Search Results for “integrated launch vehicle” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 12:53:24 +0000 en-GB hourly 1 https://wordpress.org/?v=6.2.2 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “integrated launch vehicle” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 13.1.2020 Mathematical models of hydraulic servomechanisms of space technology https://journal.yuzhnoye.com/content_2020_1-en/annot_13_1_2020-en/ Wed, 13 Sep 2023 10:58:26 +0000 https://journal.yuzhnoye.com/?page_id=31045
...hydraulic actuator, selecting optimal characteristics of slides based on specified degree of stability and response of servo actuator and conducting final modeling of rocket flight on the integrated control system test benches without using real actuators and loading stands. Using this mathematical model, the powerful actuators of a line of intercontinental ballistic missiles with swinging reentry vehicle and the main engines actuators of Zenit launch vehicle first stage were developed.
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13. Mathematical models of hydraulic servomechanisms of space technologynt

Authors:

Kozak L. R., Shakhov М. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 121-132

DOI: https://doi.org/10.33136/stma2020.01.121

Language: Russian

Annotation: Being a final executive element of rocket control systems, a hydraulic actuator is at the same time the main source of various non-linear dependencies in rocket dynamic design whose availability dramatically com plicates theoretical analysis of their dynamics and control systems synthesis. The required accuracy and complexity of mathematical models of hydraulic servo mechanisms are different for different design phases of guided rockets. The paper deals with the simplest models of hydraulic servo actuators intended to calculate rocket controllability and to define requirements to response and power characteristics of the actuators. To calculate the rocket stability regions and to evaluate own stability of servo actuators, a linearized mathematical model of hydraulic servo actuator is used that takes into account the most important parameters having impact on stability of the servo actuator itself and on that of the rocket: hardness of working fluid, stiffness of elastic suspension of the actuator and control element, slope of mechanical characteristic of the actuator in the area of small control signals, which, as full mathematical model analysis showed, is conditioned only by dimensions of initial axial clearances of slide’s throats. The full mathematical model constructed based on accurate calculations of the balance of fluid flow rate through the slide’s throats allows, as early as at designing phase, determining the values of most important static and dynamic characteristics of a future hydraulic actuator, selecting optimal characteristics of slides based on specified degree of stability and response of servo actuator and conducting final modeling of rocket flight on the integrated control system test benches without using real actuators and loading stands. It is correct and universal for all phases of rockets and their control systems designing and testing. Using this mathematical model, the powerful actuators of a line of intercontinental ballistic missiles with swinging reentry vehicle and the main engines actuators of Zenit launch vehicle first stage were developed. The results of their testing separately and in rockets practically fully comply with the data of theoretical calculations.

Key words: mathematical model, hydraulic actuator, servo actuator, stability, damping, slide

Bibliography:
1. Dinamika gidroprivoda / pod red. V. N. Prokofieva. М., 1972. 292 s.
2. Gamynin N. S. Gidravlicheskii privod system upravleniia. М., 1972. 376 s.
3. Chuprakov Yu. I. Gidroprivod i sredstva gidroavtomatiki. М., 1979. 232 s.
4. Kozak L. R. Geometriia zolotnika i dinamicheskie kharakteristiki gidroprivoda // Visnyk Dnipropetrovskoho universytetu. Vyp. 13, Tom 1. 2009.

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]]> 9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials https://journal.yuzhnoye.com/content_2020_1-en/annot_9_1_2020-en/ Wed, 13 Sep 2023 10:43:08 +0000 https://journal.yuzhnoye.com/?page_id=31035
The materials used and propellant tank manufacturing technologies ensure leak-tightness of load-bearing shell at liquid nitrogen operating pressure of 7.5 kgf/cm2 and strength at excess pressure of 15 kgf/cm2 and allow conducting approbation of prospective stage of the integrated launch vehicle.
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9. Experimental investigation of a liner-free propellant tank made from polymer composite materials

Authors:

Sidoruk А. V., Popov D. А., Zadoia А. S., Kalinichenko D. S., Aksenenko O. V., Husarova I. O., Derevianko I. I., Kharchenko V. M., Litot O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 90-98

