Search Results for “experimental simulation” – Collected book of scientific-technical articles

2.2.2025 Performance analysis and validation of a monopropellant air-detonation ramjet engine

manager — Tue, 27 Jan 2026 08:06:29 +0000

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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1.2.2025 Methods for structural strength investigations of rocketry.

manager — Tue, 27 Jan 2026 01:13:55 +0000

1. Methods for structural strength investigations of rocketry.

Date of receipt of the article for publication: 31.10.2025

Date of acceptance of the article for publication after review: 14.11.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Drobenko B. D.¹, Klymenko D. V.¹, Kushnir R. M.¹, Marchuk M. V.¹, Sirenko V. M.², Kharchenko V. M.²

ORCID authors:

Drobenko B. D.¹ ORCID, Klymenko D. V.¹ ORCID, Kushnir R. M.¹ ORCID, Marchuk M. V.¹ ORCID, Sirenko V. M.² ORCID, Kharchenko V. M.² ORCID

Organization:

Ya. S. Pidstryhach Institute for Applied Problems of Mechanics and Mathematics of the National Academy of Sciences of Ukraine¹, Yangel Yuzhnoye State Design Office²

Page: Kosm. teh. Raket. vooruž. 2025 (1); 3-11

DOI: https://doi.org/10.33136/stma2025.02.003

Language: Ukrainian

Annotation: The paper proposes a method for investigating structural strength and determining structural failure loads by computer-aided simulation and nondestructive testing. The methodology is grounded on general ratios of elastoplasticity in increments based on the Lagrangian approach and the principle of virtual translations, taking into account the geometrically nonlinear nature of structural deformation under intense loading. The baseline technique for numerical simulation was the fi nite element method. The methodology for structural strength investigation includes three steps. The fi rst step involves studying the structure in the form of a spatially two-dimensional shell-like model. An analysis of the calculated values of the model’s stress and strain is performed based on the results of the computational experiment, and the critical regions within the structure are determined, where these parameters reach their peak values. The second step yields detailed three-dimensional models of those critical regions within the structure. These models incorporate the geometrical (including the actual thicknesses of the elements) and physical specifi cs of the structure. The results of numerical experiments are applied in an analysis of the refi ned stress and strain values of the three-dimensional models, and the minimum structural failure load is determined. In the third step, strain gauges are installed in the determined critical regions, and the structure’s strength is tested using a nondestructive load. A predicted structural failure load is found by comparing the strain and translation values obtained from the test results with the outputs of computational experiments. The development of the mentioned methodology encompassed an investigation of stress and strain at diff erent internal pressures for an oxidizer tank of a launch vehicle’s fi rst stage, a quantitative estimation of the tank’s strength, and the determination of the structural failure load and regions where a structural failure is likely to start. This paper demonstrates that the results of a tank strength analysis using a criterion of a maximum stress are closest to experimental data.

Key words: strength, fi nite element method, computational experiment, strength testing

Bibliography:

1. Allen D.H., Heisler W. E. A theory for analysis of thermoplastic materials. Computers & Structures. 1981. Vol. 13. P. 129-135 https://doi.org/10.1016/0045-7949(81)90117-6
2. Bathe K.J. Finite Element Procedures Analysis. Englewood Cliffs: Prentice Hall, 1995. 1037 p.
3. Zienkiewicz O.C., Taylor R.L. Finite Element Method: Vol.1. The Basis. London: Butterworth Heinemann, 2000. 689 p.
4. Hachkevich O.P., Drobenko B.D. Modeliuvannia ta optymizatsiia v termomekhanitsi elektroprovidnykh neodnoridnykh til. Pid zah. red. Ya. Y. Buraka, R.M. Kushnira. T. 4: Termomekhanika namahnechuvanykh elektroprovidnykh termochutlyvykh til. Lviv: SPOLOM, 2010.256 s.
5. Kleiber M. Incremental Finite Element Modelling in Non-Linear Solid Mechanics. John Wiley & Sons, 1989. 187 p.
6. Computational Methods for Nonlinear Problems. Ed. by Taylor C., Owen D. R. J., Hinton E. Swansea: Pineridge Press, 1987. 384 p.
7. Marchuk M.V. Neliniine deformuvannia podatlyvykh transversalnym deformatsiiam zsuvu ta stysnennia plastyn i obolonok. Mashynoznavstvo. 2005. № 10. S. 9-14.

