Search Results for “structural ring” – Collected book of scientific-technical articles

2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

Вацлав Самусевич

2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

Authors:

Aksenenko A. V.¹, Hurskyi O. I.¹, Klochkov A. S.¹, Kondratiuk Ye. A.¹, Senkin V. S.², Siutkina-Doronina S. V.²

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.

Full text (PDF) || Content 2020 (1)

Downloads: 44

Abstract views:

3605

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Ashburn; Matawan; Baltimore; Plano; Miami; Columbus; Ashburn; Columbus; Columbus; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Boardman; Seattle	25
Singapore	Singapore; Singapore; Singapore; Singapore; Singapore; Singapore	6
Ukraine	Sumy; Dnipro; Dnipro	3
Latvia	Riga; Riga	2
China	Shanghai	1
Finland	Helsinki	1
Unknown		1
India	Mumbai	1
Canada	Monreale	1
Germany	Falkenstein	1
Romania	Voluntari	1
Netherlands	Amsterdam	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

12.1.2024 Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge

manager — Mon, 17 Jun 2024 11:36:02 +0000

12. Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge

Authors:

Nadtoka V. M.¹, Shtapenko Ye. P.², Kraeva V. S.¹, Kraev M. V.¹

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.

Full text (PDF) || Content 2024 (1)

Downloads: 14

Abstract views:

1591

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Buffalo; Chicago; Ashburn; Dallas; Seattle; Portland; Seattle	7
Germany	Falkenstein; Falkenstein	2
France		1
Unknown		1
China	Shenzhen	1
Ukraine	Kremenchuk	1
Slovakia		1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

6.1.2024 New methods of load-carrying capacity prediction for the ultimately compressed frame structures

Дмитрий Макренко — Mon, 17 Jun 2024 07:56:18 +0000

6. New methods of load-carrying capacity prediction for the ultimately compressed frame structures

Authors:

Muliar Yu. M.¹, Fedorov V. M.¹, Triasuchov L. М.², Kalakutskyi R. G.¹

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine,¹; Kharkiv Aviation Institute, Kharkiv, Ukraine²

Page: Kosm. teh. Raket. vooruž. 2024, (1); 51-60

DOI: https://doi.org/10.33136/stma2024.01.051

Language: English

Annotation: Amid acute problems that arise in the field of rocket and space technology, mechanical engineering, and other fields and require a workable engineering solution, the problem of prediction and prevention of the unpredicted collapse of the structural members of the structures subjected to loading is considered. Prediction of the load-carrying capacity and residual life of the space frames during the long-term operation is based on the analysis of the stress and strain state, using readings from the strain and displacement pickups installed in the most loaded zones. In this case the yield strength of the structural material or the fatigue strength of the material may be considered as the criterion of the maximum load. At the same time the loss of stability of the compressed structural members used in the load-carrying thin-walled structures are among the potentially dangerous failure modes. In these cases such failure occurs unexpectedly without any visible signs of change in the initial geometry. Application of the adequate diagnostic techniques and methods of prediction of the maximum loads under compression conditions will make it possible to avoid the structural failures. In this case an assembly under test may be used for other purposes. To perform static strength testing, the rocket and space companies use costly compartments of as-built dimension. Therefore, keeping compartments safe solves an important problem of saving financial costs for hardware production. Nowadays this problem is particularly acute when ground testing the new technology prototypes.

Key words: space frames, load-carrying members, stress and strain state, loss of stability, prediction of the structural failure.

