Search Results for “liquid rocket engine nozzles” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Mon, 16 Mar 2026 14:20:35 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “liquid rocket engine nozzles” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 2.2.2025 Performance analysis and validation of a monopropellant air-detonation ramjet engine https://journal.yuzhnoye.com/content_2025_2-en/annot_2_2_2025-en/ Tue, 27 Jan 2026 08:06:29 +0000 https://journal.yuzhnoye.com/?page_id=35818
Development of a liquid-propellant rocket powered by a rotating detonation engine. Performance of a rotating detonation rocket engine with various convergent nozzles and chamber lengths.
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2. Performance analysis and validation of a monopropellant air-detonation ramjet engine

Date of receipt of the article for publication: 15.10.2025

Date of acceptance of the article for publication after review: 29.10.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Stoliarchuk V. V., Tertyshnyk S. V.

ORCID authors:

Stoliarchuk V. V. ORCID, Tertyshnyk S. V. ORCID

Organization:

Page: Kosm. teh. Raket. vooruž. 2025 (2); 12-23

DOI: https://doi.org/10.33136/stma2025.02.012

Language: English

Annotation: The increasing relevance of alternative propulsion systems necessitates an exploration of the potential of monopropellant detonation engines for compact and effi cient aerospace applications. This study aimed to investigate the operating parameters and performance characteristics of a direct-fl ow air-detonation propulsion system operating on environmentally friendly monopropellants. The research was based on a combination of experimental methods and numerical simulation using validated thermochemical models. It presents the results of a series of tests conducted with modifi ed engine geometries under varying inlet temperature and pressure conditions, focusing on achieving a stable detonation wave and analysing its propagation features. A detailed comparison between experimental pressure data and numerical predictions showed a deviation of less than 6.5 %, validating the reliability of the simulation model for practical applications. The infl uence of diff erent combustion chamber lengths and injector confi gurations was also assessed, revealing that geometric optimization plays a crucial role in maintaining detonation stability across diff erent temperature regimes. The study identifi ed critical fl ow parameters for successful ignition and detonation maintenance without external oxidizers, and highlighted the performance of two promising monopropellant compositions, including a modifi ed pronit-based propellant. The fi ndings contribute to optimizing heat release dynamics and pressure gain within the detonation chamber, off ering valuable insights into designing lightweight, energy-effi cient engines for future aerospace systems. The practical value of this research lies in the potential of applying its results in the design of advanced aerospace propulsion systems that feature compact size and environmental friendliness.

Key words: detonation combustion, wave stability, experimental simulation, thermal dynamics, geometric optimisation

Bibliography:

