Search Results for “wave stability” – 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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7.2.2018 Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall

Вацлав Самусевич — Thu, 07 Sep 2023 11:12:23 +0000

7. Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Konokh V. I.¹, Shevchenko S. A.¹, Grigor’ev O. L.²

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; National Technical University “Kharkiv Polytechnic Institute”, Kharkiv, Ukraine²

Page: Kosm. teh. Raket. vooruž. 2018 (2); 57-67

DOI: https://doi.org/10.33136/stma2018.02.057

Language: Russian

Annotation: During experimental investigation of the dynamic characteristics of a pneumatic test bench for testing liquid rocket engine high-flowrate automatic units, the effect was detected of 20-35% sound speed increase in the gas flow moving along the channel with corrugated wall (metal hose) which is a part of test bench drain system. The article presents the results of experiments and the task of theoretical justification of the effect is solved. It is indicated that its causes may be two mutually complementary factors – a decrease of gas compressibility at eddy motion and oscillations of metal hose wall. The physical model is considered that describes variation of gas elasticity and density in the conditions of high flow vorticity. It is supposed that in the near-wall layer of the channel, toroidal vortexes (vortex rings) are formed, which move into turbulent core of the flow where their size decreases and the velocity of rotation around the ring axis of torus increases. The spiral shape of the corrugation ensures also axial rotation, which increases vortexes stability. The intensive rotation around the ring axis creates considerable centrifugal forces; as a result, the dependence of pressure on gas density and the sound speed increase. The mathematical model has been developed that describes coupled longitudinal-lateral oscillations of gas and channel’s corrugated shell. It is indicated that in the investigated system, two mutually influencing wave types are present – longitudinal, which mainly transfer gas pressure pulses along the channel and lateral ones, which transfer the shell radial deformation pulses. As a result of modeling, it has been ascertained that because of the lateral oscillations of the wall, the propagation rate of gas pressure longitudinal waves (having the same wave length as in the experiments at test bench) turns out to be higher than adiabatic sound speed.

Key words: rocket engine automatic units, pneumatic test bench, metal hose, corrugated shell, toroidal vortex, longitudinal-lateral oscillations

Bibliography:

1. Shevchenko S. A. Experimental Investigation of Dynamic Characteristics of Gas Pressure Regulator in Multiple Ignition LRE Starting System. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works. 2015. Issue 4 (84). P. 49-68.

2. Shevchenko S. A., Valivakhin S. A. Results of Mathematical Modeling of Transient Processes in Gas Pressure Regulator. NTU “KhPI” News. 2014. No. 39 (1082). P. 198-206.

3. Shevchenko S. A., Valivakhin S. A. Mathematical Model of Gas Pressure Regulator. NTU “KhPI” News. 2014. No. 38 (1061). P. 195-209.

4. Shevchenko S. A., Konokh V. I., Makoter A. P. Gas Dynamic Resistance and Sound Speed in Channel with Corrugated Wall. NTU “KhPI” News. 2016. No. 20 (1192). P. 94-101.

5. Flexible Metal Hoses. Catalogue. Ufimsky Aggregate Company “Hydraulics”, 2001.

6. Loytsyansky L.G. Liquid and Gas Mechanics. М., 1978. 736 p.

7. Prisnyakov V. F. et al. Determination of Gas Parameters at Vessel Emptying Taking into Account Compressibility and Manifold Resistance. Problems of High-Temperature Engineering: Collection of scientific works. 1981. P. 86-94.

8. Kirillin V. A., Sychyov V. V., Sheydlin A. E. Technical Thermodynamics. М., 2008. 486 p.

9. Grekhov L. V., Ivashchenko N. A., Markov V. A. Propellant Equipment and Control Systems of Diesels. М., 2004. 344 p.

10. Sychyov V. V., Vasserman A. A., Kozlov A. D. et al. Thermodynamic Properties of Air. М., 1978. 276 p.

11. Shariff K., Leonard A. Vortex rings. Annu. Rev. Fluid Mech. 1992. Vol. 24. P. 235-279. https://doi.org/10.1146/annurev.fl.24.010192.001315

12. Saffman F. Vortex Dynamics. М., 2000. 376 p.

13. Akhmetov D. G. Formation and Basic Parameters of Vortex Rings. Applied Mechanics and Theoretical Physics. 2001. Vol. 42, No 5. P. 70–83.

14. Shevchenko S. A., Grigor’yev A. L., Stepanov M. S. Refinement of Invariant Method for Calculation of Gas Dynamic Parameters in Rocket Engine Starting Pneumatic System Pipelines. NTU “KhPI” News. 2015. No. 6 (1115). P. 156-181.

