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Hydrogen the future transportation fuel: From production to applications.
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18. Development of autonomous power engineering systems with hydrogen energy storage

Authors:

Shevchenko A. A.1, Kozak L. R.2, Zipunnikov M. M.1, Kotenko A. L.1

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2020, (1); 160-169

DOI: https://doi.org/10.33136/stma2020.01.160

Language: Russian

Annotation: The article analyzes the energy potential of alternative sources of Ukraine. The projects using hydrogen technologies aimed at attracting solar energy to the infrastructure of energy technological complexes, in particular water desalination systems and for refueling automobile vehicles located in areas with high solar radiation potential, are considered. During the operation of water desalination plants using a solar power station as an energy source, contingencies are very likely to arise due to either a power outage (due to cloudy weather) or an emergency failure of individual elements of the system. In this case, it is required to ensure its removal from service without loss of technological capabilities (operability). For this purpose, it is necessary to provide for the inclusion in the technological scheme of the energy technological complex of an additional element that ensures operation of the unit for a given time, determined by the regulations for its operation. As such an element, a buffer system based on a hydrogen energy storage device is proposed. The current level of hydrogen technologies that are implemented in electrochemical plants developed at the Institute of Mechanical Engineering named after A. N. Podgorny of the National Academy of Sciences of Ukraine allows producing and accumulating the hydrogen under high pressure, which eliminates the use of compressor technology.

Key words: alternative energy sources, hydrogen, solar energy, hydrogen generator

Bibliography:
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18.1.2020 Development of autonomous power engineering systems with hydrogen energy storage
18.1.2020 Development of autonomous power engineering systems with hydrogen energy storage
18.1.2020 Development of autonomous power engineering systems with hydrogen energy storage

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]]> 5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep https://journal.yuzhnoye.com/content_2020_1-en/annot_5_1_2020-en/ Wed, 13 Sep 2023 06:15:53 +0000 https://journal.yuzhnoye.com/?page_id=31026
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).
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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

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

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]]> 9.1.2018 On the Peculiarities of High-Temperature Rocket Propellants Drain from Delivery Means to Filling Tank for Closed Drain https://journal.yuzhnoye.com/content_2018_1-en/annot_9_1_2018-en/ Tue, 05 Sep 2023 06:29:31 +0000 https://journal.yuzhnoye.com/?page_id=30460
Storage and Transportation of Chemical Products.
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9. On the Peculiarities of High-Temperature Rocket Propellants Drain from Delivery Means to Filling Tank for Closed Drain

Authors:

Pozdieiev H. L., Gamaza А. Е.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 53-57

DOI: https://doi.org/10.33136/stma2018.01.053

Language: Russian

Annotation: The paper presents the variation of parameters of gas-vapor mixture of hypergolic rocket propellant components in a filling tank in the process of rocket propellant components filling into it with “closed drainage” depending on tank filing coefficient and initial parameters of environment in the tank.

Key words:

Bibliography:
1. Cosmodrome / Under the general editorship of A. P. Vol’sky. М., 1977.
2. Berezhkovsky M. I. Storage and Transportation of Chemical Products. М., 1973.
3. Selection and Justification of Technology of Rocket Propellants Drain from Tank-Containers into OFS, FFS Tanks: Technical Note Cyclone-4 22.6840.155 СТ. Yuzhnoye SDO, 2005.

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9.1.2018 On the Peculiarities of High-Temperature Rocket Propellants Drain from Delivery Means to Filling Tank for Closed Drain
9.1.2018 On the Peculiarities of High-Temperature Rocket Propellants Drain from Delivery Means to Filling Tank for Closed Drain
9.1.2018 On the Peculiarities of High-Temperature Rocket Propellants Drain from Delivery Means to Filling Tank for Closed Drain
]]> 4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle https://journal.yuzhnoye.com/content_2017_1/annot_4_1_2017-en/ Thu, 22 Jun 2023 12:38:35 +0000 https://journal.yuzhnoye.com/?page_id=29370
2017 (1); 23-29 Language: Russian Annotation: The thermal analysis was made for external surfaces of a reusable high-altitude supersonic flying vehicle being a part of a space transportation system.
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4. Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle

Authors:

Husarova I. O.1, Potapov O. М.1, Golubkov G. М.1, Kalinichenko D. S.1, Poluyan M. V.1, Manko Т. А.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2017 (1); 23-29

Language: Russian

Annotation: The thermal analysis was made for external surfaces of a reusable high-altitude supersonic flying vehicle being a part of a space transportation system. The basic criteria were determined for selection of its heat-resistant and heat-protective structures.

