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13. Experience in Development of Isolating Fuel Valve with Pneumatic Drive and Hydraulic Brake for Operation under Cryogenic Conditions

Authors:

Makarenko A. O., Mashchenko O. M., Nazarenko O. P., Skochko V. V., Ustich V. V., Shevtsov E. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 65-69

Language: Russian

Annotation: To support ignition of Taurus LV first stage core structure engine, an oxidizer dividing valve has been developed that ensures minimal hydraulic resistance, opening time and hydraulic impact. The paper considers the valve design, main phases of its ground development testing and basic critical comments on the design made in the process of manufacturing and testing.

Key words:

Bibliography:
1. Report on the Results of Isolation Valve Check Tests Taurus-II.21.17039.203ОТ / Yuzhnoye SDO. Dnepropetrovsk, 2011. 30 p.
2. Report on the Results of Isolation Valve Check Tests Taurus-II.21.17050.203ОТ / Yuzhnoye SDO. Dnepropetrovsk, 2011. 23 p.
3. Report-Conclusion on the Results of Isolation Valve Developmental Tests 2TRS2S1.94.7204.0000.0000.00.0 ОЗ / Yuzhnoye SDO. Dnepropetrovsk, 2011. 161 p.

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13.2.2017 Experience in Development of Isolating Fuel Valve with Pneumatic Drive and Hydraulic Brake for Operation under Cryogenic Conditions
13.2.2017 Experience in Development of Isolating Fuel Valve with Pneumatic Drive and Hydraulic Brake for Operation under Cryogenic Conditions
13.2.2017 Experience in Development of Isolating Fuel Valve with Pneumatic Drive and Hydraulic Brake for Operation under Cryogenic Conditions
]]> 9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source https://journal.yuzhnoye.com/content_2019_1-en/annot_9_1_2019-en/ Thu, 25 May 2023 12:09:50 +0000 https://journal.yuzhnoye.com/?page_id=27714
O maximalnykh akusticheskykh nagruzkakh na rekety pri starte/ V. Metod opredeleniya vida istochnikov akusticheskogo izlucheniya v pervye secundy starta raket kosmicheskogo naznacheniya/ G. / Volnovoy parameter kak kriteriy v osnove metoda issledovaniya akusticheskikh istochnikov pro starte raket/ Aviatsionno-kosmicheskaya technika I technologia.
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9. Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source

Authors:

Sirenko V. M.1, Sokol G. I.2, Savchuk V. M.1, Kotlov V. Y.2, Savchuk T. L.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2019, (1); 64-71

DOI: https://doi.org/10.33136/stma2019.01.064

Language: Russian

Annotation: During lift-off of integrated launch vehicles, the propulsion system jet generates acoustic field. Therewith, the loads can be created that are critical for the launching equipment, rocket body and especially for the spacecraft, which are under the fairing. To take into account the effects on these elements, it is necessary to determine the characteristics of generated acoustic field. The method was developed that allows modeling the acoustic fields during integrated launch vehicle lift-off based on determination of acoustic sources type. In particular, modeling of Cyclone-4M ILV jet acoustic radiation by bulky source was performed. This provided the possibility to calculate acoustic pressure amplitudes in ILV ambient medium and to evaluate acoustic effect on the rocket body at certain points. The method is expected to be used to investigate kR wave parameter. The modeling of integrated launch vehicle propulsion system (ILV PS) jet acoustic field as bulky radiation source was performed in the rocket flight leg where ILV ascent altitude does not exceed ~ 25 m. In this case, one should be based on the value of boundary frequency fb =150 Hz which separates two types of acoustic field: fb ˂ 150 Hz – front of acoustic wave of spherical type, fb > 150 Hz – front of acoustic wave of flat type. The algorithm and program of calculation of sound pressure levels were developed in JAVA language. The characteristics of acoustic fields sound pressure levels were calculated depending on radiation frequency taking into account environmental temperature. The maximal acoustic pressure level in 150 Hz frequency in the payload area outside the fairing – 155 dB, in the instrumentation bay area – 157 dB, in the intertank bay area – 172 dB, in the aft bay area – 182 dB. In the frequencies lower than 150 Hz, the sound pressure levels are lower. The calculation data are presented graphically.

Key words: integrated launch vehicle, acoustic field, sound pressure

Bibliography:

1. Dementiev V. K. O maximalnykh akusticheskykh nagruzkakh na rekety pri starte/ V. K. Dementiev, G. Ye. Dumnov, V. V. Komarov, D.A. Melnikov// Kosmonavtika I raketostroenie. 2000. Vyp. 19. P. 44-55.
2. Tsutsumi S., Ishii T., Ut K., Tokudone S., Chuuouku Y., Wado K. Acoustic Design of Launch Pad for Epsilon Launch Vehicle / Proceedings of AJCPP2014 . Asian Joint Conference on Propulsion and Power, March 5- 8, 2014, Jeju Island, Korea. AJCPP2014-090.
3. Panda J., Mosher R., Porter D.J. Identification of Noise Sources during Rocket Engine Test Firings and a Rocket Launch a Microphone Phased-Array // NASA / TM2013-216625, December 2013. P. 1-20.
4. Sokol G. I. Metod opredeleniya vida istochnikov akusticheskogo izlucheniya v pervye secundy starta raket kosmicheskogo naznacheniya/ G. I. Sokol// Systemne proektuvannya ta analiz characteristic aerokosmichoi techniki: Zb. nauk. pr. 2018. XXIV. Dnipro: Lira, 2018. P. 91-101.
5. Sokol G. I., Frolov V. P., Kotlov V. Yu. / Volnovoy parameter kak kriteriy v osnove metoda issledovaniya akusticheskikh istochnikov pro starte raket/ Aviatsionno-kosmicheskaya technika I technologia. 2018. 3 (147), May-June 2018. Kharkov: KhAI, 2018. P. 4-13. DОІ:http://doi.org /10.20535/0203- 3771332017119600.
6. Rzhevkin S. N. Kurs lektsiy po teorii zvuka/ S. N. Rzhevkin. M.: MGU, 1960. 261 p.
7. Tyulon V. N. Vvedenie v teoriyu izlucheniya I rasseyaniya zvuka / V. N. Tyulin. M.: Nauka, 1976. 253 p.
8. Sapozhkov M. A. Electroakustica/ M. A. Sapozhkov. M.: Svyaz, 1978. 272 p.
9. Grinchenko V. T., Vovk V. V., Matsipura V. T.. Osnovy akustiki. Kyiv: Nauk. dumka, 2007. 640 p.
10. Ultrazvuk: Malaya enciclopedia. M.: Nauka, 1983. 400 p.
11. Volkov K. N. Turbulentnye strui – staticheskie modeli i modelirovanie krupnykh vikhrey/ K. N. Volkov, V. N. Emelyanov, V. A. Zazimko. M.: Fizmatlit, 2013. 960 p.
12. Schildt G. Java 8. Polnoe rukovodstvo. 9-e izd. M.: Wiliams, 2015. 137 p.

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9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source
9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source
9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source

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]]> 8.2.2019 Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head https://journal.yuzhnoye.com/content_2019_2-en/annot_8_2_2019-en/ Mon, 15 May 2023 15:45:50 +0000 https://journal.yuzhnoye.com/?page_id=27210
Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head Authors: Batutina T. Acousticheskiy journal. (2019) "Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head" Космическая техника. Available at: https://doi.org/10.33136/stma2019.02.058 . "Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head" Космическая техника. S., Hrinchenko V. T., Oliinyk V. quot;Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head", Космическая техника. T., Oliinyk V.
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8. Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head

Authors:

Batutina T. Y.1, Bondar’ D. S.1, Hrinchenko V. T.2, Oliinyk V. N.1

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Institute of Hydromechanics of National Academy of Sciences of Ukraine, Kyiv, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2019, (2); 58-62

DOI: https://doi.org/10.33136/stma2019.02.058

Language: Russian

Annotation: The article considers the procedure for evaluation of acoustic stressing parameters at the observation point nearby the launch vehicle nose cone when passing the sectors with maximum velocity heads and close to 1 Mach numbers. And the problem is set to determine the overall sound pressure level and the corresponding levels in octave and 1/3-octave frequency bands. Procedure under consideration is based on the semi-empirical dependency of characteristics of the wideband aerodynamic noise, which occurs during the launch vehicle flight at high velocities due to the turbulent pressure fluctuations and dimensionless aerodynamic parameters of the main stream. General idea of this approach is to establish relation of the velocity heads with wall pressure fluctuations in the boundary layer, calculating shear stress (friction) on the shell surface based on relationships applicable in the boundary layer theory and engineering experience. Attempts of development of similar calculation models go back to the early efforts, dedicated to the study of the aeroacoustics of the launch vehicle in flight. Main advantages of the procedure are its simplicity and versatility since it can be used to determine the acoustic loads around the payload fairings of launch vehicles of different sizes and shapes within the wide range of flight velocities and altitudes.

Key words: Launch vehicle flight, Mach number, launch vehicle payload fairing, determination of sound pressure

Bibliography:
1. Raman K. R. A study of surface pressure fluctuations in hypersonic turbulent boundary layers. NASA CR-2386, 1974. 90 p. https://doi.org/10.2514/6.1973-997
2. Aviatsionnaya akustika/ pod red. A. G. Munina. М., 1986. Ch. 1. 248 s.
3. Aviatsionnaya akustika / pod red. A. G. Munina. М., 1986. Ch. 2. 264 s.
4. Kovalnogov N. N., Lukin N. M. Osnovy teorii i rascheta pogranichnogo sloya. Ulianovsk, 2000. 86 s.
5. Monin A. S., Yaglom A. M. Statisticheskaya hydromechanika. Mechanika turbulentnosti. M., 1965. Ch. 1. 640 s.
6. Vasiliev V. V., Morozov L. V., Shakhov V. G. Raschet aerodynamicheskykh characteristic letatelnykh apparatov. Samara, 1993. 78 s.
7. Yefimtsov B. M. Kriterii podobiya spektrov pristenochnykh pulsatsiy davleniy turbulentnogo pogranichnogo sloya. Acousticheskiy journal. 1984. T. 30, № 1. S. 58–61.

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8.2.2019 Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head
8.2.2019 Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head
8.2.2019 Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head

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