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No AccessFull-Length Paper

Ariane 5 Performance Optimization Using Dual-Bell Nozzle Extension

Published Online:6 Jun 2016https://doi.org/10.2514/1.A33363

Abstract

To evaluate the impact of dual-bell nozzles on the payload mass delivered into geostationary transfer orbit by Ariane 5 Evolution Cryotechnique Type A (ECA), detailed studies were conducted. For this purpose, a multitude of Vulcain 2 extension contours were designed. The two variation parameters were the starting point and the inflection angle of the nozzle extension. As the most upstream starting point, the position of the turbine exhaust gas injection was chosen. Geometrical restrictions were imposed by the launch pad ELA 3. Considering these parameters, an analytical and a numerical method were applied to predict the impact of the dual-bell nozzle on the payload mass. The analytical approach yields a correlation between specific impulse, nozzle mass, and payload mass increment. The numerical approach was conducted applying German Aerospace Research Center’s trajectory simulation code Trajectory Optimization and Simulation of Conventional and Advanced Transport Systems. Both calculation procedures yield good agreement, and the payload gain into geostationary transfer orbit was evaluated to be up to 490 kg. The study revealed the potential of a new class of dual-bell nozzles whose mode transitions already occur during engine startup, under sea-level conditions. A payload gain up to 200 kg was found. These nozzles were designated as “sea-level transitional dual-bell.”

References

  • [1] Stark R., “Beitrag zum Verständnis der Strömungsablösung in Raketendüsen (Contribution to the Understanding of Flow Separation in Rocket Nozzles),” Ph.D. Thesis, RWTH Aachen, Germany, 2010. Google Scholar

  • [2] Génin C., “Experimental Study of Flow Behavior and Thermal Loads in Dual Bell Nozzles,” Ph.D. Thesis, Université de Valenciennes, France, 2010. Google Scholar

  • [3] Foster C. and Cowles F., “Experimental Study of Gas-Flow Separation in Overexpanded Exhaust Nozzles for Rocket Motors,” Jet Propulsion Lab., Progress Rept. 4-103, 1949. Google Scholar

  • [4] Fischer E., “Nozzle Construction,” U.S. Patent 3352495 A, Kinnelon, NJ, 1967. Google Scholar

  • [5] Horn M. and Fisher S., “Dual-Bell Altitude Compensating Nozzle,” Rocketdyne Div., NASA, CR-194719, 1994. Google Scholar

  • [6] Haidinger F., Goergen J. and Haeseler D., “Experimental and Analytical Design Verification of the Dual-Bell Concept,” 34th AIAA Joint Propulsion Conference, AIAA Paper  1998-3368, July 1998. Google Scholar

  • [7] Manski D., Hagemann G., Frey M. and Frenken G., “Optimisation of Dual Mode Rocket Engine Nozzles for SSTO Vehicles,” 49th International Astronautical Congress, IAF-98-S3.08, Melbourne, Australia, 1998. Google Scholar

  • [8] Kumakawa A., Tamura H., Niino M., Nosaka M., Yamada H., Kanmuri A., Konno A. and Atsumi M., “Propulsion Research for Rocket SSTOS at NAL/KRC,” 35th AIAA Joint Propulsion Conference, AIAA Paper  1999-2337, June 1999. LinkGoogle Scholar

  • [9] Kusaka K., Kumakawa A., Niino M., Konno A. and Atsumi M., “Experimental Study on Extendible and Dual-Bell Nozzles under High Altitude Conditions,” 36th AIAA Joint Propulsion Conference, AIAA Paper  2000-3303, July 2000. LinkGoogle Scholar

  • [10] Miyazawa M., Takeuchi S. and Takahashi M., “Flight Performance of Dual-Bell Nozzles,” 40th AIAA Aerospace Sciences Meeting & Exhibit, AIAA Paper  2002-686, Jan. 2002.. LinkGoogle Scholar

  • [11] Immich H. and Caporicci M., “FESTIP Technology Developments in Liquid Rocket Propulsion for Reusable Launch Vehicles,” 32nd AIAA Joint Propulsion Conference, AIAA Paper  1996-3113, July 1996. LinkGoogle Scholar

  • [12] Immich H. and Caporicci M., “Status of the FESTIP Rocket Propulsion Technology Programme,” 33rd AIAA Joint Propulsion Conference, AIAA Paper  1997-3311, July 1997. LinkGoogle Scholar

