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Calculated Evaluation and Experimental Check of RPC Degassing and Saturation by Helium for Filling Cyclone-4 LV: Technical Note Cyclone-4.
]]>2. Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2018 (1); 6-12
DOI: https://doi.org/10.33136/stma2018.01.006
Language: Russian
Annotation: An alternative method of kerosene dehydration is proposed, which is based on application of cyclic technology of supersaturation decrease using dry nitrogen. A comparison of nitrogen and time specific consumption in dehydration operations is done and recommendations are given for their use in the cosmodromes’ launch complexes fuel storage and preparation facilities.
Key words:
Bibliography:
1. Zrelov V. N., Seryogin E. P. Liquid Rocket Propellants. М., 1975. 320 p.
2. Energy-Intensive Fuels for Aircraft and Rocket Engines / Under the editorship of L. S. Yanovsky. М., 2009. 400 p.
3. Soyuz-2. URL: https://ru.wikipedia.org/wiki/Soyuz-2_(launch vehicle family).
4. Angara. URL: https://ru.wikipedia.org/wiki/Angara_(launch vehicle).
5. Zenit-2. URL: https://ru.wikipedia.org/wiki/Zenit-2_(launch vehicle).
6. Leshchiner L. B., Ul’yanov I. E. Designing of Aircraft Fuel Systems. М., 1975. 344 p.
7. Zenit Space Launch System from the Eyes of its Developers / Under the editorship of e.d. professor V. N. Solov’yov, e.d. professor G. P. Biryukov, N. S. Kozhukhov, N. I. Kursenkova. М., 2003. 213 p.
8. Space Rocketry Ground Infrastructure Technological Facilities: Engineering Manual. Book 1. М., 2005. 416 p.
9. Investigation of Prospective Propellant Preparation Technologies: Scientific-Technical Report 21.18258.173ОТ / Yuzhnoye SDO. 2016. 115 p.
10. Shleifer A. A., Litvinov A. N. Prospective Technologies to Prepare Propellants with Improved Performance Properties. Ul’yanovsk, 1989. 215 p.
11. Englin B. A. Use of Liquid Propellants at Low Temperatures. 3-rd edition revised and enlarged. М., 1980. 207 p.
12. Volkov A. I., Zharsky I. M. Big Chemical Guide. Minsk, 2005. 608 p.
13. Calculated Evaluation and Experimental Check of RPC Degassing and Saturation by Helium for Filling Cyclone-4 LV: Technical Note Cyclone-4. 22.6849.123 СТ / Yuzhnoye SDO. 2005. 29 p.
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2019, (1); 38-44 DOI: https://doi.org/10.33136/stma2019.01.038 Language: Russian Annotation: This article considers the issue of achievement of the specified value of propellants saturation by helium after their delivery from the manufacturers to the launch site. In spite of the fact that this procedure does not provide exact value of the specified gas saturation, its application will accelerate and make cheaper the process of fuel preparation for filling operations at the launch site, which is especially relevant in case of fuel saturation by helium. Alternative of the practical use of the study results is suggested in the form of the complex technology of fuel saturation by helium, delivered in the tank containers from the manufacturer to the launch site. Key words: oxidizer , fuel , saturation by helium , tank container , transportation Bibliography: 1. oxidizer , fuel , saturation by helium , tank container , transportation .
]]>6. Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 38-44
DOI: https://doi.org/10.33136/stma2019.01.038
Language: Russian
Annotation: This article considers the issue of achievement of the specified value of propellants saturation by helium after their delivery from the manufacturers to the launch site. Knowing the fact that propellants gas saturation or gas separation processes are labour-consuming and costly this issue is of immediate interest. In order to solve this problem number of factors have been considered, which determine the value of gas saturation in the propellants delivered to the launch site and procedure to control the value of gas saturation by the fuel manufacturer has been developed. This procedure implies that shipping tank container is pressurized after being fueled with propellants at the manufacturer’s, the pressure is characterized by the value of the known initial deficit or excess of gas in the propellants, following which tank container is delivered to the launch site. During transportation tank container is subjected to various kinds of mechanical actions (vibration, rolling and pitching in the sea, braking, transshipment), therefore intensive mixing of propellants occur. As propellants mix, process of propellant saturation occurs when certain amount of gas transits from tank container’s gas volume into the liquid, therefore certain gas saturation is reached. Article includes the measuring results of the gas liquid medium parameters inside the tank containers with fuel in the process of fuel transportation to Ukraine from PRC factories and estimations of the measuring results using the developed model which confirmed the quantitative nature of the mass exchange processes, included in the model, going on in the gas liquid medium during transportation of the tank container with fuel equipment. It has been determined that due to inevitable errors in the measuring of the specified parameters by the tank container, the achievement of the specified gas saturation with high precision is problematic. In spite of the fact that this procedure does not provide exact value of the specified gas saturation, its application will accelerate and make cheaper the process of fuel preparation for filling operations at the launch site, which is especially relevant in case of fuel saturation by helium. Based on this fuel saturation by helium procedure, the complex technology is suggested, providing controlled gas saturation during fuel delivery and subsequent adjustment of gas saturation using launch site equipment. Therefore, this article develops and studies the original model of the controlled gas saturation of the fuel during its delivery to the consumer. Alternative of the practical use of the study results is suggested in the form of the complex technology of fuel saturation by helium, delivered in the tank containers from the manufacturer to the launch site.
