Parameter Estimation of Unmanned Flight Vehicle Using Wind Tunnel Testing and Real Flight Data
Publication: Journal of Aerospace Engineering
Volume 30, Issue 1
Abstract
The work presented in this paper addresses the longitudinal parameter estimation of an unmanned configuration using wind tunnel testing and flight data. For this purpose, an unmanned aerial vehicle has been designed with a cropped delta planform and rectangular cross-section. Exhaustive full-scale wind tunnel tests were carried out on the designed unmanned flight vehicle to capture the linear and nonlinear variation of aerodynamic force and moment coefficients. The measured wind tunnel test data, in the form of signals, have been processed to forces and moments about the desired reference point of the designed unmanned platform. A comprehensive discussion on the obtained results from wind tunnel testing has been presented. In order to enhance the confidence in the generated aerodynamic database from wind tunnel testing and also to estimate the dynamic derivatives, two sets of real flight data pertaining to longitudinal dynamics (acquired during the flight tests) have been used. The parameter estimation in the linear domain has been carried out using conventional maximum likelihood and least-square methods. The estimated longitudinal parameters from the flight data were used to corroborate the aerodynamic coefficients derived from the wind tunnel measurements.
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References
Abramov, N., Goman, M., and Khrabrov, A. (2004). “Aircraft dynamics at high incidence flight with account of unsteady aerodynamic effects.” Atmospheric Flight Conf. and Exhibit, AIAA, Providence, RI, 1–19.
Anderson, J. D. (1999). Aircraft performance and design, McGraw-Hill, New York.
Austin, R. (2010). Unmanned aircraft systems—UAVs design, development and deployment, Wiley, Chichester, U.K.
Brandon, J. M., and Morelli, E. A. (2014). “Real-time global nonlinear aerodynamic modeling from flight data.” AIAA Atmospheric Flight Mechanics Conf., AIAA Aviation, Reston, VA.
Chandra, B., Gupta, R., and Sharma, G. (2000). “National wind tunnel facility, IIT Kanpur—Calibration aspects.” Proc., Recent Advances in Experimental Mechanics, IIT Kanpur, India, 294–307.
Daniel, P. R. (1999). Aircraft design: A conceptual approach, 3rd Ed., AIAA, Reston, VA.
Dhiman, M. K. (2010). “Design of 5 degree of freedom dynamic test rig for aerodynamic characterization of flight vehicle.” M.Tech thesis, Dept. of Aerospace Engineering, IIT Kanpur, India.
Fischenberg, D. (1995). “Identification of an unsteady aerodynamic stall model from flight test data.” Proc., AIAA Atmospheric Flight Mechanics Conf., AIAA, Reston, VA, 138–146.
Fischenberg, D., and Jategaonkar, R. V. (1999). “Identification of aircraft stall behavior from flight test data.” RTO Systems Concepts and Integration Symp., NATO, Paris.
Goman, M., Khrabrov, A., and Usoltsev, S. (1994). “Identification of an unsteady aerodynamic model of a delta wing at high angle of attack.” Proc., 10th IFAC Symp. on System Identification, SYSID’94, Vol. 3, Copenhagen, Denmark, 77–83.
Holzel, M. S., and Morelli, E. A. (2012). “Real-time frequency response estimation from flight data.” J. Guidance Control Dyn., 35(5), 1406–1417.
Jategaonkar, R. V. (2006). “Flight vehicle system identification—A time domain methodology.” AIAA, Reston, VA.
Klein, V. (1999). “Modeling of longitudinal unsteady aerodynamic of a wing-tail combination.”, NASA, Washington, DC.
Klein, V., and Morelli, E. A. (2006). Aircraft system identification—Theory and practice, AIAA Education Series, Reston, VA.
Klein, V., and Noderer, K. D. (1994). “Modeling of aircraft unsteady aerodynamic characteristics. Part 1—Postulated models.”, NASA, Washington, DC.
Kumar, R. (2010). “Parameter estimation using flight data of air vehicles at low and moderately high angles of attack using conventional and neural based methods.” Ph.D. thesis, Aerospace Engineering Dept., IIT Kanpur, India.
Kumar, R., Misra, A., and Ghosh, A. K. (2011). “Modelling of cascade fin aerodynamics near stall using Kirchhoff’s steady-state stall model.” Defence Sci. J., 61(2), 157–164.
LabVIEW version 2012 [Computer software]. National Instruments, Austin, TX.
Leishman, J. G., and Nguyen, K. Q. (1990). “State-space representation of unsteady airfoil behavior.” AIAA J., 28(5), 836–844.
Mehra, R. K. (1970). “Maximum likelihood identification of aircraft parameters.” Proc., 11th Joint Automatic Control Conf., American Automatic Control Council, 442–444.
Misra, A., Singhal, A., Ghosh, A. K., and Ghosh, K. (2008). “Wind tunnel study of a grid fin stabilized guided projectile.” AIAA Atmospheric Flight Mechanics Conf. Exhibit, AIAA, Reston, VA, 18–21.
Morelli, E. A. (2012). “Real-time aerodynamic parameter estimation without air flow angle measurements.” J. Aircraft, 49(4), 1064–1074.
Morelli, E. A., Rexius, S. L., and Lechniak, J. A. (2014). “Flight test experiment design and aerodynamic parameter estimation for the X-51A waverider.” 20th AIAA Int. Space Planes and Hypersonic Systems and Technologies Conf., AIAA, Reston, VA.
Napolitano, M. R. (2012). Aircraft dynamics: From modeling to simulation, Wiley, Hoboken, NJ.
Nelson, R. C. (1998). Flight stability and automatic control, 2nd Ed., McGraw-Hill, New York.
Pamadi, B. N. (2004). Performance, stability dynamics and control of airplanes, 2nd Ed., AIAA, Reston, VA.
Peyada, N. K. (2008). “Parameter estimation from flight using feed forward neural networks.” Ph.D. thesis, Aerospace Engineering Dept., IIT Kanpur, India.
Saderla, S. (2015). “Parameter estimation using flight data of unmanned flight vehicles at low and moderately high angles of attack using conventional methods.” Ph.D. thesis, Aerospace Engineering Dept., IIT Kanpur, India.
Saderla, S., Rajaram, D., and Ghosh, A. (2016). “Longitudinal parameter estimation from real flight data of unmanned cropped delta configuration.” Int. J. Intell. Unmanned Syst., 4(1), 2–22.
Saderla, S., Sharma, S., and Ghosh, A. K. (2011). “Analytical modeling trajectory simulation and control of guided projectiles.” Proc., CAR 2011, GSTF, Singapore.
Singh, S. (2007). “Estimation of aircraft parameters from flight data using neural network based method.” Ph.D. thesis, Aerospace Engineering Dept., IIT Kanpur, India.
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© 2016 American Society of Civil Engineers.
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Received: Jul 14, 2015
Accepted: Jun 9, 2016
Published online: Aug 1, 2016
Published in print: Jan 1, 2017
Discussion open until: Jan 1, 2017
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