  • [13] Hagemann G., Terhardt M., Haeseler D. and Frey M., “Experimental and Analytical Design Verification of the Dual-Bell Concept,” 36th AIAA Joint Propulsion Conference, AIAA Paper  2000-3778, July 2000. LinkGoogle Scholar

  • [14] Kuczera H., Sacher P. and Dujarric C., “FESTIP System Study–An overview,” Seventh AIAA Space Plane and Hypersonic Systems and Technology Conference, AIAA Meeting Papers on Disc, AIAA, Reston, VA, Nov. 1996, Paper A9710801. doi:https://doi.org/10.2514/6.1996-6004 Google Scholar

  • [15] Hagemann G., Frey M. and Manski D., “A Critical Assessment of Dual-Bell Nozzles,” 33rd AIAA Joint Propulsion Conference, AIAA Paper  1997-3299, July 1997. LinkGoogle Scholar

  • [16] Dumnov G., Nikulin G. and Ponomarev N., “Advanced Rocket Engine Nozzles,” 32nd AIAA Joint Propulsion Conference, AIAA Paper  1996-3221, July 1996. LinkGoogle Scholar

  • [17] Kimura T., Niu K., Yonezawa K., Tsujimoto Y. and Ishizaka K., “Experimental and Analytical Study for Design of Dual-Bell Nozzles,” 45th AIAA Joint Propulsion Conference, AIAA Paper  2009-5149, Aug. 2009. LinkGoogle Scholar

  • [18] Nürnberger-Génin C. and Stark R., “Flow Transition in Dual Bell Nozzles,” Shock Waves, Vol. 19, No. 3, 2009, pp. 265–270. CrossrefGoogle Scholar

  • [19] Tomita T., Takahashi M., Sasaki M. and Tamura H., “Investigation on Characteristics of Conventional-Nozzle-Based Altitude Compensating Nozzles by Cold-Flow Tests,” 42nd AIAA Joint Propulsion Conference, AIAA Paper  2006-4375, July 2006. LinkGoogle Scholar

  • [20] Reijasse P., Coponet D., Luyssen J.-M., Bar V., Palerm S., Oswald J., Amouroux F., Robinet J.-C. and Kuszla P., “Wall Pressure and Thrust of a Dual Bell Nozzle in a Cold Gas Facility,” Third European Conference for Aerospace Sciences (EUCASS), Versailles, France, July 2009. Google Scholar

  • [21] Nürnberger-Génin C. and Stark R., “Experimental Study on Flow Transition in Dual Bell Nozzles,” Journal of Propulsion and Power, Vol. 26, No. 3, 2010, pp. 497–502. LinkGoogle Scholar

  • [22] Verma S., Stark R., Nürnberger-Génin C. and Haidn O., “Cold-Gas Experiments to Study the Flow Separation Characteristics of a Dual-Bell Nozzle During Its Transition Modes,” Shock Waves, Vol. 20, No. 3, pp. 191–203, 2010. CrossrefGoogle Scholar

  • [23] Génin C. and Stark R., “Influence of the Test Environment on the Transition of Dual-Bell Nozzles,” 28th International Symposium on Space Technology and Science Special Issue, Vol. 10, No. 1, 2012, pp. 49–53. Google Scholar

  • [24] Génin C., Stark R., Haidn O., Quering K. and Frey M., “Experimental and Numerical Study of Dual Bell Nozzle Flow,” Progress in Flight Physics, Vol. 5, No. 1, 2013, pp. 363–376. CrossrefGoogle Scholar

  • [25] Verma S., Stark R. and Haidn O., “Effect of Ambient Pressure Fluctuations on Dual-Bell Transition Behavior,” Journal of Propulsion and Power, Vol. 30, No. 5, 2014, pp. 1192–1198. LinkGoogle Scholar

  • [26] Génin C. and Stark R., “Side Loads in Subscale Dual Bell Nozzles,” Journal of Propulsion and Power, Vol. 27, No. 4, 2011, pp. 828–837. LinkGoogle Scholar

  • [27] Génin C., Gernoth A. and Stark R., “Experimental and Numerical Study of Heat Flux in Dual Bell Nozzles,” Journal of Propulsion and Power, Vol. 29, No. 1, 2013, pp. 21–26. LinkGoogle Scholar

  • [28] Onofri M., Nasuti F. and Martelli E., “Analysis of the Transition Process in Dual-Bell Nozzles,” Fourth International Conference on Launcher Technology, Centre National d'Etudes Spatiales (CNES), Liège, Belgium, Dec. 2002. Google Scholar

