Methane, kerosene and hydrogen comparative as a rocket fuel for launch vehicle pneumohydraulic supply system development

1Mykhalchyshyn, RV, 1Brezgin, MS, 1Lomskyi, DA
1Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Space Sci.&Technol. 2018, 24 ;(2):12-17
Publication Language: English
Liquid oxygen and methane are often regarded as new promising propellant components. The topic of this paper is a comparative analysis of methane, kerosene, and hydrogen as a rocket fuel in combination with liquid oxygen. Advantages and disadvantages of each component are shown. Pneumohydraulic system has been developed with optimized parameters of subsystems.
Keywords: chilldown, gas bottle, payload, pneumohydraulic supply system, pressurization, propellant components, tank
1. Belyaev N. M. Calculation of pneumohydraulic missile systems. Moscow, Mashinostroenie, 219 p. (1983) [in Russian].
2. Cracker A., Peery S. System Sensitivity Studies of a LOX/ Methane Expander Cycle Upper Stage Engine. AIAA 98- 3674, 14 p. (1998).
3. Gorokhov V. D., Rachuk V. S. CADB’s Development of the LRE operating with Liquefied Natural Gas and Oxygen. 9 p. (2009) [in Russian].
4. Ierardo N., Biagioni M., Pirrelli P. Development of the LM10-Mira LOX-LNG Expander Cycle for the Lyra Launch Vehicle. IAC S.24-146, 12 p. (2014).
5. Kalmykov G. P., Mossolov S. V. Liquid Rocket. Engines Working on Oxygen/Methane for Space. Transportation systems of the XXI century. IAF-00-S.2.10, 14 p. (2000) [in Russian].
6. Kyoung-Ho Kim, Dae-Sung Ju, Development of 'Chase10' liquid rocket engine having 10tf thrust using LOX & LNG (Methane). AIAA-2006-4907, 16 p. (2006).
doi: org/10.2514/6.2006-4907.
7. Pavlyuk Yu. S. Ballistic rocket designing] Chelyabinsk, 92 p. (1996) [in Russian].
8. Tamura H. Lox/methane Staged Combustion Rocket Investigation. AIAA 07-1856, 17 p. (2007).
9. Technical report «Circulation parameters determination for liquid oxygen in the chilldown system» 22.8234.123. Dnipro, 34 p. (2016). [in Russian].