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Research Papers

Coupled Flight-Dynamic and Low-Order Aeroelastic Model for a Slender Launch Vehicle

[+] Author and Article Information
Andrew J. Sinclair

Associate Professor
Aerospace Engineering Department,
Auburn University,
Auburn, Alabama 36849
e-mail: sinclair@auburn.edu

George T. Flowers

Professor
Mechanical Engineering Department,
Auburn University,
Auburn, Alabama 36849
e-mail: flowegt@auburn.edu

Contributed by the Design Engineering Division of ASME for publication in the Journal of Vibration and Acoustics. Manuscript received January 24, 2011; final manuscript received April 30, 2012; published online February 25, 2013. Assoc. Editor: Bogdan Epureanu.

J. Vib. Acoust 135(2), 021002 (Feb 25, 2013) (8 pages) Paper No: VIB-11-1015; doi: 10.1115/1.4023049 History: Received January 24, 2011; Revised April 30, 2012

This paper presents a method to develop a low-order aeroelastic model that qualitatively captures some of the phenomena experienced by launch vehicles, suitable for use in preliminary controller design. Equations of motion for the two-dimensional dynamics are derived by treating the vehicle as a beam with a gimbaled nozzle attached at the aft end. The flexible-body dynamics are kinematically described using a modal representation. An aerodynamic model focuses on flow separations at diameter transitions in the transonic regime that can lead to lengthwise variations in the applied aerodynamic force. Additionally, convective effects are modeled that lead to time lag in the aerodynamic forces. The equations of motion are tenth order when neglecting convective effects and twelfth order when including convective effects. The model demonstrates some of the possible coupling that occurs between rigid-body, flexible-body, and aerodynamic states. For representative parameter values, the aeroelastic coupling can destabilize the flexible-body motion. The resulting linearized model is not fully controllable, however, is stabilizable.

