Search Results for “space launcher” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Wed, 25 Mar 2026 20:11:30 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “space launcher” – 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
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. Thirdly, it helps to increase the payload capabilities of space launchers lifting from launch sites closer to the equator. 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. Key words: sea launch , sea-based space launch site , space launcher , fl oating launch platform Bibliography: 1. sea launch , sea-based space launch site , space launcher , fl oating launch platform .
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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.
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14. WST-24R Retractable Thruster. Buklet firmy Wärtsilä Corporation. 2017. 2 s.

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]]> 5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep https://journal.yuzhnoye.com/content_2020_1-en/annot_5_1_2020-en/ Wed, 13 Sep 2023 06:15:53 +0000 https://journal.yuzhnoye.com/?page_id=31026
Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep ISSN: 2617-5525 e-ISSN: 2617-5533 Authors: Hudramovych V. The problems of determining the lifetime of space launch vehicles and launching facilities should be noted separately, as it is connected with damages that arise at alternating-sign thermomechanical loads of high intensity. Development of the normative framework methodology for justifying the launcher structures resource of launch vehicles. Aerospace Sci. (2020) "Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep" Космическая техника.
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5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Hudramovych V. S.2, Sirenko V. M.1, Klimenko D. V.1, Hart Ye. L.3

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2; Oles Honchar Dnipro National University, Dnipro, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2020, (1); 44-56

DOI: https://doi.org/10.33136/stma2020.01.044

Language: Russian

Annotation: The shell structures widely used in space rocket hardware feature, along with decided advantage in the form of optimal combination of mass and strength, inhomogeneities of different nature: structural (different thicknesses, availability of reinforcements, cuts-holes et al.) and technological (presence of defects arising in manufacturing process or during storage, transportation and unforseen thermomechanical effects). The above factors are concentrators of stress and strain state and can lead to early destruction of structural elements. Their different parts are deformed according to their program and are characterized by different levels of stress and strain state. Taking into consideration plasticity and creeping of material, to determine stress and strain state, the approach is effective where the calculation is divided into phases; in each phase the parameters are entered that characterize the deformations of plasticity and creeping: additional loads in the equations of equilibrium or in boundary conditions, additional deformations or variable parameters of elasticity (elasticity modulus and Poisson ratio). Then the schemes of successive approximations are constructed: in each phase, the problem of elasticity theory is solved with entering of the above parameters. The problems of determining the lifetime of space launch vehicles and launching facilities should be noted separately, as it is connected with damages that arise at alternating-sign thermomechanical loads of high intensity. The main approach in lifetime determination is one that is based on the theory of low-cycle and high-cycle fatigue. Plasticity and creeping of material are the fundamental factors in lifetime substantiation. The article deals with various aspects of solving the problem of strength and stability of space rocket objects with consideration for the impact of plasticity and creeping deformations.

Key words: shell structures, stress and strain state, structural and technological inhomogeneity, thermomechanical loads, low-cycle and high-cycle fatigue, lifetime

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]]> 3.2.2018 Possible Ways of Modernization of VEGA Launch Vehicle AVUM Stage Main Engine Assembly https://journal.yuzhnoye.com/content_2018_2-en/annot_3_2_2018-en/ Thu, 07 Sep 2023 08:42:19 +0000 https://journal.yuzhnoye.com/?page_id=30733
4th International Conference on Launcher Technology “Space Launcher Liquid Propulsion”.
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3. Possible Ways of Modernization of VEGA Launch Vehicle AVUM Stage Main Engine Assembly

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Prokopchuk O. O., Shulga V. A., Strelchenko E. V., Konokh V. I., Kovalenko A. M., Dibrivny O. V., Lapin O. V., Kukhta A. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 16-24

DOI: https://doi.org/10.33136/stma2018.02.016

Language: Russian

Annotation: The Ukrainian companies Yuzhnoye SDO and SE PA YMZ supply VG143 main engine assembly for Vega LV AVUM upper stage, which is a one-chamber LRE of 250 kg thrust with five ignitions in flight. By the present, 11 successful launches of Vega LV have been made. In the process of flight operation, there were no critical comments on engines operation. This LRE has a combination of attractive characteristics, such as high specific pulse, low mass, multiple ignitions in flight, high reliability confirmed by good results of flight test of the prototype engines. The reserve of this engine from the viewpoint of further modernization is far from being exhausted. Enhancing the capabilities of payload injection by launch vehicles into various orbits of artificial Earth satellites is the main task for the developers of ILV as a whole and for the developers of separate assemblies and systems, such as LRE being part of ILV. With consideration for the experience of prototype engines testing, we should note the following ways of main engine assembly modernization: – increasing the specific pulse due to the increase of nozzle expansion ratio; – decreasing the volume of internal manifolds and mass of chamber; – increasing the operation time; – increasing the ignitions number; – increasing the duration of pauses between ignitions and orbital functioning time. Increasing the thrust and specific pulse of Vega LV VG143 main engine assembly and AVUM stage takes place due to the use of pneumopump propellant feeding system instead of standard pressure feeding. Besides, the information is presented on RD859, RD864, RD866 and RD869 prototype engines, the data on their basic characteristics, testing and operation. The below information is of interest to LRE and LV developers.

