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By the example of payload fairing and interstage bay of Cyclone-4 launch vehicle, high efficiency is shown of proposed methodology implementation when selecting their rational design and technological parameters. Comparison of Payload Fairings of Existing and Prospective Domestic Launch Vehicles and their Foreign Analogs / А. Optimization of Cyclone-4 Launch Vehicle Payload Fairing Design Parameters / V. Mass Optimization of Launch Vehicle Payload Fairing Irregular Zones.
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20. Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments

Authors:

Potapov O. М.1, Kovalenko V. O.1, Kondrat’ev А. V.2, Gaidachuk V. Е.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Kharkiv Aviation Institute, Kharkiv, Ukraine2 

Page: Kosm. teh. Raket. vooruž. 2017 (2); 112-120

Language: Russian

Annotation: Some main results of scientific support of development of launch vehicle head module composite loadbearing bays are presented. The methodology is proposed for developing these units. By the example of payload fairing and interstage bay of Cyclone-4 launch vehicle, high efficiency is shown of proposed methodology implementation when selecting their rational design and technological parameters.

Key words:

Bibliography:
1. Degtyarev A. V. Rocket Technology. Problems and Prospects. Selected scientific-technical publications. Dnepropetrovsk, 2014. 420 p.
2. Kovalenko V. A., Kondrat’yev A. V. Use of Polymer Composite Materials in Space Rockets as Reserve of Increasing their Mass and Functional Effectiveness. Aerospace Engineering and Technology. 2011. No. 5 (82). P. 14-20.
3. Kondrat’yev A. V. et al. Analysis of Nomenclature of Type Composite Units of Space Rockets and Structural Schemes Applied for them / A. V. Kondrat’yev, A. G. Dmitrenko, K. D. Stenile, А. А. Tsaritsynsky. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 3 (79). Kharkiv, 2014. P. 19 – 30.
4. Potapov A. M. et al. Comparison of Payload Fairings of Existing and Prospective Domestic Launch Vehicles and their Foreign Analogs / А. М. Potapov, V. A. Kovalenko, A. V. Kondrat’yev. Aerospace Engineering and Technology. 2015. No. 1(118). P. 35 – 43.
5. Gaidachuk A. V. et al. Methodology of Developing Effective Design and Technological Solutions of Space Rocketry Composite Units: Monography in 2 volumes. Vol. 2. Synthesis of Space Rocketry Composite Units Parameters at Heterogeneous Loading / A. V. Gaidachuk, V. E. Gaidachuk, A. V. Kondrat’yev, V. A. Kovalenko, V. V. Kirichenko, А. M. Potapov / Under the editorship of A. V. Gaidachuk. Kharkiv, 2016. 250 p.
6. Gaidachuk A. V. et al. Methodology of Developing Effective Design and Technological Solutions of Space Rocketry Composite Units: Monography in 2 volumes. Vol. 1. Creation of Space Rocketry Units with Specified Quality of Polymer Composite Materials / A. V. Gaidachuk, V. E. Gaidachuk, A. V. Kondrat’yev, V. A. Kovalenko, V. V. Kirichenko, А. M. Potapov / Under the editorship of A. V. Gaidachuk. Kharkiv, 2016. 263 p.
7. Smerdov A. A. Development of Methods to Design Space Rocketry Composite Materials and Structures: Dissertation of Doctor of Engineering Science: 05.07.02, 05.02.01. М., 2007. 410 p.
8. Slyvyns’kyy V. et al. Basic parameters’ optimization concept for composite nose fairings of launchers / V. Slyvyns’kyy, V. Gajdachuk, V. Kirichenko, A. Kondratiev. 62nd International Astronautical Congress, IAC 2011 (Cape Town, 3-7 October 2011). Red Hook, NY: Curran, 2012. Vol. 9. P. 5701-5710.
9. Gaidachuk V. E. et al. Optimization of Cyclone-4 Launch Vehicle Payload Fairing Design Parameters / V. E. Gaidachuk, V. I. Slivinsky, A. V. Kondrat’yev, A. P. Kushnar’ov, Effectiveness of Honeycomb Structures in Aerospace Products: Proceedings of III International Scientific-Practical Conference (Dnepropetrovsk, 27-29 May 2009). Dnepropetrovsk, 2009. P. 88 – 95.
10. Zinov’yev A. M. et al. Design and Technological Solution and Carrying Capacity of Cyclone-4 Launch Vehicle Interstage Bay Made of Polymer Composite Materials / А. М. Zinov’yev, А. P. Kushnar’ov, A. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Aerospace Engineering and Technology. 2013. No. 3 (100). P. 46-53.
11. Karpov Y. S. Connection of Parts and Units Made of Composite Materials: Monography. Kharkiv, 2006. 359 p.
12. Kondrat’yev A. V. Mass Optimization of Launch Vehicle Payload Fairing Irregular Zones. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 47 (4). Kharkiv, 2006. P. 126 – 133.
13. Degtyarev A. V. et al. Evaluation of Carrying Capacity of Launch Vehicle Bays Separation System Composite Fitting / A. V. Degtyarev, A. P. Kushnar’ov, V. V. Gavrilko, V. A. Kovalenko, А. V. Kondrat’yev, А. М. Potapov. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2013. Issue 1. P. 18-21.
14. Patent 81537 UA, MPK (2013.01) F42B 15/36 (2006.01) B64D 1/00 Fitting of Rocket’s Three-Layer Shell / О. М. Zinov’yev, О. P. Kuznetsov, V. V. Gavrilko, О. М. Potapov, V. O. Kovalenko et al.; Applicant and patent holder NVF Dniprotechservice, Yuzhnoye SDO. No. u 2012 11210; Claimed 27.09.2012; Published 10.07.13, Bulletin 13. 4 p.
15. Zinov’yev A. M. et al. Manufacturing Technology of Cyclone-4 Launch Vehicle Experimental Large-Sized Interstage Bay Made of Carbon Plastics / А. M. Zinov’yev, А. P. Kushnar’ov, А. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 2 (74). Kharkiv, 2013. P. 7 – 17.
16. Zinov’yev A. M. et al. Static Tests of Cyclone-4 Launch Vehicle Experimental Interstage Bay Made of Carbon Plastic / А. М. Zinov’yev, А. P. Kushnar’ov, А. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Aerospace Engineering and Technology. 2013. No. 4(101). P. 28-35.

