Search Results for “versatility” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Mon, 16 Mar 2026 17:59:18 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “versatility” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 6.2.2025 Floating launch platform of a sea-based space launch site https://journal.yuzhnoye.com/content_2025_2-en/annot_6_2_2025-en/ Tue, 27 Jan 2026 08:37:10 +0000 https://journal.yuzhnoye.com/?page_id=35831
Thanks to the versatility of the fl oating launch platform, it is possible to outline its appearance and characteristics according to the strategy for the launch services market.
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6. Floating launch platform of a sea-based space launch site

Date of receipt of the article for publication: 07.12.2025

Date of acceptance of the article for publication after review: 22.12.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Pustovharov A. A.

ORCID authors:

Pustovharov A. A. ORCID

Organization:

Yangel Yuzhnoye State Design Office

Page: Kosm. teh. Raket. vooruž. 2025 (2); 58-66

DOI: https://doi.org/10.33136/stma2025.02.058

Language: Ukrainian

Annotation: One of the courses in the evolution of space rocket complexes is the relocation of launch sites for space launchers to the World Ocean. Firstly, it provides the opportunity to render space services for countries that encounter complications in fi nding locations for spaceports on land. Secondly, it allows for a larger number of launch azimuths. Thirdly, it helps to increase the payload capabilities of space launchers lifting from launch sites closer to the equator. The article reviews the current global progress in utilizing ships as part of sea-based space launch sites. It notes that more and more countries are becoming interested in the development and construction of maritime space launch sites. As one of the leading enterprises in the rocket and space industry, Yuzhnoye State Design Offi ce also conducts relevant research and development, which has already yielded a conceptual design for such a launch site for the Cyclone-1K lightweight space launcher. A specifi cally equipped naval vessel was selected as the launch platform for this rocket. The article outlines initial data applied for the overall design of the launch facility and the launch platform in particular. The design process involved modern software for 3D modeling and fi nite element analysis. A conceptual view and the primary characteristics of the launch platform, obtained through the design, are presented. The platform’s primary systems are described. The specifi city of equipment arrangement to support launch vehicle preparation and ensure the liftoff , as well as the relation between such arrangement and the launch platform’s appearance and internal structure, are demonstrated. The results of this work will be valuable for the practical implementation of the sea-based space launch site project. A fl oating launch platform is the essential element of a sea-based space launch facility, as it accommodates everything necessary for launching space rockets from the sea surface. Thanks to the versatility of the fl oating launch platform, it is possible to outline its appearance and characteristics according to the strategy for the launch services market.

Key words: sea launch, sea-based space launch site, space launcher, fl oating launch platform

Bibliography:

1. Jeff Foust, February 14, 2023. SpaceX drops plans to convert oil rigs into launch platforms. URL: https://spacenews.com/ spacex-drops-plans-to-covert-oil-rigs-into-launch-platforms (data zvernennia 25.09.2025).
2. A Spaceport for Germany. The driver for a strong business and aerospace location. URL: https://www.offshore-spaceport.de/en (data zvernennia 25.09.2025).
3. Andrew Jones, December 9, 2022. China launches 14 satellites with new solid rocket from mobile sea platform. URL: https://spacenews.com/china-launches-14-satellites-with-new-solid-rocket-from-mobile-sea-platform (data zvernennia 25.09.2025).
4. Andrew Jones, January 13, 2025. Chinese sea launch sends 10 navigation enhancement satellites into orbit. URL: https://spacenews.com/chinese-sea-launch-sends-10-navigation-enhancement-satellites-into-orbit (data zvernennia 25.09.2025).
5. Andrew Jones, October 11, 2025. Huge commercial Chinese solid rocket launches 3 satellites from barge in the Yellow Sea. URL: https://spacenews.com/huge-commercial-chinese-solid-rocket-launches-3-satellites-from-barge-in-the-yellow-sea (data zvernennia 12.10.2025).
6. Larkin Yu. M., Onyshchenko A. F. Osoblyvosti proiektuvannia balkeriv. Visn. Odeskoho natsionalnoho morskoho universytetu. 2015. № 3 (45). S. 219 – 228.
7. Rehistr sudnoplavstva Ukrainy. Pravyla shchodo obladnannia morskykh suden. T. 2. Chastyny: ІІ «Korpus»; ІІІ «Prystroi, obladnannia i zabezpechennia»; ІV «Ostiinist»; V «Podil na vidsiky»; ХVІ «Konstruktsiia ta mitsnist korpusiv suden iz polimernykh kompozytsiinykh materialiv». Rehistr sudnoplavstva Ukrainy. 2020. 792 s.
8. Dontsov S. V. Osnovy teorii sudna. Odesa, 2020. 188 s.
9. Novikov A. I., Zinkovskii-Horbatenko V. H., Kot V. P. Vantazhna marka morskykh suden. Navch. posibn . Sevastopol, 2006. 160 s.
10. Hurs I. F. Praktychni rozrakhunki morekhidnykh yakostei sudna. Izmailskyi morskyi trenazhernyi tsentr. Izmail, 2001. 29 s.
11. Eyres D. J., Bruce G. J. Ship construction. 7th edition. Elsevier ltd, 2012. 388 p. https://doi.org/10.1016/B978-0-08-097239-8.00036-2
12. Syzov V. H. Teoriia korablia: Navch. posibn. Odeska nats. mor. akad. Odesa: FENIKS, 2003. 284 s.
13. Presentatsiia rushiiv Azipod® serii VI. Buklet firmy ABB Oy, Marine. 2010. 36 s.
14. WST-24R Retractable Thruster. Buklet firmy Wärtsilä Corporation. 2017. 2 s.

