Keywords cloud
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. 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.
]]>6. New methods of load-carrying capacity prediction for the ultimately compressed frame structures
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.
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Turning of space hardware and services into marketable commodity requires their new qualities that determine competitiveness. Key words: space hardware , launch services , performance characteristics , operation model , organizational-and-technical decisions Bibliography: 1. space hardware , launch services , performance characteristics , operation model , organizational-and-technical decisions .
]]>21. Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 184-192
DOI: https://doi.org/10.33136/stma2020.01.184
Language: Russian
Annotation: The article deals with the problems of applying new approaches to formation and improvement of operation system. Turning of space hardware and services into marketable commodity requires their new qualities that determine competitiveness. The main task of presented works was approbation of new approaches to improvement of space launch systems operation quality and operation process effectiveness by the example of prospective Cyclone-4M space rocket complex. The works to form and improve its operation system were performed using the methods based on general theory of space systems operation and the pocedures based on the results of research work conducted by Yuzhnoye SDO in 2015 for analytical evaluation of launch services costs. The topicality of the article is confirmed by the results of practical application of new approaches in main directions of Cyclone-4M space rocket complex operation system improvement, which allowed increasing commercial attractibility of Yuzhnoye SDO-developed systems due to reduction of direct recurring costs and annual expenses. The article describes the course of development of operation model of a created object; based on investigation of the processes of this model, the object’s performance characteristics are detemined. The basis of the article are the organizational-and-technical decisions used herewith and the results obtained for Cyclone-4M space rocket complex. The article is of practical interest for specialists involved in creation of space rocket complexes and other sophisticated systems where the operation system is a multi-level organizational-technical system.
Key words: space hardware, launch services, performance characteristics, operation model, organizational-and-technical decisions
Bibliography:
1. Analiticheskaia otsenka ob’ema rabot i zatrat na puskovye uslugi i napravleniia rabot dlia ikh snizheniia v perspektivnykh RKK razrabotki GP “KB “Yuzhnoye”: tekhn. otchet / GP “KB “Yuzhnoye”. Dnepropetrovsk, 2015. 344 s.
2. Teoriia i praktika ekspluatatsii ob’ektov kosmicheskoi infrastruktury: monografiia / N. D. Anikeichik i dr. SPb., 2006. Т. 1: Ob’ekty kosmicheskoi infrastruktury. 400 s.
3. Ispytaniia i ekspluatatsiia raketnykh kompleksov: kurs lektsii / А. V. Agarkov i dr.; pod red. А. V. Degtyareva. GP “KB “Yuzhnoye”. Dnipro, 2016. Kn. 1. 505 s.
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Keywords cloud
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).
]]>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:
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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.
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Keywords cloud
2018 (2); 151-156 DOI: https://doi.org/10.33136/stma2018.02.151 Language: Russian Annotation: Contemporary trends in developing space-rocket hardware indicate the increased demand for light and ultra-light rockets.
]]>18. Angular Stabilization of an Object Rapidly Rotating around Longitudial Axis
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2018 (2); 151-156
DOI: https://doi.org/10.33136/stma2018.02.151
Language: Russian
Annotation: Contemporary trends in developing space-rocket hardware indicate the increased demand for light and ultra-light rockets. The first trend in developing the up-to-date light and ultra-light rocket hardware includes improving accuracy of cargo delivery to the specified area; the second trend covers the enhancement of energetic properties and the reduction of production and operational costs. Spinning about the longitudinal axis of symmetry may be one of the ways to improve the light and ultra-light rocket hardware in these trends. Spinning significantly increases stability of a moving object and partially evens out the negative impact of external and internal disturbing factors (skewness and eccentricities of propulsion system and control elements, wind). Refusal to use systems that provide stabilization about the longitudinal axis of symmetry leads to reduction in mass of the control system equipment, thus increasing energetic perfection of the rocket hardware. Hence, rotation of the rocket about the longitudinal axis may be caused by the spinning elements on purpose as well as by disturbing impacts in case of control failure in the roll channel. This article considers suggestions on algorithmic realization of light rocket control methods under conditions of rapid rotation about the longitudinal axis for each of the options mentioned above. This article offers control methods for the rocket, rotating about the longitudinal axis, that provide angular stabilization, improve the transient quality, and determine the angle of roll after program stop of rotation about the longitudinal axis.
