Energetic Compositions Application for the Reduction of the Environmental Pollution Because of Space Vehicle Launches

Keywords: worked-off stages, space pollution, re-entry, combustion, thermites


Technogeneous impact of rocket and space activities on the environment is one of the most actual problems of practical cosmonautics. This technogeneous impact is not only the pollution of near Earth space with space debris (worked-off stages of space launch vehicle (SLV)), but also the pollution of significant areas on the Earth surface with worked-off lower stages of SLV, which fall down after having accomplished their mission. In OmSTU and IPCP RAS it was suggested to apply different self-burning compositions, generating hot gases for the evaporation of the unused residues of liquid propellant in tanks of SLV. Then the mixture of the evaporated compounds together with the gaseous combustion products from gas-generating compositions is used as propellant mixture for the autonomous gas rocket engine. Such a solution would decrease considerably the level of the environment pollution and additionally it increases the energetic characteristics of SLV. For example, in the case of the second stage of SLV «Soyuz-2.1.v» it increases the total velocity by 5%. Also it is proposed to use firing the pyrotechnic compositions like (thermites) for the fairings heating up to the temperature when the fairing material can be ignited in air. It would reduce considerably the amount and the mass of the separating parts of SLV that fall to the Earth.



[1]. V.I. Kurenkov, Bases of space launch vehicles designing. The choice of main characteristics and formation of constructive shape. Samara State Aerospace University: 2011, 458 p. (in Russian).

[2]. V.V. Adushkin; S.I. Kozlov; A.V. Petrov, Ecological problems and risks of rocket-space technology influence on the environment. Handbook. Ankil: Moscow, 2000, 640 p. (in Russian).

[3]. Ya. Shatrov, Ensuring environmental safety of rocket-space activity. Part 1. Handbook: CNIImash: Korolev, Russia, 2010, 261 p. (in Russian).

[4]. Prevention of space debris generation / Under the science. Ed. Doct. tech. Sciences, prof. G. Raikunov - Moscow: FIZMATLIT, 2014. - 188 p. - ISBN 978-5-9221-1504-9.

[5]. V. Trushlyakov, E. Yutkin. Review of existing developments of means for launching large-sized space debris as operations for servicing apparatuses in orbit. Omskij nauchnyj vestnik [Omsk Scientific Bulletin] 1 (97) (2015) 92–95 (in Russian).

[6]. L. Anselmo, C. Pardini, Acta Astronaut.122 (2016) 19–27. Crossref

[7]. IADC Space Debris Mitigation Guidelines, Inter- Agency Space Debris Coordination Committee, IADC-02-01, paragraph 3.3.2. October, 2002. Rev. 1 issued in September 2007.

[8]. P. Huang, F. Zhang, Z. Meng, Z. Liu, Acta Astronaut. 128 (2016) 416–430. Crossref

[9]. L. Jasper; H. Schaub. Acta Astronaut. 96 (2014) 128–137. Crossref

[10]. K. Hovell; S. Ulrich, Attitude stabilization of an uncooperative spacecraft in an orbital environment using visco-elastic tethers. AIAA Guidance, Navigation, and Control Conference. AIAA: Gaylord Trail, Grapevine, Texas, 2016, p. 1–16.

[11]. S. Aleina, V. Nicole, S. Fabrizio, M. Viscio, S. Ferraris, Acta Astronaut. 128 (2016) 21–32. Crossref

[12]. S. Cleary, W.J. O’Connor, J. Guid. Control. Dynam. 39 (2016) 1392–1406. Crossref

[13]. R.P. Patera, K.R. Bohman, M.A. Landa, C. Pao, R.T. Urbano, M.A. Weaver, Capt. D.C. White. Controlled deorbit of the delta IV upper stage for the DMSP-17 mission. Proc. 2nd IAASS Conf. “Space Safety in a Global World” 14-16 May 2007, Chicago, USA.

[14]. J.-C. Liou, N.L. Johnson, Acta Astronaut. 64 (2–3) (2009) 236–243. Crossref

[15]. K. Takase, M. Tsuboi, Sh. Mori, K. Kobayashi. Demonstration for Upper Stage Controlled Re-entry Experiment by H-IIB Launch Vehicle. Mitsubishi Heavy Industries Technical Review. 48 (2014) 11–16.

[16]. V. Trushlyakov, D. Lempert, M. Belkova, Combust. Explo. Shock 51 (2015) 326–332. Crossref

[17]. V. Trushlyakov, D. Lempert, I. Lesnyak, Withdrawal of carrier rocket stage separated part from payload orbit and device to this end. RU Patent, 2014, No. 2518918.

[18]. V. Trushlyakov, D. Lempert. Increasing efficiency of space rocket with liquid-propellant engine. RU Patent, 2015, No. 2562826.

[19]. V. Trushlyakov, D. Lempert, V. Kudentsov. Method for increasing the energy of liquid components for rocket engines and the device for its realization. RU Patent, 2012, No. 2442010.

[20]. V. Trushlyakov, V. Kudentsov, Ya. Shatrov, I. Agapov, Method for separating part of space launch vehicles descent and the device for its realization. RU Patent, 2009, No. 2414391.

[21]. I.I. Kuznetsov, Yu.L. Kuznetsov, M.Zh. Mukhamedzhanov, D.S. Ukraintsev, G.V. Shokhov. Kosmonavtika i raketostroenie [Astronautics and rocket science] 3 (88) (2016) 83–92 (in Russian).

[22]. M. Shoemaker, J. van der Ha, S. Abe, K. Fujita, J. Spacecraft. Rockets 50 (2013) 326–336. Crossref

[23]. B. Fritsche, H. Klinkrad, A. Kashkovsky, E. Grinberg, Acta Astronaut. 47 (2000) 513–522. Crossref

[24]. A. Tewari, J. Spacecraft. Rockets 46 (2009) 299–306. Crossref

[25]. V. Trushlyakov, Ya. Shatrov. Method for minimizing exclusion zones for separated parts of rockets. RU Patent, 2014, No. 2585395.

[26]. V. Trushlyakov, Ya. Shatrov, D. Lempert, Yu. Iordan, V. Zarko. Fairing. RU Patent, 2016, No 2581636.

[27]. V. Trushlyakov, D. Lempert, Ya. Shatrov. Method for minimizing exclusion zones for separated parts of rockets. Method for minimizing exclusion zones for separated parts of rockets. Application for RU Patent, 2015, No. 2015137375.

[28]. V. Trushlyakov, D. Lempert, V. Zarko, Combust. Explo. Shock 51 (2015) 619–622. Crossref

[29]. B. Trusov. Program System TERRA for Simulation Phase and Thermal Chemical Equilibrium. XIV International Symposium on Chemical Thermodynamics. Institute of Chemistry, St-Petersburg, Russia, 2002, 483 p.
How to Cite
V. Trushlyakov, D. Lempert, and Y.- Shu, “Energetic Compositions Application for the Reduction of the Environmental Pollution Because of Space Vehicle Launches”, Eurasian Chem.-Technol. J., vol. 19, no. 3, pp. 239-244, Sep. 2017.