Journal of Technology in Aerospace Engineering

Journal of Technology in Aerospace Engineering

Design of Cryogenic Propulsion Feeding System for Second Stage of Special Rocket Based on Space Standards

Document Type : Research Article

Authors
Seyyed Mohamad Amin Borghei 1
Mohammad Amin Eskandari 2
1 M. Sc., Faculty of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran
2 Ph. D., Faculty of Aerospace Engineering, K. N. Toosi University of Technology, Tehran, Iran
10.22034/jtae.2024.8.3.2
Abstract
In general, according to the Russian Gost standard, the space propulsion engine system includes injection subsystems, a thrust chamber, a heat transfers and cooling system, a launch system, a feeding system, a thrust vector control system, and fuel and oxidizer tanks, which due to overlap and penetration The manifolds between the engine reservoirs and the fuel system are usually designed as a pair. In the conducted investigations, in addition to knowing the elements of the circuit and how to arrange the circuit, it also leads to knowing the requirements, goals, and main requirements of the system design. Then, based on the studies, the circuit design of the feeding system and the selection of its elements have been done. By using simple fluid relations, the pressure drop of each of these elements is calculated and extracted by establishing the pressure energy balance of the reservoirs. After that, taking into account the remaining mass of pressurized gas in the tanks, the total required mass of pressurized gas has been calculated. Considering the cryogenic (super-cold) propellants in this project, considerations for the design of routes and tanks will be more important, and finally, after presenting pressure changes in both fuel and oxidizer routes, piping and instrumentation diagrams have been discussed. One of the main goals of this research is to design based on standards to achieve high reliability. In this article, the types of feeding systems, ahead problems, and challenges are discussed. Finally, the two-dimensional model of this subsystem will be presented based on the country's TRL level.
Keywords
Conceptual Design
Pressure Fed System
Cryogenic Propellants
Piping and Instrumentation Diagrams
Design Based on the TRL
Subjects

 [1] R. Humble, Space Propulsion Analysis and Design, McGraw-Hill Companies, Incorporated, 1995.

[2]      G. P. Sutton and O. Biblarz, Rocket Propulsion Elements, 8rd ed., John Wiley & Sons, 2011.

[3]      J. E. John, Gas Dynamics, 3rd ed. Pearson, 2006.

[4]      Dieter K. Huzel, David H. Huang, Modern Engineering for Design of Liquid-Propellant Rocket Engines, United States: American Institute of Aeronautics and Astronautics, 1992.

[5]        M. A. Eskandari, M. Farshchi, "Conceptual design of a special Two-Component zemastic combustion chamber," M.S. thesis, Sharif University of Technology, Tehran, Iran, 2018.

[6]       S. M. A. Borghei and A. Madadi, "Conceptual design of space motocryogenics with liquid hydrogen fuel," M. S. thesis, Amirkabir University of Technology, Tehran, Iran, 2022, (In Persion).

[7]  M. Barrere, Rocket Propulsion, New York: Elsevier Publishing Company, 1960.

 [8]   T. Aoki, T. Ishikawa, and Y. Morino, "Overview of basic research activities on cryogenic composite propellant tanks in Japan," in 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, Kyoto, Japan, 2001, Paper AIAA-2001-1878, https://doi.org/10.2514/6.2001-1878.

[9]  S. Durteste, "A transient model of the VINCI cryogenic upper stage rocket engine," in 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH,  2007, Paper AIAA-2007-5531, https://doi.org/10.2514/6.2007-5531.

[10] R. Eidson, "Cryogenic upper stage propulsion systems evolution," in 28th Joint Propulsion Conference and Exhibit, Nashville, TN, USA, 1992, Paper AIAA- 1992-3594, https://doi.org/10.2514/6.1992-3594.

[11] K. Ennix and M. Coleman, "Liquid propulsion technology for expendable and sts launch vehicle transfer stages," in 23rd Joint Propulsion Conference, San Diego, CA, U.S.A., 1987, Paper AIAA- 1987- 1934, https://doi.org/10.2514/6.1987-1934.

