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Aerodynamic Design of Payload Fairing of Satellite Launch Vehicle

Rakhab Chandra Mehta(1*)

(1) Department of Aeronautical Engineering, Noorul Islam University, Kumarakoil, India
(*) Corresponding author


DOI: https://doi.org/10.15866/irease.v8i5.8000

Abstract


This paper presents computation of aerodynamic coefficients for various bulbous heat shield of a typical satellite launch vehicle at supersonic speeds. Numerical simulations are carried out by solving time-dependent, three-dimensional, compressible Euler equations in conjunction with a finite volume scheme at freestream Mach number 1.2 and 1.8 which are, respectively, corresponding to the conditions of maximum aerodynamic drag and dynamic pressure experienced by the satellite launch vehicle during the ascent period of the trajectory. The numerical scheme captures all the essential flowfield features of high speed flow such as a formation of bow shock wave, compression and expansion region over the bulbous payload shroud. A controlled random search method is employed to obtain required geometrical parameters of the bulbous heat shield that will satisfy the prescribed aerodynamic loads conditions at Mach 1.2 and 1.8. The controlled random search algorithm does not need computation of derivatives. The algorithm works even when the differentiability requirements cannot be ensured in the feasible domain and also the starting condition is not crucial. The computed normal force distributions and centre of pressure are compared with wind-tunnel data and are found in good agreement between them. The determination of the optimum geometrical parameters of heat shield for the prescribed aerodynamic loads is essential to maintain the structural integrity of the payload fairing during ascent phase of the launch. The CFD approach with the CRS will help to reduce the number of costly and time consuming wind tunnel testing.
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Keywords


Aerodynamics; CFD; High Speed Flow; Optimization

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References


Buffeting during atmospheric ascent, NASA Special Vehicle Design Criteria, NASA SP 8001, November 1970.

Mehta, R., Influence of Geometrical Parameters of Heat Shield on Flow Characteristics at Transonic Mach, (2013) International Review of Aerospace Engineering (IREASE), 6 (1), pp. 64-75.

Muraca, R. J., An empirical method for determining static distributed aerodynamic loads on axisymmetric multistage launch vehicles, NASA TN D-3283, March 1966.

Mehta, R. C. and Sastry, M. S., Computational aerodynamic loads and coefficient for satellite launch vehicle, Indian Journal of Engineering and Material Sciences, Vol. 4, April 1997, pp. 41-48.

Sooy, T. J. and Schmidt, R. Z., Aerodynamic predictions, comparisons, and validations using DATCOM (97) and Aero prediction 98 (AP98), Journal of Spacecraft and Rockets, Vol. 42, No. 2, March 2005, pp. 257-265.
http://dx.doi.org/10.2514/1.7814

Blevins, J. A., Cambell, J. R., Bennett, D. W., Rausch, R. D., R. J. Gomez, and Kiris, C. C., An overview of the characterization of the space launch vehicle aerodynamic environments, AIAA conference, 2015.
http://dx.doi.org/10.2514/6.2014-1253

Hall, L., Eppard, W., Applebaum, M., and Blevins, J. A., Cartesian Euler code application for launch vehicle systems, 49th AIAA Aerospace Sciences Meeting including the new Horizon forum and Aerospace Exposition, Jan., 2011.
http://dx.doi.org/10.2514/6.2011-1113

Pinier, J. T., Bennett, D. W., Blevins, J. A.,, Erickson, G. E., Faveregh, N. M., Houlden, H. P., and Tomek, W. G., Space launch system ascent static aerodynamic database development, 52nd AIAA Aerospace Sciences Meetings, 2014.
http://dx.doi.org/10.2514/6.2014-1254

Bigarella, E. D. V., Azevedo, J. L. F., Mello, O. A. F., Normal Force Calculations for Rocket like Configurations, Journal of the Brazilian Society of Mechanical Science and Engineering, Vol. 24, No. 3, 2004, pp. 290-296.
http://dx.doi.org/10.1590/s1678-58782004000300005

Brower, T. L., Titan launch vehicle; Ground test history, Journal of Spacecraft and rockets, Vol. 43, No. 1, Jan. Feb. 2006, pp. 147-160.
http://dx.doi.org/10.2514/1.12863

Pritchett, V. E., Maybe, M. N., Blevins, J. A., Crosby, W. A., and Purinton, D. C., Aerodynamic tests of the space launch system for database development, 52nd AIAA Aerospace Sciences Meetings, 2014.
http://dx.doi.org/10.2514/6.2014-1256

Price A., A controlled random search procedure for global optimization, in Towards Global Optimization (Eds. Dixon, L. C. W. and Szego, G. P), North-Holland Publishing Co., The Netherlands, Vol. 2, 1978, pp. 71-84.

Kordulla, W. and Vinokur, M., Efficient computation of volume in flow predictions, AIAA Journal, Vol. 21, No. 6, June 1983, pp. 917-918.
http://dx.doi.org/10.2514/3.8174

Jameson, A., Schmidt, W., Turkel, E., Numerical solution of Euler equations by finite volume methods using Runge-Kutta time stepping schemes, AIAA 81-1259, 1981.
http://dx.doi.org/10.2514/6.1981-1259

Mehta, R. C., A quasi three dimensional automatic grid generation method, in the proceedings of the 25th National and International Conference on Fluid Dynamics and Fluid Power, IIT, Delhi, India, Dec. 1998, pp. 89-98.

Mehta, R. C., Flow direction estimation based on computed and flight measured surface pressure, Computational Fluid Dynamics Journal, Vol. 12, No. 3, Oct. 2003, pp. 555-561.

R.C.Mehta and S.B.Tiwari, Controlled random search technique for estimation of convective heat transfer coefficient, Heat and Mass Transfer Journal, Vol. 43, 2007, pp. 1171 - 1177.
http://dx.doi.org/10.1007/s00231-006-0185-8

R. C. Mehta, Direct Search Optimization Technique for the Solution of Inverse Nonlinear Heat Conduction Problem, Indian Journal of Engineering & Materials Sciences, Vol. 19, No. 1, February, 2012, pp. 67 - 71.


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