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Petrenko V. (2018) "The Solid–Propellant Motors with Regulated Thrust" Космическая техника. "The Solid–Propellant Motors with Regulated Thrust" Космическая техника. quot;The Solid–Propellant Motors with Regulated Thrust", Космическая техника. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 46—52.doi: https://doi.org/10.33136/stma2018.01.046 . Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 46—52.doi: https://doi.org/10.33136/stma2018.01.046 . Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 46—52.doi: https://doi.org/10.33136/stma2018.01.046 .
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8. The Solid–Propellant Motors with Regulated Thrust

Authors:

Glazkov V. O., Yenotov V. H., Kozak L. R., Fomenko V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 46-52

DOI: https://doi.org/10.33136/stma2018.01.046

Language: Russian

Annotation: The paper considers the results of scientific research and experimental works performed by Yuzhnoye SDO on solid–propellant motors with controlled thrust. The possibility in principle is shown of creating such motors and stabilizing their characteristics in different operation modes due to the throat area regulation system and selection of relevant control algorithm.

Key words:

Bibliography:
1. Petrenko V. I., Sokoovsky M. I. et al. Control of Solid-Propellant Propulsion Systems. М., 2003. 463 p.
2. Presnyakov V. F. Solid Rocket Motor Dynamics. М., 1984. 248 p.
3. Sorokin R. E. Solid Rocket Motor Gas Thermodynamics. М., 1967. 368 p.

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8.1.2018 The Solid–Propellant Motors with Regulated Thrust
8.1.2018 The Solid–Propellant Motors with Regulated Thrust
8.1.2018 The Solid–Propellant Motors with Regulated Thrust
]]> 8.2.2017 Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems https://journal.yuzhnoye.com/content_2017_2/annot_8_2_2017-en/ Tue, 08 Aug 2023 12:49:21 +0000 https://journal.yuzhnoye.com/?page_id=29763
Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems Authors: Petrenko R. (2017) "Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems" Космическая техника. "Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems" Космическая техника. Petrenko R. quot;Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems", Космическая техника. Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems Автори: Petrenko R. Missile armaments Том: 2017 Випуск: 2017 (2) Рік: 2017 Сторінки: 41—48.doi: . Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems Автори: Petrenko R. Missile armaments Том: 2017 Випуск: 2017 (2) Рік: 2017 Сторінки: 41—48.doi: . Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems Автори: Petrenko R. Missile armaments Том: 2017 Випуск: 2017 (2) Рік: 2017 Сторінки: 41—48.doi: . Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems Автори: Petrenko R. Missile armaments Том: 2017 Випуск: 2017 (2) Рік: 2017 Сторінки: 41—48.doi: .
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8. Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems

Authors:

Petrenko R. М.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 41-48

Language: Russian

Annotation: The paper considers the method of calculation of generative pressurization system for a tank with nitrogen tetroxide in which an attempt is made to model the temperature stratification of gas in the tank throughout the height of the tank. The applied physical model takes into account the impact of gas dynamic processes, heat-mass-exchange, and chemical reactions on gas parameters in the tank. The satisfactory convergence of the calculation results with the experimental data is shown.

Key words:

Bibliography:
1. Antonov V. A., Logvinenko A. I., Moseiko V. A. et al. Calculation of Long-Range Missiles Fuel (UDMH) Tanks Pressurization with Hot Gases. Defense Engineering. 1967. No. 10.
2. Belyayev N. M. Launch Vehicle Propellant Tanks Pressurization Systems. М., 1974. 336 p.
3. Test Facilities and Development Testing of Liquid Rocket Engines / А. G. Galeyev, K. P. Denisov, V. I. Ishchenko, V. A. Liseikin, G. G. Saydov, А. Y. Cherkashin. М., 2012. 362 p.
4. Thermal Dynamic and Thermal Physical properties of Combustion Products. Vol. 4 / Under the editorship of V. P. Glushko. М., 1974. 263 p.
5. Thermodynamic and Transfer Properties of Chemically Reacting Gas Systems. Part 1 / Under the editorship of A. K. Krasin, B. V. Nesterenko et al. Minsk, 1967. 206 p.

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8.2.2017 Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems
8.2.2017 Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems
8.2.2017 Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems
]]> 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
Petrenko. Соntact mechanics of shell structures under local loading/ International Аррlied Месhanics. Ргоjесtion-itеrаtive modification оf the method of local variations for problems with a quadratic functional / Journal of Аррlied Мahtematics and Meсhanics. (2019) "Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime" Космическая техника. "Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime" Космическая техника. quot;Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime", Космическая техника.
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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

Bibliography:

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5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

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