TY - GEN
T1 - PDE boundary control for flexible articulated aircraft wings
AU - Paranjape, Aditya A.
AU - Chung, Soon Jo
AU - Krsticz, Miroslav
PY - 2011/12/1
Y1 - 2011/12/1
N2 - The paper considers a boundary control formulation for PDEs with a system output given by a spatial integral of weighted functions of the state. This formulation is directly applicable to the control of an aircraft with articulated flexible wings, in which case the output of interest is a net aerodynamic force or moment. Flexible wings can be controlled via actuation at the root or the tip. The problem of beam twist is analysed in detail to illustrate the formulation, and it shown that the control law ensures that the error between the desired output signal and the actual output signal decreases exponentially to an uniform ultimate bound. Stability of the closed loop system is proved by Lyapunov techniques. The formulation is demonstrated by simulations.
AB - The paper considers a boundary control formulation for PDEs with a system output given by a spatial integral of weighted functions of the state. This formulation is directly applicable to the control of an aircraft with articulated flexible wings, in which case the output of interest is a net aerodynamic force or moment. Flexible wings can be controlled via actuation at the root or the tip. The problem of beam twist is analysed in detail to illustrate the formulation, and it shown that the control law ensures that the error between the desired output signal and the actual output signal decreases exponentially to an uniform ultimate bound. Stability of the closed loop system is proved by Lyapunov techniques. The formulation is demonstrated by simulations.
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M3 - Conference contribution
AN - SCOPUS:84880577563
SN - 9781600869525
T3 - AIAA Guidance, Navigation, and Control Conference 2011
BT - AIAA Guidance, Navigation, and Control Conference 2011
T2 - AIAA Guidance, Navigation and Control Conference 2011
Y2 - 8 August 2011 through 11 August 2011
ER -