Evaluating the Probability of End-of-Life Failure-Free Performance of Liquid-Propellant Rocket Engine of Reusable Space Tug
Authors: Borovik I.N. | Published: 07.04.2014 |
Published in issue: #2(95)/2014 | |
Category: Inspection and Diagnostics | |
Keywords: rocket engine, orbital transfer vehicle |
A method is given for evaluating the probability of failure-free performance of the liquid-propellant rocket engine of a reusable orbital transfer vehicle (essentially a reusable "space tug") by the end of its operational life, taking into account that a probability of failure-free operation reduces with every start of the engine as its operational life draws to a close. The resulting expression allows one to estimate the probability of failure-free operation with consideration of design parameters of the propulsion system and the reusable space tug as a whole. It is found that for providing a high probability of failure-free performance of the propulsion system of a reusable space tug, it is more important to plan the larger margins of the engine service life and the number of its in-flight starts while designing than to achieve higher reliability through extensive testing at the stage of finishing.
References
[1] Legostaev V.P., Lopota V.A., eds. Luna - shag k tekhnologiyam osvoeniya Solnechnoy sistemy [Moon is the step forward in the Solar system exploration]. Moscow, RKK "Energiya" im. S.P. Koroleva Publ., 2011. 584 p.
[2] Borovik I.N., Kozlov A.A. Mathematical model of the mass properties estimation of the hydrogen-oxygen antigenerator liquid-propellant engine on its main design parameters. Elektronnyy zhurnal "Trudy MAI" [Proc. Moscow Aviation Institute (National Research University)], 2008, no. 32, pp. 1-24. Available at: http://www.mai.ru/science/trudy/ (accessed 11.02.14) (in Russ.).
[3] Borovik I.N, Kozlov A.A. Determination method of optimum main design parameters of LOx-LH2 expander-cycle LRE for reusable OTV (orbital transfer vehicle). Proc. 60th Int. Astronautical Congr., Daejeon, Korea, 2009, IAC-09, C4.1.10, pp. 1-12.
[4] Borovik I.N. Formation technical aspect of reusable powerplant of orbital transfer vehicle. Vestn. Mosk. Aviatsionnogo Inst. [Herald of the Moscow Aviation Inst. (National Res. Un.], 2011, vol. 18, no. 2, pp. 99-108 (in Russ.).
[5] Alifanov O.M., Andreev A.N., Gushchin V.N., Zolotov A.A., eds. Ballisticheskie rakety i rakety-nositeli [Ballistic missilery and launch vehicle]. Moscow, Drofa Publ., 2004. 512 p.
[6] Kolomentsev A.I., Kraev M.V., Nazarov V.P. Ispytaniya i obespechenie nadezhnosti [Test operations and reliability control of rocket engine]. Krasnoyarsk, Sib. Gos. Aerokosmich. Un. (MAI) Publ., 2006. 335 p.