DOI: https://doi.org/10.33136/stma2020.01.090

Language: Russian

Annotation: The exploratory and experimental investigations were conducted into design of propellant tank made of composite polymer materials for work in cryogenic environment at operating pressure of 7.5 kgf/cm2 . When determining the configuration of a liner-free composite propellant tank, the main requirement was ensuring its leak-tightness at internal excess pressure and cryogenic temperature effect. The world experience of creating similar designs was analyzed and the requirements were defined imposed on configuration of propellant tank load-bearing shells. Before defining the final configuration, the types of materials, reinforcing patterns, and possible ways to ensure leak-tightness were analyzed, and preliminary tests were conducted of physical and mechanical characteristics of thin-wall samples of composite materials and tubular structures with different reinforcing patterns. The tests of carbon plastic samples were conducted at different curing modes to determine the most effective one from the viewpoint of strength characteristics and the tests for permeability by method of mouthpiece were conducted. The tests of pilot propellant tank showed that the calculated values of deformations and displacements differ from the experimental values by no more than 10 %. Using the parameters measurement results from the tests on liquid nitrogen, the empirical formulas were obtained to calculate linear thermal expansion coefficient of the package of materials of load -bearing shell. The empirical dependences were constructed of relative ring deformations at load-bearing shell middle section on pressure and temperature. The tests confirmed correctness of adopted solutions to ensure strength and leak-tightness of propellant tank load-bearing shell at combined effect on internal excess pressure and cryogenic temperature, particularly at cyclic loading. The materials used and propellant tank manufacturing technologies ensure leak-tightness of load-bearing shell at liquid nitrogen operating pressure of 7.5 kgf/cm2 and strength at excess pressure of 15 kgf/cm2 and allow conducting approbation of prospective stage of the integrated launch vehicle.

Key words: load-bearing shell, permeability, cryogenic propellant, relative deformations, linear thermal expansion coefficient

Bibliography:
1. Frantsevich I. М., Karpinos D. М. Kompozitsionnye materialy voloknistogo stroeniia. K., 1970.
2. TSM YZH ANL 009 00. Composite fuel tank for ILV, Dnipro, Yuzhnoye SDO, 2019.
3. Zheng H., Zeng X., Zhang J., Sun H. The application of carbon fiber composites in cryotank. Solidification. 2018. https://doi.org/10.5772/intechopen.73127

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9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials
9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials
9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials

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]]> 12.2.2017 Determination Procedure for Pneudraulic System and Its Components No-Failure Operation Probability https://journal.yuzhnoye.com/content_2017_2/annot_12_2_2017-en/ Wed, 09 Aug 2023 11:32:23 +0000 https://journal.yuzhnoye.com/?page_id=29785
2017 (2); 60-64 Language: Russian Annotation: The calculation procedure is proposed, the analysis is made and the ranges of optimal probability values of no-failure operation of pneumohydraulic propellant supply system and its elements are determined based on general requirements to integrated launch vehicle.
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12. Determination Procedure for Pneudraulic System and Its Components No-Failure Operation Probability

Authors:

Nazarenko O. P., Yakimets S. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 60-64

Language: Russian

Annotation: The calculation procedure is proposed, the analysis is made and the ranges of optimal probability values of no-failure operation of pneumohydraulic propellant supply system and its elements are determined based on general requirements to integrated launch vehicle.

Key words:

Bibliography:
1. Berlow R., Proshan F. Statistic Reliability Theory and Dependability Tests / Translation from English. М., 1984. 328 p.
2. Lloyd D., Lipov M. Reliability. Organization of Investigation, Methods, Mathematical Apparatus / Translation from English; Under the editorship of Buslenko N. P. М.,1964. 686 p.
3. Ensuring Reliability of Prospective Injection Means. URL: http://www. sciential.ru/technology/kosmos/199.html.
4. Yuzhnoye SDO Rockets and Spacecraft / Under general editorship of S. N. Konyukhov. Dnepropetrovsk, 2000. 236 p.
5. Degtyarev A. V. et al. System Approach to Development of Modular Launch Vehicle Family / A. V. Degtyarev, А. E. Kahanov, N. G. Litvin, V. A. Shulga. DNU News (Series RKT; Issue 15). Vol. 1. 2012.
6. Reliability Analysis of Taurus-II LV Stage One Core Structure Pneumohydraulic Propellants Supply System: Technical Report / Taurus-II. 21.18231.123 ОТ. Yuzhnoye SDO, 2016. 35 p.

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12.2.2017 Determination Procedure for Pneudraulic System and Its Components No-Failure Operation Probability
12.2.2017 Determination Procedure for Pneudraulic System and Its Components No-Failure Operation Probability
12.2.2017 Determination Procedure for Pneudraulic System and Its Components No-Failure Operation Probability
]]> 5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle https://journal.yuzhnoye.com/content_2017_2/annot_5_2_2017-en/ Tue, 08 Aug 2023 12:36:28 +0000 https://journal.yuzhnoye.com/?page_id=29750
Structural Perfection of Cyclone-4 Integrated Launch Vehicle Authors: Zhuk N. 2017 (2); 25-28 Language: Russian Annotation: The comparison of Integrated Launch Vehicles structural perfection coefficients shows that Yuzhnoyedeveloped Cyclone-4 launch vehicle has structural perfection at the best world rocket model level Key words: Bibliography: 1. (2017) "Structural Perfection of Cyclone-4 Integrated Launch Vehicle" Космическая техника. "Structural Perfection of Cyclone-4 Integrated Launch Vehicle" Космическая техника. quot;Structural Perfection of Cyclone-4 Integrated Launch Vehicle", Космическая техника. Structural Perfection of Cyclone-4 Integrated Launch Vehicle Автори: Zhuk N. Structural Perfection of Cyclone-4 Integrated Launch Vehicle Автори: Zhuk N. Structural Perfection of Cyclone-4 Integrated Launch Vehicle Автори: Zhuk N. Structural Perfection of Cyclone-4 Integrated Launch Vehicle Автори: Zhuk N.
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5. Structural Perfection of Cyclone-4 Integrated Launch Vehicle

