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Key words: rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design. rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design.
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9. General-purpose thermostating module – new approach in development of up-to-date thermostating systems for rocket and space complexes

Authors:

Fateev D. M., Bikova G. M, Petukhov O. M., Pokataiev V. M.,Yelanskyi Yu. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 78-84

DOI: https://doi.org/10.33136/stma2024.01.078

Language: Ukrainian

Annotation: These days when creating any rocket space complex, it is important to ensure its advancement and competitive ability. To create such complex, the technical systems it consists of must be implemented with minimal economic and energy costs. Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Development of the competitive rocket and space complex also requires the new approach in the development of the thermostatting system. One of the main tasks is to create a system that can be mass-produced and used as part of any rocket and space complex. Solving this problem will significantly reduce the cost of creating and operating the thermostatting systems and the whole rocket and space complex. One of the ways to solve this task is to create a general-purpose thermostatting system. The modular principle for such thermostatting system would be optimal, which means making up a system from separate modules. It simplifies the all-round installation of various system options and simplifies its setup and operation. The paper demonstrates the possibility and prospects of creating modular thermostatting systems, which enable air supply with the required parameters to different consumers. Characteristics and design of the general-purpose thermostatting module are specified, which can be used as the main component without changing anything in the composition of stationary and mobile thermostatting systems.

Key words: rocket and space complex, launch vehicle, technological systems of the ground complex, thermostatting systems, open type system, versatility, modular design.

Bibliography:
  1. . Tsiklon-4M. URL: https://www. yuzhnoye.com.
  2. . KRK «Tsiklon-4M». C4M YZH SPS 090 02 Technicheskoe zadanie na sostavnuyu chast’ OKR «Sistema termostatirovaniya rakety-nositelya i golovnogo bloka» GP «KB «Yuzhnoye». 78 s.
  3. . KRK «Tsiklon-4M». C4M YZH SPS 119 02 Technicheskoe zadanie na sostavnuyu chast OKR «Transportnaya systema termostatirovaniya» GP «KB «Yuzhnoye». 2018. 40 s.

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9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes
9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes
9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes

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]]> 18.1.2020 Development of autonomous power engineering systems with hydrogen energy storage https://journal.yuzhnoye.com/content_2020_1-en/annot_18_1_2020-en/ Wed, 13 Sep 2023 11:57:42 +0000 https://journal.yuzhnoye.com/?page_id=31056
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.
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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

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18.1.2020 Development of autonomous power engineering systems with hydrogen energy storage
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]]> 19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles https://journal.yuzhnoye.com/content_2018_2-en/annot_19_2_2018-en/ Thu, 07 Sep 2023 12:23:58 +0000 https://journal.yuzhnoye.com/?page_id=30801
Filtration and Stochastic Control in Dynamic Systems: Collection of articles / Under the editorship of K. Reliability and Accuracy of Triple Measurements of Analog Technological Variables. Combined Estimation of Complex Systems Characteristics.
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19. Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles

Authors:

Aksiuta О. А., Balyayev O. A., Konstantinov G. I., Sidoruk V. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 157-172

DOI: https://doi.org/10.33136/stma2018.02.157

Language: Russian

Annotation: The measurement errors upon conducting flight tests for launch vehicles are evaluated by considering the interferences and uncertainties in the measurement system procedure. Formal use of this approach can lead to unpredictable consequences. More reliable evaluation of errors upon conducted measurements can be achieved if the measurement process is regarded as a procedure of successive activities for designing, manufacturing, and testing the measurement system and the rocket including measurements and their processing during the after-flight analysis of the received data. The sampling rates of the main controlled parameters are three to ten times higher than the frequency range of their changing. Therefore, it is possible to determine the characteristics of the random error components directly on the basis of registered data. The unrevealed systematic components create the basic uncertainty in the evaluation of the examined parameter’s total measurement error. To evaluate the precision and measurement accuracy of a particular launch, the article suggests specifying the preliminary data on measurement error components determined during prelaunch processing and launch. Basic structures of algorithms for evaluation of precision and measurement accuracy for certain mathematical models that form the measured parameters were considered along with the practical case when static correlation existed among the measured parameters.

Key words: flight tests, sensor, measurement error, mathematical model

Bibliography:
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19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles
19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles
19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles

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]]> 5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime https://journal.yuzhnoye.com/content_2019_1-en/annot_5_1_2019-en/ Thu, 25 May 2023 12:09:25 +0000 https://journal.yuzhnoye.com/?page_id=27710
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. 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.
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5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

Authors:

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

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

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