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]]> 9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes https://journal.yuzhnoye.com/content_2024_1-en/annot_9_1_2024-en/ Mon, 17 Jun 2024 08:48:18 +0000 https://journal.yuzhnoye.com/?page_id=35030
Key words: rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design. rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design.
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9. General-purpose thermostating module – new approach in development of up-to-date thermostating systems for rocket and space complexes

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Fateev D. M., Bikova G. M, Petukhov O. M., Pokataiev V. M.,Yelanskyi Yu. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 78-84

DOI: https://doi.org/10.33136/stma2024.01.078

Language: Ukrainian

Annotation: These days when creating any rocket space complex, it is important to ensure its advancement and competitive ability. To create such complex, the technical systems it consists of must be implemented with minimal economic and energy costs. Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Development of the competitive rocket and space complex also requires the new approach in the development of the thermostatting system. One of the main tasks is to create a system that can be mass-produced and used as part of any rocket and space complex. Solving this problem will significantly reduce the cost of creating and operating the thermostatting systems and the whole rocket and space complex. One of the ways to solve this task is to create a general-purpose thermostatting system. The modular principle for such thermostatting system would be optimal, which means making up a system from separate modules. It simplifies the all-round installation of various system options and simplifies its setup and operation. The paper demonstrates the possibility and prospects of creating modular thermostatting systems, which enable air supply with the required parameters to different consumers. Characteristics and design of the general-purpose thermostatting module are specified, which can be used as the main component without changing anything in the composition of stationary and mobile thermostatting systems.

Key words: rocket and space complex, launch vehicle, technological systems of the ground complex, thermostatting systems, open type system, versatility, modular design.

Bibliography:
  1. . Tsiklon-4M. URL: https://www. yuzhnoye.com.
  2. . KRK «Tsiklon-4M». C4M YZH SPS 090 02 Technicheskoe zadanie na sostavnuyu chast’ OKR «Sistema termostatirovaniya rakety-nositelya i golovnogo bloka» GP «KB «Yuzhnoye». 78 s.
  3. . KRK «Tsiklon-4M». C4M YZH SPS 119 02 Technicheskoe zadanie na sostavnuyu chast OKR «Transportnaya systema termostatirovaniya» GP «KB «Yuzhnoye». 2018. 40 s.

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]]> 15.2.2018 Topical Issues of Creation of Space Rocket Thermostatic System Mating Points https://journal.yuzhnoye.com/content_2018_2-en/annot_15_2_2018-en/ Thu, 07 Sep 2023 12:09:41 +0000 https://journal.yuzhnoye.com/?page_id=30786
Of special note is the versatility of the proposed technical solution for use in any of the space launch systems known in the world’s practice.
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15. Topical Issues of Creation of Space Rocket Thermostatic System Mating Points

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Bigun S. O.1, Khorolskyi M. S.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; State Enterprise DINTEM Ukrainian Research Design-Technological Institute of Elastomer Materials and Products2

Page: Kosm. teh. Raket. vooruž. 2018 (2); 132-138

DOI: https://doi.org/10.33136/stma2018.02.132

Language: Russian

Annotation: The problem is defined of designing the space rocket low-pressure air thermostating systems joints. The basic requirements imposed to the joints from the side of space rocket and ground complex are determined and stated. For this purpose, the analysis of operating conditions and possible situations during rocket launches is made. Besides, the methodological principles based on problematic, systematic, and structuralfunctional approach were applied using the theoretical and empirical capabilities, attraction of general scientific and special investigation methods, as well as historical and logical methods. The list of topical issues is reflected for implementation in joint’s design. The ways are proposed to create the joints meeting the requirements imposed. As a result, it was ascertained that the joints can be made of simpler and at the same time failure-free design in the form of combined triune rubber hose fitted with a metal fixation/release unit installed on a sealing flange in a special groove. Of special note is the versatility of the proposed technical solution for use in any of the space launch systems known in the world’s practice. The article is concluded with following: the basic requirements have been formulated for ground complexes thermostating systems joints to ensure space rockets prelaunch processing and launch, in doing so, the topical problems were defined; the scientific principles were proposed to design the thermostating systems joints for comprehensive solution of the topical problems , including potential critical situations; the thermostating systems joints have been developed, manufactured and have successfully passed the ground development tests with simulation of the conditions maximally close to operating ones at static operating air pressures and in off-nominal situations.

Key words: planetary roving vehicle, self-propelled modular platform, generic module, interchangeability

Bibliography:
1. Bigun S. A., Khorolsky M. S et al. Types and Design Features of Thermostating System Mating Points of Launch Vehicle Payload Units and Launch Vehicle and Spacecraft Bays. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2013. Issue 1. 123 p.
2. Bigun S. A., Khorolsky M. S et al. Experimental Investigations of Cyclone-4 ILV Thermostating System Mating Points Test Results. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2016. Issue 2. 105 p.

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Rubber as an advanced structural material for thermal conditioning system interfaces
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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.
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8. Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head

ISSN: 2617-5525

e-ISSN: 2617-5533

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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The effect of the acoustoelastic interaction in forming the acoustic loads under the fairing of the rocket head
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Збірник науково-технічних статей


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Збірник науково-технічних статей


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