Keywords cloud
Hydrogen was added to the argon-nitrogen gaseous medium to intensify the nitriding process. Working pressure in the chamber was maintained within the range of 250-300 Pa, the duration of the process was 120 minutes. The choice of the optimal temperature and time parameters of gas nitriding of steel.
]]>12. Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Ukrainian State University of Science and Technologies2
Page: Kosm. teh. Raket. vooruž. 2024, (1); 102-113
DOI: https://doi.org/10.33136/stma2024.01.102
Language: Ukrainian
Annotation: Steel hardening technology is considered, which implies modification of the steel surface with the method of ion-plasma nitriding in glow discharge. Ion-plasma nitriding is a multi-factor process, which requires the study of the influence of nitriding process conditions on the structure of modified layers, which, in its turn, determines their mechanical properties. The subjects of research included: austenitic steel 12X18Н10T, carbon steel Ст3 and structural steel 45. There were two conditions of plasma creation during the research: free location of samples on the surface of the cathode (configuration I) and inside the hollow cathode (configuration II). Optimal parameters of the ion-plasma nitriding process have been determined, which provide stability of the process and create conditions for intensive diffusion of nitrogen into the steel surface. Hydrogen was added to the argon-nitrogen gaseous medium to intensify the nitriding process. Working pressure in the chamber was maintained within the range of 250-300 Pa, the duration of the process was 120 minutes. Comparative characteristics of the structure and microhardness of the modified surfaces of the steels under study for two ion-plasma nitriding technologies are presented. Metallographic examination of the structure of the surface modified layers in the cross section showed the presence of the laminated nitrided layer, which consists of different phases and has different depths, depending on the material of the sample and treatment mode. Nitrided layer of 12Х18Н10Т steel consisted of four sublayers: upper “white” nitride layer, double diffuse layer and lower transition layer. The total depth of the nitrided layer after the specified treatment time reached 23 μm, use of hollow cathode increased it by 26% to 29 μm. The nitrided layers of steel Ст3 and steel 45 consisted of two sublayers – thick “white” nitride layer and general diffuse layer with a thickness of about 18 μm. The microhardness of the nitrided layer of steel Ст3 was 480 HV, increasing by 2,5 times, and for steel 45 was 440 HV, increasing by 1,7 times. The use of hollow cathode for these steels reduces the depth of the nitrided layer, but at the same time the microhardness increases due to the formation of a thicker and denser nitride layer on the surface. The results of the conducted research can be used to strengthen the surfaces of the steel parts in rocket and space technology, applying high-strength coatings.
Key words: ion nitriding, glow discharge, cross-sectional layer structure, hardening, microhardness
Bibliography:
1. Loskutova T. V., Pogrebova I. S., Kotlyar S. M., Bobina M. M., Kapliy D. A., Kharchenko N. A., Govorun T. P. Physichni ta tekhnologichni parametry azotuvannya stali Х28 v seredovyschi amiaku. Journal nano-elektronnoi physiki. 2023. №1(15). s. 1-4.
2. Al-Rekaby D. W., Kostyk V., Glotka A., Chechel M. The choice of the optimal temperature and time parameters of gas nitriding of steel. Eastern-European journal of Enterprise Technologies. 2016. V. 3/5(81). P.44-49. https://doi.org/10.15587/1729-4061.2016.69809
3. Yunusov A. I., Yesipov R. S. Vliyanie sostava gazovoy sredy na process ionnogo azotirovaniya martensitnoy stali 15Х16К5НР2МВФАБ-Ш. Vestnik nauki. 2023. №5(62). s. 854-863.
4. Zakalov O. V. Osnovy tertya i znoshuvannya u mashinah: navch. posibnik, vydavnytstvo TNTU im. I. Pulyuya, Ternopil. 2011. 332 s.
5. Kindrachuk M. V., Zagrebelniy V. V., Khizhnyak V. G., Kharchenko N. A. Technologichni aspeckty zabespechennya pratsezdatnosti instrument z shvydkorizalnykh staley. Problemy tertya ta znoshuvannya. 2016. №1 (70). S. 67-78.