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3.1.2025 Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks

manager — Wed, 27 Aug 2025 12:40:38 +0000

3. Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks

ISSN: 2617-5525

e-ISSN: 2617-5533

Автори: Shulha V. A., Pidhainyi A. I., Mudrov D. S.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2025 (1); 19-27

DOI: https://doi.org/10.33136/stma2025.01.019

Language: Ukrainian

Annotation: This paper presents the results of comprehensive research on the operational performance of diaphragm separators utilized in the fuel storage and supply systems for liquid-propellant rocket engines (LPRE). The relevance of this study arises from the need to ensure the reliable separation of gas and liquid duringthe operation of aerospace systems under diff erent conditions. In this context, special attention is given to autonomous bench tests that enable the evaluation of the key performance parameters of diaphragms before integrating them into production models. The paper examines the shape transformation of spherical diaphragms under external loads, presents an analytical calculation of the initial diaphragm inversion radius, and identifi es the critical pressures that cause buckling. The results of this calculation demonstrate a satisfactory correlation with the experimental data obtained during testing. The methodology for qualifi cation tests conducted on fi ve diff erent diaphragm variants is described. Several technological and design measures have been implemented to enhance product quality. They included increasing the number of drawing passes from two to three with intermediate annealing, reducing the thickness of the blanks, and enlarging the non-rolled polar zone. It was found that the primary factor ensuring defect-free diaphragm inversion is the reduced number of roller passings along the diaphragm contour, which prevents the tearing of the surface layer. The test results for diff erent diaphragm variants confi rmed satisfactory performance. An analysis of pressure diff erentials across the diaphragms during inversion confi rmed compliance with the technical specifi cations. The study concluded that the diaphragm design, when it incorporates all corrective measures, ensures defect-free inversion while maintaining the required pressure diff erential and is recommended for further testing as part of standard tank assemblies.

Key words: Strength parameters; aircraft, space and rocket technologies; design parameters; mathematical simulation; fuel tank; separation diafragm; autonomous bench testing; critical pressure

Bibliography:

1. Ballinger I. A., Lay W. D., Tam W. H. Review and History of PSI Elastomeric Diaphragm Tanks. 31st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 10-12
July 1995, San Diego, CA, USA. DOI: https://doi.org/10.2514/6.1995-2534.

2. Hartwig J. W. A detailed historical review of propellant management devices for low gravity propellant acquisition. 52nd AIAA/SAE/ASEE Joint Propulsion Conference,
25-27 July 2016, Salt Lake City, USA. Reston: American Institute of Aeronautics and Astronautics. DOI: https://doi.org/10.2514/6.2016-4772.

3. Lenahen B., Gangadharan S., Desai M. A Computational and Experimental Analysis of Spacecraft Propellant Tanks Implemented with Flexible Diaphragms. Proceedings of
the 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Boston, Massachusetts, USA: American Institute of Aeronautics and
Astronautics. DOI: https://doi.org/10.2514/6.2013-1886.

4. Sabaghzadeh H., Shafaee M. Reversal modeling and optimal design of hyper-elastic diaphragm in space fuel tanks. SN Applied Sciences. 2021. Vol. 3, Article number:
792. DOI: https://doi.org/10.1007/s42452-021-04785-0

5. Conomos H. A., Alongi C. G., Moore J., Yager J., Goddard R., Salzler T., Fetes J., Burch K. Development of 10 inch Diameter Titanium Rolling Metal Diaphragm Tank
for Green Propellant. AIAA Propellant Storage and Management II. DOI: https://doi.org/10.2514/6.2017-4915.

6. Jøraholmen T., Korsvold S., Sandvold P., Luktvasslimo Ø., Snilsberg K. E.
Roadmap towards a qualified aluminium green propellant diaphragm tank. Aerospace Europe Conference 2023 – 10ᵀᴴ EUCASS – 9ᵀᴴ CEAS, 9-13 July 2023, Lausanne, Switzerland.
Lausanne: EUCASS. DOI: https://doi.org/10.13009/EUCASS2023-093.

7. Shen Y. A computational analysis of reversal behaviors of a spacecraft propellant management device. International Conference Optoelectronic Information and Optical
Engineering (OIOE 2024), 2024, Wuhan, China. Bellingham: SPIE, 2025. (Proceedings of SPIE; Vol. 13513). DOI: https://doi.org/10.1117/12.3045569.

