Search Results for “computational models” – Collected book of scientific-technical articles

17.1.2020 Acoustic problems of rocket launch

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

17. Acoustic problems of rocket launch

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

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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8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation

manager — Thu, 25 May 2023 12:09:45 +0000

8. Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation

Authors:

Tonkonozhenko A. M.¹, Kozharin V. Y.¹, Martynenko G. Y.³, Chernobryvko M. V.², Avramov K. V.²

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine²; National Technical University “Kharkiv Polytechnic Institute”, Kharkiv, Ukraine³

Page: Kosm. teh. Raket. vooruž. 2019, (1); 54-63

DOI: https://doi.org/10.33136/stma2019.01.054

Language: Russian

Annotation: This paper describes the effective approach for the technology of the rocket airframe development testing, based on the method of numerical modelling, which enables the virtual experimental runs prior to the beginning of the development testing to check the performance of the standard airframes and predict issues of concern. The method is realized based on the computer models developed in the ANSYS Workbench environment. Based on the offered method the complex mechanical system, which attaches the cluster projectiles in the conditions of the temperature exposure and heat cycling, underwent the virtual tests. Computational models, criteria and test procedures necessary for the analysis of the mechanical condition and prediction of the performance of the actual airframe of the warhead were developed. Moreover, computational models consider all the design and technological features of the airframe: layout of the projectiles attachments, initial stress-strain state of the system after the tightening of the threaded connections, friction between the components of the system and their mutual displacement, temperature dependence of the physical and mechanical characteristics and ultimate stress of materials. For the specified loading conditions during the ground operations with the warhead, the most dangerous computational cases are determined which have been implemented during the virtual tests. Test results were used to conduct the static analysis of the mechanical condition, strength and conditions for performance of the actual structure of the attachment under the impact of the operating levels of temperature exposure and heat cycling. Results of the virtual tests confirm the performance of the projectiles attachment system and are introduced into production in the phase of engineering development.

Key words: computer modelling, computational models, ground operations, mechanical condition, performance

Bibliography:

1. Birger I. A., Iosilevich G. B. Rezbovye i flantsevye soedineniya. M.: Mashinostroenie, 1990. 368 p.
2. Kukhling Ch. Spravochnik po phisike. M.: Mir, 1985. 520 p.
3. Nikolskiy B. P., Rabinovich V. A. Spravochnil chimika. T. 6. L.: Chimiya, 1967. 1009 p.
4. Stali I splavy. Marochnik: Sprav. izd. / pod red. V. G. Sorokina, M. A. Gervasieva. M.: Intermet Engineering, 2001. 608 p.
5. Numerical simulation of missile warhead operation / G. Martynenko, M. Chernobryvko, K. Avramov, V. Martynenko, A. Tonkonozhenko, V. Kozharin, D. Klymenko / Advances in Engineering Software. 2018. Vol. 123. P. 93-103. https://doi.org/10.1016/j.advengsoft.2018.07.001

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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

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

Bibliography:

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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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