Keywords cloud
The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.
]]>2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2020, (1); 13-25
DOI: https://doi.org/10.33136/stma2020.01.013
Language: Russian
Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. The guided missiles of multiple launch rocket system are intended for delivering munitions to the given spatial point with required and specified kinematic motion parameters at the end of flight. The aim of the article is an analysis of the development trends of the guided missiles with the solid rocket motors for the multiple launch rocket systems, identifying the characteristics and requirements for the flight trajectories, design parameters, control programs, overall dimensions and mass characteristics, structural layout and aerodynamic schemes of missiles. The formalization of the complex task to optimize design parameters, trajectory parameters and motion control programs for the guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories is given. The complex task belongs to a problem of the optimal control theory with limitations in form of equa lity, inequality and differential constraints. To simplify the problem, an approach to program forming is proposed for motion control in the form of polynomial that brings the problem of the optimal control theory to a simpler problem of nonlinear mathematical programming. When trajectory parameters were calculated the missile was regarded as a material point of variable mass and the combined equations for center-of-mass motion of the guided missile with projections on axes of the terrestrial reference system were used. The structure of the mathematical model was given along with the calculation sequence of the criterion function that was used for determination of the optimal parameters, programs and characteristics. The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.
Key words: multiple launch rocket systems (MLRS), complex problem of the optimal control theory, problem of nonlinear mathematical programming, main solid rocket motor, limitations for motion parameters and basic characteristics of the guided missiles
Bibliography:
1. Degtyarev A. V. Raketnaia tekhnika. Problemy i perspektivy: izbrannye nauchno-tekhnicheskie publikatsii. Dnepropetrovsk, 2014. 420 s.
2. Pro zatverdzhennia Poriadku zdiisnennia derzhavnoho kontriliu za mizhnarodnymy peredachamy tovariv podviinoho vykorystannia:Postanova Kabinetu Ministriv Ukrainy vid 28 sichnia 2004 r. № 86. Date: 29.11.2018. URL: https://zakon.rada.gov.ua/laws/show/86-2004-%D0%BF (Access date 01.09.2019).
3. Catalogue China Aerospase Long-march International. February, 2017. 136 p.
4. Reaktivnye sistemy zalpovogo ognia zarubezhnykh stran: obzor po materialam otkrytoi pechati za 1987–2016 gg. i interneta. Dnipro, 2016. Ч. I. 205 s.
5. Upravliaemye OTRK i TRK stran mira: obzor po materialam otkrytoi otechestvennoi i zarubezhnoi pechati za 2008–2014 gg. i interneta. Dnipro, 2014. 162 s.
6. Tail controlled rocket demonstrates near-vertical impact at extended range. URL: https://www.army.mil/article-amp/207357/tail_controlled_rocket_demonstrates_near_vertical_impact_at_extended_range (Access date 01.09.2019).
7. SY-400 Short-Range Ballistic Missile. URL: http://www.military-today.com/missiles/sy_400.htm (Access date 01.09.2019).
8. Vohniana “Vilkha”: nova vysokotochna systema zalpovoho vohnyu. Vpershe – detalno. URL: https://defence-ua.com/index.php/statti/4588-vohnyana-vilkha-nova-vysokotochna-systema-zalpovoho-vohnyu-vpershe-detalno (Access date 01.09.2019).
9. Gurov S. V. Reaktivnye sistemy zalpovogo ognia: obzor. 1-е izd. Tula, 2006. 432 s.
10. The new M30A1 GMLRS Alternate Warhead to replace cluster bombs for US Army Central 71601171. URL: https://www.armyrecognition.com/weapons_defence_industry_military_technology_uk/the_new_m30a1_gmlrs_alternate_warhead_to_replace_cluster_bombs_for_us_army_central_71601171.html (Access date 01.09.2019).
11. High-Mobility Artillery Rocket System (HIMARS), a member of MLRS family. URL: https://army-technology.com/projects/himars/ (Access date 01.09.2019).
12. SR-5 Multiple Launch Rocket System. URL: http://www.military-today.com/artillery/sr5.htm (Access date 01.09.2019).
13. Effectivnost slozhnykh system. Dinamicheskie modeli / V. А. Vinogradov, V. А. Hrushchansky, S. S. Dovhodush i dr. М., 1989. 285 s.