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2.1.2017 Ultimate Stability Stresses in Smooth Cylindrical Skins. Dynamic Problem

Виктория Лемех — Tue, 27 Jun 2023 11:52:29 +0000

2. Ultimate Stability Stresses in Smooth Cylindrical Skins. Dynamic Problem

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Kaplya P. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 8-17

Language: Russian

Annotation: This work deals with the problem of cylindrical shell stability within Donnel-Vlasov linear theory based on updated equilibrium equations and dynamic approach to their solution. The new theoretical results of critical stress determination that are well agreed with experimental data are presented here. The plot of critical stress as a function of dynamic behavior of specific shell is shown here. The wave generation parameters for the moment of equilibrium loss for each specific case are also presented in this work.

Key words:

Bibliography:

1. Volmir A. S. Stability of Elastic Systems. М., 1963. P. 463-471, 491-495.

2. Bolotin V. V. Nonconservative Problems of Elastic Stability Theory. М., 1961. P. 335.

3. Gladky V. F. Flying Vehicle Structural Dynamics. М., 1969. P. 129-134.

4. Kiselyov V. A. Structural Mechanics. М., 1969. P. 35-40.

5. Kaplya P. G., Pinyagin V. D. On Dynamics of Stiffened Cylindrical Shells. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2009. Issue 2. P. 59–73.

6. Rabotnov Y. N. Strength of Materials. М., 1967. P. 88-89.

7. Timoshenko S. P. Stability of Rods, Plates and Shells. М., 1971. P. 257-259, 457-472.

8. Galaka P. I. Investigation of Impact of Axial Compressive Forces on Oscillation Frequencies and Modes of Ribbed Cylindrical Shells / P. I. Galaka, V. A. Zarutsky, P. G. Kaplya, V. I. Matsner, A. M. Nosachenko. Kyiv, 1975. Vol. XI, Issue 8. P. 41–48.

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7.2.2019 On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem

manager — Mon, 15 May 2023 15:45:47 +0000

7. On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Kaplya P. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 50-57

DOI: https://doi.org/10.33136/stma2019.02.050

Language: Russian

Annotation: New theoretical results were obtained in definition of the stability longitudinal stress of the stiffened cylindrical shells both with internal and external arrangement of the stiffened stacks. They were obtained due to application of the dynamic approach to the solution of the refined equilibrium equations, introduction of the Qfactor of the structural elements into the system of equations, definition and application of the forces and moments in the calculation, that act in the sections of the joint bending of the shell and elements of stiffening. Expressions are given, which define the process of stability loss, including parameters of wave generation and amplitude of shell oscillation from the moment of application of the axial compressive force P0 up to the moment of snap action. With dynamic approach to the solution of the problem of the shell’s longitudinal stability the achievement of the first zero frequency by one of the higher modes of bending oscillations of the shell will indicate the loss of stability under the impact of the axial compressive force P0. This process is most obvious during testing of the absolutely flexible shells, which permit multiple loading. In the initial step of shell loading with axial compressive force P0, high-frequency bending oscillations with m, n ˃˃ 1 modes and low amplitudes occur. With a rise in force P0 oscillation frequency begins to drop, and amplitude to increase, with oscillatory mode remaining unchanged. There is a snap action when zero frequency is achieved for the first time by one of the oscillatory modes. This fact allowed formulation of the basic principles of nondestructive method for estimation of the critical stability stress of the flight-ready shell, main point of which is in the comparison of the theoretical curve of the frequency drop due to force P0 action on the structure versus the actual curve of the frequency drop of the flight-ready structure under the impact of the same values of P0 in the elastic range.

Key words: shell rigidity, dynamical problem, nondestructive testing

Bibliography:

1. Kaplya P. G. K voprosu o kriticheskykh napryazheniyakh prodolnoy ustoichivosti gladkykh tsilendricheskikh obolochek. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauchn.- techn. st. / GP “KB “Yuzhnoye”. Dnepr, 2017. Vyp. 1. S. 8-17.

2. Kaplya P. G., Pinyagin V. D. K voprosu dinamiki podkreplennykh tsilendricheskikh obolochek. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauchn.- techn. st. / GP “KB “Yuzhnoye”. Dnepr, 2009. Vyp. 2. S. 59–73.

3. Timoshenko S. P. Ustoichivost’ sterzhney, plastin I obolochek. M., 1971. S. 257–259, 457–472.

4. Volmir A. S. Ustoichivost’ uprugykh system. M., 1963. S. 463–471, 491–495, 541.

5. Tikhonov V. I. Statisticheskaya radiotechnika. M., 1966. S. 112–115.

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