8. Windisch M., Beck R. Numerical Simulation and Optimisation of a Hemisсherical Metallic Membrane Designed for Positive Expulsion of a Propellant Tank (for
Replacement of Conventional PMD). Spacecraft Structures, Materials and Mechanical Testing: Proceedings of a European Conference, 4-6 November 1998, Braunschweig,
Germany. Paris: European Space Agency (ESA), 1999. Vol. 428. P. 45. ISBN 9290927127.

9. Mudrov D.S., Zil V.V. Doslidzhennia napruzheno-deformovanoho stanu vytysknykh diafrahm. Heotekhnichna mekhanika: zb. nauk. prats. / In-t heotekh. mekh. im. M.S.
Poliakova NAN Ukrainy. Dnipro, 2016. Vyp. 131. S. 173-182.

10. Mozharovskii M.S. Teoriia pruzhnosti, plastychnosti i povzuchosti: pidruchnyk / M.S. Mozharovskyi. K. : Vyshcha shkola, 2002. 308 s.

11. Libai A., Simmonds J.G. The Nonlinear Theory of Elastic Shells. 2nd ed. Cambridge: Cambridge University Press, 1998. 564 p. ISBN 978-0-521-01976-7.

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4.1.2024 The dynamics of servo drives

Дмитрий Макренко — Wed, 12 Jun 2024 16:08:46 +0000

4. The dynamics of servo drives

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Degtiarov М. O., Karpenko V. Y., Kozak L. R.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 29-39

DOI: https://doi.org/10.33136/stma2024.01.029

Language: Ukrainian

Annotation: The article gives the analysis results for the servo drives dynamics, obtained from the theoretical calculations and during the development testing of the high power electric drives. Theoretical research was conducted, using the complete mathematical model of the servo drive, which included the equations of the control signal shaping path, electric motor, reducer and load. The equations of the control signal shaping network include only the characteristics of the compensating element in the assumption that all other delays in the transformation path are minimized. The electric motor equations are assumed in the classical form, taking into account the influence of the following main parameters on the motor dynamics: inductance and stator winding resistance, torque and armature reaction coefficients and rotor moment of inertia. Interaction of the motor with the multimass system of the reducer and load is presented in the form of force interaction of two masses – a reduced mass of the rotor and mass of the load through the certain equivalent rigidity of the kinematic chain. To describe the effect of gap in the kinematic connection the special computational trick, which considerably simplifies its mathematical description, is used. Efficiency of the reducer is presented in the form of the internal friction, proportional to the transmitted force. Calculation results with the application of the given mathematical model match well with the results of the full-scale testing of different specimens of servo drives, which makes it possible to use it for the development of new servomechanisms, as well as for the correct flight simulation when testing the aircraft control systems. In particular, based on the frequency response calculations of the closed circuit with the application of the given mathematical model, it is possible to define optimal parameters of the correcting circuit. Reaction on the step action with the various values of circular amplification coefficient in the circuit gives complete information on the stability regions of the closed circuit and influence of various drive parameters on these regions. Based on the conducted theoretical and experimental studies, the basic conclusions and recommendations were obtained and presented, accounting and implementation of which will provide high dynamic characteristics of the newly designed servo drives.

Key words: electric drive, servo drive, reducer, stability, mathematical model.

Bibliography:

Kozak L. Dynamika servomechanismov raketnoy techniki. Inzhenernye metody issledovaniya. Izd-vo LAP LAMBERT Academic Publiching, Germania. 2022.
Kozak L. R., Shakhov M. I. Matematicheskie modely hydravlicheskikh servomekhanismov raketno-kosmicheskoy techniki. Kosmicheskaya technika. Raketnoe vooruzhenie. 2019. Vyp. 1.