Key words: angular stabilization, spinning, rotation about the longitudinal axis of symmetry, light rocket, drive delay, determination of the angle of roll, aerodynamic control surfaces, algorithm for maneuver determination of the angle of roll
Bibliography:
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2. Igdalov I. M. et al. Rocket as Control Object: Tutorial / Under the editorship of S. N. Konyukhov. Dnepropetrovsk, 2004. 544 p.
3. Pugachyov V. S. et al. Rocket Control Systems and Flight Dynamics. М., 1965. 610 p.
4. Sikharulidze Y. G. Flying Vehicles Dynamics. М., 1982. 352 p.
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Keywords cloud
Aerospace Hardware and Technology.
]]>11. Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Kharkiv Aviation Institute, Kharkiv, Ukraine2 .
Page: Kosm. teh. Raket. vooruž. 2018 (1); 63-68
DOI: https://doi.org/10.33136/stma2018.01.063
Language: Russian
Annotation: Several measures to ensure long service life of electrochemical batteries are proposed: electrochemical battery performance evaluation, study of theoretical basis for improvement and building of experimental bench equipment.
Key words:
Bibliography:
1. Davidov А. О. Development of Technique of Alkaline Nickel-Cadmium Accumulators Recovery to Prolong their Service Life. Aerospace Hardware and Technology. 2009. No. 8 (65). P. 132-137.
2. Bezruchko K. V., Vasilenko A. S., Davidov A. О., Kharchenko А. А. Recovery of Open-Type Nickel-Cadmium Accumulators Capacity by Acting on Active Mass of Oxide-Nickel Electrode. Problems and Chemistry and Chemical Technology. 2002. No. 2. P. 66-70.
3. Azarnov A. L. et al. Express-Diagnostics Technique for Electrochemical Accumulators. The ХII International Scientific-Practical Youth Conference “Man and Space”: Collection of abstracts. Dnepropetrovsk, 2010. P. 78.
4. Bezruchko K. V., Davidov A. O. Express-Diagnostics Method for Electrochemical Energy Storage Units of Space Rocketry Power Systems. Space Technologies: Present and Future: The III International Conference: Collection of Abstracts (Dnepropetrovsk, 20-22 April, 2011). Dnepropetrovsk, 2011. P. 5-6.
5. Bezruchko K. V., Davidov A. O., Sinchenko S. V. Pulse Diagnostics Method for Nickel-Cadmium Accumulators. The V Scientific–Technical Conference “Present-Day Problems of Space Rocketry and Space Technologies”: Collection of abstracts. Kharkiv, 2010. P. 13.
6. Bezruchko K. V., Davidov A. O., Katorgina J. G., Sinchenko S. V., Shirinsky S. V. Method of Predicting the Performance of Electrochemical Batteries Working during Long Time in Space Rocketry Power Systems. Electrical and Electronic Engineering. 2013. Vol. 3 (3). P. 81-85.
7. Bezruchko K. V. et al. Development and Approbation of Mathematical Model to Predict the Characteristics of Electrochemical Accumulators of Space Rocketry Power Systems. MAI News. 2013, Vol. 20, No. 1. P. 38-49.
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The ІХ International Scientific-Technical Conference “Gyro Technologies, Navigation, Motion Control, and Aerospace Hardware Designing” (Ukraine, Kyiv, 17–18 April, 2013): Proceedings, Part 1.