14. Ilichev А. V., Volkov V. D., Hrushchansky V. А. Effectivnost proektiruemykh elementov slozhnykh system: ucheb. posobie. М., 1982. 280 s.
15. Krotov V. F., Gurman V. I. Metody I zadachi optimalnogo upravleniia. М., 1973. 446 s.
16. Pontriagin L. S., Boltiansky V. G., Gamkrelidze R. V., Mishchenko Е. F. Matematicheskaia teoriia optimalnykh protsesov. М., 1969. 385 s.
17. Tarasov Е. V. Algoritm optimalnogo proektirovaniia letatelnogo apparata. М., 1970. 364 s.
18. Shcheverov D. N. Proektirovanie bespilotnykh letatelnykh apparatov. М., 1978. 264 s.
19. Siniukov А. М., Volkov L. I., Lvov А. I., Shishkevich А. М. Ballisticheskaia raketa na tverdom toplive / pod red. А. М. Siniukova. М., 1972. 511 s.
20. Burov М. А., Varfolomeev V. I., Volkov L. I. Proektirovanie i ispytanie ballisticheskikh raket / pod red. V. I. Varfolomeeva, М. I. Kopytova. М., 1970. 392 s.
21. Siutkina-Doronina S. V. K voprosu optimizatsii proektnykh parametrov i programm upravleniia raketnogo ob’ekta s raketnym dvigatelem na tverdom toplive. Aviatsionno-kosmicheskaia tekhnika i tekhnologiia. 2017. № 2 (137). S. 44–59.
22. Aksenenko A. V., Baranov E. Yu., Hursky A. I., Klochkov A. S., Morozov A. S., Alpatov A. P., Senkin V. S., Siutkina-Doronina S. V. Metodicheskoe obespechenie dlia optimizatsii na nachalnom etape proektirovaniia proektnykh parametrov, parametrov traektorii i programm upravleniia dvizheniem raketnogo ob’ekta. Kosmicheskaia tekhnika. Raketnoe vooruzhenie: sb. nauch.-tekhn. st. / GP “KB “Yuzhnoye”. Dnipro, 2018. Vyp. 2 (116). S. 101–116. https://doi.org/10.33136/stma2018.02.101
23. Metodicheskoe obespechenie dlia optimizatsii na nachalnom etape proektirovaniia proektnykh parametrov, programm upravleniia, ballisticheskikh, energeticheskikh i gabaritno-massovykh kharakteristik upravliaemykh raketnykh ob’ektov, osushchestvliaiushchikh dvizhenie po aeroballisticheskoi traektorii: otchet po NIR / ITM NANU i GKAU, GP “KB “Yuzhnoye”. Dnepropetrovsk, 2017. 159 S.
24. Senkin V. S. K Vyboru programm upravleniia dvizheniem raketnogo ob’ekta po ballisticheskoi traektorii. Tekhnicheskaia mekhanika. 2018. № 1. S. 48–59.
25. Alpatov A. P., Senkin V. S. Metodicheskoe obespechenie dlia vybora oblika, optimizatsii proektnykh parametrov i programm upravleniia poletom rakety-nositelia. Tekhnicheskaia mekhanika. 2013. № 4. S. 146–161.
26. Alpatov A. P., Senkin V. S. Kompleksnaia zadacha optimizatsii osnovnykh proektnykh parametrov i programm upravleniia dvizheniem raket kosmicheskogo naznacheniia. Tekhnicheskaia mekhanika. 2011. № 4. S. 98–113.
27. Senkin V. S. Optimizatsiia proektnykh parametrov rakety-nositelia sverkhlegkogo klassa. Tekhnicheskaia mekhanika. 2009. № 1. S. 80–88.
28. Lebedev А. А., Gerasiuta N. F. Ballistika raket. М., 1970. 244 s.
29. Razumev V. F., Kovalev B. K. Osnovy proektirovaniia ballisticheskikh raket na tverdom toplive: ucheb. posobie dlia vuzov. М., 1976. 356 s.
30. Erokhin B. Т. Teoreticheskie osnovy oroektirovaniia RDTT. М., 1982. 206 s.
31. Abugov D. I., Bobylev V. М. Teoriia i raschet raketnykh dvigatelei tverdogo topliva: uchebnik dlia mashinostroitelnykh vuzov. М., 1987. 272 s.
32. Shishkov А. А. Gasodinamika porokhovykh raketnykh dvigatelei: inzhenernye metody rascheta. М., 1974. 156 s.
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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. 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 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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Keywords cloud
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.