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9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

manager — Tue, 03 Oct 2023 11:48:27 +0000

9. Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Sirenko V. M., Zhivotov O. Yu.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 63-70

DOI: https://doi.org/10.33136/stma2019.02.063

Language: Russian

Annotation: A promising experimental bench – a shock wind tunnel was put into operation at Yuzhnoye SDO. The shock wind tunnel is designed to simulate the incident flow during rocket flight at high supersonic and hypersonic velocities. To solve actual design problems facing Yuzhnoye SDO, it was necessary to expand the range of velocities under investigation in a shock wind tunnel by low supersonic Mach numbers (Mа=1.5; 2; 3). As a result of this work, a modernized configuration of the shock wind tunnel was developed, which allows simulating flow parameters at low supersonic velocities. The results of aerodynamic experiment performed in the modernized shock wind tunnel, which are close to full scale ones, can be obtained using as much data on peculiarities of supersonic flow formation in it as possible. Therefore, the study of the distribution of Mach numbers profiles in the working section of the modernized shock wind tunnel at low and high supersonic velocity was chosen as the main line of research. The results of the research presented in the article are based on the use of numerical simulation methods, as well as data obtained experimentally. As a result of gasdynamic simulation of a supersonic flow conducted for the nozzle Mа=4 and the nozzle Mа=2, the calculated and experimental data on the distribution pattern and field values of Mach numbers in the working section of the tunnel were obtained. A comparative analysis was carried out. The boundaries of the region of equal velocities, within which the condition of quasistatic supersonic flow is satisfied, and the lifetime of the operating mode for the selected nozzle type were determined. At the flow from the nozzle Mа=2, a peculiarity was revealed in the distribution pattern of Mach numbers fields associated with the appearance of “blocking” effect of the supersonic flow. The methods for eliminating the effect of flow “blocking” at low supersonic velocities are proposed.

Key words: incident flow modeling, velocity fields in the wind tunnel working section, aerodynamic experiment

Bibliography:

1. Zvegintsev V. I. Gasodynamicheskie ustanovki kratkovremennogo deistviya. V dvuh chastyakh. Ch. 1. Ustanovki dlya nauchnykh issledovaniy. Novosibirsk, 2014. 551 s.

2. Computerno-vymiryuvalni tekhnologii kontrolu ta upravlinnya raketno-kosmichnoi techniki / monogr. pid zagal. red. prof. V. P. Malaichuka. Dnipro, 2018. 344 s.

3. «Sirius-18». Systema izmereniya i upravleniya impulsnoi aerodynamicheskoi truboi. Rukovodstvo po ekspluatatsii. ELVA4.044.901 RE. 2018. 45 s.

4. Abramovich G.N. Prikladnaya gazovaya dynamika. M., 1978. 888 s.

5. Raschet vnutrennego davlenia v otsekakh RN. YSF YZH UMN 041 01. Rukovodstvo operatora. 2016. 138 s.

6. Issledovania characteristic hyperzvukovoi aerodynamicheskoi truby AT-303. Ch. 1. Polya skorostey / A. M. Kharitonov at al. Teplophysika i aeromekhanika. 2006. T. 13, № 1. S. 1–17.

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17.1.2020 Acoustic problems of rocket launch

Вацлав Самусевич — Wed, 13 Sep 2023 11:36:44 +0000

17. Acoustic problems of rocket launch

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Hrinchenko V. T.

Organization:

Institute of Hydromechanics of National Academy of Sciences of Ukraine, Kyiv, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 155-159

DOI: https://doi.org/10.33136/stma2020.01.155

Language: Russian

Annotation: Due to an increase of power of rocket engines, the high intensity sound field generated by the exhaust jets have become an important factor, which determines the success rate of a rocket launch. Ensuring a successful launch of a rocket system became harder due to new engineering problems. Identification and definition of acoustic sources structure within a complex supersonic jet, being a one of the most important scientific problems, which have to be solved to find the ways to control accoustic radiation. A three components of acoustic sources can be defined here – broadband signals from large and small components of of turbulent jet and tonal signals which usually being overlooked during the estimation of overall sound pressure level. The paper considers various aspects of acoustics of the launch of rocket systems, which includes characteristics of acoustic sources in supersonic jets, possibilities and physical limitation factors, under which it is possible to control the sound radiation. Among the possible ways to control the process of sound generation by a jet, a method of water injection in a jet is being studied. While saving the general thrust of the engine this method can not greatly reduce the sound radiation by a jet. It is recommended to use big amounts of water-air mix to protect the launch pad from damage. Significant progress on the topic of understanding the process of sound generation by supersonic jets can be achieved via mathematical modeling of sound radiation. The latest achievements of mathematical modeling of sound generation by supersonic jets being presented.