Bibliography:

Prochnost raketnyh konstruktsyi. Ucheb. posobie pod redaktsiyei V.I. Mossakovskogo. M.: Vyssh. shk., 1990. S. 359 (in Russian).
Truesdell C. A first course in rational continuum mechanics. The Johns Hopkins University, Baltimore, Maryland, 1972. Russian translation was published by Mir, M., 1975. P. 592.
Rabotnov Yu. Mehanika deformiruyemogo tverdogo tela.: Nauka, 1979. S. 744.
Bolotin V. Nekonservativnyie zadachi teoriyi uprugoy ustoychivosti. Phyzmatgiz, M., 1961. S. 339.
Feodosyev V. Izbrannyie zadachi i voprosy po soprotivleniyu materialov. Nauka. , 1973. S. 400.
Muliar Yu. M., Fedorov V.M., Triasuchev L.M. O vliyanii nachalnyh nesovershenstv na poteryu ustoychivosti sterzhney v usloviyah osevogo szhatiya. Kosmicheskaya tehnicka. Raketnoye vooruzheniye: Sb. nauch.-tehn. st. 2017. Vyp. 1 (113). S. 48-58. https://doi.org/10.15193/zntj/2017/113/210
Volmir A. Ustoychivost deformiruyemyh sistem. M., 1967. S. 984.
Muliar Yu. M. K voprosy ob ustoichivosty szhatogo sterzhnya. Tekhnicheskaya mekhanika. Dnepropetrovsk: ITM. 2000. No S. 51.
Muliar Yu. M., Perlik V.I. O matematicheskom modelnom predstavlenii informatsionnogo polia v nagruzhennoy deformiruyemoy sisteme. Informatsionnyie i telekommunikatsionnyie tehnologii. M.: Mezhdunar. akad. nauk informatizatsii, informatsionnyh protsessov i tehnologiy. 2012. No 15. S. 61.
Koniuhov S. N., Muliar Yu. M., Privarnikov Yu. K. Issledovaniye vliyaniya malyh vozmuschayuschih vozdeystviy na ustoychivost obolochki. Mehanika. 1996. 32, No 9. S. 50-65.

Full text (PDF) || Content 2024 (1)

Downloads: 18

Abstract views:

805

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Las Vegas; Buffalo; Dallas; New Haven; San Francisco; Chicago; Los Angeles; Seattle;; Portland; Ashburn	11
Germany	Falkenstein; Falkenstein	2
France		1
Unknown		1
China	Shenzhen	1
Singapore	Singapore	1
Ukraine	Kremenchuk	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system

manager — Fri, 14 Jun 2024 11:36:31 +0000

7. Selection of the functional units for the Cyclone-4M ILV separation system

Authors:

Logvinenko A. I., Makarenko A. O., Khomyak V. O., Olesiyuk A. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 61-71

DOI: https://doi.org/10.33136/stma2024.01.061

Language: Ukrainian

Annotation: Separation of the spent LV stages is one of the important problems of the rocket technology, which requires the comprehensive analysis of different types of systems, evaluation of their parameters and structural layouts. Basic requirements are specified that need to be taken into account when engineering the separation system: reliable and safe separation, minimal losses in payload capability, keeping sufficient distance between the stages at the moment of the propulsion system start. Detailed classification of their types («cold», «warm», «hot», «cold-launched» separation) is given and their technical substance with advantages and drawbacks is described. Certain types of «cold» and «warm» separation of the spent stages of such rockets as Dnepr, Zenit, Antares, Falcon-9 with different operating principle are introduced – braking with the spent stage and pushing apart two stages. Brief characteristics of these systems are given, based on the gas-reactive nozzle thrust, braking with solid-propellant rocket engines, separating with spring or pneumatic pushers. Development of the separation system for the advanced Cyclone-4M ILV is taken as an example and design sequence of stage separation is suggested: determination of the necessary separation velocity and capability of the separation units, determination of the number of active units, calculation of design and energy parameters of the separation units, analysis of the obtained results followed by the selection of the separation system. Use of empirical dependences is shown, based on the great scope of experimental and theoretical activities in the process of design, functional testing and flight operation of similar systems in such rockets as Cyclone, Dnepr and Zenit. According to the comparative analysis results, pneumatic separation system to separate Cyclone-4M Stages 1 and 2 was selected as the most effective one. Its basic characteristics, composition, overall view and configuration are specified. Stated materials are of methodological nature and can be used to engineer the separation systems for LV stages, payload fairings, spacecraft etc.