]]>4. The dynamics of servo drives
Organization:
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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Keywords cloud
The task arises of selection of structure and parameters of devices consisting of several subsystems whose dynamic characteristics must be brought into agreement with each other in optimal way. Using Lagrange transformation as applied to ball screw transmission, the expression for reduced mass of output element was derived. Key words: pneumatic drive , functional arrangement , hydrodynamic force , reduced mass , Lagrange transformations , ball screw transmission , transient process , frequency characteristic Bibliography: 1. pneumatic drive , functional arrangement , hydrodynamic force , reduced mass , Lagrange transformations , ball screw transmission , transient process , frequency characteristic .
]]>10. Dynamic performance of the gas drive with jet motor
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (2); 71-79
DOI: https://doi.org/10.33136/stma2019.02.071
Language: Russian
Annotation: The use of servo drives on flying vehicles determines the requirements to their dynamic characteristics. The problems of dynamics of drive with jet motor are not practically covered in publications. The task arises of selection of structure and parameters of devices consisting of several subsystems whose dynamic characteristics must be brought into agreement with each other in optimal way. The purpose of this work is to develop mathematical dependences for calculation of dynamic characteristics. The functional arrangement of the drive is considered consisting of jet motor based on Segner wheel with de Laval nozzle, mechanical transmission, pneumatic distributing device – jet pipe controlled by electromechanical converter. The layout is presented of mechanical segment of servo drive with jet motor with screw-nut transmission. The dynamic model is presented and the algebraic relations to determine natural frequencies of the drive are given. The motion equations of output rod at full composition of load are given. Using Lagrange transformation as applied to ball screw transmission, the expression for reduced mass of output element was derived. The reduced mass of load depends on the jet motor design and exerts basic influence on the drive’s natural frequencies. The evaluation is given of reduced mass change from the jet motor moment of inertia and reducer transmission coefficient. Based on the proposed algorithms, the dynamic characteristics of servo drive were constructed: transient process and amplitude-frequency characteristic. The drive has relatively low pass band, which is explained by the value of reduced mass of load.
Key words: pneumatic drive, functional arrangement, hydrodynamic force, reduced mass, Lagrange transformations, ball screw transmission, transient process, frequency characteristic
Bibliography:
1. Pnevmoprivod system upravleniya letatelnykh apparatov /V. A. Chaschin, O. T. Kamladze, A. B. Kondratiev at al. M., 1987. 248 s.
2. Berezhnoy A. S. Sovershenstvovanie rabochikh characteristic struino-reaktivnogo pnevmoagregata na osnove utochneniya modeli rabochego processa: dis. cand. techn. nauk: 05.05.17. Zaschischena 03.10.14. Sumy, 2014. 157 s.
3. Oleinik V. P., Yelanskiy Yu. A., Kovalenko V. N. et al. Staticheskie characteristiki gazovogo privoda so struinym dvigatelem /Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2016. Vyp. 2. S. 21-27.
4. Abramovich G. N. Prikladnaya gazovaya dynamika. M., 1976. 888 s.
5. Strutinskiy V. B. Matematichne modelyuvannya processiv ta system mechaniki. Zhitomir, 2001. 612 s.
6. Shalamov A. V., Mazein P. G. Dynamicheskaya model’ sharikovintovoi pary/ Izv. Chelyabinskogo nauchnogo centra UrO RAN. №4. Chelyabinsk, 2002. S.161-170.
7. Kripa K.Varanasi, Samir A. Nayfer. The Dynamics of Lead-Screw Drivers: Low-Order Modeling and Experiments /Journal of Dynamic System, Measurement and Control. June 2004. Vol. 126. P. 388-395. https://doi.org/10.1115/1.1771690
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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.
]]>9. Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel
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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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. (2020) "Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations" Космическая техника. "Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations" Космическая техника. quot;Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations", Космическая техника. Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations Автори: Furkalo S. Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations Автори: Furkalo S.
]]>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
The tests of pilot propellant tank showed that the calculated values of deformations and displacements differ from the experimental values by no more than 10 %. Using the parameters measurement results from the tests on liquid nitrogen, the empirical formulas were obtained to calculate linear thermal expansion coefficient of the package of materials of load -bearing shell. The empirical dependences were constructed of relative ring deformations at load-bearing shell middle section on pressure and temperature. Key words: load-bearing shell , permeability , cryogenic propellant , relative deformations , linear thermal expansion coefficient Bibliography: 1.