Key words: Acoustics of rocket launch, acoustic efficiency of a jet, semi-empirical models of of jet acoustics, numeric-computational methods in aeroacoustics, control of jet-generated acoustic levels

Bibliography:

1. Lighthill M. J. On Sound Generated Aerodynamically: I. General Theory. Proc. Roy. Soc. London Ser. A, 211. 1952. Р. 564–581. https://doi.org/10.1098/rspa.1952.0060

2. Tam C. K. W. Jet noise. Theoretical Computftional Fluid Dynamics. 1998. No 10. Р. 393–405. https://doi.org/10.1007/s001620050072

3. Lubert C. P. Sixty years of launch vehicle acoustics. Proc.Mtgs.Acoust. Vol. 31. 2017. https://doi.org/10.1121/2.0000704

4. Ask the Astronaut: What does launch feel like? URL: https://www.airspacemag. com/ask-astronaut/ask-astronaut-what-does-launch-feel-what-thoughts-and-emotions-run-through-your-mind-180959920/

5. Tim P. Ask an Astronaut: My Guide to Life in Space. 2018. 272 p.

6. Saucer B. What’s the Deal with Rocket Vibration? MIT Technology Review. July 15, 2009. URL: https://www.technology-review.com/s/414364https:/whats-the-deal-with-rocket-vibrations/

7. Ross D. Mechanics of Underwater noise. 1976. 266 p.

8. Varnier J. Experimental study and simulation of rocket engine free jet noise. AIAA J. 2001. Vol. 39, Nо 10. P. 1851–1859. https://doi.org/10.2514/2.1199

9. Eldred K. M. Acoustic loads generated by the propulsion system. NASA SP-8072, 1971. 49 p.

10. Balakrishnan P., Srinivason K. Impinging get noise reduction using non-circular jets. Applied Acoustics. 2019. Vol. 143. Р. 19-30. https://doi.org/10.1016/j.apacoust.2018.08.016

11. Tsutsumi S. Acoustic generation mechanism of a supersonic jet impinging on deflectors / S. Tsutsumi, R. Takaki, Y. Nakanishi, K. Okamoto, S. Teramoto 52th AIAA Aerospace Sci. Meet. AIAA Pap. 2014-0882. 2014. 12 p. https://doi.org/10.2514/6.2014-0882

12. Ahuja K. K., Manes J. P., Massey K. C., Calloway A. B. An Evaluation of various concepts of Reducing Supersonic Jet Noise, AIAA-90-3982. AIAA 13th Aeroacoustic Conference, 1990. Р. 1-21. https://doi.org/10.2514/6.1990-3982

13. Krathapalli A., Lenkatakrishnan L., Elovarsan R., Laurenco L. Supersonic Jet Noise Suppression by Water Injection. AIAA 2000-2025. 6th AIAA/CEAS Aeroacoustic Conference, 2000. Р. 1-25.

14. Moratilla-Vega M. A., Lackhole K., Janicka J., Xia H., Page C. J. Jet Noise Analysis using an Efficient LES/ High-Order Acoustic Coupling Method. Computer and Fluid. 2020. https://doi.org/10.1016/j.compfluid.2020.104438

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10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

Вацлав Самусевич — Thu, 07 Sep 2023 11:29:45 +0000

10. Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Nikitenko K. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 83-93

DOI: https://doi.org/10.33136/stma2018.02.083

Language: Russian

Annotation: At Yuzhnoye State Design Office, the Cyclone-4 launch vehicle 3rd stage engine has been developed and is under testing. For adjustment of the engine and test bench systems, in the first firing tests the radiation-cooled nozzle extension was replaced with a steel water-cooled one. It was planned to start the engine with water-cooled nozzle extension without vacuumizing and without gad dynamic pipe, which conditioned operation with flow separation at the output edge of water-cooled nozzle extension. Therefore, the calculation of flow in the nozzle with water-cooled extension, flow separation place, and thermal load on watercooled nozzle extension during operation in ground conditions is an important task. Selection of turbulent flow model has a noticeable impact on prediction of flow characteristics. The gas dynamic analysis of the nozzle with water-cooled extension showed the importance of using the turbulent flow model k-ω SST for the flows with internal separation of boundary layer and with flow separation at nozzle section. The use the flow model k-ω SST for calculation of nozzle with flow separation or with internal transitional layer allows adequately describing the flow pattern, though, as the comparison with experimental data showed, this model predicts later flow separation from the wall than that obtained in the tests. The calculation allows obtaining a temperature profile of the wall and providing the recommendations for selection of pressure measurement place in the nozzle extension for the purpose of reducing sensors indication error. With consideration for the special nature of the nozzle extension wall temperature field, the cooling mode was selected. The tests of RD861K engine nozzle with water-cooled extension allow speaking about its successful use as a required element for testing engine start and operation in ground conditions without additional test bench equipment.