6. Skiba M. Ye., Stechishyna N. M., Medvechku N. K., Stechishyn M. S., Lyukhovets’ V. V. Bezvodneve azotuvannya u tliyuchomu rozryadi, yak metod pidvyschennya znosostiykisti konstruktsiynykh staley. Visn. Khmelnitskogo natsionalnogo universitetu. 2019. №5. S. 7-12. https://doi.org/10.23939/law2019.22.012
7. Axenov I. I. Vakkumno-dugovye pokrytiya. Technologiya, materialy, struktura i svoistva. Kharkov, 2015. 379 s.
8. Pastukh I. M., Sokolova G. N., Lukyanyuk N. V. Azotirovanie v tleyuschem razryade: sostoyanie i perspektyvy. Problemy trybologii. 2013. №3. S. 18-22.
9. Pastukh I. M. Teoriya i praktika bezvodorodnogo azotirovanniya v tleuschem razryade: izdatelstvo NNTs KhFTI. Kharkov, 2006. 364 s.
10. Sagalovich O. V., Popov V. V., Sagalovich V. V. Plasmove pretsenziyne azotuvannya AVINIT N detaley iz staley i splaviv. Technologicheskie systemy. 2019. №4. S. 50-56.
11. Kozlov A. A. Nitrogen potential during ion nitriding process in glow-discharge plasma. Science and Technique. 2015. Vol. 1. P. 79-90.
12. Nadtoka V., Kraiev M., Borisenko А., Kraieva V. Multi-component nitrated ion-plasma Ni-Cr coating. Journal of Physics and Electronics. 2021. №29(1). Р. 61–64. DOI 10.15421/332108. https://doi.org/10.15421/332108
13. Nadtoka V., Kraiev M., Borisenko A., Bondar D., Gusarova I. Heat-resistant MoSi2–NbSi2 and Cr–Ni coatings for rocket engine combustion chambers and respective vacuum-arc deposition technology/ 74th International Astronautical Congress (IAC-23-C2.4.2), Baku, Azerbaijan, 2-6 October 2023.
14. Kostik K. O., Kostik V. O. Porivnyalniy analiz vplyvu gazovogo ta ionno-plazmovogo azotuvannya na zminu struktury i vlastyvostey legovannoi stali 30Х3ВА. Visnik NTU «KhPI». 2014. №48(1090). S. 21-41.
15. Axenov I. I., Axenov D. S., Andreev A. A., Belous V. A., Sobol’ O.V. Vakuumno-dugovye pokrytiya: technologia, materialy, struktura, svoistva: VANT NNTs KhFTI, Kharkov. 2015. 380 s.
16. Pidkova V. Ya. Modyfikuvannya poverkhni stali 12Х18Н10Т ionnoyu implantatsieyu azotom. Technology audit and production reserves. 2012. Vol. 3/2(5). P. 51-52. https://doi.org/10.15587/2312-8372.2012.4763
17. Kosarchuk V. V., Kulbovsliy I. I., Agarkov O. V. Suchasni metody zmitsnennya i pidvyschennya znosostiykosti par tertya. Ch. 2. Visn. Natsionalnogo transportnogo universytetu. 2016. Vyp. 1(34). S. 202-210.
18. Budilov V. V., Agzamov R. D., Ramzanov K. N. Issledovanie i razrabotka metodov khimiko-termicheskoy obrabotki na osnove strukturno-fasovogo modifitsirovaniya poverkhnisti detaley silnotochnymi razryadami v vakuume. Vestnik UGATU. Mashinostroenie. 2007. T. 9, №1(19). S. 140-149.
19. Abrorov A., Kuvoncheva M., Mukhammadov M. Ion-plasma nitriding of disc saws of the fiber-extracting machine. Modern Innovation, Systems and Technologies. 2021. Vol. 1(3). P. 30-35. https://doi.org/10.47813/2782-2818-2021-1-3-30-35
20. Smolyakova M. Yu., Vershinin D. S., Tregubov I. M. Issledovaniya vliyaniya nizkotemperaturnogo azotirovanniya na strukturno-fasoviy sostav i svoistva austenitnoy stali. Vzaimodeystvie izlecheniy s tverdym telom: materialy 9-oi Mezhdunarodnoy konferentsii (Minsk, 20-22 sentyabrya 2011 g.). Minsk, 2011. S. 80-82.