1. Zhang H., Jiang L., Liu W. D. & Liu S. J. Characteristic of rotating detonation wave in an H2/Air hollow chamber with Laval nozzle. International Journal of Hydrogen Energy. 2021. 46 (24). 13389–13401. https://doi.org/10.1016/j.ijhydene.2021.01.143
2. Xue S., Ying Z., Hu M., & Zhou C. Experimental study on the rotating detonation engine based on a gas mixture. Frontiers in Energy Research. 2023. 11. 1136156. https://doi.org/10.3389/fenrg.2023.1136156
3. Xue S., Ying Z., Ma H., & Zhou C. Experimental investigation on two-phase rotating detonation fueled by kerosene in a hollow directed combustor. Frontiers in Energy Research. 2022. 10, 951177. https://doi.org/10.3389/fenrg.2022.951177
4. Kawalec M., Wolanski P., Perkowski W., & Bilar A. Development of a liquid-propellant rocket powered by a rotating detonation engine. Journal of Propulsion and Power. 2023. 39(4). 554–561. https://doi.org/10.2514/1.B38771
5. Zolotko O. Y., Zolotko O. V., Aksyonov O. S., Stoliarchuk V. V., & Cherniavskyi O. S. Analysis of the characteristics of the ejector regime of the impulse-detonation engine of the combined cycle of acceleration. Aerospace technic and technology. 2024. 6 (200). 52–59. https://doi.org/10.32620/aktt.2024.6.05
6. Camacho, R. G., & Huang, C. Component-based reduced order modelling of two-dimensional rotating detonation engine with non-uniform injection. AIAA SCITECH 2025 Forum.
https://doi.org/10.2514/6.2025-1397
7. Feng W., Zhang Q., Xiao Q., Meng H., Han X., Cao Q., Huang H., Wu B., Xu H., & Weng C. Effects of cavity length on operating characteristics of a ramjet rotating detonation enjine fueled by liquid kerosene. Fuel. 2023. 332. 126129. https://doi.org/10.1016/j.fuel.2022.126129
8. Bennewitz J. W., Bigler B. R., Ross M. C., Danczyk S. A., Hargus W. A. Jr. & Smith R. D. Performance of a rotating detonation rocket engine with various convergent nozzles and chamber lengths. Energies. 2021. 14(8). 2037. https://doi.org/10.3390/en14082037
9. Curran D., Wheatley V. & Smart M. High Mach number operation of accelerator scramjet engine. Journal of Spacecraft and Rockets. 2023. 60(3). https://doi.org/10.2514/1.A35511
10. Sun D., Dai Q., Chai W. S., Fang W. & Meng H. Experimental studies on parametric effects and reaction mechanisms in electrolytic decomposition and ignition of HAN solutions. ACS Omega. 2022. 7(22). 18521–18530. https://doi.org/10.1021/acsomega.2c01183
11. Stoliarchuk V. V. Validation of efficiency enhancement methods for detonation jet engines. Aerospace technic and technology. 2024. 4(1). 82–88. https://doi.org/10.32620/aktt.2024.4sup1.12
12. Wang J., Liu Y., Huang W., Zhang Y. & Qiu H. Direct numerical simulation of inflow boundary-layer turbulence effects on cavity flame stabilisation in a model scramjet combustor. Aerospace Science and Technology. 2025. 165. 110463. https://doi.org/10.1016/j.ast.2025.110463
13. Li W., Oh H. & Ladeinde F. Comparison of flamelet and transported species-based modeling of rotating detonation engines. AIAA SCITECH 2024 Forum. https://doi.org/10.2514/6.2024-2599.
14. Chen Y., Liu S., Peng H., Zhong S., Zhang H., Yuan X., Fan W. & Liu W. Propagation and heat release characteristics of rotating detonation in a ramjet engine with a divergent combustor. Physics of Fluids, 2025 37(2), 026132. https://doi.org/10.1063/5.0254419
15. Kailasanath K. Review of propulsion applications of detonation waves. AIAA Journal. 2000. 38(9). 1698–1708. https://doi.org/ 10.2514/2.1156
16. Heiser W. H., & Pratt D. T. Thermodynamic cycle analysis of pulse detonation engines. Journal of Propulsion and Power. 2002. 18(1), 68–76. https://doi.org/10.2514/2.5899
17. Munipalli R., Shankar V., Wilson D. R., Kim H., Lu F. K. & Liston G. Performance assessment of ejector-augmented pulsed detonation rockets. In 39th Aerospace Sciences Meeting and Exhibit (Paper 2001-0830). Reno: AIAA. https://doi.org/10.2514/6.2001-830
18. Lu F. K. & Braun E. M. Rotating detonation wave propulsion: Experimental challenges, modeling, and engine concepts. Journal of Propulsion and Power. 2014. 30(5). 1125–1142. https://doi.org/10.2514/1.B34802
19. Armbruster W. et al. Design and testing of a hydrogen–oxygen pre-detonator for RDEs. CEAS Space Journal. 2025. 17. 969-979.
https://doi.org/10.1007/s12567-025-00605-y

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]]> 16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations https://journal.yuzhnoye.com/content_2020_1-en/annot_16_1_2020-en/ Wed, 13 Sep 2023 11:18:27 +0000 https://journal.yuzhnoye.com/?page_id=31052
The presented work contains simulation of liquid rocket engine combustion products jet flowing into the gas duct at the rocket lift-off, taking into account the following input data: the parameters of propulsion system, geometric parameters of launch complex elements, propulsion systems nozzles and gas duct.
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16. Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Furkalo S. A., Stelmakh K. L., Lazarev T. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 149-154

DOI: https://doi.org/10.33136/stma2020.01.149

Language: Russian

Annotation: Launch vehicle lift-off is one of the most critical phases of the whole mission requiring special technical solutions to ensure trouble-free and reliable launch. A source of increased risk is the intense thermal and pressure impact of rocket propulsion jet on launch complex elements and on rocket itself. The most accurate parameters of this impact can be obtained during bench tests, which are necessary to confirm the operability of the structure, as well as to clarify the parameters and configuration of the equipment and systems of complex. However, full-scale testing is expensive and significantly increases the development time of the complex. Therefore, a numerical simulation of processes is quite helpful in the design of launch complexes. The presented work contains simulation of liquid rocket engine combustion products jet flowing into the gas duct at the rocket lift-off, taking into account the following input data: the parameters of propulsion system, geometric parameters of launch complex elements, propulsion systems nozzles and gas duct. A three-dimensional geometric model of the launch complex, including rocket and gasduct, was constructed. The thermodynamic parameters of gas in the engine nozzle were verified using NASA CEA code and ANSYS Fluent. When simulating a multicomponent jet, the equations of conservation of mass, energy, and motion were solved taking into account chemical kinetics. The three-dimensional problem was solved in ANSYS Fluent in steady-state approach, using Pressure-based solver and RANS k-omega SST turbulence model. The calculation results are the gas-dynamic and thermodynamic parameters of jets, as well as distribution of gas-dynamic parameters at nozzle exit, in flow and in boundary layer at gas duct surface. The methodology applied in this work makes it possible to qualitatively evaluate the gas-dynamic effect of combustion products jets on gas duct for subsequent optimization of its design.