Key words: turbulent flow, flow separation, cooling, technological extension

Bibliography:

1. Massiet P., Rocheque E. Experimental Investigation of Exhaust Diffusors for Rocket Engines. Investigation of Liquid Rocket Engines. М., 1964. P. 96-109.

2. Mezhevov A. V., Skoromnov V. I., Kozlov A. V. et al. Introduction of Radiation Cooling Nozzle Head of Made of Carbon-Carbon Composite Material on DM-SL Upper Stage 11D58M Main Engine. News of Samara Aerospace University. No. 2 (10). 2006. P. 260-264.

3. Fluent. Software Package, Ver. 6.2.16, Fluent Inc., Lebanon, NH, 2004.

4. Wilcox D. C. Turbulence Modeling for CFD. DCW Industries, Inc. La Canada, California, 1998. 460 р.

5. Andersen D., Tannehill J., Platcher R. Computational Hydromechanics and Heat Exchange: in 2 volumes М., 1990. 384 p.

6. Rodriguez C. G., Culter, A. D. Numerical Analysis of the SCHOLAR Supersonic Combustor, NASA-CR-2003-212689. 2003. 36 р.

7. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952

8. Spalart P., Allmaras S. A one-equation turbulence model for aerodynamic flows: Technical Report. American Institute of Aero-nautics and Astronautics. AIAA-92-0439. 1992. Р. 5-21. https://doi.org/10.2514/6.1992-439

9. Launder B. E., Spalding D. B. Lectures in Mathematical Models of Turbulence. London, 1972. Р. 157-162.

10. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952

11. Ten-See Wang. Multidimensional Unstructured Grid Liquid Rocket-Engine Nozzle Performance and Heat Transfer Analysis. Journal of Propulsion and Power. Vol. 22. No. 1. 2006. 21 р. https://doi.org/10.2514/1.14699

12. Hyun Ko, Woong-Sup Yoon. Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle. Journal of Propulsion and Power. Vol. 18, No. 3. 2002. Р. 585-591. https://doi.org/10.2514/2.5972

13. Wilson E. A., Adler D., Bar-Yoseph P. Thrust-Vectoring Nozzle Performance Mode-ling. Journal of Propulsion and Power. Vol. 19, No. 1. 2003. Р. 39-47. https://doi.org/10.2514/2.6100

14. Gross A., Weiland C. Numerical Simulation of Hot Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 5. 2004. Р. 879-891. https://doi.org/10.2514/1.5001

15. Gross A., Weiland C. Numerical Simulation of Separated Cold Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 3. 2004. Р. 509-519. https://doi.org/10.2514/1.2714

16. Deck S., Guillen P. Numerical Simulation of Side Loads in an Ideal Truncated Nozzle. Journal of Propulsion and Power. Vol. 18, No. 2. 2002. Р. 261-269. https://doi.org/10.2514/2.5965

17. Östlund J., Damgaard T., Frey M. Side-Load Phenomena in Highly Overexpanded Rocket Nozzle. Journal of Propulsion and Power. Vol. 20, No. 4. 2004. Р. 695-704. https://doi.org/10.2514/1.3059

18. Goldberg U. C. Separated Flow Treatment with a New Turbulence Model. AIAA Journal. Vol. 24, No. 10. 1986. Р. 1711-1713. https://doi.org/10.2514/3.9509

19. Golovin V.S., Kolchugin B.A., Labuntsov D.A. Experimental Investigation of Heat Exchange and Critical Heat Loads at Water Boiling in Free Motion Conditions. 1963. Vol. 6, No 2. p. 3-7.

20. Mikheyev М. А., Mikheyeva I. M. Heat-Transfer Principles. 2nd edition stereotyped. М., 1977. 343 p.

21. Kutateladze S. S., Leontyev A. I. Heat-Mass Exchange and Friction in Turbulent Boundary Layer. М., 1972. 341 p.

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9.1.2017 Mathematical Simulation of Gas-Jet Control System Distributor for Launch Vehicles

Виктория Лемех — Tue, 27 Jun 2023 12:09:02 +0000

9. Mathematical Simulation of Gas-Jet Control System Distributor for Launch Vehicles

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Oliinyk V. P., Yelanskyi Yu. A., Kaluger L. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 59-66

Language: Russian

Annotation: The differential equations of the gas-jet control system two-stage hot gas distributor are considered.