[12] D. Fiot, G. Vigier, D. Valentian, and R Bec, "Low Thrust Propulsion Systems for ELV Upper Stage System and Stage Analysis," in 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, 2006, Paper AIAA-2006-4437, https://doi.org/10.2514/6.2006-4437.

[13] M. F. Fisher, "Propellant management in booster and upper-stage propulsion systems," Journal of Propulsion and Power, vol. 14, no. 5, pp. 649-656, 1998, https://doi.org/10.2514/2.5326.

[14] V. Gautam and A. Gupta, "Cryogenic flow and mixing from a single element coaxial rocket injector," in 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, 2006, Paper AIAA-2006-4529, https://doi.org/10.2514/6.2006-4529.

[15] V. Gautam and A. Gupta, "Fate of cryogenic fluid flow and atomization from a sheer coaxial injector under pre-ignition conditions," in 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Hartford, CT, 2008, Paper AIAA-2008-5024, https://doi.org/10.2514/6.2008-5024.

[16] D. Glover, "NASA cryogenic fluid management space experiment efforts, " in Conference on Advanced SEI Technologies, Cleveland, OH, U.S.A., 1991, Paper AIM-91-3538,  https://doi.org/10.2514/6.1991-3538.

[17] W. D. Greene, D. L. Boxx, and B. K. Tiller, "Propellant densification for shuttle: The SSME perspective," in 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, IN, 2002, Paper AIAA-2002-3602.

[18] I. Cho, T. Jung, Y. Jung, O. Kwon, S. Oh, and D. Lee, "Development of korea sounding rocket - iii propulsion feeding system," in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, 2003, Paper 4899, AIAA-2003-4899, https://doi.org/10.2514/6.2003-4899.

[19] R. V. Burry, S. F. Iacobellis, and V. R. Larson, " Liquid propellant rocket engines: Their status and future," Journal of Spacecraft and Rockets, vol. 4, no. 12, pp. 1569-1580, 1967, https://doi.org/10.2514/3.29135.

[20] H. Immich and W. Mayer, "Cryogenic liquid rocket engine technology developments within the german national technology programme," in 33rd Joint Propulsion Conference and Exhibit,  Seattle,WA, U.S.A., Paper AIAA- 1997-2822, https://doi.org/10.2514/6.1997-2822.

[21] S. J. Isakowitz, "International reference guide to space launch systems," NASA STI/Recon Technical Report A, vol. 91, p. 51425, 1991.

[22] S. H. Kim, Y. M. Han, S. Seo, I. Y. Moon, J. K. Kim, and W. S. Seol, "Effects of  LOX post recess on the combustion characteristics for Bi-Swirl coaxial injector," in 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2005, Tucson, Arizona, Paper AIAA-2005-4445, https://doi.org/10.2514/6.2005-4445.

[23] T. Lak, M. Nguyen, and S. Hauver, "Fixed orifice pressurization system for the Space Shuttle LO2 tank," in 26th Joint Propulsion Conference, Orlando, FL, U.S.A., 1990, Paper AIAA-1990-2350, https://doi.org/10.2514/6.1990-2350.

[24] T. Lak and F. Chandler, "A safe and low cost cryogenic upper stage design for the Space Shuttle," in Space 2000 Conference and Exposition, Long Beach, CA, U.S.A., 2010, Paper AIAA-2010-5286, https://doi.org/10.2514/6.2000-5286.

[25] R. P. Lindstedt and L. Q. Maurice, "Detailed chemical–kinetic model for aviation fuels, " Journal of Propulsion and Power, vol. 16, no. 2, pp. 187, 2000, https://doi.org/10.2514/2.5582.

[26] M. Ellion, D. Frizell, and R. Meese, "Liquid propulsion systems for orbit insertion of unmanned spacecraft," in 12th Propulsion Conference, Palo Alto, CA, USA, 1976, Paper AIAA-1976-711, https://doi.org/10.2514/6.1976-711.