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References

Whorton, M. S., Hall, C. E., and Cook, S. A., 2007, “Ascent Flight Control and Structural Interaction for the Ares-I Crew Launch Vehicle,” AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Honolulu, HI, April 23–26, Paper No. AIAA 2007-1780. [CrossRef]
Hall, C., Lee, C., Jackson, M., Whorton, M., West, M., Brandon, J., Hall, R. A., Jang, J.-W., Bedrossian, N., Compton, J., and Rutherford, C., 2008, “Ares I Flight Control System Overview,” AIAA Guidance, Navigation, and Control Conference, Honolulu, HI, April 18–21, Paper No. AIAA 2008-6287. [CrossRef]
Gupta, K. K., 1996, “Development of a Finite Element Aeroelastic Analysis Capability,” J. Aircr., 33(5), pp. 995–1002. [CrossRef]
Friedmann, P. P., McNamara, J. J., Thuruthimattam, B. J., and Nydick, I., 2004, “Aeroelastic Analysis of Hypersonic Vehicles,” J. Fluids Struct., 19(5), pp. 681–712. [CrossRef]
McNamara, J. J., Friedmann, P. P., Powell, K. G., Thuruthimattam, B. J., and Bartels, R. E., 2008, “Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow,” AIAA J., 46(10), pp. 2591–2610. [CrossRef]
McNamara, J. J. and Friedmann, P. P., 2011, “Aeroelastic and Aerothermoelastic Analysis in Hypersonic Flow: Past, Present, and Future,” AIAA J., 49(6), pp. 1089–1122. [CrossRef]
Bartels, R. E., 2008, “Development of Advanced Computational Aeroelasticity Tools at NASA Langley Research Center,” NATO RTO Specialists Meeting on Advanced Aeroelasticity, Paper No. AVT-154-003.
Bartels, R. E., Vatsa, V., Carlson, J.-R., Park, M., and Mineck, R. E., 2010, “FUN3D Grid Refinement and Adaptation Studies for the Ares Launch Vehicle,” AIAA Applied Aerodynamics Conference, Chicago, June 28–July 1, Paper No. AIAA 2010-4372. [CrossRef]
Bartels, R. E., Chwalowski, P., Massey, S. J., Heeg, J., Wieseman, C. D., and Mineck, R. E., 2010, “Computational Aeroelastic Analysis of the Ares Launch Vehicle During Ascent,” AIAA Applied Aerodynamics Conference, Chicago, June 28–July 1, Paper No. AIAA 2010-4374. [CrossRef]
Dowell, E. H. and Hall, K. C., 2001, “Modeling of Fluid-Structure Interaction,” Ann. Rev. Fluid Mech., 33, pp. 445–490. [CrossRef]
Dowell, E., Thomas, J., and Hall, K., 2004, “Transonic Limit Cycle Oscillation Analysis Using Reduced Order Aerodynamic Models,” J. Fluids Struct., 19(1), pp. 17–27. [CrossRef]
Silva, W. and Bartels, R., 2004, “Development of Reduced-Order Models for Aeroelastic Analysis and Flutter Prediction Using the CFL3Dv6.0 Code,” J. Fluids Struct., 19(6), pp. 729–745. [CrossRef]
Silva, W., 2005, “Identification of Nonlinear Aeroelastic Systems Based on the Volterra Theory: Progress and Opportunities,” Nonlinear Dyn., 39, pp. 25–62. [CrossRef]
Lieu, T., Farhat, C., and Lesoinne, M., 2006, “Reduced-Order Fluid/Structure Modeling of a Complete Aircraft Configuration,” Comput. Methods Appl. Mech. Eng., 195, pp. 5730–5742. [CrossRef]
Lieu, T. and Farhat, C., 2007, “Adaptation of Aeroelastic Reduced-Order Models and Application to an F-16 Configuration,” AIAA J., 46(6), pp. 1244–1257. [CrossRef]
Mastroddi, F., Stella, F., Polli, G. M., and Giangi, M., 2008, “Sensitivity Analysis for the Dynamic Aeroelasticity of a Launch Vehicle,” J. Spacecr. Rockets, 45(5), pp. 999–1009. [CrossRef]
Silva, W. A., 2008, “Simultaneous Excitation of Multiple-Input/Multiple-Output CFD-Based Unsteady Aerodynamic Systems,” J. Aircr., 45(4), pp. 1267–1274. [CrossRef]
Silva, W. A., Vatsa, V. N., and Biedron, R. T., 2010, “Reduced-Order Models for the Aeroelastic Analysis of Ares Launch Vehicles,” AIAA Applied Aerodynamics Conference, Chicago, June 28–July 1, Paper No. AIAA 2010-4375. [CrossRef]
Sekula, M. K., Piatak, D. J., and Rausch, R. D., 2010, “Analysis of a Transonic Alternating Flow Phenomenon Observed During Ares Crew Launch Vehicle Wind Tunnel Tests,” AIAA Applied Aerodynamics Conference, Chicago, June 28–July 1, Paper No. AIAA 2010-4370. [CrossRef]
Ericsson, L.-E., and Reding, J. P., 1965, “Analysis of Flow Separation Effects on the Dynamics of a Large Space Booster,” J. Spacecr. Rockets, 2(4), pp. 481–490. [CrossRef]
Ericsson, L. E., 1967, “Aeroelastic Instability Caused by Slender Payloads,” J. Spacecr. Rockets, 4(1), pp. 65–73. [CrossRef]
Reding, J. P. and Ericsson, L. E., 1995, “Hammerhead and Nose-Cylinder-Flare Aeroelastic Stability Revisited,” J. Spacecr. Rockets, 32(1), pp. 55–59. [CrossRef]
Ericsson, L. E., 1997, “Hammerhead Wake Effects on Elastic Vehicle Dynamics,” J. Spacecr. Rockets, 34(2), pp. 145–151. [CrossRef]
Dotson, K. W., Baker, R. L., and Sako, B. H., 1998, “Launch Vehicle Self-Sustained Oscillation From Aeroelastic Coupling—Part I: Theory,” J. Spacecr. Rockets, 35(3), pp. 365–373. [CrossRef]
Dotson, K. W., Baker, R. L., and Bywater, R. J., 1998, “Launch Vehicle Self-Sustained Oscillation From Aeroelastic Coupling—Part II: Analysis,” J. Spacecr. Rockets, 35(3), pp. 374–379. [CrossRef]
Dotson, K. W., Baker, R. L., and Sako, B. H., 2000, “Launch Vehicle Buffeting With Aeroelastic Coupling Effects,” J. Fluids Struct., 14, pp. 1145–1171. [CrossRef]
Ericsson, L. E., 2001, “Unsteady Flow Separation Can Endanger the Structural Integrity of Aerospace Launch Vehicles,” J. Spacecr. Rockets, 38(2), pp. 168–179. [CrossRef]
Heeg, J., Gilbert, M. G., and Pototzky, A. S., 1993, “Active Control of Aerothermoelastic Effects for a Conceptual Hypersonic Aircraft,” J. Aircr.t, 30(4), pp. 453–458. [CrossRef]
Zeiler, T. A., McGhee, D., and Brunty, J. A., 1999, “Preliminary Static Aeroelastic Analysis of Reusable Launch Vehicle Stability and Control Derivatives,” J. Spacecr. Rockets, 36(1), pp. 67–74. [CrossRef]
Baldelli, D. H., Chen, P. C., and Panza, J., 2006, “Unified Aeroelastic and Flight Dynamic Formulation Via Rational Function Approximations,” J. Aircr., 43(3), pp. 763–772. [CrossRef]
Bolender, M. A. and Doman, D. B., 2007, “Nonlinear Longitudinal Dynamical Model of an Air-Breathing Hypersonic Vehicle,” J. Spacecr. Rockets, 44(2), pp. 374–387. [CrossRef]
Falkiewicz, N. J., Cesnik, C. E. S., Bolender, M. A., and Doman, D. B., 2009, “Thermoelastic Formulation of a Hypersonic Vehicle Control Surface for Control-Oriented Simulation,” AIAA Guidance, Navigation, and Control Conference, Chicago, August 10–13, Paper No. AIAA 2009-6284 [CrossRef].
Frendreis, S. G. V. and Cesnik, C. E. S., 2010, “3D Simulation of Flexible Hypersonic Vehicles,” AIAA Atmospheric Flight Mechanics Conference, Toronto, Canada, August 2–5, Paper No. AIAA 2010-8229. [CrossRef]
Blevins, R. D., 1979, Formulas for Natural Frequency and Mode Shape, Krieger, Malabar, FL, Sect. 8.1.2.
Baruh, H., 1999, Analytical Dynamics, McGraw-Hill, New York.
Ogata, K., 2009, Modern Control Engineering, 5th ed., Prentice Hall, New York.

Figures

Grahic Jump Location
Fig. 1

Kinematic definitions for the aeroelastic model

Grahic Jump Location
Fig. 2

First two modes for a free-free beam

Grahic Jump Location
Fig. 3

Aerodynamic normal force

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