]]>9. Experimental investigation of a liner-free propellant tank made from polymer composite materials
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 90-98
DOI: https://doi.org/10.33136/stma2020.01.090
Language: Russian
Annotation: The exploratory and experimental investigations were conducted into design of propellant tank made of composite polymer materials for work in cryogenic environment at operating pressure of 7.5 kgf/cm2 . When determining the configuration of a liner-free composite propellant tank, the main requirement was ensuring its leak-tightness at internal excess pressure and cryogenic temperature effect. The world experience of creating similar designs was analyzed and the requirements were defined imposed on configuration of propellant tank load-bearing shells. Before defining the final configuration, the types of materials, reinforcing patterns, and possible ways to ensure leak-tightness were analyzed, and preliminary tests were conducted of physical and mechanical characteristics of thin-wall samples of composite materials and tubular structures with different reinforcing patterns. The tests of carbon plastic samples were conducted at different curing modes to determine the most effective one from the viewpoint of strength characteristics and the tests for permeability by method of mouthpiece were conducted. The tests of pilot propellant tank showed that the calculated values of deformations and displacements differ from the experimental values by no more than 10 %. Using the parameters measurement results from the tests on liquid nitrogen, the empirical formulas were obtained to calculate linear thermal expansion coefficient of the package of materials of load -bearing shell. The empirical dependences were constructed of relative ring deformations at load-bearing shell middle section on pressure and temperature. The tests confirmed correctness of adopted solutions to ensure strength and leak-tightness of propellant tank load-bearing shell at combined effect on internal excess pressure and cryogenic temperature, particularly at cyclic loading. The materials used and propellant tank manufacturing technologies ensure leak-tightness of load-bearing shell at liquid nitrogen operating pressure of 7.5 kgf/cm2 and strength at excess pressure of 15 kgf/cm2 and allow conducting approbation of prospective stage of the integrated launch vehicle.
Key words: load-bearing shell, permeability, cryogenic propellant, relative deformations, linear thermal expansion coefficient
Bibliography:
1. Frantsevich I. М., Karpinos D. М. Kompozitsionnye materialy voloknistogo stroeniia. K., 1970.
2. TSM YZH ANL 009 00. Composite fuel tank for ILV, Dnipro, Yuzhnoye SDO, 2019.
3. Zheng H., Zeng X., Zhang J., Sun H. The application of carbon fiber composites in cryotank. Solidification. 2018. https://doi.org/10.5772/intechopen.73127
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Keywords cloud
Key words: productivity , carrying capacity , fuel efficiency , parameter formation Bibliography: 1. productivity , carrying capacity , fuel efficiency , parameter formation .
]]>8. Determining the main parameters of transport aircraft modifications considering the fuel efficiency
Organization:
Antоnov Company, Kyiv, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 85-89
DOI: https://doi.org/10.33136/stma2020.01.085
Language: Russian
Annotation: The main parameters are understood as: carrying capacity mг, range L and fuel efficiency qт, which largely determine the competitiveness of aircraft of this type, including military transport aircraft. The reason for the creation of modifications of transport category aircraft is the requirement for a constant increase in their flight performance by increasing the carrying capacity and range. Among the main goals of implementing such decisions there is an indispensable increase in the fuel efficiency of modifications, since the cost of fuel reaches 80 % of the cost of an airplane hour during operation. There are a number of models that make it possible to assess the influence of the weight and aerodynamic parameters of the airframe of the aircraft and the fuel performance of the power plant (specific engine consumption) on the integral indicator of the fuel efficiency of the modification at cruising mode and the average hourly fuel consumption at the certification stage, when all parameters of the airframe and engine are fixed and consideration of options is not possible. A new model is proposed for the stage of designing modifications, in which deep modification changes are made in the geometry of wing and in the power plant with various variants of their correlation and coordination. The parameters of new model: specific fuel efficiency – specific route productivity, in order to form the relative carrying capacity and relative range of action for the required specific fuel efficiency. An analysis of such dependencies showed: – with an increase in relative range L , fuel costs per flight also increase; – the adequacy of changes in route performance is observed only at L < 0.5. At L > 0.5 productivity is constantly decreasing, while the specific indicator of fuel consumption per unit of work increases exponentially; – if in the analysis we take into account the specific value of transport efficiency, that is, the characteristic “load – range” ( mп.н f L ), it becomes obvious that the most favorable (from the point of view of fuel efficiency) are relative ranges of 0,3 < L < 0,5. In this range L , not only acceptable fuel efficiency values are realized, but also the maximum value of the route performance, that is the main parameters for which modifications are developed.