[27] H. J. Namkoung, P. G. Han, K. H. Lee, Y. S. Kim, Ch. Kim and Y. B. Yoon, "A study on heat transfer characteristics of small liquid rocket engine with calorimeter, " in 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, 2006, Paper AIAA-2006-5195, https://doi.org/10.2514/6.2006-5195.

[28] R. Nicolay, T. Mattstedt and D. Thelemann, "Status of cryogenic thrust chamber development for ariane 5 at astrium," in 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Las Vegas, NV, U.S.A., 2000, Paper AIAA-2000-3167, https://doi.org/10.2514/6.2000-3167.

[29] B. Yazici, "Conceptual design optimization for liquid rocket propulsion system of Multi-Stage launch vehicle," in 3rd International Conference on Recent Advances in Space Technologies-RAST, 2007, Paper 60005-3

 [1] R. Humble, Space Propulsion Analysis and Design, McGraw-Hill Companies, Incorporated, 1995.
[2]      G. P. Sutton and O. Biblarz, Rocket Propulsion Elements, 8rd ed., John Wiley & Sons, 2011.
[3]      J. E. John, Gas Dynamics, 3rd ed. Pearson, 2006.
[4]      Dieter K. Huzel, David H. Huang, Modern Engineering for Design of Liquid-Propellant Rocket Engines, United States: American Institute of Aeronautics and Astronautics, 1992.
[5]        M. A. Eskandari, M. Farshchi, "Conceptual design of a special Two-Component zemastic combustion chamber," M.S. thesis, Sharif University of Technology, Tehran, Iran, 2018.
[6]       S. M. A. Borghei and A. Madadi, "Conceptual design of space motocryogenics with liquid hydrogen fuel," M. S. thesis, Amirkabir University of Technology, Tehran, Iran, 2022, (In Persion).
[7]  M. Barrere, Rocket Propulsion, New York: Elsevier Publishing Company, 1960.
 [8]   T. Aoki, T. Ishikawa, and Y. Morino, "Overview of basic research activities on cryogenic composite propellant tanks in Japan," in 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, Kyoto, Japan, 2001, Paper AIAA-2001-1878, https://doi.org/10.2514/6.2001-1878.
[9]  S. Durteste, "A transient model of the VINCI cryogenic upper stage rocket engine," in 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH,  2007, Paper AIAA-2007-5531, https://doi.org/10.2514/6.2007-5531.
[10] R. Eidson, "Cryogenic upper stage propulsion systems evolution," in 28th Joint Propulsion Conference and Exhibit, Nashville, TN, USA, 1992, Paper AIAA- 1992-3594, https://doi.org/10.2514/6.1992-3594.
[11] K. Ennix and M. Coleman, "Liquid propulsion technology for expendable and sts launch vehicle transfer stages," in 23rd Joint Propulsion Conference, San Diego, CA, U.S.A., 1987, Paper AIAA- 1987- 1934, https://doi.org/10.2514/6.1987-1934.
[12] D. Fiot, G. Vigier, D. Valentian, and R Bec, "Low Thrust Propulsion Systems for ELV Upper Stage System and Stage Analysis," in 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, 2006, Paper AIAA-2006-4437, https://doi.org/10.2514/6.2006-4437.
[13] M. F. Fisher, "Propellant management in booster and upper-stage propulsion systems," Journal of Propulsion and Power, vol. 14, no. 5, pp. 649-656, 1998, https://doi.org/10.2514/2.5326.
[14] V. Gautam and A. Gupta, "Cryogenic flow and mixing from a single element coaxial rocket injector," in 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, 2006, Paper AIAA-2006-4529, https://doi.org/10.2514/6.2006-4529.
[15] V. Gautam and A. Gupta, "Fate of cryogenic fluid flow and atomization from a sheer coaxial injector under pre-ignition conditions," in 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Hartford, CT, 2008, Paper AIAA-2008-5024, https://doi.org/10.2514/6.2008-5024.