Key words: oxidizer, fuel, saturation by helium, tank container, transportation
Bibliography:
1. Volskiy A. P. Kosmodrom. M.: Voenizdat, 1977. 311 p.
2. Stepanov A. N., Vorobiev A. M., Grankin B. K. Kompleksy zapravki raket I kosmicheskikh apparatov. SPB:OM-PRESS, 2004. 26 p.
3. Kiriyanova A. N., Matveeva O. P. Opredelenie kolebania davlenia v gazovoy polosti hermetychikh emkostey transportnozapravochnykh containerov dlya raketnykh topliv pri temperaturnykh vozdeistviyakh/ Nauka i innovatsii. 2016. Vyp. 7.
4. Berezhkovskiy M. I. Khranenie i transportirovka khimicheskykh produktov. – M.: Khimia, 1973. – 272 s.
5. Perepelkin K. Ye., Matveev V. S. Gazovye emulsii. L.:Khimia, 1979. 200 p.
6. Issledovanie protsessov degazirovaniya komponentov topliva v conteinere-tsisterne pri dostavke topliva potrebitelyu. Cyclone4M 21.18425.174 OT: Techn. report. Dnepropetrovsk: Yuzhnoye SDO, 2017. 39 p.
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The article considers the preparation of propellant for filling the launch vehicle stages with high-boiling propellant components of nitrogen tetroxide (oxidizer) and unsymmetrical dimethyl hydrazine (fuel) in terms of propellant saturation with helium and denitrogenation. Usually these issues refer to the common technology of propellant preparation and are tackled sequentially: first, propellant is drained into the filling tank of the filling system, then the propellant is denitrogened, for example purging the propellant by helium under atmospheric pressure in the tank, then propellant is saturated with helium to the given concentration by bubbling helium in the propellant, maintaining the set pressure of helium in the tank. Key words: saturation with helium and denitrogenation of the propellant , drain with closed vent device , excessive pressure draining , gas-vapor mixture , neutralization system Bibliography: 1. saturation with helium and denitrogenation of the propellant , drain with closed vent device , excessive pressure draining , gas-vapor mixture , neutralization system .
]]>5. Fueling-neutralization stations. New developments and applications
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2023 (1); 48-55
DOI: https://doi.org/10.33136/stma2023.01.048
Language: Ukrainian
Annotation: The article dwells on development and study of the multifunctional operations while preparing propellant components for launch vehicle tank filling by high-boiling propellant components at the neutralization stations. The article considers the preparation of propellant for filling the launch vehicle stages with high-boiling propellant components of nitrogen tetroxide (oxidizer) and unsymmetrical dimethyl hydrazine (fuel) in terms of propellant saturation with helium and denitrogenation. Usually these issues refer to the common technology of propellant preparation and are tackled sequentially: first, propellant is drained into the filling tank of the filling system, then the propellant is denitrogened, for example purging the propellant by helium under atmospheric pressure in the tank, then propellant is saturated with helium to the given concentration by bubbling helium in the propellant, maintaining the set pressure of helium in the tank. This technology significantly complicates the process of propellant preparation, increases helium consumption, as well as the amount of the generated vapor, which requires recycling in the neutralization units.
This article studies multifunctional operations, where the propellant is simultaneously drained from delivery vehicles, saturated with helium and denitrogenated. Amount of residual nitrogen in the propellant and the main direction of deep denitrogenation of the propellant are calculated. Amount of generated vapor and consumed helium are determined. The process of propellant draining by extrusion, maintaining the given pressure in the tank and alternating the propellant drain on the closed vent device (compression) and open vent device (decompression) is studied.
As a result, the theoretical justification of multifunctional operations in preparation of high–boiling propellant components to fill the launch-vehicle stages is presented.
Key words: saturation with helium and denitrogenation of the propellant, drain with closed vent device, excessive pressure draining, gas-vapor mixture, neutralization system
Bibliography:
1. Pozdeev G. L., Kucherenko R. A., Kucherenko T. V. Issledovanie osobennostey dostavki na kosmodrom komponentov raketnogo topliva s zadannym gazonasyschenniem. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. / GP «KB «Yuzhnoye». Dnepr, 2019. Vyp. 1. S. 38–44. https://doi.org/10.33136/stma2019.01.038
2. Pozdeev G. L. Razrabotka I issledovanie metodov obespecheniya zadannyh parametrov pri zapravke: dis. na soiskanie kand. tehn. nauk. GP «KB «Yuzhnoye», 1978. Dnepropetrovsk. 123 s.
3. KRK «Tsiklon-4M». Zapravochno-neitralizatsionnaya stantsia. Tehnicheskiy proekt. С4М YZH-ANL 02802. GP «KB «Yuzhnoye». 2017. 108 s.
4. KRK «Tsiklon-4M». Predlozheniya po helirovaniyu komponentov topliva dlya zapravki 2-oy stupeni rakety-nositelya na ZNS s uchetom osobennostey dostavki topliva v hermetichnyh konteynerah-tsisternah. Nauchno-tehnicheskiy otchet. Tsiklon-4M. 21.18668.174 OT. GP «KB «Yuzhnoye», 2019. 33 s.
5. Sposob zakrytoy zapravki toplivnogo baka zhidkim toplivom i systema dlya ego osuschestvlenniya: pat. RU 2489327. В64F1/28.
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