Key words: separation system, functional units of separation, «cold separation», «warm separation», pneumatic pusher, spring pusher, SPRE, gas-reactive nozzles, Zenit LV, Dnepr LV, Falcon 9 rocket, Cyclone-4М LV.

Bibliography:

Pankratov Yu. , Novikov A. V., Tatarevsky K. E., Azanov I. B. Dynamika perekhodnykh processov. 2014.
Sinyukov A. M., Morozov N. I. Konstruktsia upravlyaemykh ballisticheskykh raket. 1969.
Kabakova Zh. V., Kuda S. A., Logvinenko A. I., Khomyak V. A. Opyt razrabotki pneumosystemy dlya otdelenita golovnogo aerodynamicheskogo obtekatelya. Kosmicheskaya technika. Raketnoe vooruzhenie. 2017. Vyp. 2 (114).
Kolesnikov K. S., Kozlov V. V., Kokushkin V. V. Dynamika razdeleniya stupeney letatelnykh apparatov. 1977.
Antares – Spaceflight Insider: web site. URL: https://www. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023).
Falcon 9 – pexels: website. URL: https://www. pexels.com/Falcon 9 (data zvernennya 31.10.2023).
Kolesnikov K. , Kokushkin V. V., Borzykh S. V., Pankova N. V. Raschet i proektirovanie system razdeleniya stupeney raket. 2006.
Cyclone-4M – website URL: https://www.yuzhnote.com (data zvernennya 31.10.2023)
Logvinenko A. Sozdanie gasoreaktivnykh system otdeleniya i uvoda otrabotavshykh stupeney – noviy shag v RKT. Kosmicheskaya tekhnika. Raketnoe vooruzhenie, KBU, NKAU, vyp. 1, 2001.
Logvinenko A. I., Porubaimekh V. I., Duplischeva O. M. Sovremennye metody ispytaniy system i elementov konstruktsiy letatelnykh apparatov. Monografia. Dnepr, KBU, 2018.

Full text (PDF) || Content 2024 (1)

Downloads: 16

Abstract views:

1215

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Ashburn; Chicago; Chicago; Buffalo; Buffalo; Ashburn; San Francisco; Los Angeles; Seattle; Portland	10
Germany	Falkenstein; Falkenstein	2
France		1
Unknown		1
China	Shenzhen	1
Ukraine	Kremenchuk	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

11.2.2017 Remote Monitoring Method of Pneudraulic System Structural Elements Integrity

Виктория Лемех — Thu, 30 May 2024 12:33:16 +0000

11. Remote Monitoring Method of Pneudraulic System Structural Elements Integrity

Authors:

Babii H. M., Tishchenko Y. S., Mogilevtsev O. А.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 57-59

Language: Russian

Annotation: The remote control method of launch vehicle hydrosystem detachable joints airtightness by mass spectrometer at the Launch Complex in conditions of limited access to hydrosystem elements is under consideration. The additional design development of hydrosystems prior to article roll-out to the launch side is provided for control.

Key words:

Bibliography:

1. Volkov V. P., Kulik A. V. et al. Technological Processes of Strength and Leak Tests in Space Rocketry Production / Under the editorship of L. D. Kuchma. Dnepropetrovsk, 2014. 264 p.

2. Sanin F. P. et al. Leak-Tightness in Space Rocketry: Tutorial / F. P. Sanin, E. O. Dzhur, L. D. Kuchma, V. A. Naidyonov. Dnipropetrovsk, 1995. 168 p.

3. Babkin V. T., Zaichenko A. A. et al. Leak-Tightness of Hydraulic Systems Fixed Connections. М., 1977. 120 p.

4. OST 92-1527-89. Leak Tests of Products Using Mass-Spectrometer Helium Leak Detectors. Test Methods. 138 p.

Full text (PDF) || Content 2017 (2)

Downloads: 41

Abstract views:

602

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Boardman; Matawan; Baltimore; Plano; Dublin; Columbus; Monroe; Ashburn; Seattle; Ashburn; Ashburn; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn	21
Singapore	Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore	8
Germany	Frankfurt am Main; Frankfurt am Main; Falkenstein	3
Unknown	Brisbane;	2
Ukraine	Dnipro; Dnipro	2
Belgium	Brussels	1
Finland	Helsinki	1
Canada	Monreale	1
Romania	Voluntari	1
Netherlands	Amsterdam	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

manager — Fri, 29 Sep 2023 18:22:49 +0000

3. Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

Authors:

Degtiarov М. O.¹, Avramov K. V.²

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine²

Page: Kosm. teh. Raket. vooruž. 2020, (1); 26-33

DOI: https://doi.org/10.33136/stma2020.01.026

Language: Russian

Annotation: The study of thermal strength of the hold-down bay is considered. The hold-down bay is a cylindrical shell with the load-bearing elements as the standing supports. The case of the hold-down bay consists of the following structural elements: four standing supports and the compound cylindrical shell with two frames along the top and bottom joints. The purpose of this study was the development of a general approach for the thermal strength calculation of the hold-down bay. This approach includes two parts. Firstly, the unsteady heat fields on the hold-down bay surface are calculated by means of the semi-empirical method, which is based on the simulated results of the combustion product flow of the main propulsion system. The calculation is provided by using Solid Works software. Then the unsteady stress-strain behavior of the hold-down bay is calculated, taking into consideration the plastoelastic deformations. The material strain bilinear diagram is used. The finiteelement method is applied to the stress-strain behavior calculation by using NASTRAN software. The thermal field is assumed to be constant throughout the shell thickness. As a result of the numerical simulation the following conclusions are made. The entire part of the hold-down bay, which is blown by rocket exhaust jet, is under stress-strain behavior. The stresses of the top frame and the shell are overridden the breaking strength that caused structural failure. The structure of the hold-down bay, which is considered in the paper, is unappropriated to be reusable. The hold-down bay should be reconstructed by reinforcement in order to provide its reusability.

Key words: stress-strain behavior, finite-element method, plastoelastic deformations, breaking strength, reusability

Bibliography:

1. Elhefny A., Liang G. Stress and deformation of rocket gas turbine disc under different loads using finite element modeling. Propulsion and Power Research. 2013. № 2. P. 38–49. https://doi.org/10.1016/j.jppr.2013.01.002
2. Perakis N., Haidn O. J. Inverse heat transfer method applied to capacitively cooled rocket thrust chambers. International Journal of Heat and Mass Transfer. 2019. № 131. P. 150–166. https://doi.org/10.1016/j.ijheatmasstransfer.2018.11.048
3. Yilmaz N., Vigil F., Height J., et. al. Rocket motor exhaust thermal environment characterization. Measurement. 2018. № 122. P. 312–319. https://doi.org/10.1016/j.measurement.2018.03.039
4. Jafari M. Thermal stress analysis of orthotropic plate containing a rectangular hole using complex variable method. European Journal of Mechanics A /Solids. 2019. № 73. P. 212–223. https://doi.org/10.1016/j.euromechsol.2018.08.001
5. Song J., Sun B. Thermal-structural analysis of regeneratively cooled thrust chamber wall in reusable LOX / Methane rocket engines. Chinese Journal of Aeronautics. 2017. № 30. P. 1043–1053.
6. Ramanjaneyulu V., Murthy V. B., Mohan R. C., Raju Ch. N. Analysis of composite rocket motor case using finite element method. Materials Today: Proceedings. 2018. № 5. P. 4920–4929.
7. Xu F., Abdelmoula R., Potier-Ferry M. On the buckling and post-buckling of core-shell cylinders under thermal loading. International Journal of Solids and Structures. 2017. № 126–127. P. 17–36.
8. Wang Z., Han Q., Nash D. H., et. al. Thermal buckling of cylindrical shell with temperature-dependent material properties: Conventional theoretical solution and new numerical method. Mechanics Research Communications. 2018. № 92. P. 74–80.
9. Duc N. D. Nonlinear thermal dynamic analysis of eccentrically stiffened S-FGM circular cylindrical shells surrounded on elastic foundations using the Reddy’s third-order shear de-formation shell theory. European Journal of Mechanics A /Solids. 2016. № 58. P. 10–30.
10. Trabelsi S., Frikha A., Zghal S., Dammak F. A modified FSDT-based four nodes finite shell element for thermal buckling analysis of functionally graded plates and cylindrical shells. Engineering Structures. 2019. № 178. P. 444–459.
11. Trinh M. C., Kim S. E. Nonlinear stability of moderately thick functionally graded sandwich shells with double curvature in thermal environment. Aerospace Science and Technology. 2019. № 84. P. 672–685.
12. Лойцянский Л. Г. Механика жидкости и газа. М., 2003. 840 с.
13. Launder B. E., Sharma B. I. Application of the energy dissipation model of turbulence to the calculation of flow near a spinning disc. International Journal of Heat and Mass Transfer. 1974. № 1. P. 131–138.
14. Михеев М. А., Михеева И. М. Основы теплопередачи. М., 1977. 345 с.
15. Малинин Н. Н. Прикладная теория пластичности и ползучести. М., 1968. 400 с.