21. Adhajani H., Behrangi S. Plasma Nitriding of Steel: Topics in Mining, Metallurgy and Material Engineering by series editor Bergmann C.P. 2017. 186 p. https://doi.org/10.1007/978-3-319-43068-3
22. Fernandes B.B. Mechanical properties of nitrogen-rich surface layers on SS304 treated by plasma immersion ion implantation. Applied Surface Science. 2014. Vol. 310. P. 278-283. https://doi.org/10.1016/j.apsusc.2014.04.142
23. Khusainov Yu. G., Ramazanov K. N., Yesipov R. S., Issyandavletova G. B. Vliyanie vodoroda na process ionnogo azotirovanniya austenitnoy stali 12Х18Н10Т. Vestnik UGATU. 2017. №2(76). S. 24-29.
24. Sobol’ O. V., Andreev A. A., Stolbovoy V. A., Knyazev S. A., Barmin A. Ye., Krivobok N. A. Issledovanie vliyaniya rezhimov ionnogo azotirovanniya na strukturu i tverdost’ stali. Vostochno-Yevropeyskiy journal peredovykh tekhnologiy. 2015. №2(80). S. 63-68. https://doi.org/10.15587/1729-4061.2016.63659
25. Kaplun V. G. Osobennosti formirovanniya diffusionnogo sloya pri ionnom azotirovannii v bezvodorodnykh sredakh. FIP. 2003. T1, №2. S. 145.
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This may play both negative (off-design increase of chamber pressure) and positive role (for example, increasing the launch thrust-to-weight ratio of the rocket). Gas flow rate in each interval of the grain channel is calculated using gas-dynamic equations. The combustion chamber pressure had been calculated for four erosive burning models proposed by different authors. All the models showed convergence with the experimental SRM test data sufficient for engineering estimate (in particular, for maximum chamber pressure and combustion time). Gasodynamicheskie funktsii.
]]>8. Theoretic-experimental evaluation of the solid-propellant grain erosive burning
Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2024, (1); 72-77
DOI: https://doi.org/10.33136/stma2024.01.072
Language: Ukrainian
Annotation: The high demands for the flow rate and thrust characteristics specified for the modern solid-propellant rocket motors (SRM) under the strict mass and overall dimensions constraints require high level of mass fraction of propellant. And in the process of propellant grain combustion, erosive burning often takes place (increase of propellant burning rate depending on combustion products flow rate along the grain channel). This may play both negative (off-design increase of chamber pressure) and positive role (for example, increasing the launch thrust-to-weight ratio of the rocket). It is typical of the main SRMs of various rocket systems (multiple launch rocket systems, anti-aircraft guided missiles, tactical missiles, boosters). This paper proposes a methodology for calculating the internal ballistic characteristics of a solid propellant rocket motor under erosive burning, which is relatively time and resource consuming. The methodology is based on equidistant model of propellant grain combustion, where grain is divided lengthwise into a number of intervals. For any point of time during the engine operation, burning area and port area of each interval are calculated, taking into account erosive impact on each interval; total burning area is the sum of all intervals burning areas. Gas flow rate in each interval of the grain channel is calculated using gas-dynamic equations. The motor mass flow rate is a mass input sum of all the intervals; and the burning rate in each interval is estimated with proper erosion factor. The combustion chamber pressure had been calculated for four erosive burning models proposed by different authors. All the models showed convergence with the experimental SRM test data sufficient for engineering estimate (in particular, for maximum chamber pressure and combustion time). Selected as a result erosive burning model may be used to design new motors with solid propellants similar in chemical composition, and the model parameters are to be further customized using the test specimens.
Key words: rocket motor, solid propellant, erosive burning, internal ballistic characteristics
Bibliography:
- Arkhipov V. Erosionnoe gorenie condensirovannykh system. Sb. tr. ІХ Vserossiyskoy nauch. conf. 2016 g. (FPPSM-2016). Tomsk, 2016.