Key words:

Bibliography:

1. Belyayev N. M., Uvarov E. I. Calculation and Designing of Spacecraft Reaction Control Systems. М., 1974. 200 p.

2. Volkov E. B., Golovkov L. T., Syritsin Т. А. Liquid Rocket Engines. М., 1970. 592 p.

3. Abramovich G. N. Applied Gas Dynamics. М., 1976. 888 p.

4. Mamontov M. A. Some Cases of Gas Flowing in Pipes, Heads and Flow Vessels. М., 1951. 469 p.

5. Gerz E. V., Kreinin G. V. Dynamics of Pneumatic Actuators of Automatic Machines. М., 1964. 233 p.

6. Flying Vehicle Control System Pneumatic Actuators / V. A. Chashhin, О. Т. Kamladze, А. B. Kondrat’yev et al. М., 1987. 248 p.

7. Simakov N. N. Experimental Confirmation of Early Critical Region on Single Sphere. Journal of Technical Physics. Vol. 80, Issue 7. 2010.

8. Deich М. Е. Technical Gas Dynamics. М.-L., 1961. 412 p.

9. Sitnikov B. T., Matveyev I. B. Calculation and Investigation of Safety and Relief Valves. М., 1972. 127 p.

10. Danilov Y. A., Kirillovsky Y. L., Kolpakov Y. G. Equipment of Massive Hydraulic Actuators: Operating Processes and Characteristics. М., 1990. 272 p.

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4.1.2019 Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays

manager — Thu, 25 May 2023 12:09:18 +0000

4. Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Akimov D. V.¹, Larionov I. F.¹, Klimenko D. V.¹, Gryshchak V. Z.², Gomenyuk S. I.²

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2019, (1); 21-27

DOI: https://doi.org/10.33136/stma2019.01.021

Language: Russian

Annotation: This paper presents the overview and features of the stress-strain state analysis of the multilayer shell structures widely used in the design of the missile compartments. As a result of analysis of the current situation with the stress-strain state studies of the complex configuration shell structures and mathematical support of the load-bearing capacity calculation of the aerospace structures, the following actual research trends can be singled out: 1) improvement of the methods of analytical estimation of the thin-walled structures’ strength and resistance; 2) improvement of the numerical methods of composite materials mechanical properties analysis; 3) development or application of the existing software packages and ADE-systems, automatizing stress-strain state analysis with visualization of the processes under study. One of the most important steps of the third research trend is development of the initial data input media (setting the model parameters) and presentation of analysis results with account of the user interface visualization. The description of the mathematical simulation and experimental studies of the stress-strain state of the interstage bay made of carbon fiber sandwich structure is presented and short description of the structure condition after the tests is provided. Based on the analysis it can be concluded that development of the geometric simulation methods, taking into account the manufacturing deviations, is an independent problem from the point of view of practical applications in the aerospace technology.

Key words: sandwich structure, interstage bay, finite-element model, manufacturing deviations, test loads