[16] D. Glover, "NASA cryogenic fluid management space experiment efforts, " in Conference on Advanced SEI Technologies, Cleveland, OH, U.S.A., 1991, Paper AIM-91-3538,  https://doi.org/10.2514/6.1991-3538.
[17] W. D. Greene, D. L. Boxx, and B. K. Tiller, "Propellant densification for shuttle: The SSME perspective," in 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, IN, 2002, Paper AIAA-2002-3602.
[18] I. Cho, T. Jung, Y. Jung, O. Kwon, S. Oh, and D. Lee, "Development of korea sounding rocket - iii propulsion feeding system," in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, 2003, Paper 4899, AIAA-2003-4899, https://doi.org/10.2514/6.2003-4899.
[19] R. V. Burry, S. F. Iacobellis, and V. R. Larson, " Liquid propellant rocket engines: Their status and future," Journal of Spacecraft and Rockets, vol. 4, no. 12, pp. 1569-1580, 1967, https://doi.org/10.2514/3.29135.
[20] H. Immich and W. Mayer, "Cryogenic liquid rocket engine technology developments within the german national technology programme," in 33rd Joint Propulsion Conference and Exhibit,  Seattle,WA, U.S.A., Paper AIAA- 1997-2822, https://doi.org/10.2514/6.1997-2822.
[21] S. J. Isakowitz, "International reference guide to space launch systems," NASA STI/Recon Technical Report A, vol. 91, p. 51425, 1991.
[22] S. H. Kim, Y. M. Han, S. Seo, I. Y. Moon, J. K. Kim, and W. S. Seol, "Effects of  LOX post recess on the combustion characteristics for Bi-Swirl coaxial injector," in 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2005, Tucson, Arizona, Paper AIAA-2005-4445, https://doi.org/10.2514/6.2005-4445.
[23] T. Lak, M. Nguyen, and S. Hauver, "Fixed orifice pressurization system for the Space Shuttle LO2 tank," in 26th Joint Propulsion Conference, Orlando, FL, U.S.A., 1990, Paper AIAA-1990-2350, https://doi.org/10.2514/6.1990-2350.
[24] T. Lak and F. Chandler, "A safe and low cost cryogenic upper stage design for the Space Shuttle," in Space 2000 Conference and Exposition, Long Beach, CA, U.S.A., 2010, Paper AIAA-2010-5286, https://doi.org/10.2514/6.2000-5286.
[25] R. P. Lindstedt and L. Q. Maurice, "Detailed chemical–kinetic model for aviation fuels, " Journal of Propulsion and Power, vol. 16, no. 2, pp. 187, 2000, https://doi.org/10.2514/2.5582.
[26] M. Ellion, D. Frizell, and R. Meese, "Liquid propulsion systems for orbit insertion of unmanned spacecraft," in 12th Propulsion Conference, Palo Alto, CA, USA, 1976, Paper AIAA-1976-711, https://doi.org/10.2514/6.1976-711.
[27] H. J. Namkoung, P. G. Han, K. H. Lee, Y. S. Kim, Ch. Kim and Y. B. Yoon, "A study on heat transfer characteristics of small liquid rocket engine with calorimeter, " in 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, 2006, Paper AIAA-2006-5195, https://doi.org/10.2514/6.2006-5195.
[28] R. Nicolay, T. Mattstedt and D. Thelemann, "Status of cryogenic thrust chamber development for ariane 5 at astrium," in 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Las Vegas, NV, U.S.A., 2000, Paper AIAA-2000-3167, https://doi.org/10.2514/6.2000-3167.
[29] B. Yazici, "Conceptual design optimization for liquid rocket propulsion system of Multi-Stage launch vehicle," in 3rd International Conference on Recent Advances in Space Technologies-RAST, 2007, Paper 60005-3

  • Receive Date 24 May 2023
  • Revise Date 27 July 2023
  • Accept Date 07 September 2023
  • First Publish Date 07 September 2023