- Mukunda S., Paul P. J. Universal behaviour in erosive burning of solid propellants. Combustion and flame, 1997. https://doi.org/10.1016/S0010-2180(96)00150-2
- Sabdenov K. , Erzda M., Zarko V. Ye. Priroda i raschet skorosti erozionnogo goreniya tverdogo raketnogo topliva. Inzhenerniy journal: nauka i innovatsii, 2013. Vyp. 4.
- Evlanova A., Evlanov A. A., Nikolaeva Ye. V. Identifikatsiya parametrov erozionnogo goreniya topliva po dannym ognevykh stendovykh ispytaniy. Izvestiya TulGU. Tekhn. nauki. 2014. Vyp. 12, ch. 1.
- Yanjie Ma, Futing Bao, Lin Sun, Yang Liu, and Weihua Hui. A New Erosive Burning Model of Solid Propellant Based on Heat Transfer Equilibrium at Propellant Surface. Hindawi International Journal of Aerospace Engineering, Vol. 2020, Article ID 8889333. https://doi.org/10.1155/2020/8889333
- Williams, Forman A., Combustion Theory. The Benjamin/Cummings Publishing , Menlo Park, 1985.
- Irov Yu. D., Keil E. V., Maslov B.N., Pavlukhin Yu. A., Porodenko V. V.,
Stepanov Ye. A. Gasodynamicheskie funktsii. Mashinostroenie, Moskva, 1965. - William Orvis. EXCEL dlya uchenykh, inzhenerov i studentov. Kiev: «Junior», 1999.
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Keywords cloud
By method of explosive substance action on case structural elements, the pyrobolts are divided into two types: the pyrobolts using the shock wave formed at detonation of brisant explosive substance for case wall destruction and the pyrobolts using the pressure of gases arising at pyrotechnical charge blasting. The above segments a re actuated using a rod with sealing rings and a piston connected to the rod through a rubber gasket; the piston moves under pressure of gases formed during pyro cartridge action.
]]>19. Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 170-176
DOI: https://doi.org/10.33136/stma2020.01.170
Language: Russian
Annotation: The pyrobolts, or explosive bolts, belong to the pyrotechnical devices with monolithic case consisting o f the cap, as a rule with hexagonal surface, and of cylindrical part with thread. The pyrobolts are separated into parts using the pyrotechnical charge placed inside the case. Owing to the simple design, reliability and short action time, the pyrobolts have found wide application in aerospace engineering for separation of assemblies and bays, in particular, stages, head modules, launching boosters, etc. So, for example, about 400 pyrobolts are used in the Proton launch vehicle. The designs of pyrobolts are markedly different. By method of explosive substance action on case structural elements, the pyrobolts are divided into two types: the pyrobolts using the shock wave formed at detonation of brisant explosive substance for case wall destruction and the pyrobolts using the pressure of gases arising at pyrotechnical charge blasting. By method of separation into parts, they are divided into fragmenting pyrobolts with ridge-cut, with piston, and shear pyrobolts. The paper deals with the design of various types of pyrobolts, their disadvantages are considered. The Yuzhnoye SDO-developed pyrobolt of shear type with segments is presented that uses radial shear forces of segments located in the hole of cylindrical part to separate the case parts. The above segments a re actuated using a rod with sealing rings and a piston connected to the rod through a rubber gasket; the piston moves under pressure of gases formed during pyro cartridge action. The following calculations are presen ted: strength analyses with determination of case load-carrying capacity; power analyses with justification of pyro cartridge selection for pyrobolt actuation. In the developed pyrobolt of shear type with segments, the case parts are separated without considerable shock loads and without high-temperature gases and fragments release into environment, ensuring reliable separation of bays and assemblies without damaging sensitive equipment.
Key words: explosive bolt, shock wave, brisant explosive substance, pyro cartridge, electric igniting fuse, high-temperature gases
Bibliography:
1. Mashinostroenie. Entsiklopediia / А. P. Adzhian i dr.; pod red. V. P. Legostaeva. М., 2012. Т. IV-22. V 2-kh kn. Kn. 1. 925 s.
2. Bement L. J., Schimmel M. L. A Manual for Pyrotechnic Design, Development and Qualification: NASA Technical Memorandum 110172. 1995.