Key words: productivity, carrying capacity, fuel efficiency, parameter formation
Bibliography:
1. Balabuev P. V. Osnovy obshchego proektirovaniia samoletov s gazoturbinnymi dvigateliami. Kharkiv, 2003. Ch. 2. 389 s.
2. Yugov О. K. Soglasovanie kharakteristik samoleta i dvigatelia. 1975. 204 s.; 2-е izd., 1980. 200 s.
3. Korol’ V. N. Kontseptsiia sozdaniia mezhdunarodnogo konsortsiuma “Srednii transportnyi samolet”. Voprosy proektirovaniia i proizvodstva konstruktsii letalelnykh apparatov. Kharkiv, 2002. Vyp. 30(3). S. 6-27.
4. Global Market Forecast. Future Journeys 2013 – 2020 / AIRBUS S.A.S Blagnac Cedex: Art @ Caractere, 2013. 125 p. [electronic resource]. Access mode: http://www.airbus.com/company/market/forecast/elD=dam.
5. 747-400 Freighter Main deck cargo arrangements. Boeing, 2010 10 p. [electronic resource]. Access mode: http://www.boeing.com.
6. 6. ICAO. 3.2bn passengers used air transport in 2014. [electronic resource]. Access mode: http://www.aviatime.com/-en/airports/airports-news.
7. An-188. Srednii voenno-ttansportnyi samolet ukorochennogo vzleta i posadki. Kyiv, 2018. S. 118.
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Keywords cloud
Taking into consideration plasticity and creeping of material, to determine stress and strain state, the approach is effective where the calculation is divided into phases; in each phase the parameters are entered that characterize the deformations of plasticity and creeping: additional loads in the equations of equilibrium or in boundary conditions, additional deformations or variable parameters of elasticity (elasticity modulus and Poisson ratio).
]]>5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2; Oles Honchar Dnipro National University, Dnipro, Ukraine3
Page: Kosm. teh. Raket. vooruž. 2020, (1); 44-56
DOI: https://doi.org/10.33136/stma2020.01.044
Language: Russian
Annotation: The shell structures widely used in space rocket hardware feature, along with decided advantage in the form of optimal combination of mass and strength, inhomogeneities of different nature: structural (different thicknesses, availability of reinforcements, cuts-holes et al.) and technological (presence of defects arising in manufacturing process or during storage, transportation and unforseen thermomechanical effects). The above factors are concentrators of stress and strain state and can lead to early destruction of structural elements. Their different parts are deformed according to their program and are characterized by different levels of stress and strain state. Taking into consideration plasticity and creeping of material, to determine stress and strain state, the approach is effective where the calculation is divided into phases; in each phase the parameters are entered that characterize the deformations of plasticity and creeping: additional loads in the equations of equilibrium or in boundary conditions, additional deformations or variable parameters of elasticity (elasticity modulus and Poisson ratio). Then the schemes of successive approximations are constructed: in each phase, the problem of elasticity theory is solved with entering of the above parameters. The problems of determining the lifetime of space launch vehicles and launching facilities should be noted separately, as it is connected with damages that arise at alternating-sign thermomechanical loads of high intensity. The main approach in lifetime determination is one that is based on the theory of low-cycle and high-cycle fatigue. Plasticity and creeping of material are the fundamental factors in lifetime substantiation. The article deals with various aspects of solving the problem of strength and stability of space rocket objects with consideration for the impact of plasticity and creeping deformations.