]]>26. State of the Art and Prospects for Nuclear-Quadrupole Resonance Thermometry in Ukraine
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Ivan Franko National University of Lviv, Lviv, Ukraine2; Research and Production Center for Standartization, Metrology, Lviv, Ukraine3
Page: Kosm. teh. Raket. vooruž. 2017 (2); 146-150
Language: Russian
Annotation: The information is presented on the development of nuclear quadrupole resonace thermometry instruments at Yuzhnoye SDO and other Ukrainian companies. The problems are analyzed arising at the creation of standard wide-band nuclear quadrupole resonance temperature meters, the ways to overcome them, and the possibilities of improving due to the use of modern integrated electronics. It is shown that the methods of building the instruments based on nuclear quadrupole resonance proposed and implemented in Ukraine are not inferior to the foreign ones.
Key words:
Bibliography:
1. Dehmelt H. G., Krüger H. Kurze Originalmitteilungen. Kernquadrupolfrequenzen in festem Dichloräthylen. Naturwiss. No. 37. 1950. P. 111–112.
2. Bayer H. On the Theory of Spin-lactice Relaxation in Molecular Crystals. J. Phys. 1951. Vol. 129, No. 4. P. 227-238.
3. Lenovenko A. M. Quantum Portable Working Frequency Standard / А. М. Lenovenko, V. V. Parakuda, N. O. Koval’chuk. The ІХ International Scientific-Technical Conference “Gyro Technologies, Navigation, Motion Control, and Aerospace Hardware Designing” (Ukraine, Kyiv, 17–18 April, 2013): Proceedings, Part 1. К., 2013. P. 218–223.
4. Benedek G. B., Kushida T. Precise Nuclear Resonance Thermometry. The Review of Scientific Instruments. 1957. Vol. 28, No. 2. P. 92-95.
5. Vanier J. Temperature Dependence of the Pure Nuclear Quadrupole Resonance Frequency in KClO3. Canadian Journal of Physics. 1960. Vol. 38, No. 11. P. 1397-1405.
6. Utton D. B. Nuclear Resonance Thermo-metry. Metrologia. 1967. Vol. 3, No. 4. P. 98-104.
7. NQR standard Thermometer (model 2571). Catalogue of Yokogawa Electric Works. Japan, 1983.
8. Ohte A., Iwaoka H. A Precision on Nuclear Quadrupole Resonance Thermometer. IEEE Trans. on Instrum. аnd Measurement. 1976. Vol. IM-25, No. 4. P. 357-362.
9. Ohte A., Iwaoka H. Accurate Calibration A Precision of New NQR Thermometer (203 K to 398 K Range Calibration at the NRML). Metrologia. 1979. Vol. 15, No. 4. P. 195–199.
10. Utton D. B. Sample purity and the N.Q.R. of Cl35 in KClO3 at 0-C. J. Res. NBS. 1967. 71A. P. 125.
11. Lenovenko A. M., Koval’chuk N. O. Standard Nuclear-Quadrupole Resonance Thermometer YaKRT-5M. Proceedings of VІІ International Scientific-Technical Conference “Metrology and Measuring Instruments ” (Metrology 2010) in 2 volumes (Kharkiv, 12-14 October, 2010). P. 247-250.
12. Lenovenko A. Measuring Complex for Calibration, Checking and Certification of Temperature Measurement Instruments Based on Standard Nuclear-Quadrupole Thermometer of First Class YaKRT-5M / А. Lenovenko, B. Stadnik, P. Stolyarchuk, V. Parakuda, N. Koval’chuk. Measuring Instruments and Metrology. Lviv, 2013. No. 74. P. 127-132.
13. Lenovenko A. M. Theoretical and Experimental Investigations of Super-Regenatory Detectors of Nuclear Quadrupole Resonance / Dissertation of Candidate of Physical and Mathematical Sciences. Lviv, 1971. 136 p.
14. Vasilyuk V. et al. Nature of Signal in Super-Regenatory Detectors of Nuclear Quadrupole Resonance / Vasilyuk V., Lenovenko А., Stolyarchuk P. Measuring Instruments and Metrology. 2005. No. 65. P. 7–10.