3. Yumashev L. P. Ustroistvo raket-nositelei (vspomagatelnye sistemy): ucheb. posob. Samara, 1999. 190 s.
4. Lee J., Han J.-H., Lee Y., Lee H. Separation characteristics study of ridge-cut explosive bolts. Aerospace Science and Technology. 2014. Vol. 39. Р. 153-168. https://doi.org/10.1016/j.ast.2014.08.016
5. Yanhua L., Jingcheng W., Shihui X., Li C., Yuquan W., Zhiliang L. Numerical Study of Separation Characteristics of Piston-Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2019/2092796
6. Yanhua L., Yuan L., Xiaogan L., Yuquan W., Huina M., Zhiliang L. Identification of Pyrotechnic Shock Sources for Shear Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2017/3846236
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Keywords cloud
Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations Authors: Furkalo S. 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 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. The three-dimensional problem was solved in ANSYS Fluent in steady-state approach, using Pressure-based solver and RANS k-omega SST turbulence model.
]]>16. Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations
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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Keywords cloud
Use of Statistic Approaches in Analysis of Gas Dynamic Parameters in LV Vented Bays. Vt222М Absolute Pressure Sensor: ТU Vt2.832.075TU.
]]>19. Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2018 (2); 157-172
DOI: https://doi.org/10.33136/stma2018.02.157
Language: Russian
Annotation: The measurement errors upon conducting flight tests for launch vehicles are evaluated by considering the interferences and uncertainties in the measurement system procedure. Formal use of this approach can lead to unpredictable consequences. More reliable evaluation of errors upon conducted measurements can be achieved if the measurement process is regarded as a procedure of successive activities for designing, manufacturing, and testing the measurement system and the rocket including measurements and their processing during the after-flight analysis of the received data. The sampling rates of the main controlled parameters are three to ten times higher than the frequency range of their changing. Therefore, it is possible to determine the characteristics of the random error components directly on the basis of registered data. The unrevealed systematic components create the basic uncertainty in the evaluation of the examined parameter’s total measurement error. To evaluate the precision and measurement accuracy of a particular launch, the article suggests specifying the preliminary data on measurement error components determined during prelaunch processing and launch. Basic structures of algorithms for evaluation of precision and measurement accuracy for certain mathematical models that form the measured parameters were considered along with the practical case when static correlation existed among the measured parameters.
Key words: flight tests, sensor, measurement error, mathematical model
Bibliography:
1. Novitsky P. V., Zograf I. A. Evaluation of Measurement Errors. L., 1985. 248 p.
2. Shmutzer E. Relativity Theory. Modern Conception. Way to Unity of Physics. М., 1981. 230 p.
3. Blekhman I. I., Myshkis A. D., Panovenko Y. G. Applied Mathematics: Subject, Logic, Peculiarities of Approaches. К., 1976. 270 p.
4. Moiseyev N. N. Mathematical Problems of System Analysis. М., 1981. 488 p.
5. Bryson A., Ho Yu-Shi. Applied Theory of Optimal Control. М., 1972. 544 p.
6. Yevlanov L. G. Monitoring of Dynamic Systems. М., 1972. 424 p.
7. Sergiyenko A. B. Digital Signal Processing: Collection of publications. 2011. 768 p.
8. Braslavsky D. A., Petrov V. V. Precision of Measuring Devices. М., 1976. 312 p.
9. Glinchenko A. S. Digital Signal Processing: Course of lectures. Krasnoyarsk, 2008. 242 p.
10. Garmanov A. V. Practice of Optimization of Signal-Noise Ratio at ACP Connection in Real Conditions. М., 2002. 9 p.
11. Denosenko V. V., Khalyavko A. N. Interference Protection of Sensors and Connecting Wires of Industrial Automation Systems. SТА. No. 1. 2001. P. 68-75.
12. Garmanov A. V. Connection of Measuring Instruments. Solution of Electric Compatibility and Interference Protection Problems. М., 2003. 41 p.