Key words: shell structures, stress and strain state, structural and technological inhomogeneity, thermomechanical loads, low-cycle and high-cycle fatigue, lifetime
Bibliography:
1. Iliushin A. A. Trudy v 4-kh t. М., 2004. T. 2. Plastichnost. 408 s.
2. Ishlinskii А. Yu., Ivlev D. D. Matematicheskaya teoriia plastichnosti. М., 2001. 700 s.
3. Hutchinson J. W. Plastic buckling. Advances in Appl. Mech. 1974. V. 14. P. 67 – 144. https://doi.org/10.1016/S0065-2156(08)70031-0
4. Hudramovich V. S. Ustoichivost uprugo-plasticheskikh obolochek / otv. red. P. I. Nikitin. Kiev, 1987. 216 s.
5. Parton V. Z., Morozov Е. М. Mekhanika uprugoplastichnogo razrusheniia. М., 1985. 504 s.
6. Tomsen E., Yang Ch., Kobaiashi Sh. Mekhanika plasticheskikh deformatsii pri obrabotke metalla. М., 1968. 504 s.
7. Mossakovsky V. I., Hudramovich V. S., Makeev E. M. Kontaktnye vzaimodeistviia elementov obolochechnykh konstruktsii / otv. red. V. L. Rvachev. Kiev, 1988. 288 s.
8. Hudramovych V. S. Contact mechanics of shell structures under local loading. Int. Appl. Mech. 2009. V. 45, No 7. P. 708 – 729. https://doi.org/10.1007/s10778-009-0224-5
9. Iliushin A. A. Trudy v 4-kh t. М., 2009. Т. 4. Modelirovanie dinamicheskikh protsessov v tverdykh telakh i inzhenernye prilozheniia. 526 s.
10. Hudramovich V. S. Plasticheskoe vypuchivanie tsilindricheskoi obolochki konechnoi dliny pri impulsnom lokalnom nagruzhenii. Teoriia obolochek i plastin: tr. 8-i Vsesoiuzn. konf. Po teorii obolochek i plastin (Rostov-na-Donu, 1971 g.). М., 1973. S. 125 – 130.
11. Nelineinye modeli i zadachi mekhaniki deformiruemogo tverdogo tela. Sb. nauch. tr., posv. 70-letiiu so dnia rozhd. Yu. N. Rabotnova / otv. red. K. V. Frolov. М., 1984. 210 s.
12. Binkevich Е. V., Troshin V. G. Ob odnom sposobe linearizatsii uravnenii teorii obolochek srednego izgiba. Prochnost i dolgovechnost elementov konstruktsii: sb. nauch. tr. / otv. red. V. S. Hudramovich. Kiev, 1983. S. 53 – 58.
13. Rabotnov Yu. N. Problemy mekhaniki deformiruemogo tverdogo tela. Izbrannye Trudy / otv. red. K. V. Frolov. М., 1991. 196 s.
14. Hudramovich V. S. Teoriia polzuchesti i ee prilozheniia k raschetu elementov tonkostennykh konstruktsii. Kiev, 2005. 224 s.
15. Hudramovych V. S., Hart E. L., Ryabokon’ S. A. Plastic deformation of nonhomogeneous plates. J. Math. Eng. 2013. V. 78, Iss. 1. P. 181 – 197. https://doi.org/10.1007/s10665-010-9409-5
16. Hart E. L., Hudramovych V. S. Applications of the projective-iterative versions of FEM in damage problems for engineering structures. Maintenance 2012. Proceedings of 2th Int. Conf. (Zenica, Bosnia and Herzegovina, 2012). Zenica, 2012. P. 157 – 164.
17. Hudramovich V. S., Hart E. L. Konechnoelementnyi analiz protsessa rasseiannogo razrusheniia ploskodeformiruemykh uprugoplasticheskikh sred s lokalnymi kontsentratsiami napriazhenii. Uprugost i neuprugost: materialy Mezhdunar. simp. Po problemam mekhaniki deform. tel, posv. 105-letiiu so dnia rozhd А. А. Iliushina (Moskva, yanv. 2016 g.). М., 2016. S. 158 – 161.
18. Lazarev Т. V., Sirenko V. N., Degtyarev М. А. i dr. Vysokoproizvoditelnaia vychislitelnaia sistema dlia raschetnykh zadach GP KB “Yuzhnoye”. Raketnaia tekhnika. Novyie vozmozhnosti: nauch.-tekhn. sb. / pod red. A. V. Degtyareva. Dnipro, 2019. S. 407 – 419.
19. Sirenko V. N. O vozmozhnosti provedeniia virtualnyks ispytanii pri razrabotke raketno-kosmicheskoi tekhniki s tseliu opredeleniia nesushchikh svoistv. Aktualni problemy mekhaniky sytsilnoho seredovyshcha i mitsnosti konstruktsii: tezy dop. II Mizhnar. nauk.-tekhn. konf. pam’iati akad. NANU V. І. Mossakovskoho (do storichchia vid dnia narodzhennia). (Dnipro, 2019 r.). Dnipro, 2019. S. 43 – 44.
