Extended discrete‐time transfer matrix approach to modeling and decentralized control of lattice‐based structures

Summary This paper presents the modeling and control of an aircraft wing structure constructed by lattice-based cellular materials/components. A novel model reduction process is proposed that utilizes the extended discrete-time transfer matrix method (E-DT-TMM). Through recursive application of the E-DT-TMM, an effective reduced-order model can be obtained in which a decentralized discrete-time linear quadratic regulator (LQR) controller can be designed. To demonstrate the efficiency of the proposed concept, a prototype wing structure is studied. The analysis and simulation results show that the performance of the proposed E-DT-TMM based decentralized LQR controller is comparable with that of the full-state continuous LQR controller. Copyright © 2016 John Wiley & Sons, Ltd.

[1]  Yang Wang.  Time‐delayed dynamic output feedback ℋ︁∞ controller design for civil structures: A decentralized approach through homotopic transformation , 2011 .

[2]  T. S. Sankar,et al.  A new transfer matrix method for response analysis of large dynamic systems , 1986 .

[3]  Xiaoting Rui,et al.  Controller Parameters Tuning Based on Transfer Matrix Method for Multibody Systems , 2014 .

[4]  Ryan W. Krauss,et al.  Discrete-time transfer matrix modeling of flexible robots under feedback control , 2013, 2013 American Control Conference.

[5]  Nhan Nguyen,et al.  Aeroelastic Modeling of Elastically Shaped Aircraft Concept via Wing Shaping Control for Drag Reduction , 2012 .

[6]  Kenneth C. Cheung,et al.  Reversibly Assembled Cellular Composite Materials , 2013, Science.

[7]  Ryan W Krauss.  Computationally efficient modeling of flexible robots using the transfer matrix method , 2012 .

[8]  Nhan Nguyen,et al.  NASA Innovation Fund 2010 Project Elastically Shaped Future Air Vehicle Concept , 2010 .

[9]  T. M. Tan,et al.  A modified finite element-transfer matrix for control design of space structures , 1990 .

[10]  John L. Junkins,et al.  Robust Control of Redundantly Actuated Dynamical Systems , 2006 .

[11]  Zafer Gürdal,et al.  Mechanism for Warp-Controlled Twist of a Morphing Wing , 2010 .

[12]  John L. Junkins,et al.  Design of a morphing wing: Modeling and experiments , 2007 .

[13]  Manoranjan Majji,et al.  Robust control of redundantly actuated dynamical systems , 2006 .

[14]  Samuel Eli Calisch,et al.  Physical finite elements , 2014 .

[15]  Mark S. Shephard,et al.  Combined finite element-transfer matrix method based on a mixed formulation , 1985 .

[16]  Li Ma,et al.  Fabrication and crushing behavior of low density carbon fiber composite pyramidal truss structures , 2010 .

[17]  Irina V. Belova,et al.  Theoretical and Lattice Monte Carlo analyses on thermal conduction in cellular metals , 2010 .

[18]  Guoping Wang,et al.  Discrete time transfer matrix method for dynamics of multibody system with real-time control , 2010 .

[19]  Nhan T. Nguyen,et al.  Aeroelastic Wing Shaping Control Subject to Actuation Constraints. , 2014 .

[20]  Shaker A. Meguid,et al.  Shape morphing of aircraft wing: Status and challenges , 2010 .

[21]  Michael J. Aftosmis,et al.  Optimized Off-Design Performance of Flexible Wings with Continuous Trailing-Edge Flaps , 2015 .

[22]  M. Ashby,et al.  The mechanics of three-dimensional cellular materials , 1982, Proceedings of the Royal Society of London. A. Mathematical and Physical Sciences.

[23]  Eric Ting,et al.  A Mission-Adaptive Variable Camber Flap Control System to Optimize High Lift and Cruise Lift-to-Drag Ratios of Future N+3 Transport Aircraft , 2013 .

[24]  Bin He,et al.  Discrete time transfer matrix method for dynamics of multibody system with flexible beams moving in space , 2012 .

[25]  V. V. Vasiliev,et al.  Anisogrid composite lattice structures for spacecraft and aircraft applications , 2006 .

[26]  Kenneth C. Cheung,et al.  Digital cellular solids : reconfigurable composite materials , 2012 .