Key words: liquid rocket engine, combustion products, multicomponent flow, ANSYS Fluent

Bibliography:
1. Bonnie J. McBride, Sanford Gordon. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications. II. Users Manual and Program Descriptions: NASA Reference Publication 1311. 1996.
2. Ten-See Wang. Thermophysics Characterization of Kerosene Combustion. Journal of Thermophysics and Heat Transfer. 2001. № 2, Vol. 15. P. 140–147. https://doi.org/10.2514/2.6602
3. Maas U., Warnatz J. Ignition Processes in Carbon-Monoxide-Hydrogen-Oxygen Mixtures: Twenty-Second Symposium (International) on Combustion. The Combustion Institute, 1988. P. 1695–1704. https://doi.org/10.1016/S0082-0784(89)80182-1
4. Timoshenko V. I. Teoreticheskiie osnovy tekhnicheskoj gazovoj dinamiki. Kiev, 2013. S. 154–155.

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]]> 8.2.2018 Development of Nozzle Blocks New Manufacturing Technology without Blazing https://journal.yuzhnoye.com/content_2018_2-en/annot_8_2_2018-en/ Thu, 07 Sep 2023 11:21:51 +0000 https://journal.yuzhnoye.com/?page_id=30757
Key words: liquid rocket engine nozzles , laser , laser welding , laser surfacing Bibliography: Full text (PDF) || liquid rocket engine nozzles , laser , laser welding , laser surfacing .
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8. Development of Nozzle Blocks New Manufacturing Technology without Blazing

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Kovalenko A. M.1, Kirsanov D. V.1, Mirosidi M. A.1, Shelyagin V. D.2, Bernatsky A. V.2, Siora O. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; STC «Paton Welding Institute», Kiev, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2018 (2); 68-75

DOI: https://doi.org/10.33136/stma2018.02.068

Language: Russian

Annotation: The article describes the problems of manufacturing large-size nozzle blocks by classical for Ukrainian space industry method of high-temperature brazing. The Yuzhnoye SDO-selected way of solving this problem and the first strides on the way to organization of new production using innovative technologies of laser welding and surfacing are presented. The step-by-step sequence and procedure of research work to develop and test a new technology of cooled nozzle block manufacturing are described. Four phases are identified, out of which the first two phases have already been successfully performed. The laser welding and surfacing technology will allow avoiding the use of costly and unique equipment and will allow reducing and optimizing the technological manufacturing cycle rejecting the long –term and energy-consuming technological operations. The scientific-and-technological works performed showed the principle feasibility of making connection between the external jacket and internal wall of a nozzle block using laser welding. The test samples manufactured confirmed the high strength characteristics, which had been preliminary obtained by the theoretical calculation methods. The sections obtained by surfacing demonstrate good metallurgical connection between the layers. On the test samples, the technique was tried-out allowing repairing defect areas in a welded seam obtained by laser welding method. This is especially important from the technological and economic viewpoints, as the technology of high-temperature brazing applied currently does not allow making guaranteed repair of brazed joints.

Key words: liquid rocket engine nozzles, laser, laser welding, laser surfacing

Bibliography:

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New Technologies and Problems of Their Introducing in Ukraine
A. N. Kovalenko, A. A. Prokopchuk, I. L. Snegiryov (2019)
Mathematical Model and Solution Algorithm for Virtual Localization Problem
Sergiy Plankovskyy, Yevgen Tsegelnyk, Oleksandr Pankratov, Tetyana Romanova, Serhiy Maximov (2022)
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]]> 5.2.2018 Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office https://journal.yuzhnoye.com/content_2018_2-en/annot_5_2_2018-en/ Thu, 07 Sep 2023 11:01:49 +0000 https://journal.yuzhnoye.com/?page_id=30749
Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office ISSN: 2617-5525 e-ISSN: 2617-5533 Authors: Konokh V. The present-day spacecraft gas-jet orientation and stabilization systems use as propulsion devices the electromagnetic valves with nozzles whose thrust is, as a rule, not more than 30 N and the working medium pressure is up to 24 MPa. Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office. Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office. Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office. (2018) Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office, Космическая техника. "Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office." Космическая техника. Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office.
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5. Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Konokh V. I., Boiko V. S., Troyak A. B., Ivashura A. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 34-48