20. Degtyarev А. V. Shestdesiat let v raketostroyenii i kosmonavtike. Dniepropetrovsk, 2014. 540 s.
21. Mak-Ivili А. Dzh. Analiz avariinykh razrushenii. М., 2010. 416 s.
22. Song Z. Test and launch control technology for launch vehicles. Singapore, 2018. 256 p. https://doi.org/10.1007/978-981-10-8712-7
23. Hudramovich V. S., Sirenko V. N., Klimenko D. V., Daniev Ju. F., Hart E. L. Development of the normative framework methodology for justifying the launcher structures resource of launch vehicles. Strength of Materials. 2019. Vol. 51, No 3. P. 333 – 340. https://doi.org/10.1007/s11223-019-00079-4
24. Grigiliuk E. I., Shalashilin V. V. Problemy nelineinogo deformirovaniia. Metod prodolzheniia po parametru v nelineinykh zadachakh mekhaniki deformiruemogo tverdogo tela. М., 1988. 232 s.
25. Hudramovych V. S. Features of nonlinear deformation of shell systems with geometrical imperfections. Int. Appl. Mech. 2006. Vol. 42, Nо 7. Р. 3 – 37. https://doi.org/10.1007/s10778-006-0204-y
26. Hudramovich V. S. Kriticheskoe sostoianie neuprugikh obolochek pri slozhnom nagruzhenii. Ustoichivost v MDTT: materialy Vsesoiuzn. simp. (Kalinin, 1981 g.) / pod red. V. G. Zubchaninova. Kalinin, 1981. S. 61 – 87.
27. Hudramovich V. S. Ustoichivost i nesushchaia sposobnost plasticheskikh obolochek. Prochnost i dolgovechnost konstruktsii: sb. nauch. tr. / otv. red. V. S. Budnik. Kiev, 1980. S. 15 – 32.
28. Hudramovich V. S., Pereverzev E. S. Nesushchaia sposobnost i dolgovechnost elementov konstruktsii / otv. red. V. I. Mossakovsky. Kiev, 1981. 284 s.
29. Hudramovich V. S., Konovalenkov V. S. Deformirovanie i predelnoie sostoianie neuprugikh obolochek s uchetom istorii nagruzheniia. Izv. AN SSSR. Mekhanika tverdogo tela. 1987. №3. S. 157 – 163.
30. Нudramovich V. S. Plastic and creep instability of shells with initial imperfections. Solid mechanics and its applications / Ed. G. M. L. Gladwell V. 64. Dordrecht, Boston, London, 1997. P. 277–289. https://doi.org/10.1007/0-306-46937-5_23
31. Нudramovich V. S., Lebedev A. A., Mossakovsky V. I. Plastic deformation and limit states of metal shell structures with initial shape imperfections. Light-weight steel and aluminium structures: proceedings Int. Conf. (Helsinki, Finland, 1999) / Ed. P. Makelainen. Amsterdam, Lousanne, New York, Tokyo, 1999. P. 257–263. https://doi.org/10.1016/B978-008043014-0/50133-5
32. Kushnir R. M., Nikolyshyn М. М., Osadchuk V. А. Pruzhnyi ta pruzhnmoplastychnyi hranychnyi stan obolonok z defectamy. Lviv, 2003. 320 s.
33. Hudramovich V. S. Predelnyi analiz – effektivnyi sposob otsenki konstruktsionnoi prochnosti obolochechnykh system. III Mizhnar. konf. «Mekhanika ruinuvannia i mitsnist konstruktsii» (Lviv, 2003) / pid red. V. V. Panasiuka. Lviv, 2003. S.583–588.
34. Herasimov V. P., Hudramovich V. S., Larionov I. F. i dr. Plasticheskoe razrushenie sostavnykh obolochechnykh konstruktsii pri osevom szhatii. Probl. prochnosti. 1979. №11. S. 58 – 61.
35. Hudramovich V. S. Herasimov V. P., Demenkov A. F. Predelnyi analiz elementov konstruktsii / otv. red. V. S. Budnik. Kiev, 1990. 136 s.
