional wing subject to bounded external disturbance are developed from previous models according to =-=[21,35]-=- mT mwxb mwxb I " # h " # ch 0 0 c " # _h _ " # kh 0 0 k " # h " # LLg MMg " # (1) All the definitions of symbols used in Eq. (1) can be found in the Nomenclature. The quasi-st... |

4 | Benchmark Active Control Technology - Mukhopadhyay - 2001 |

3 |
Output feedback form and adaptive stabilization of a nonlinear aeroelastic system
- SN, Wang
- 2002
(Show Context)
Citation Context ...icient by using a typical section with leading- and trailing-edge flaps. Disturbance rejection, gust alleviation, and flutter suppression were also demonstrated in the experimental investigations. In =-=[16]-=-, an adaptive backstepping design technique was used to control the pitch angle with only output measurements. In [17], an Received 23 March 2011; revision received 29 July 2011; accepted for publicat... |

3 |
Global robust control of an aeroelastic system using output feedback
- Lee, Singh
- 2007
(Show Context)
Citation Context ...ts performance toward suppressing flutter and limit cycle oscillations (LCOs), as well as reducing the aeroelastic response in the subcritical flight-speed regime was also demonstrated. Lee and Singh =-=[18]-=- designed a robust control law for the global regulation of a two-degree-of-freedom (2-DOF) aeroelastic system. The model had polynomial type structural nonlinearity and only the pitch angle was measu... |

3 |
W.: Adaptive and Neural Control of a Wing Section Using Leading- and Trailing-edge Surfaces
- Gujjula, Singh, et al.
(Show Context)
Citation Context ...daptive full state feedback control law was provided in [21]. However, only an inversion of a nominal input gain matrix was used to decouple the control inputs without considering the uncertainty. In =-=[22]-=-, adaptive and radial basis function neural network controllers were provided in order to compensate for the system nonlinearity and compared via simulation. In [23], an output feedback adaptive contr... |

3 |
Adaptive Output Feedback Control for a Class of MIMO Nonlinear Systems
- Chen, Behal, et al.
- 2006
(Show Context)
Citation Context ...h that GS is positive-definite and symmetric. Based on the assumption that the HFG matrix was known, an adaptive backstepping technique was proposed for parametric strict feedback systems in [27]. In =-=[28]-=-, a Lyapunov-based adaptive output feedback control was designed for a general class of MIMO systemwith unknown constant parameters, but susceptible to singularities owing to the existence of an algeb... |

2 | Adaptive aeroelastic Vibration Suppression of a Supersonic Airfoil with Flap - Rao, Behal, et al. - 2006 |

2 |
Nonlinear Adaptive Control of an Aeroelastic Two-Dimensional Lifting Surface
- Behal, Marzocca, et al.
(Show Context)
Citation Context ...flutter suppression were also demonstrated in the experimental investigations. In [16], an adaptive backstepping design technique was used to control the pitch angle with only output measurements. In =-=[17]-=-, an Received 23 March 2011; revision received 29 July 2011; accepted for publication 15 August 2011. Copyright © 2011 by Z. Wang, A. Behal, and P. Marzocca. Published by the American Institute of Aer... |

2 |
Active flutter suppression of a nonlinear aeroelastic system using pi-observer,” in Motion and Vibration
- Zhang, Söffker
- 2009
(Show Context)
Citation Context ...hereas the bounds of uncertainties were assumed to be known in the control design. Another robust control strategy for active flutter suppression of a nonlinear 2-D wing-flap system was introduced in =-=[19]-=-. An optimized state feedback robust stabilizer with a proportional– integral observer (PI-observer) was designed in which the PIobserver was adopted to estimate both the system states and the bounds ... |

2 |
Immersion and invariance based adaptive control of a nonlinear aeroelastic system
- Lee, Singh
- 2009
(Show Context)
Citation Context ... nonlinearities in the aeroelastic system. Based on the immersion and invariance approach, the adaptive control design problem for aeroelastic wing sections with structural nonlinearity was solved in =-=[20]-=-. Several control algorithms were proposed in [21–23] for the 2DOFaeroelastic system,which efficiently improved the performance through an extension to a wing section with both trailingedge control su... |

2 |
Model-Free Control Design for MIMO Aeroelastic System Subject to External Disturbance
- Wang, Behal, et al.
- 2011
(Show Context)
Citation Context ...y-free controller. The backstepping approach in [23] led to a very complicated control design: more than 200 parameters needed to be tuned online, due to significant overparameterization problems. In =-=[24]-=-, a modular output feedback controller was proposed to suppress aeroelastic vibrations on unmodeled nonlinear wing section subject to a variety of external disturbances. Although the computation load ... |

1 |
Advances in the Adaptive Robust Control of Aeroelastic Structural Systems
- Wang, Behal, et al.
(Show Context)
Citation Context ...ber of contributions related to the topic are discussed at length in [1–6]. Among the latest active control methodologies, adaptive and robust control of nonlinear aeroelastic models was presented in =-=[5]-=-, the -method for robust aeroservoelastic stability analysis in [7], gain scheduled controllers in [8], and neural and adaptive control in [9]. Linear control theory, feedback linearizing techniques,... |

1 |
RobustAdaptiveControl Design for a Class of Uncertain MIMO Nonlinear Systems
- Wang, Chen, et al.
- 2010
(Show Context)
Citation Context ...back control was designed for a general class of MIMO systemwith unknown constant parameters, but susceptible to singularities owing to the existence of an algebraic loop in the controller. Later, in =-=[29]-=-, this problem was solved by designing a singularity-free output feedback controller with parameter uncertainty. In [30], the proposed controller yields semiglobal uniformly ultimately bounded trackin... |

1 |
Robust Feedback Control for aClass ofUncertainMIMONonlinear Systems
- Chen, Behal, et al.
- 2008
(Show Context)
Citation Context ...n [30], the proposed controller yields semiglobal uniformly ultimately bounded tracking result while compensating for unstructured uncertainty in both the drift vector and the input matrix. Later, in =-=[31]-=-, a locally uniformly ultimately bounded result was obtained by applying an output feedback robust continuous control law for a class of MIMO system with uncertain C2 nonlinearities; a neural network ... |

1 | Nonlinear Aeroelastic Formulation for Flexible High-Aspect Ratio Wings via Geometrically Exact Approach,” AIAA Paper 2011-1916 - Arena, Lacarbonara, et al. |