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7. Noor A. K., Burton W. S., Bert C. W. Computational Models for Sandwich Panels and Shells / Applied Mechanics Reviews. 1996. Vol. 49, No 3. P. 155–199.
8. Piskunov V. G., Rasskazov A. O. Razvitie teorii cloistykh plastin I obolochek // Prikladnaya mechanika. 2002. T. 38, № 2. P. 22–56.
9. Grigorenko Ya. M., Budak V. D., Grigorenko O. Ya. Rozvyazannya zadach teorii bolonok na osnovi disrento –continualnykh metodiv: Navch. posib. Mykolaiv: Ilion, 2010. 294 p.
10. Carrera Е., Brischetto S. A Survey With Numerical Assessment of Classical and Refined Theories for the Analysis of Sandwich Plates // Applied Mechanics Reviews. 2009. Vol. 62, No 1. P. 1–17.
11. Grigolyuk E. I. Uravnenia trekhsloinykh obolochek s legkim zapolnitelem // Izv. AN SSSR. Otdelenie tekhnicheskikh nauk. 1957. № 1. P. 77–84.
12. Ambartsumyan S. A. Teoria anizotropnykh plastin: Prochnost’, ustoichivost’ i kolebania. M.: Nauka, 1987. 360 p.
13. Carrera Е. Historical review of Zig-Zag theories for multilayered plates and shells / Applied Mechanics Reviews. 2003. Vol. 56, No 3. P. 287–308.
14. Teichman F. K., Wang C.-T. Finite deflections of Curved Sandwich Cylinders. Sherman M. Fairchild Publ. Fund. Inst. Aero. Sci. Paper FF-4. Institute of the Astronautical Sciences, 1951. P. 14.
15. Teichman F. K., Wang C.-T., Gerard G. Buckling of Sandwich Cylinders under Axial Compression / Journal of the Aeronautical Sciences. 1951. Vol. 18, No 6. P. 398–406.
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24. Chumachenko Ye. N., Polyakova T. V., Aksenov A. S. i dr. Matematicheskoe modelirovanie v nelineinoy mechanike: Obzor programmnykh complexov dlya resheniya zadach modelirovania slozhnykh system, Pr-2155. M.: Institut kosmicheskykh issledovaniy RAN, 2009. 44 p.
25. Opyt i novye tekhnologii inzhenernogo analiza v interesakh kosmosa: press-reliz / I. Novikov / GNKTs im. M. V. Khrunicheva. Rezhim dostupa: www.khrunichev.ru/ main.php?id=18mid=2132.

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4 citations in Crossref database (as of 16.07.2026 14:17)

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15.1.2019 Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test

manager — Wed, 24 May 2023 16:00:27 +0000

15. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Lysenko M. T., Rohulin V. V., Bezkrovny І. B., Kalnysh R. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 102-108

DOI: https://doi.org/10.33136/stma2019.01.103

Language: Ukrainian

Annotation: This paper describes the firing rig test of the solid rocket motor, fastened to the rig in order to measure the thrust level. It is shown that when the motor enters the steady-state mode, the rig with solid rocket motor starts experiencing mechanical oscillations due to the sudden thrust build-up. Motion of the oscillating system is studied under the impact of the linearly or suddenly increasing impulse load. Mechanical oscillations damping is considered on the basis of the viscous friction model. Procedure of the analytical modeling of the damped oscillations is suggested for the complex pattern of the loading variations, based on the fundamental principle of superposition, according to which the motor displacement during the oscillating motion is considered as sum of displacements due to the impact of the impulsive, sudden and linearly increasing loadings. This procedure simulates different time variations of thrust as motor enters the steady-state mode. Oscillating motion with parameters of the oscillating system and thrust change with time option have been simulated as they were realized during the firing rig tests of one of the solid rocket motors. Simulated and experimental (thrust sensor readings) curves of the elastic force were compared, which showed the qualitative and quantitative conformity of the suggested model of oscillations to the actual oscillations of the solid rocket motor, installed in the rig during the firing rig test. Values of the initial thrust, initial impulse and other simulation parameters were updated, adjusting the simulated curve of the elastic force to the experimental one. It was concluded that simulation of the elastic oscillations of the solid rocket motor in the rig using the suggested analytical model will enable more reliable definition of the initial thrust of the motor and its time behavior, impulse loading due to the separation of the plug and used elements that separate with it. Application of the suggested procedure of motor oscillations simulation in the phase of rig design will enable more detailed prediction of the occurring processes as well as the estimation of parameters of the individual elements, units and rig as a whole.

Key words: elastic oscillations, motor starting operation, sudden loading, measurement of thrust, principle of superposition, initial thrust

Bibliography:

1. Beskrovniy I. B., Kirichenko A. S., Balitskiy I. P. i dr. Opyt predpriyatiya po proektirovaniyu i ekspluatatsii stapeley dlya ispytaniy RDTT / Kosmicheskaya technika. Raketnoye vooruzhenie: Sb. nauch.- techn. st. 2008. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 119–127.
2. Bidermann V. L. Teoria mechanicheskykh kolebaniy: Uchebnik dlya VUZov. M.: Vyssh. shk., 1980. 408 p.
3. Yablonskiy A. A., Noreyko S. S. Kurs teorii kolebaniy. Ucheb. Posobie dlya studentov VUZov. Izd. 3-e, ispr. i dop. M.: Vyssh. shk., 1975. 248 p.

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