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System Designing and Analysis of Aerospace Hardware Characteristics: Collection of scientific works / Science Editor A. System Designing and Analysis of Aerospace Hardware Characteristics: Collection of scientific works / Science Editor A.
]]>22. Advanced Aluminum Alloys for Launch Vehicle Pipeline Parts Manufacture
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2.
Page: Kosm. teh. Raket. vooruž. 2017 (2); 127-130
Language: Russian
Annotation: The comparison has been made of mechanical characteristics based on yield strength values of prospective aluminum alloys and steels with the stresses arising in pipeline parts. The conclusions have been drawn about the principal feasibility of manufacturing the pipelines of given materials and replacing the steels with the high-strength aluminum alloys for majority of the parts.
Key words:
Bibliography:
1. Davydov S. A. Analysis of Overall Dimensions of Launch Vehicle Pipeline Parts from Viewpoint of their Manufacturing by Method of Indirect Extrusion on Vertical Presses / S. A. Davydov, О. V. Bondarenko, Y. V. Tishchenko. System Designing and Analysis of Aerospace Hardware Characteristics: Collection of scientific works / Science Editor A. S. Davydov, Doctor of Engineering Science. Dnipropetrovsk, 2015. P. 23-28.
2. Alekseyev Y. S. Space Rocket Flying Vehicles Manufacturing Technology: Tutorial / Y. S. Alekseyev, E. O. Dzhur, О. V. Kulik, L. D. Kuchma, E. Y. Nikolenko, V. V. Khutorny / Under the editorship of E. O. Dzhur, Doctor of Engineering Science. Dnipropetrovsk, 2007. 480 p.
3. Birger I. A., Iosilevich B. G. Threaded and Flange Connections. М., 1990. 368 p.
4. Timoshenko S. P. Platelets and Shells / Translation from English V. I. Kontovt. М., L., 1948. 460 p.
5. GOST 19749-84. Fixed Detachable Connections of Pnemohydraulic Systems. Closed Regulating Valves. Types and Technical Requirements. М., 1984. 21 p. (USSR State Standards).
6. Bondarenko О. Sealing of Pipelines Flange Connections in Conditions of Fasteners Tightening Torgue Reducing / O. Bondarenko, A. Dziub. Applied Mechanics and Materials. Vol. 630 (2014). Switzerland: Trans tech Publications, 2014. P. 283-287.
7. Bondarenko O. V. Preliminary Determination of Geometrical Dimensions of Bellows Made of Aluminum Alloys / О. V. Bondarenko, Y. K. Demchenko. System Designing and Analysis of Aerospace Hardware Characteristics: Collection of scientific works / Science Editor A. S. Davydov, Doctor of Engineering Science. Dnipropetrovsk, 2016. P. 3-8.