DOI: https://doi.org/10.33136/stma2018.02.034

Language: Russian

Annotation: In the pneumohydraulic systems of liquid rocket engines and propulsion systems, electromagnetic valves that allow making the pneumohydraulic systems more simple and ensuring multiple ignition of liquid rocket engines have found wide application. The Yuzhnoye-developed electromagnetic valves are designed according to two schemes – of direct and indirect action. In the direct-action electromagnetic valves, the shutting-off device opens (closes) the throat with the force developed by electric magnet. They have gained acceptance in the pneumohydraulic systems with the working medium pressure of ~8.5 MPa, they are of simple design and have high operating speed (0.001…0.05 s). In the electromagnetic valves with amplification, the electromagnet armature is connected with control valve and the main shutting-off device moves due to the force from working medium pressure drop on it. They are used in the operating pressure range of 0.5…56 MPa, at that, the action time is 0.025…0.15 s. For the European Vega launch vehicle fourth stage main engine assembly that has pressure propellant feeding system, the electrohydraulic valve with amplification and drainage was developed. The dependence of this electrohydraulic valve high speed from the line’s output length is decreased to the maximum due to the installation of Venturi nozzle at the output connecting branch. This electrohydraulic valve is operable at the pressure below 8 MPa, the action time is 0.08…0.12 s. The present-day spacecraft gas-jet orientation and stabilization systems use as propulsion devices the electromagnetic valves with nozzles whose thrust is, as a rule, not more than 30 N and the working medium pressure is up to 24 MPa. Yuzhnoye State Design Office developed for 15B36 gas-jet system the electropneumatic valve with amplification and nozzle, which is operable at the pressure below 45 MPa, ensures the action frequency of up to 10 Hz and is capable of creating the thrust of 100 N on gaseous argon. To solve the task of decreasing the dependence of operability and high speed of electromagnetic valves with drainage and amplification on geometry of lines in which a valve is installed, the electropneumatic valve was developed that has spool elements ensuring reliable and quick action with long input lines of 0.004 m diameter. Its mass is 2…2.5 times lower than the mass of analogs. Recently, Yuzhnoye State Design Office develops the apogee RD840 LRE with 400 N thrust, for the conditions of which the direct-action electrohydraulic valve was developed and tested with the following characteristics: pressure – up to 2.15 MPa, consumed power in operation mode – less than 7.1 W, action time – not more than 0.02 s, mass – 0.19 kg. The presented electromagnetic valves by their technical and operational characteristics meet the highest world requirements and have found wide utility in liquid rocket engines and propulsion systems.

Key words: electrohydraulic valve, electropneumatic valve, pneumohydraulic system, direct-action electric valve, electric valve with amplification, action time

Bibliography:
1. Electric Hydraulic Valve: Patent 89948 Ukraine: MPK F 16K 32/02 / Shnyakin V. M., Konokh V. I., Kotrekhov B. I., Troyak A. B., Boiko V. S.; Applicant and patent holder Yuzhnoye State Design Office. а 2006 02543; claimed 09.03.2006; published 25.03.2010, Bulletin No. 6.
2. Boiko V. S., Konokh V. I. Stabilization of Opening Time of Electric Hydraulic Valve with Boost in Liquid Rocket Engine Hydraulic System. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works. 2015. Issue 4 (84). P. 39-48.
3. Electric Valve: Patent 97841, Ukraine: MPK F 16K 32/02 / Shnyakin V. M., Konokh V. I., Kotrekhov B. I., Troyak A. B., Boiko V. S., Ivashura A. V.; Applicant and patent holder Yuzhnoye State Design Office. а 2009 12002; claimed 23.11.2009; published 26.03.2012, Bulletin No. 6.
4. Boiko V. S., Konokh V. I. Increase of Action Stability of Electric Pneumatic Valve with Boost in the System with Increased Inlet Hydraulic Resistance. Aerospace Engineering and Technology: Scientific-Technical Journal. 2013. Issue 3 (100). P. 90-95.
5. Flying Vehicles Pneumatic Systems Units / Lyaskovsky I. F., Shishkov A. I., Romanenko N. T., Romanenko M. T., Chernov M. T., Yemel’yanov V. V. / Under the editorship of N. T. Romanenko. М., 1976. 176 p.

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Development of improved performance electromagnetic valve for liquid rocket engine
А. А. Иголкин, T. A. Chubenko, A. D. Maksimov (2020)
1 citations in OpenCitations database (as of 22.03.2026 23:47)
Works that cite this article in OpenCitations:
Development of improved performance electromagnetic valve for liquid rocket engine
A. A. Igolkin, T. A. Chubenko, A. D. Maksimov (2020)
1 citations in Crossref database (as of 20.03.2026 02:11)
0 citations in Google Scholar database (as of 23.03.2026 05:11)
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