Full text (PDF) || Content 2020 (1)

Downloads: 48

Abstract views:

1721

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Boardman; Matawan; Boydton; Plano; Miami; Columbus; Columbus; Columbus; Detroit; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Ashburn; Boardman; Seattle; Portland; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Ashburn; Ashburn	26
Singapore	Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore	11
Ukraine	Dnipro; Kyiv; Dnipro	3
Germany	;; Falkenstein	3
Finland	Helsinki	1
Great Britain	London	1
Canada	Monreale	1
Romania	Voluntari	1
Netherlands	Amsterdam	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

19.1.2020 Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO

Вацлав Самусевич — Wed, 13 Sep 2023 12:02:02 +0000

19. Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO

Authors:

Samoilenko I. D., Voloshin V. V., Onofriienko V. I., Bezkorsyi D. M.

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

Full text (PDF) || Content 2020 (1)

Downloads: 50

Abstract views:

1818

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Boardman; Matawan; Baltimore; Plano; Columbus; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Seattle; Ashburn; Ashburn; Seattle; Tappahannock; Portland;; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Ashburn; Ashburn	24
Singapore	Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore	7
Ukraine	Kyiv; Kyiv; Kyiv; Dnipro	4
Great Britain	London; Newcastle upon Tyne	2
Romania	; Voluntari	2
Germany	Limburg an der Lahn; Falkenstein	2
China	Shanghai	1
India		1
Finland	Helsinki	1
Unknown		1
Indonesia		1
Canada	Monreale	1
Netherlands	Amsterdam	1
Serbia	Belgrade	1
Czech		1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

15.1.2020 Simulation of thermomechanical processes in functionally-gradient materials of inhomogeneous structure in the manufacturing and operation of rocket structural elements

Вацлав Самусевич — Wed, 13 Sep 2023 11:07:28 +0000

15. Simulation of thermomechanical processes in functionally-gradient materials of inhomogeneous structure in the manufacturing and operation of rocket structural elements

Authors:

Usov A. V., Kunitsyn М. V.

Organization:

Institute of Mechanical Engineering of Odessa National Polytechnic University, Odessa, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 137-148