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In different countries they have their own characteristics, depending on the type and performance of the launch vehicles, infrastructure features (geography of the site, nomenclature of the space objects, development level of rocket and space technology), problems that are solved during launches, etc. Launch sites are the combination of technologically and functionally interconnected mobile and fixed hardware, controls and facilities, designed to support and carry out all types of operations with integrated launch vehicles. Space Technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
]]>5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
Organization:
The Institute of Technical Mechanics, Dnipro, Ukraine1; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine2; Oles Honchar Dnipro National University, Dnipro, Ukraine3
Page: Kosm. teh. Raket. vooruž. 2019, (1); 28-37
DOI: https://doi.org/10.33136/stma2019.01.028
Language: Russian
Annotation: This article contains results of methodology and standards development for life prediction of launch site structures to launch various types’ launch vehicles into near-earth orbit. Launch sites have been built in various countries of the world (European Union, India, China, Korea, Russia, USA, Ukraine, France, Japan, etc.). In different countries they have their own characteristics, depending on the type and performance of the launch vehicles, infrastructure features (geography of the site, nomenclature of the space objects, development level of rocket and space technology), problems that are solved during launches, etc. Solution of various issues, arising in the process of development of the standards for justification of launch site life is associated with the requirement to consider complex problems of strength and life of nonuniform structural elements of launch sites and structures of rocket and space technology. Launch sites are the combination of technologically and functionally interconnected mobile and fixed hardware, controls and facilities, designed to support and carry out all types of operations with integrated launch vehicles. Launch pad, consisting of the support frame, flue duct lining and embedded elements for frame mounting, is one of the principal components of the launcher and to a large extent defines the life of the launch site. Main achievements of Ukrainian scientists in the field of strength and life are specified, taking into account the specifics of various branches of technology. It is noted that the physical nonlinearity of the material and statistical approaches determine the strength analysis of useful life. Main methodological steps of launch site structures life prediction are defined. Service limit of launch site is suggested to be the critical time or the number of cycles (launches) over this period, after which the specified limiting states are achieved in the dangerous areas of the load-bearing elements: critical cracks, destruction, formation of unacceptable plastic deformations, buckling failure, corrosion propagation, etc. Classification of loads acting on the launch sites is given. The useful life of launch site is associated with estimation of the number of launches. Concept of low and multiple-cycle fatigue is used. Developing strength standards and useful life calculation basis, it is advisable to use modern methods of engineering diagnostics, in particular, holographic interferometry and acoustic emission, and to develop the high-speed circuits of numerical procedures for on-line calculations when testing the designed systems.
Key words: classification of loads and failures; shock wave, acoustic and thermal loads; low-cycle fatigue; hierarchical approach in classification; projection-iterative schemes of numerical procedur
Bibliography:
1. Vidy startovykh kompleksov: GP KB «Yuzhnoye»: Rezhim dostupa. http://www.yuzhnoe.com/presscenter/media/ photo/techique/launch-vehique.
2. Modelyuvannya ta optimizatsia v nermomechanitsi electroprovidnykh neodnoridnykh til: u 5 t. / Pid. zag. red. akad. NANU R. M. Kushnira. Lvyv: Spolom, 2006–2011. T. 1: Termomechanika bagatokomponentnykh til nyzkoi electroprovodnosti. 2006. 300 p. T. 2: Mechanotermodiffusia v chastkovo prozorykh tilakh. – 2007. 184 p. T. 3: Termopruzhnist’ termochutlyvykh til. 2009. 412 p. T. 4: Termomechanica namagnychuvannykh electroprovodnykh nermochutlyvykh til. 2010. 256 p. T. 5. Optimizatsia ta identifikatsia v termomechanitsi neodnoridnykh til. 2011. 256 p.
3. Prochnost’ materialov I konstruktsiy / Pod obsch. red. acad. NANU V. T. Troschenko. K.: Academperiodika, 2005.1088 p.
4. Bigus G. A. Technicheskaya diagnostica opasnykh proizvodstvennykh obiektov/ G. A. Bigus, Yu. F. Daniev. М.: Nauka, 2010. 415 p.
5. Bigus G. A., Daniev Yu. F., Bystrova N. A., Galkin D. I. Osnovy diagnostiki technicheskykh ustroistv I sooruzheniy. M.: Izdatelstvo MVTU, 2018. 445 p.
6. Birger I. A., Shorr B. F., IosilevichG. B. Raschet na prochnost’ detaley machin: spravochnik. M.: Mashinostroenie, 1993. 640 p.
7. Hudramovich V. S. Ustoichivost’ uprugoplasticheskykh obolochek. K.: Nauk. dumka, 1987. 216 p.
8. Hudramovich V. S. Teoria polzuchesti i ee prilozhenia k raschetu elementov konstruktsiy. K.: Nauk. dumka, 2005. 224 p.