  • [29] Wong H. and Schwane R., “Numerical Investigation of Transition in Flow Separation in a Dual-Bell Nozzle,” Fourth International Conference on Launcher Technology, Centre National d'Etudes Spatiales (CNES), Liège, Belgium, Dec. 2002. Google Scholar

  • [30] Karl S. and Hannemann K., “Numerical Investigation of Transient Flow Phenomena in Dual-Bell Nozzles,” Sixth International Symposium on Launcher Technologies, Centre National d'Etudes Spatiales (CNES), Nov. 2005. Google Scholar

  • [31] Martelli E., Nasuti F. and Onofri M., “Effect of the Wall Shape and Real Gas Properties on Dual-Bell Nozzle Flowfield,” 41st AIAA Joint Propulsion Conference, AIAA Paper  2005-3943,  July 2005. LinkGoogle Scholar

  • [32] Nasuti F., Onofri M. and Martelli E., “Role of Wall Shape on the Transition in Axisymmetric Dual-Bell Nozzles,” Journal of Propulsion and Power, Vol. 21, No. 2, 2005, pp. 243–250. LinkGoogle Scholar

  • [33] Martelli E., Nasuti F. and Onofri M., “Numerical Parametric Analysis of Dual-Bell Nozzle Flows,” AIAA Journal, Vol. 45, No. 3, 2007, pp. 640–650. LinkGoogle Scholar

  • [34] Martelli E., Nasuti F. and Onofri M., “Film Cooling Effect on Dual-Bell Nozzle Flow Transition,” 45th AIAA Joint Propulsion Conference, AIAA Paper  2009-4953, Aug. 2009. LinkGoogle Scholar

  • [35] Perigo D., Schwane R. and Wong H., “A Numerical Comparison of the Flow in Conventional and Dual-Bell Nozzles in the Presence of an Unsteady External Pressure Environment,” 39th AIAA Joint Propulsion Conference, AIAA Paper  2003-4731, July 2003. LinkGoogle Scholar

  • [36] Proschanka D., Koichi Y., Tsukuda H., Araka K., Tsujimoto Y., Kimura T. and Yokota K., “Jet Oscillation at Low-Altitude Operation Mode in Dual-Bell Nozzle,” Journal of Propulsion and Power, Vol. 28, No 5, 2012, pp. 1071–1080. LinkGoogle Scholar

  • [37] Hagemann G., Immich H., Van Nguyen T. and Dumnov G., “Advanced Rocket Nozzles,” Journal of Propulsion and Power, Vol. 14, No. 5, 1998, pp. 620–634. LinkGoogle Scholar

  • [38] Hagemann G., Immich H., Nguyen T. and Dumnov G., “Rocket Engine Nozzle Concepts,” Progress in Astronautics and Aeronautics, Liquid Rocket Thrust Chambers: Aspects of Modeling, Analysis, and Design, edited by Yang V., Habiballah M., Hulka J. and Popp M., Vol. 200, 2004, pp. 437–467, Chap. 12. Google Scholar

  • [39] Fromm C. and Génin C., “Ariane 5 ECA Launch Trajectory Simulation with Dual Bell Nozzle,” 63th Deutscher Luft- und Raumfahrtkongress, Augsburg, Germany, No. 288, Deutsche Gesellschaft fuer Luft- und Raumfahrt (DGLR), Sept. 2014.. Google Scholar

  • [40] Perez E., “Ariane 5 User’s Manual,” Arianespace, No. 5, Rev. 1, 2011, www.arianespace.com [accessed 14 April 2016]. Google Scholar

  • [41] Safran/Snecma, “Vulcain 2,” www.snecma.com, Product Sheet, 2012. Google Scholar

  • [42] Safran/Snecma, , “HM7B,” www.snecma.com, Product Sheet, 2011. Google Scholar

  • [43] Barenski S., “Vulcain 2, Funneling Efforts into the Nozzle,” Snecma Magazine, No. 4, pp. 24–27 (1638-4156, Engl. Ed.), , 2003. Google Scholar

  • [44] VULCAIN 2 Thrust Chamber, Astrium, www.space-propulsion.com, Product Sheet, 2005. Google Scholar

  • [45] United States Committee on Extension to the Standard Atmosphere, “U.S. Standard Atmosphere, 1976,” National Oceanic and Atmospheric Administration NOAA–S/T-76-1562, 1976. Google Scholar

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