DOI: https://doi.org/10.33136/stma2020.01.137

Language: Ukrainian

Annotation: The strength of real solids depends essentially on the defect of the structure. In real materials, there is always a large number of various micro defects, the development of which under the influence of loading leads to the appearance of cracks and their growth in the form of local or complete destruction. In this paper, based on the method of singular integral equations, we present a unified approach to the solution of thermal elasticity problems for bodies weakened by inhomogeneities. The purpose of the work is to take into account the heterogeneities in the materials of the elements of the rocket structures on their functionally-gradient properties, including strength. The choice of the method of investigation of strength and destruction of structural elements depends on the size of the object under study. Micro-research is related to the heterogeneities that are formed in the surface layer at the stage of preparation, the technology of manufacturing structural elements. Defectiveness allows you to adequately consider the mechanism of destruction of objects as a process of development of cracks. In studying the limit state of real elements, weakened by defects and constructing on this basis the theory of their strength and destruction in addition to the deterministic one must consider the probabilistic – statistical approach. In the case of thermal action on structural elements in which there are uniformly scattered, non-interacting randomly distributed defects of the type of cracks, the laws of joint distribution of the length and angle of orientation of which are known, the limiting value of the heat flux for the balanced state of the crack having the length of the “weakest link” is determined. The influence of heterogeneities of technological origin (from the workpiece to the finished product) that occur in the surface layer in the technology of manufacturing structural elements on its destruction is taken into account by the developed model. The strength of real solids depends essentially on the defect of the structure. In real materials, there are always many various micro defects, the development of which under the influence of loading leads to the appearance of cracks and their growth in the form of local or complete destruction. In this paper, based on the method of singular integral equations, we present a unified approach to the solution of thermal elasticity problems for bodies weakened by inhomogeneities. The purpose of the work is to take into account the heterogeneities in the materials of the elements of the rocket structures on their functionally gradient properties, including strength. The choice of the method of investigation of strength and destruction of structural elements depends on the size of the object under study. Micro-research is related to the heterogeneities that are formed in the surface layer at the stage of preparation, the technology of manufacturing structural elements. Defectiveness allows you to adequately consider the mechanism of destruction of objects as a process of development of cracks. In studying the limit state of real elements, weakened by defects and constructing on this basis the theory of their strength and destruction besides the deterministic one must consider the probabilistic – statistical approach. With thermal action on structural elements in which there are uniformly scattered, non-interacting randomly distributed defects of the cracks, the laws of joint distribution of the length and angle of orientation of which are known, the limiting value of the heat flux for the balanced state of the crack having the length of the “weakest link” is determined. The influence of heterogeneities of technological origin (from the workpiece to the finished product) that occur in the surface layer in the technology of manufacturing structural elements on its destruction is taken into account by the developed model. The solution of the singular integral equation with the Cauchy kernel allows one to determine the intensity of stresses around the vertexes of defects of the cracks, and by comparing it with the criterion of fracture toughness for the material of a structural element, one can determine its state. If this criterion is violated, the weak link defect develops into a trunk crack. Also, a criterion correlation of the condition of the equilibrium defect condition with a length of 2l was got, depending on the magnitude of the contact temperature. When the weld is cooled, it develops “hot cracks” that lead to a lack of welding elements of the structures. The results of the simulation using singular integral equations open the possibility to evaluate the influence of thirdparty fillers on the loss of functional properties of inhomogeneous systems. The exact determination of the order and nature of the singularity near the vertices of the acute-angled imperfection in the inhomogeneous medium, presented in the analytical form, is necessary to plan and record the corresponding criterion relations to determine the functional properties of inhomogeneous systems.

Key words: mathematical model, linear systems, singular integral equations, impulse response, defects, criteria for the destruction of stochastically defective bodies, Riemann problem, thermoelastic state

Bibliography:

1. Gakhov F. D. Kraievye zadachi. M.: Nauka,1977. 640 s.

2. Gakhov F. D. Uravneniia tipa svertki. M.: Nauka, 1978.296 s.

3. Litvinchuk G. S. Kraievye zadachi i singuliarnye integralnye uravneniia so sdvigom. M.: Nauka, 1977. 448 s.

4. Muskhelishvili N. I. Singuliarnye integralnye uravneniia. M.: Nauka, 1968. 512 s.

5. Panasiuk V. V. Metod singuliarnykh integralnykh uravnenii v dvukhmernykh zadachakh difraktsii. K.: Nauk. dumka, 1984. 344 s.

6. Siegfried PROSSDORF Einige Klassen singularer Gleichungen.Akademie Verlag Berlin, 1974. 494 s. https://doi.org/10.1007/978-3-0348-5827-4

7. Oborskii G. А. Modelirovanie sistem : monografiia. Odessa: Astroprint, 2013. 664 s.

8. Usov A. V. Matematicheskoe modelirovanie protsessov kontrolia pokrytiia elementov konstruktsii na baze SIU. Problemy mashinostroeniia. 2010. Т.13. №1. s. 98−109.