9. Hudramovich V. S., Klimenko D. V., Gart E. L. Vliyanie vyrezov na prochnost’ cylindricheskykh otsekov raketonositeley pri neuprugom deformirovanii materiala/ Kosmichna nauka i technologia. 2017. T. 23, № 6. P. 12–20.
10. Hudramovich V. S., Pereverzev Ye. S. Nesuschaya sposobnost’ sposobnost’ i dolgovechnost’ elementov konstruktsiy. K.: Nauk. dumka, 1981. 284 p.
11. Hudramovich V. S., SIrenko V. N., Klimenko D. V., Daniev Yu. F. Stvorennya metodologii nornativnykh osnov rozrakhunku resursu konstruktsii startovykh sporud ksomichnykh raket-nosiiv / Teoria ta practika ratsionalnogo proektuvannya, vygotovlennya i ekspluatatsii machinobudivnykh konstruktsiy: materialy 6-oy Mizhnar. nauk.-techn. conf. (Lvyv, 2018). Lvyv: Kinpatri LTD, 2018. P. 5–7.
12. Hudramovich V. S., Skalskiy V. R., Selivanov Yu. M. Golografichne ta akustico-emissine diagnostuvannya neodnoridnykh konstruktsiy i materialiv: monografia/Za red. akad. NANU Z. T. Nazarchuka. Lvyv: Prostir-M, 2017. 492 p.
13. Daniev Y. F. Kosmicheskie letatelnye apparaty. Vvedenie v kosmicheskuyu techniku/ Pod obsch. red. A. N. Petrenko. Dnepropetrovsk: ArtPress, 2007. 456 p.
14. O klassifikatsii startovogo oborudovania raketno-kosmicheskykh kompleksov pri obosnovanii norm prochnosti/ A. V. Degtyarev, O. V. Pilipenko, V.S. Hudramovich, V. N. Sirenko, Yu. F. Daniev, D. V. Klimenko, V. P. Poshivalov// Kosmichna nauka i technologia. 2016. T. 22, №1. P. 3–13. https://doi.org/10.15407/knit2016.01.003
15. Karmishin A. V. Osnovy otrabotky raketno -kosmicheskykh konstruktsiy: monografia. M.: Mashinostroenie, 2007. 480 p.
16. Mossakovskiy V. I. Kontaktnyue vzaimodeistvia elementov obolochechnykh konstruktsiy/ Kosmicheskaya technika. Raketnoye vooruzhenie. Space Technology. Missile Armaments. 2019. Vyp. 1 (117) 37. K.: Nauk. dumka, 1988. 288 p.
17. Pereverzev Ye. S. Sluchainye signaly v zadachakh otsenki sostoyaniya technicheskikh system. K.: Nauk. dumka, 1992. 252 p.
18. Prochnost’, resurs, zhivuchest’ i bezopasnost’ mashin/ Otv. red. N. A. Makhutov. M.: Librokom, 2008. 576 p.
19. Technichna diagnostika materialov I konstruktsiy: Dovidn. posibn. u 8 t. / Za red. acad. NANU Z. N. Nazarchuka. T. 1. Ekspluatatsina degradatsia konstruktsiynykh materialiv. Lvyv: Prostir-M, 2016. 360 p.
20. TEchnologicheskie obiekty nazemnoy infrastructury raketno-kosmicheskoy techniki: monografia/ Pod red. I. V. Barmina. M.: Poligrafiks RPK, 2005. Kn. 1. 412 p.; 2006. Kn. 2. 376 p.