Key words:

Bibliography:
1. Kondratenko F. I. et al. Aerodynamic Heating and Thermal Protection of Intercontinental Ballistic Missiles / F. I. Kondratenko, P. S. Savoysky, V. I. Sidov, I. M. Fomishenko. М, 1973. 288 p.
2 Avduyevsky V. S. et al. Fundamentals of Heat Transfer in Aerospace Engineering / V. S. Avduyevsky, B. M. Galitseisky, G. A. Glebov. М., 1975. 624 p.

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4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle
]]> 6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing https://journal.yuzhnoye.com/content_2019_1-en/annot_6_1_2019-en/ Thu, 25 May 2023 12:09:32 +0000 https://journal.yuzhnoye.com/?page_id=27711
During transportation tank container is subjected to various kinds of mechanical actions (vibration, rolling and pitching in the sea, braking, transshipment), therefore intensive mixing of propellants occur. Article includes the measuring results of the gas liquid medium parameters inside the tank containers with fuel in the process of fuel transportation to Ukraine from PRC factories and estimations of the measuring results using the developed model which confirmed the quantitative nature of the mass exchange processes, included in the model, going on in the gas liquid medium during transportation of the tank container with fuel equipment. Key words: oxidizer , fuel , saturation by helium , tank container , transportation Bibliography: 1. oxidizer , fuel , saturation by helium , tank container , transportation .
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6. Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing

Authors:

Pozdieiev H. L., Kucherenko R. A., Kucherenko T. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 38-44

DOI: https://doi.org/10.33136/stma2019.01.038

Language: Russian

Annotation: This article considers the issue of achievement of the specified value of propellants saturation by helium after their delivery from the manufacturers to the launch site. Knowing the fact that propellants gas saturation or gas separation processes are labour-consuming and costly this issue is of immediate interest. In order to solve this problem number of factors have been considered, which determine the value of gas saturation in the propellants delivered to the launch site and procedure to control the value of gas saturation by the fuel manufacturer has been developed. This procedure implies that shipping tank container is pressurized after being fueled with propellants at the manufacturer’s, the pressure is characterized by the value of the known initial deficit or excess of gas in the propellants, following which tank container is delivered to the launch site. During transportation tank container is subjected to various kinds of mechanical actions (vibration, rolling and pitching in the sea, braking, transshipment), therefore intensive mixing of propellants occur. As propellants mix, process of propellant saturation occurs when certain amount of gas transits from tank container’s gas volume into the liquid, therefore certain gas saturation is reached. Article includes the measuring results of the gas liquid medium parameters inside the tank containers with fuel in the process of fuel transportation to Ukraine from PRC factories and estimations of the measuring results using the developed model which confirmed the quantitative nature of the mass exchange processes, included in the model, going on in the gas liquid medium during transportation of the tank container with fuel equipment. It has been determined that due to inevitable errors in the measuring of the specified parameters by the tank container, the achievement of the specified gas saturation with high precision is problematic. In spite of the fact that this procedure does not provide exact value of the specified gas saturation, its application will accelerate and make cheaper the process of fuel preparation for filling operations at the launch site, which is especially relevant in case of fuel saturation by helium. Based on this fuel saturation by helium procedure, the complex technology is suggested, providing controlled gas saturation during fuel delivery and subsequent adjustment of gas saturation using launch site equipment. Therefore, this article develops and studies the original model of the controlled gas saturation of the fuel during its delivery to the consumer. Alternative of the practical use of the study results is suggested in the form of the complex technology of fuel saturation by helium, delivered in the tank containers from the manufacturer to the launch site.