9. Kunitsyn M. V., Tribocorrosion research of NI-Al2O3/TIO2 composite materials obtained by the method of electrochemical deposition. M.V. Kunitsyn, A.V Usov. Zb. nauk. prats, Suchasni tekhnolohii v mashinobuduvanni. Vyp. 12. Kharkiv: NTU KhPI, 2017. s. 61−70.

10. Savruk M. P. Chislennyi analiz v ploskikh zadachakh teorii tershchin. K.: Nauk. dumka, 1989. 248 s.

11. Usov A. V. Vvedenie v metody optimizatsii i teoriiu tekhnicheskikh sistem. Odessa: Astroprint, 2005. 496 s.

12. Popov G. Ya. Kontsentratsiia uprugikh napriazhenii vozle shtampov, razrezov, tonkikh vkliuchenii i podkreplenii. M.: Nauka, 1982. 344 s.

13. Cherepanov G. P. Mekhanika khrupkogo razrusheniia. M.: Nauka., 1974. 640 s.

14. Stashchuk N. G. Zadachi mekhaniki uprugikh tel s treshchinopodobnymi defectami. K.: Nauk. dumka, 1993. 358 s.

15. Ekobori T. Nauchnye osnovy prochnosti i razrusheniia materialov. Per. s yap. K.: Nauk. dumka, 1978. 352 s.

16. Morozov N. F. Matematicheskie voprosy teorii treshchin. M.: Nauka, 1984. 256 s.

17. Popov G. Ya. Izbrannye trudy. Т. 1, 2. Odessa: VMV, 2007. 896 s.

18. Grigirian G. D., Usov A. V., Chaplia М. Yu. Vliianie shlifovochnykh defektov na prochnost detalei nesushchei sistemy. Vsesoiuzn. konf. Nadezhnost i dolgovechnost mashin i priborov. 1984. s.101−106.

19. Rais Dzh. Matematicheskie metody v mekhanike razrusheniia. Razrushenie. V 2 t. М.: Mir, 1975.Т.2. S. 204−335.

20. Karpenko G. V. Fiziko-khimicheskaia mekhanika konstruktsionnykh materialov: V 2-kh t. K. : Nauk. dumka, 1985. Т. 1 228 s.

21. Kormilitsina Е. А., Salkovskii F. М., Usov A. V., Yakimov А. V. Prichiny poiavliniia defektov pri shlifovanii magnitotverdykh splavov. Tekhnologiia elektrotekhnicheskogo proizvodstva. М.: Energiia. № 4. 1982. s.1−5.

22. Usov A. V. Smeshannaia zadacha termouprugosti dlia kusochno-odnorodnykh tel s vkliucheniiami i treshchinami. IV Vsesoiuzn. konf. Smeshannye zadachi mechaniki deformiruemogo tela: Tez. dokl.-Odessa,1990. s.116.

23. Yakimov А. V., Slobodianyk P. T., Usov A. V. Teplofizika mekhanicheskoi obrabotki. K.: Nauk. dumka,1991. S. 270.

24. Vitvitskii P. M., Popina S. Yu. Prochnost i kriterii khrupkogo razrusheniia stokhaticheski defektnykh tel. K.: Nauk. dumka, 1980. 187 s.

Full text (PDF) || Content 2020 (1)

Downloads: 42

Abstract views:

1736

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Boardman; Matawan; Baltimore;; Plano; Miami; Columbus; Columbus; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Seattle; Ashburn; Ashburn; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Ashburn	25
Singapore	Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore	7
Germany	;; Falkenstein	3
Ukraine	Odessa; Dnipro	2
Cambodia	Phnom Penh	1
Finland	Helsinki	1
Canada	Monreale	1
Romania	Voluntari	1
Netherlands	Amsterdam	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

Вацлав Самусевич — Wed, 13 Sep 2023 06:15:53 +0000

5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

Authors:

Hudramovych V. S.², Sirenko V. M.¹, Klimenko D. V.¹, Hart Ye. L.³

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.