13. TP ACS Encyclopedia. bookASUTR.ru.
14. Smolyak S. A., Titarenko B. P. Stable Estimation Methods. М., 1980. 208 p.
15. Fomin A. F. et al. Rejection of Abnormal Measurement Results. М., 1985. 200 p.
16. Medich J. Statistically Optimal Linear Estimations and Control. М., 1973. 440 p.
17. Sage E., Mells J. Estimation Theory and its Application in Communication and Control. М., 1976. 496 p.
18. Filtration and Stochastic Control in Dynamic Systems: Collection of articles / Under the editorship of K. T. Leondes. М., 1980. 408 p.
19. Krinetsky E. I. et al. Flight Tests of Rockets and Spacecraft. М., 1979. 464 p.
20. Viduyev N. G., Grigorenko A. G. Mathematical Processing of Geodesic Measurements. К., 1978. 376 p.
21. Aivazyan S. A., Yenyukov I. S., Meshalkin L. D. Applied Statistics. Investigation of Dependencies. М., 1985. 487 p.
22. Sirenko V. N., Il’yenko P. V., Semenenko P. V. Use of Statistic Approaches in Analysis of Gas Dynamic Parameters in LV Vented Bays. Space Technology. Missile Armaments: Collection of scientific-technical articles. Issue 1. P. 43-47.
23. Granovsky V. A., Siraya T. N. Methods of Experimental Data Processing at Measurements. L., 1990. 288 p.
24. Zhovinsky A. N., Zhovinsky V. N. Engineering Express Analysis of Random Processes. М., 1979. 112 p.
25. Anishchenko V. A. Control of Authenticity of Duplicated Measurements in Uncertainty Conditions. University News. Minsk, 2010. No. 2. P. 11-18.
26. Anishchenko V. A. Reliability and Accuracy of Triple Measurements of Analog Technological Variables. University News. Minsk, 2017. No. 2. P. 108-117.
27. Shenk H. Theory of Engineering Experiment. М., 1972. 381 p.
28. Bessonov А. А., Sverdlov L. Z. Methods of Statistic Analysis of Automatic Devices Errors. L., 1974. 144 p.
29. Pugachyov V. N. Combined Methods to Determine Probabilistic Characteristics. М., 1973. 256 p. https://doi.org/10.21122/1029-7448-2017-60-2-108-117
30. Gandin L. S., Kagan R. L. Statistic Methods of Meteorological Data Interpretation. L., 1976. 360 p.
31. Zheleznov I. G., Semyonov G. P. Combined Estimation of Complex Systems Characteristics. М., 1976. 52 p.
32. Vt222М Absolute Pressure Sensor: ТU Vt2.832.075TU. Penza, 1983.
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Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests Authors: Nikitenko K. 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 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. Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle. Numerical Simulation of Hot Gas Nozzle Flows.
]]>10. Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests
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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Keywords cloud
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. 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. Experimental Investigation of Dynamic Characteristics of Gas Pressure Regulator in Multiple Ignition LRE Starting System. Results of Mathematical Modeling of Transient Processes in Gas Pressure Regulator. Mathematical Model of Gas Pressure Regulator.
]]>7. Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall
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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Keywords cloud
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.
]]>5. Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office
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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Keywords cloud
Features of Measurement System for Gas-Dynamic Model Tests of Rocket Complex Elements Authors: Aksiuta О. 2017 (1); 67-69 Language: Russian Annotation: The design proposals for sensor equipment of the measurement system used during gas dynamic model tests of rocket systems elements are presented. Microelectronic Pressure Sensors / N. Silicon Pressure Transducer with Differential Sensitive Element Based on Transverse Electromotive Force Effect / I. (2017) "Features of Measurement System for Gas-Dynamic Model Tests of Rocket Complex Elements" Космическая техника. "Features of Measurement System for Gas-Dynamic Model Tests of Rocket Complex Elements" Космическая техника.
]]>10. Features of Measurement System for Gas-Dynamic Model Tests of Rocket Complex Elements
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2017 (1); 67-69
Language: Russian
Annotation: The design proposals for sensor equipment of the measurement system used during gas dynamic model tests of rocket systems elements are presented.