Key words: oxidizer, fuel, saturation by helium, tank container, transportation

Bibliography:

1. Volskiy A. P. Kosmodrom. M.: Voenizdat, 1977. 311 p.
2. Stepanov A. N., Vorobiev A. M., Grankin B. K. Kompleksy zapravki raket I kosmicheskikh apparatov. SPB:OM-PRESS, 2004. 26 p.
3. Kiriyanova A. N., Matveeva O. P. Opredelenie kolebania davlenia v gazovoy polosti hermetychikh emkostey transportnozapravochnykh containerov dlya raketnykh topliv pri temperaturnykh vozdeistviyakh/ Nauka i innovatsii. 2016. Vyp. 7.
4. Berezhkovskiy M. I. Khranenie i transportirovka khimicheskykh produktov. – M.: Khimia, 1973. – 272 s.
5. Perepelkin K. Ye., Matveev V. S. Gazovye emulsii. L.:Khimia, 1979. 200 p.
6. Issledovanie protsessov degazirovaniya komponentov topliva v conteinere-tsisterne pri dostavke topliva potrebitelyu. Cyclone4M 21.18425.174 OT: Techn. report. Dnepropetrovsk: Yuzhnoye SDO, 2017. 39 p.

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6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing
6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing
6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing

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]]> 2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight https://journal.yuzhnoye.com/content_2023_1-en/annot_2_1_2023-en/ Fri, 12 May 2023 16:10:21 +0000 https://test8.yuzhnoye.com/?page_id=26986
14 CFR, Commercial space transportation, Federal aviation administration, Department of transportation Subchapter C – Licensing, part 420 – License to Operate a Launch Site, 2000 20.
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2. How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight

Authors:

Hladkyi Ye. H., Perlyk V. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 14-30

DOI: https://doi.org/10.33136/stma2023.01.014

Language: Ukrainian

Annotation: Safety of the up-to-date rocket and space complexes remains a topical problem for the developers of rocket and space technology. The integral component of this problem along with the safety of operations during launch vehicle ground pre-launch processing is organization of flight safety. The basic task of this rocket and space complexes safety component is to prevent or minimize serious consequences in case of launch vehicle failure in the flight leg, after all such accidents can cause damage to the population and facilities (including personnel and facilities of the ground complex), located along the flight paths. It is shown that the flight safety assurance of the launch vehicle is based on the experience of combat missile systems. Flight safety during the launch vehicle launches is provided by laying flight paths through sparsely populated (unpopulated) territories and using special onboard flight safety systems. This system limits the size of impact zones of emergency launch vehicle and its debris by emergency engine shutdown. Recently flight safety process is organized based on the acceptable risk concept. It is based on a risk assessment for the ground-based facilities and people, and it should not exceed the established standards. Such approach requires development and upgrading of the mathematical models of risk assessment in case of launch vehicle failure in the flight phase. Formation of the risk-oriented approach to flight safety in Yuzhnoye SDO is shown. Key moment in this process is to develop the separate structural unit, which started working on rocket and space complexes flight safety assurance and analysis. The basic model for assessing the risks of damage to facilities and people is analyzed, using the maximum impact zone of an emergency launch vehicle, which is realized in case of loss of control and flight safety system activation. The main directions of the basic model improvement are shown, which led to the development of a number of new original models of flight safety assessment in the Yuzhnoye SDO. First of all, the developed models take into account the flight safety system specifics, which are used to equip the launch vehicles, developed by Yuzhnoye SDO: criteria of activation, blocking of the engine emergency shutdown in the initial flight phase and Fe functional. Such models allow to take into account the different nature of emergency situations in the launch vehicle flight phase and ways of their representation, representation of the damage areas of facilities in the form of convex polygons, possible fragmentation of the emergency launch vehicle at the free- fall leg etc. The developed models have found wide application in the practice of assessing flight safety indicators in the Yuzhnoye SDO projects.

Key words: launch vehicle, acceptable risk, launch vehicle failure in the flight phase, flight safety system, emergency launch vehicle impact zone, risk of damage to facilities, collection risk

Bibliography:

1. Gladkiy E.G. Opredelenie kollektivnogo riska v cluchae avarii rakety-nositelya «Tsiklon-4M» na etape poleta s ispolzovaniem predstavlenniya naselennyh territoriy v vide mnogougolnikov. Kosmichna nauka i tehnologia. K., 2020. T. 26. № 3. S. 32–41. https://doi.org/10.15407/knit2020.03.032
2. Gladkiy E.G. Opredelenie riska dlya obiektov startovogo kompleksa s uchetom ih obvalovki v cluchae avarii rakety-nositelya na nachalnom uchastke poleta. Tehnicheskaya mehanika. Dnepropetrovsk: ITM NAN i GKA Ukrainy, 2020. №1. S. 31–41.
3. Gladkiy E.G. Otsenka riska porazheniya lineynogo obiekta v cluchae avarii rakety-nositelya na etape poleta. Kosmichna nauka i tehnologia. Kiev: GAO, 2019. T. 25. № 4. S. 22–28.
4. Gladkiy E.G. Protsedura otsenki poletnoy bezopasnosti raket-nositeley, ispolzuyuschaya geometricheskoe predstavlenie zony porazheniya obiekta v vide mnogougolnika. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2015. Vyp. 3. S. 50–56.
5. Gladkiy E.G., Kryukov A.V. Opredelenie veroyatnosti padenia avariynoy rakety-nositelya na ploschadnye obiekty, raspolozhennye bdol trassy vyvedennia. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2008. Vyp. 1. S. 81−90.
6. Gladkiy E.G., Perlik V.I. Vybor interval vremeni blokirovki avriynogo vykluchenniya dvigatelya na nachalnom uchastke poleta pervoy stupeni. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2011. Vyp. 2. S. 266–280.
7. Gladkiy E.G., Perlik V.I. Matematicheskie modeli otsenki riska dlya nazemnyh obiektov pri puskah raket-nositeley. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2010. Vyp. 2. S. 3–19.
8. Gladkiy E.G., Perlik V.I. Model otsenki urovnya bezopasnosti raketno-kosmicheskyh system. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU. 2006. Vyp. 1−2. S. 45–57.
9. Metodika opredeleniya pokazateley bezopasnosti po trassam puskov i v raionah padeniya otdelyauschihsya chastey raket-nositeley. OOO «NTTs «Ekon TsNIImash», 2006.
10. Programma «Grom-2». Operativno-takticheskiy raketniy kompleks. Poletnaya bezopasnost. GR2 YZH ANL 016 00 [Isp. Gladkiy E.G. Zheludkov A.V. i dr.]
11. Programma «Tsiklon-4M». Raketno-kosmicheskiy kompleks. Analiz poletnoy bezopasnosti RKK. C4M YZH ANL 062 00. 2018. Vyp. 1. 92 s. [Isp. Gladkiy E.G., Zheludkov A.V. i dr.].
12. Proekt TKRK Analiz priemlimosti alternativnoy tochki # 7 dlya razmescheniya KPTs ТКРК SL-YN-TD-R-009
13. Razrabotka metodicheskyh materialov po otsenke stepeni riska po trasse poleta i v rayonah padeniya otdelyauschihsya chastey pri puskah sredstv vyvedeniya. Kniga 1. Metodicheskie materialy. NTO. TSNIImash. 1990. 68 s.
14. Raketa kosmicheskogo naznacheniya «Tsiklon-4». Utochnenie characteristic zon padeniya RKN «Tsiklon-4» v cluchae avarii. Otsenka bezopasnosti vybrannyh mest rameschenniya obiktov NK KRK «Tsiklon-4». Tsiklon-4 21.16011.117 OT: Tehn. onchet. Dnepropetrovsk: GP «KB «Yuzhnoye», 2008. 110 s.
15. Raketa kosmicheskogo naznacheniya «Tsiklon-4». Opasnye zony pri avariynom poete RKN «Tsiklon-4». Tsiklon-4 21.16522.635 OT: Tehn. otchet. Dnepropetrovsk: GP «KB «Yuzhnoye», 2009. 69 s.
16. Uvyazka KA Lybid s RKK «Zenit-M»: Poyasnitelnaya zapiska Zenit-M. Lybid PZ, 2012. 363 s.
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19. 14 CFR, Commercial space transportation, Federal aviation administration, Department of transportation Subchapter C – Licensing, part 420 – License to Operate a Launch Site, 2000
20. E. Gladky Mathematical Models of the Safety Assessment of Ground Facilities in Case of Failure of Launch Vehicle Equipped with Onboard Automatic Emergency Engine Shutdown/ Proceedings of the International Astronautical Congress, IAC. 2015. P. 9665 – 9675.

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2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight
2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight
2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight

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