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20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments
20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments
20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments
]]> 18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions https://journal.yuzhnoye.com/content_2017_2/annot_18_2_2017-en/ Wed, 09 Aug 2023 12:19:09 +0000 https://journal.yuzhnoye.com/?page_id=29858
Development Test of Payload Fairing Separation Dynamics under Ground Conditions Authors: Shevtsov E. Fundamentals of Spacecraft Launch Vehicles Designing / Under the editorship of V. (2017) "Development Test of Payload Fairing Separation Dynamics under Ground Conditions" Космическая техника. "Development Test of Payload Fairing Separation Dynamics under Ground Conditions" Космическая техника. quot;Development Test of Payload Fairing Separation Dynamics under Ground Conditions", Космическая техника. Development Test of Payload Fairing Separation Dynamics under Ground Conditions Автори: Shevtsov E.
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18. Development Test of Payload Fairing Separation Dynamics under Ground Conditions

Authors:

Shevtsov E. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 102-106

Language: Russian

Annotation: The paper presents the original test methods with simulation of axial loads nx＜＜ 1 and nx ＞＞1 and the test stands which were used on testing the Zenit-2 ILV large-sized nose fairing.

Key words:

Bibliography:
1. Fundamentals of Spacecraft Launch Vehicles Designing / Under the editorship of V. P. Mishin. М., 1991. 415 p.
2. Kolesnikov K. S., Kozlov V. V., Kokushkin V. V. Flying Vehicles Stages Separation Dynamics. М., 1977. 224 p.
3. Аuthor’s Certificate 285792. Stand for Testing Rocket Fairing Separation in Ground Conditions / O. A. Semenenko, E. I. Shevtsov, V. A. Gontarovsky, V. A. Petrushevsky et al. Claimed 10.05.1989.
4. Аuthor’s Certificate 323879. Method of g-Loads Simulation during Testing of Separation Systems of Cylindrical-Conical Fairing that Separates into Doors / E. I. Shevtsov, V. A. Gontarovsky et al. Claimed 07.02.1989.

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18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions
18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions
18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground 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
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. The method was developed that allows modeling the acoustic fields during integrated launch vehicle lift-off based on determination of acoustic sources type. 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. 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.
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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
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. Launch vehicle flight , Mach number , launch vehicle payload fairing , determination of sound pressure .
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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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