Key words:
Bibliography:
1. Cyclone-4. 21.17827.122ОТ: Report on research work / Yuzhnoye SDO. Dnipropetrovsk, 2014. P. 12.
2. Krivorotov N. P. Microelectronic Pressure Sensors / N. P. Krivorotov, Т. I. Izaak, L. M. Romas’, Y. G. Svinolupov, S. S. Shchyogol. News of Tom. State University. 2005. No. 285. P. 139-147.
3. Zhadko I. P. Silicon Pressure Transducer with Differential Sensitive Element Based on Transverse Electromotive Force Effect / I. P. Zhadko, G. G. Babichev, S. I. Kozlovskiy, V. A. Romanov, N. N. Sharan, E. A. Zinchenko. Institute of Semiconductor Physics, National Academy of Science of the Ukraine. К., 2001. 7 р.
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Important role of the gas sprayer design in pressurization system parametric configuration is described, and the advanced versions are shown taking into account g-loads, changes in temperature, pressure and propellant level inside the tank. Key words: gas generator , sprayer , propulsion system , tank , gas pressure , gas temperature Bibliography: 1. gas generator , sprayer , propulsion system , tank , gas pressure , gas temperature .
]]>7. Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 45-53
DOI: https://doi.org/10.33136/stma2019.01.045
Language: Russian
Annotation: Long-term experience in development, development testing and use of generating systems of fuel tanks pressurization for rockets powered by nitrogen tetroxide and unsymmetrical dimethylhydrazine is summarized. Replacement of gas bottle pressurization systems with generating ones on such launch vehicles as 15A14, 15A15, 11K68 (8K67), 15A18M substantially simplified operation, reduced the pneumohydraulic feed system mass at least twice and its cost – by five times. Typical stages of development and introduction of the pressurization generating systems are shown: development of generators, their development testing, study of the composition and parameters of gas. The important steps were the development of methodology for pressurization system parameters calculation, which enabled achievement of the substantial improvements of their characteristics, appearance of the high-performance hightemperature (up to ~ 1000o C) unsymmetrical dimethylhydrazine tank pressurization system, study of the degree of impact of each of the pressurization system parameters on the tank pressure. Accounting of the correlation between the flow rate and the generator gas temperature improved the output performance, as well as simplified and reduced the amount of development testing of the pressurization system. Important role of the gas sprayer design in pressurization system parametric configuration is described, and the advanced versions are shown taking into account g-loads, changes in temperature, pressure and propellant level inside the tank. Significant phase in the development of the generating pressurization system was the effective use of the high-temperature pressurization of the fuel tank with submerged propulsion system. Besides for the first time the effect of mechanical temperature destratification of the propellant in the tanks was observed, which occurs during the propulsion systems shutdown. Due to this effect, the Dnepr LV payload capability enhanced. Successful engineering solutions in the design of the pressurization system were defended by ~80 copyright certificates and patents of invention, ~40 of which were successfully implemented.
Key words: gas generator, sprayer, propulsion system, tank, gas pressure, gas temperature
Bibliography:
1. Belyaev N. M. Systemy nadduva toplivnykh bakov raket. M.: Mashinostroenie, 1976. 336 p.
2. Logvinenko A. I. Osnovnyie napravlenia sovershenstvovania PGS sovremennykh RN / Dokl. Mezhd. astronavt. kongress. IAA. C4.1 IAC-63. Naples, Italia, 2012.
3. Kozlov A. A., Novikov V. N., Soloviev Ye. V. Systemy pitania i upravlenia zhidkostnykh raketnykh dvigatelnykh ustanovok. M.: Mashinostroenie, 1988. 352 p.
4. Logvinenko A. I. Tendentsii razvitia system nadduva toplivnykh bakov RN// Tez. dokl. Mezhdunar. astronavt. congressa IAC–05–C4.1.10, IAC-56. Fukuoka, Japan, 2005.
5. Logvinenko A. Gas-generation pressurization system experimental development method of the LV propellant tanks / Acta Astronautica. 2009. AA3161. №64. Р. 84-87. https://doi.org/10.1016/j.actaastro.2008.06.008
6. Ivanitskiy G. M., Logvinenko A. I., Tkachev V. A. K voprosu rascheta temperatury gazanadduva v bakakh raket / Systemne proektuvannya aerokosmichnoi techniki. 2001. T. III. P. 44-47.
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