Full text (PDF) || Content 2020 (1)

Downloads: 43

Abstract views:

2555

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Boardman; Ashburn; Columbus; Matawan; Baltimore; North Bergen; Boydton; Plano; Miami; Dublin; Dublin; Detroit; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Ashburn; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Ashburn	28
Singapore	Singapore; Singapore; Singapore; Singapore; Singapore; Singapore	6
Ukraine	Odessa; Dnipro	2
Finland	Helsinki	1
Ethiopia	Addis Ababa	1
Canada	Monreale	1
Germany	Falkenstein	1
Latvia	Riga	1
Romania	Voluntari	1
Netherlands	Amsterdam	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud

15.2.2018 Topical Issues of Creation of Space Rocket Thermostatic System Mating Points

Вацлав Самусевич — Thu, 07 Sep 2023 12:09:41 +0000

15. Topical Issues of Creation of Space Rocket Thermostatic System Mating Points

Authors:

Bigun S. O.¹, Khorolskyi M. S.²

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; State Enterprise DINTEM Ukrainian Research Design-Technological Institute of Elastomer Materials and Products²

Page: Kosm. teh. Raket. vooruž. 2018 (2); 132-138

DOI: https://doi.org/10.33136/stma2018.02.132

Language: Russian

Annotation: The problem is defined of designing the space rocket low-pressure air thermostating systems joints. The basic requirements imposed to the joints from the side of space rocket and ground complex are determined and stated. For this purpose, the analysis of operating conditions and possible situations during rocket launches is made. Besides, the methodological principles based on problematic, systematic, and structuralfunctional approach were applied using the theoretical and empirical capabilities, attraction of general scientific and special investigation methods, as well as historical and logical methods. The list of topical issues is reflected for implementation in joint’s design. The ways are proposed to create the joints meeting the requirements imposed. As a result, it was ascertained that the joints can be made of simpler and at the same time failure-free design in the form of combined triune rubber hose fitted with a metal fixation/release unit installed on a sealing flange in a special groove. Of special note is the versatility of the proposed technical solution for use in any of the space launch systems known in the world’s practice. The article is concluded with following: the basic requirements have been formulated for ground complexes thermostating systems joints to ensure space rockets prelaunch processing and launch, in doing so, the topical problems were defined; the scientific principles were proposed to design the thermostating systems joints for comprehensive solution of the topical problems , including potential critical situations; the thermostating systems joints have been developed, manufactured and have successfully passed the ground development tests with simulation of the conditions maximally close to operating ones at static operating air pressures and in off-nominal situations.

Key words: planetary roving vehicle, self-propelled modular platform, generic module, interchangeability

Bibliography:

1. Bigun S. A., Khorolsky M. S et al. Types and Design Features of Thermostating System Mating Points of Launch Vehicle Payload Units and Launch Vehicle and Spacecraft Bays. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2013. Issue 1. 123 p.

2. Bigun S. A., Khorolsky M. S et al. Experimental Investigations of Cyclone-4 ILV Thermostating System Mating Points Test Results. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2016. Issue 2. 105 p.

Full text (PDF) || Content 2018 (2)

Downloads: 39

Abstract views:

583

Dynamics of article downloads

Dynamics of abstract views

Downloads geography

Country	City	Downloads
USA	Boardman; Matawan; Baltimore; Plano; Dublin; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Seattle; Ashburn; Seattle; Seattle; Tappahannock; Portland; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Ashburn; Boardman	23
Singapore	Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore	7
Ukraine	Dnipro;	2
Finland	Helsinki	1
Unknown		1
Philippines	Mandaluyong City	1
Canada	Monreale	1
Germany	Falkenstein	1
Romania	Voluntari	1
Netherlands	Amsterdam	1

Downloads, views for all articles

Articles, downloads, views by all authors

Articles for all companies

Geography of downloads articles

Keywords cloud