36. Druker D. Makroskopicheskie osnovy teorii khrupkogo razrusheniia. Razrushenie. М., 1973. Т. 1. S. 505 – 569.
37. Galkin V. F., Hudramovich V. S., Mossakovsky V. I., Spiridonov I. N. O vliianii predela tekuchesti na ustoichivost tsilindricheskikh obolochek pri osevom szhatii. Izv. AN SSSR. Mekhanika tverdogo tela. 1973. №3. С 180 – 182.
38. Hudramovich V. S., Dziuba A. P., Selivanov Yu. М. Metody golograficheskoi interferometrii v mechanike neodnorodnykh tonkostennykh konstruktsii. Dnipro, 2017. 288 s.
39. Hudramovich V. S., Skalskii V. R., Selivanov Yu. М. Holohrafichne te akustyko-emisiine diahnostuvannia neodnoridnykh konstruktsii i materialiv / vidpovid. red. Z. Т. Nazarchuk. Lviv, 2017. 488 s.
40. Pisarenko G. S., Strizhalo V. А. Eksperimentalnye metody v mekhanike deformiruemogo tverdogo tela. Kiev, 2018. 242 s.
41. Guz’ A. N., Dyshel M. Sh., Kuliev G. G., Milovanova O. B. Razrushenie i lokalnaia poteria ustoichivosti tonkostennykh tel s vyrezami. Prikl. mekhanika. 1981. Т. 17, №8. S. 3 – 24. https://doi.org/10.1007/BF00884086
42. Hudramovich V. S., Diskovskii I. A., Makeev E. M. Tonkostennye element zerkalnykh antenn. Kiev, 1986. 152 s.
43. Hudramovich V. S., Hart E. L., Klimenko D. V., Ryabokon’ S. A. Mutual influence of openings on strength of shell-type structures under plastic deformation. Strength of Materials. 2013. V. 45, Iss. 1. P. 1 – 9. https://doi.org/10.1007/s11223-013-9426-5
44. Hudramovich V. S., Klimenko D. V., Hart E. L. Vliianie vyrezov na prochnost tsilindricheskikh otsekov raket-nositelei pri neuprugom deformirovanii materiala. Kosmichna nauka i tekhnolohiia. 2017. Т. 23, № 6. S. 12 – 20.
45. Hart E. L., Hudramovich V. S. Proektsiino-iteratsiini skhemy realizatsii variatsiino-sitkovykh metodiv u zadachakh pruzhno-plastychnoho deformuvannia neodnoridnykh tonkostinnykh konstruktsii. Matematychni metody I fizyko-mechanichni polia. 2019. Т. 51, № 3. S. 24 – 39.
46. Nikitin P. I., Hudramovich V. S., Larionov I. F. Ustoichivost obolochek v usloviiakh polzuchesti. Polzuchest v konstruktsiakh: tez. dokl. Vsesoiuzn. Simpoziuma (Dniepropetrovsk, 1982 g.). Dniepropetrovsk, 1982. S. 3 – 5.
47. Hudramovich V. S. Ob issledovaniiakh v oblasti teorii polzuchesti v Institute tekhnicheskoi mekhaniki NANU i GKAU. Tekhn. mekhanika. 2016. №4. S. 85 – 89.
48. Hoff N. J., Jahsman W. E., Nachbar W. A. A study of creep collapse of a long circular shells under uniform external pressure. J. Aerospace Sci. 1959. Vol. 26, No 10. P. 663 – 669. https://doi.org/10.2514/8.8243
49. Barmin I. V. Tekhnologicheskiie obiekty nazemnoi infrastruktury raketno-kosmicheskoi tekhniki. V 2-kh kn. M., 2005. Kn. 1. 412 s. М., 2005. Kn. 2. 376 s.
50. Makhutov N. А., Matvienko D. G., Romanov А. N. Problemy prochnosti, tekhnogennoi bezopasnosti i konstruktsionnogo materialovedenia. М., 2018. 720 s.
51. Gokhfeld D. А., Sadakov О. S. Plastichnost i polzuchest elementov konstruktsii pri povtornykg nagruzheniiakh. М., 1984. 256 s.
52. Troshchenko V. Т., Sosnovskii L. А. Soprotivlenie ustalosti metallov i splavov: spravochnik v 2-kh t. Kiev, 1987. Т. 1. 510 s. Kiev, 1987. Т. 2. 825 s.
53. Manson S. S. and Halford G. R. Fatigue and durability of structural materials. ASM International Material Park. Ohio, USA, 2006. 456 p.
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Formation and Basic Parameters of Vortex Rings.
]]>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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