The Presentation of a Mathematical Model for Aerodynamic Coefficients Extraction in Supersonic Aeroballistics Projectile Test

Document Type : Original Article

Authors

1 Kavoashgar Khorshid Research Center, Shiraz University

2 Kavoshgar Khorshid Research Center Shiraz University

3 kavoshgar khorshid research complex, shiraz university, shiraz, iran

Abstract

The precise method for aerodynamic parameters measurement in aeroballistics labs, is the free flight method. It can be used to test different models at a wide range of flight speeds including subsonic, transonic, supersonic and hypersonic speeds, and in the millimetric to metric range dimensions. It can be utilized to measure the path-equation related parameters and the aerodynamic and aeroelastic parameters. Moreover, it has the capability for checking the performance of designed control systems, testing material temperature tolerance, testing structural strength and addressing high-speed collision and re-entry problems. In this lab, stations for measuring flight model data are located at certain distances that extract data using imaging and telemetry techniques. The main goal is to provide a suitable mathematical model with precise accuracy in order to extract aerodynamic coefficients from raw data measured according to the number of measurement stations and their intervals. Therefore, for the purpose of using imaging data, an overview of aerodynamic coefficients extraction in the aeroballistics test is carried out. The results show that static and dynamic coefficients are not independent in extraction and should be calculated simultaneously. Dynamic coefficients cannot be ignored if the magnitudes are significant. The measurement accuracy required when the dynamic coefficients cause the damping of the oscillations is about 0.1 degree with 20 stations, while the accuracy of 0.1 degree with 10 stations is inadequate and higher than that is required.

Keywords

References

  1. Gershenson, J. “Capstone Design Course for NASA ESMD”, 2009.##
  2. Chambers, J. “Modeling Flight NASA Latest Version: The Role of Dynamically Scale Free Flight Models in Support of NASA Aerospace Programs”, 3, 2015.##
  3. Khristenko, Y.F., Zelepugin, S.A., and Gerasimov, A.V. “New Light-Gas Guns for the High-Velocity Throwing of Mechanical Particles”, 12, No.22, pp. 6606-6610, 2017.##
  4. Russell, J.J.T.A.J. “Aircraft Performance and Design”, JD Anderson. McGraw-Hill Publishing Company, Shoppenhangers Road, Maidenhead, Berks SL6 2QL, UK. 1999. 580pp. Illustrated.£ 25.99. 0-07-116010-8. Vol. 104, No. 1036, p. 297, 2000.##
  5. Seiler, F. and Igra, O. “Hypervelocity Launchers”, Springer, 2016.##
  6. Davis, B.S., Guidos, B.J., and Harkins, T.E. “Complementary Roles of Spark Range and Onboard Free-Flight Measurements for Projectile Development”, Army Research Lab Aberdeen Proving Ground Md Weapons And Materials Research,2009.##
  7. Topper, B., Brown, T.G., Bukowski, E., Davis, B.S., Hall, R.A., Muller, P.C., Vong, T.T. and Brandon, F.J., “Feasibility of Determining Aerodynamic Coefficients for a NASA Apollo Body with the Use of Telemetry Data from Free Flight Range Testing”, Army Research Lab Aberdeen Proving Ground Md Weapons And Materials Research, 2007.##
  8. West, I.T. “Hypersonic Aerodynamic Flight Coefficients Determined from Free Flight”, The UNSW Canberra at ADFA Journal of Undergraduate Engineering Research, Vol.1, No. 2, p. 36, 2009.##
  9. Chhabildas, L.C. and Knudson, M.D. “Techniques to Launch Projectile Plates to Very High Velocities, in High-Pressure Shock Compression of Solids VIII”, Springer, pp. 143-199, 2005.##
  10. Carmona-Reyes, J., Cook, M., Schmoke, J., Harper, K., Reay, J., Matthews, L. and Hyde, T. “Impact Studies Using a One Stage Light Gas Gun”, Lunar and Planetary Science Conference. 2004.##
  11. Grinstead, J.H., Wilder, M.C., Reda, D.C., Cornelison, C.J., Cruden, B.A., and Bogdanoff, D.W. “Shock Tube and Ballistic Range Facilities at NASA Ames Research Center”, National Aeronautics and Space Administration Moffett Field Ca Ames Research, 2010.##
  12. Van Donkelaar, F. “Development of an Expedient Two-Stage Gas Gun”, University of Washington, 2021.##
  13. Swift, H.F. “Light-Gas Gun Technology: a Historical Perspective, in High-Pressure Shock Compression of Solids VIII”, Springer, pp. 1-35.##
  14. Abdelkefi, A., Vasconcellos, R., Nayfeh, A.H., and Hajj, M.R. “An Analytical and Experimental Investigation into Limit-Cycle Oscillations of an Aeroelastic System”, 71, No. 1, pp. 159-173, 2013.##
  15. Haya, R., Kerr, M. and Bonetti, D. “Entry, Descent, and Landing Systems Short Course”, 2013.##
  1. Bhagwandin, V.A., Sahu, J. “Numerical Prediction of Pitch Damping Stability Derivatives for Finned Projectiles”, Journal of Spacecraft and Rockets, 51, No. 5, pp. 1603-1618, 2014.##
  2. Dupuis, A. and Hathaway, W. “Flight Dynamics of a Projectile with High Drag Retarder Devices at Subsonic Velocities”, 19th Symposium of Ballistics. 2011.##
  3. Kokes, J., Costello, M., and Sahu, J. “Generating an Aerodynamic Model for Projectile Flight Simulation Using Unsteady Time Accurate Computational Fluid Dynamic Results”, 45, p. 11131, 2007.##
  4. Oosterom, W. “Flying-V Family Design”, 2021.##
  5. Klatt, D., Proff, M., and Hruschka, R. “Investigation of the Flight Behavior of a Flare-Stabilized Projectile Using 6DoF Simulations Coupled with CFD”, 2019.##
  6. Sun, S. and de Visser, C. “Aerodynamic Model Identification of a Quadrotor Subjected to Rotor Failures in the High-Speed Flight Regime”, 4, No. 4, pp. 3868-3875, 2019.##
  7. Sung, C.-h. and Kwon, J. “Aerodynamic Design Optimization Using the Navier-Stokes and Adjoint Equations”, 39th Aerospace Sciences Meeting and Exhibit. 2001.##

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History

  • Receive Date: 19 June 2020
  • Revise Date: 18 July 2021
  • Accept Date: 06 October 2021
  • Publish Date: 22 May 2021

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