21. Нudrаmоvich V. S. Соntact mechanics of shell structures under local loading/ International Аррlied Месhanics. 2009. Vol. 45, № 7. Р. 708– 729. https://doi.org/10.1007/s10778-009-0224-5
22. Нudrаmоvich V. Еlесtroplastic deformation of nonhomogeneous plates / I. Eng. Math. 2013. Vol. 70, Iss. 1. Р. 181–197. https://doi.org/10.1007/s10665-010-9409-5
23. Нudrаmоvich V. S. Mutual influence of openings on strength of shell-type structures under plastic deformation / Strenght of Materials. 2013. Vol. 45, Iss. 1. Р. 1–9. https://doi.org/10.1007/s11223-013-9426-5
24. Mac-Ivily A. J. Analiz avariynykh razrusheniy / Per. s angl. M.: Technosfera, 2010. 416 p.
25. Наrt Е. L. Ргоjесtion-itеrаtive modification оf the method of local variations for problems with a quadratic functional / Journal of Аррlied Мahtematics and Meсhanics. 2016. Vol. 80, Iss. 2. Р. 156–163. https://doi.org/10.1016/j.jappmathmech.2016.06.005
26. Mesarovich M. Teoria ierarkhicheskykh mnogourovnevykh system/ M. Mesarovich, D. Makho, I. Tohakara / Per. s angl. M.: Mir, 1973. 344 p.
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Keywords cloud
The possibility and suitability of the selective laser melting technology to manufacture parts and space-rocket hardware are evaluated.
]]>25. Technological Peculiarities of Manufacturing Products of Irregular Profile by Method of Selective Laser Melting of 316L Powder Metal Material
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 171-181
DOI: https://doi.org/10.33136/stma2019.01.171
Language: Russian
Annotation: This article considers the practical data on parts (specimens) manufacturing from powder metal material 316L using the innovative method of selective laser melting; the comparative study of the structure and physical and mechanical properties of 316L material, the combined influence of heat treatment and specimen orientation relative to the arrangement plate on the physical and mechanical properties and structure of specimens made of 316L alloy. Results are presented of the following: comparative study of the physical and mechanical properties and structure of specimens, manufactured using the selective laser melting technologies with horizontal and vertical placement relative to the arrangement plate; dependence of the ultimate strength and unit elongation on the annealing temperature. The possibility and suitability of the selective laser melting technology to manufacture parts and space-rocket hardware are evaluated. Experimental study of the specimens heat treatment conditions after selective laser melting enabled the definition of the optimal condition for the 316L alloy and have shown that heat treatment of the manufactured specimens under the heating at 1230 °С with the subsequent tempering at the temperature of 510 °С gives the homogeneous structure to the material of specimens made of alloy 316L, its dendritic structure, inherent in the specimen material in its initial condition, disappears after selective laser melting. Results of the mechanical tests of the obtained specimens have shown that the technology of selective laser melting provides development of products made of powder metal material 316L with optimal complex of physical and mechanical properties. It is shown that transition to the selective laser melting technology will enable production of the aerospace products, in particular geometrically-complex parts made of powder metal material 316L, in one technological cycle, excluding cutting, punching, refinement, cropping, welding, manufacturing of special tools or stamps
Key words: specimens, heat treatment, alloy, physical and mechanical properties, technological cycle
Bibliography:
1. Dovbysh V. M., Zabednev P. V., Zelenko M. A. Additivnye technologii I izdeliya iz metalla// Bibliotechka liteischika. №8–9. 2014. P. 33-38.
2. Kempen K., Thijs L., Van Humbeeck J., Kruth J.-P. Mechanical properties of AlSi10Mg produced by SLM / Physics Procedia. №39. 2012. Р. 439–446. https://doi.org/10.1016/j.phpro.2012.10.059
3. Olakanmi E. O. Selective laser sintering/melting (SLS/SLM) of pure Al, Al–Mg, and Al–Si powders: Effect of processing conditions and powder properties / Journal of Materials Processing Technology. №213. 2013. Р. 1387–1405. https://doi.org/10.1016/j.jmatprotec.2013.03.009
4. Eleftherios Louvis, Fox Peter, Sutcliffe Christopher J. Selective laser melting of aluminium components // Journal of Materials Processing Technology. – №211. 2011. Р. 275–284. https://doi.org/10.1016/j.jmatprotec.2010.09.019
5. Aboulkhair Nesma T., Everitt Nicola M., Ashcroft Ian, Tuck Chris. Reducing porosity in AlSi10Mg parts processed by selective laser melting // Additive Manufacturing Journal. №1–4. 2014. Р. 77 – 86. https://doi.org/10.1016/j.addma.2014.08.001
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Options of Their Use in Space Rocket Hardware Authors: Naiden O. The use of gasars in space hardware will help to considerably reduce the mass of launch vehicle structural elements without worsening strength properties. Options of Their Use in Space Rocket Hardware" Космическая техника. Options of Their Use in Space Rocket Hardware" Космическая техника. Options of Their Use in Space Rocket Hardware", Космическая техника. Options of Their Use in Space Rocket Hardware Автори: Naiden O. Options of Their Use in Space Rocket Hardware Автори: Naiden O. Options of Their Use in Space Rocket Hardware Автори: Naiden O. Options of Their Use in Space Rocket Hardware Автори: Naiden O.