Key words: main engine assembly, liquid rocket engine, ways of modernization, engine chamber

Bibliography:
1. Shnyakin V., Shul’ga V., Zhivotov A., Dibrivny A. Creating a new generation of space-craft liquid rocket engines basing on pneumopump propellant supply systems. Space Propulsion: International Conference. France, Bordeaux. 2012.
2. Shul’ga V. Development status and improvement methods for upper stage engines of Vega and Cyclone launch vehicles. Space Propulsion; International Conference. Germany, Cologne. 2014.
3. De Rose L., Parmigiani P., Shnyakin V., Shulga V., Pereverzyev V., Caramelli F. Main engine of the Vega fourth stage: characteristics and heritage. 4th International Conference on Launcher Technology “Space Launcher Liquid Propulsion”. Netherlands, Noordwijk. 2018.
4. Kovalenko A. N., Pereverzev V. G., Marchan R. A., Blishun Y. V. Experimental Confirmation of Feasibility of Improving Power-Mass Characteristics of LRE for Vega Launch Vehicle Upper Stage: Paper presentation at the International Scientific-Technical Conference. S. P. Korolev SGAU, 2014.

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]]> 20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments https://journal.yuzhnoye.com/content_2017_2/annot_20_2_2017-en/ Wed, 09 Aug 2023 12:26:27 +0000 https://journal.yuzhnoye.com/?page_id=29866
Use of Polymer Composite Materials in Space Rockets as Reserve of Increasing their Mass and Functional Effectiveness. Aerospace Engineering and Technology. Analysis of Nomenclature of Type Composite Units of Space Rockets and Structural Schemes Applied for them / A. Zhukovsky Aerospace University “KhAI”. Aerospace Engineering and Technology. Methodology of Developing Effective Design and Technological Solutions of Space Rocketry Composite Units: Monography in 2 volumes. Basic parameters’ optimization concept for composite nose fairings of launchers / V.
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20. Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments

ISSN: 2617-5525

e-ISSN: 2617-5533

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:
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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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]]> 5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime https://journal.yuzhnoye.com/content_2019_1-en/annot_5_1_2019-en/ Thu, 25 May 2023 12:09:25 +0000 https://journal.yuzhnoye.com/?page_id=27710
In different countries they have their own characteristics, depending on the type and performance of the launch vehicles, infrastructure features (geography of the site, nomenclature of the space objects, development level of rocket and space technology), problems that are solved during launches, etc. Launch pad, consisting of the support frame, flue duct lining and embedded elements for frame mounting, is one of the principal components of the launcher and to a large extent defines the life of the launch site. Space Technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
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5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Hudramovych V. S.1, Sirenko V. M.2, Klimenko D. V.2, Daniyev Y. F.1, Hart Ye. L.3

Organization:

The Institute of Technical Mechanics, Dnipro, Ukraine1; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine2; Oles Honchar Dnipro National University, Dnipro, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2019, (1); 28-37

DOI: https://doi.org/10.33136/stma2019.01.028

Language: Russian

Annotation: This article contains results of methodology and standards development for life prediction of launch site structures to launch various types’ launch vehicles into near-earth orbit. Launch sites have been built in various countries of the world (European Union, India, China, Korea, Russia, USA, Ukraine, France, Japan, etc.). In different countries they have their own characteristics, depending on the type and performance of the launch vehicles, infrastructure features (geography of the site, nomenclature of the space objects, development level of rocket and space technology), problems that are solved during launches, etc. Solution of various issues, arising in the process of development of the standards for justification of launch site life is associated with the requirement to consider complex problems of strength and life of nonuniform structural elements of launch sites and structures of rocket and space technology. Launch sites are the combination of technologically and functionally interconnected mobile and fixed hardware, controls and facilities, designed to support and carry out all types of operations with integrated launch vehicles. Launch pad, consisting of the support frame, flue duct lining and embedded elements for frame mounting, is one of the principal components of the launcher and to a large extent defines the life of the launch site. Main achievements of Ukrainian scientists in the field of strength and life are specified, taking into account the specifics of various branches of technology. It is noted that the physical nonlinearity of the material and statistical approaches determine the strength analysis of useful life. Main methodological steps of launch site structures life prediction are defined. Service limit of launch site is suggested to be the critical time or the number of cycles (launches) over this period, after which the specified limiting states are achieved in the dangerous areas of the load-bearing elements: critical cracks, destruction, formation of unacceptable plastic deformations, buckling failure, corrosion propagation, etc. Classification of loads acting on the launch sites is given. The useful life of launch site is associated with estimation of the number of launches. Concept of low and multiple-cycle fatigue is used. Developing strength standards and useful life calculation basis, it is advisable to use modern methods of engineering diagnostics, in particular, holographic interferometry and acoustic emission, and to develop the high-speed circuits of numerical procedures for on-line calculations when testing the designed systems.

Key words: classification of loads and failures; shock wave, acoustic and thermal loads; low-cycle fatigue; hierarchical approach in classification; projection-iterative schemes of numerical procedur

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