]]>24. Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 163-170
DOI: https://doi.org/10.33136/stma2019.01.163
Language: Russian
Annotation: Gasars is a new type of porous cast materials manufactured on the basis of metals and their alloys, some types of ceramics. The basis of the process is gas-eutectic conversion in the system metal-hydrogen. The process of investigation and creation of gasars was commenced in 1979 in the National Metallurgical Academy of Ukraine and is currently continued in Ukraine, the USA, China, Japan, South Korea, Poland and others. The gasars production technological process consists in melting the specified material (metal, alloy, ceramics) in hydrogen (or other active gas) atmosphere at a certain pressure. After the melt is saturated with active gas to a certain concentration, the crystallization process begins at which the pore formation process is launched. As the pores growth occurs perpendicular to crystallization front, the orientation of heat withdrawal influences pores location. So, for example, to obtain radial porosity, radial heat withdrawal is required. To obtain various structures, along with directed crystallization process, the pressure in crystallization chamber is an important factor, which drives the gasar morphology. The porous structure of gasars is diverse, there are the gasars with longitudinal, cylindrical, spherical, conical pores. It is possible to alternate the porosity layers and monolithic metal layers. The dimensions of gasars pores are in the limits from 10 μm to 10 mm at total porosity from 7 to 55 (75%). However, there is a possibility to obtain the pores with smaller diameter. The mechanical properties of gasars have a number of advantages as compared with conventional porous materials produced by different methods. Subsequent processing of the gasars does not differ from analogous non-porous materials, which is also an advantage over conventional porous materials. And in case when the diameter of pores is less than 50 μm, the exceedance of mechanical properties of gasars as compared with monolithic materials of the same chemical composition is observed. This is caused by the fact that the pores were formed during crystallization and at the action of pressure on a gasar, local hardening occurs. At present, the gasars have already found application as light and strong structural materials, filters, heat exchangers, dampers, slide bearings, catalyst elements, friction materials, etc. The use of gasars in space hardware will help to considerably reduce the mass of launch vehicle structural elements without worsening strength properties. The possibility of welding and soldering the gasars allows finding their application in the structure of propellant systems, compressed gas and propellants supply systems, creating filtering elements based on the gasars, including propellant spraying and mixing systems.
Key words: gasars, gas-eutectic conversion, eutectics, porosity
Bibliography:
1. Shapovalov V. I. Legirovanie vodorodom. D.: Zhurfond, 2013. 385 p.
2. Shapovalov V. TERMEC 2006 // International Conference on Processing and Manufacturing of Advanced Materials, July 4–8, 2006, Vancouver, Canada. Р. 529.
3. Komissarchuk Olga, Xu Zhengbin, Hao Hai, Zhang Xinglu, Karpov V. Pore structure and mechanical properties of directionally solidified porous aluminum alloys / Research & Development. Vol. 11, No.1, January 2014.
4. Karpov V. V., Karpov V. Yu. Vliyanie poristosti na teploprovodnost’ gazov/ Teoriya I praktica metallurgii. 2003. № 4.
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