Authors:

Zhuk N. P., Makarenko A. O., Shevtsov E. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 25-28

Language: Russian

Annotation: The comparison of Integrated Launch Vehicles structural perfection coefficients shows that Yuzhnoyedeveloped Cyclone-4 launch vehicle has structural perfection at the best world rocket model level

Key words:

Bibliography:
1. Fundamentals of Spacecraft Launch Vehicles Designing / Under the editorship of V. P. Mishin. М., 1991. 415 p.
2. Kobelev V. N., Milovanov A. G. Launch vehicles: Tutorial. М., 1993. 185 p.
3. Umansky S. P. Launch Vehicles. Launch Sites. М., 2001. 216 p.
4. Kobelev V. N., Milovanov A. G. Spacecraft Injection Means. М., 2009. 528 p.

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5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle
5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle
5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle
]]> 16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System https://journal.yuzhnoye.com/content_2017_1/annot_16_1_2017-en/ Wed, 28 Jun 2023 12:02:33 +0000 https://journal.yuzhnoye.com/?page_id=29514
Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System Authors: Deno О. (2017) "Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System" Космическая техника. "Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System" Космическая техника. quot;Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System", Космическая техника. Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System Автори: Deno О. Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System Автори: Deno О. Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System Автори: Deno О. Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System Автори: Deno О.
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16. Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System

Authors:

Deno О. N., Filonenko А. V., Didenko O. V., Tkalenko G. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 100-106

Language: Russian

Annotation: The basic principles of building the flight safety systems for the space launch vehicles operated at present, the structure of autonomous onboard flight safety system that meets the requirements of the international regulatory documents in the field of space launch vehicle flight safety assurance, the feasibility of building the space launch vehicle autonomous onboard flight safety system developed in Ukraine are considered and the main directions of system’s components creation are defined.

Key words:

Bibliography:
1. Convention on International Responsibility for Damage Caused by Space Objects. Adopted by Resolution 2777 (XXVI) of the UN General Assembly of 29.11.1971.
2. Ideology of Constructing Autonomous Flight Safety System: Technical Report / Yuzhnoye SDO. Dnipropetrovsk, 2015. 91 p.
3. Safety Requirements of Western and Eastern Ranges: Maintenance Work Request 127-1. Т. 1. 1997. P. 1-24.
3. Bull James B., Lanzi Raymond J. An Autonomous Flight Safety System. 2016. URL: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20080044860.pdf.

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16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System
16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System
16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System
]]> 7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays https://journal.yuzhnoye.com/content_2017_1/annot_7_1_2017-en/ Tue, 27 Jun 2023 12:14:44 +0000 https://journal.yuzhnoye.com/?page_id=29425
Zenit-3SL Integrated Launch Vehicle.
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7. Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays

Authors:

Sirenko V. M., Il’enko P. V., Semenenko P. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 43-47

Language: Russian

Annotation: The methodology is proposed of probabilistic assessment of fulfilment of the requirements to gas dynamic parameters in launch vehicle vented bays in the cases when it is impossible to categorically ensure satisfaction of all limitations. By the example of Zenit LV it is shown that when using the statistic assessment, it is possible to considerably expand the launch vehicles application field from the viewpoint of ensuring required conditions in the spacecraft area.

Key words:

Bibliography:
1. Calculation of Venting Parameters in Zenit-3SL ILV Bays PLB, US and IB in Injection Leg. Zenit-3SL 21.13651.122 ОТ: Technical Report. Dnipropetrovsk, 1998. 104 p.
2. Verification of Gas Dynamic and Design Parameters of Thermostating System and Globalstar SC X-Panels Local Blow off System: Report on research work / NASU ITM No12-12/97. 1997. 79 p.
3. Idelchik I. E. Guide on Hydraulic Resistances / Under the editorship of M. O. Steinberg. 3rd edition revised and enlarged. М., 1992. 672 p.
4. Kremer N. Sh. Theory of Probability and Mathematical Statistics: Tutorial. М., 2010. 551 p.
5. Zenit-3SL Integrated Launch Vehicle. Zenit-2S Launch Vehicle. Aerodynamic Analysis. P. 1. Materials on Aero Gas Dynamics. Book 5. Zenit-2S / Thuraya Р01.05: RBD Materials. Dnipropetrovsk, 2000. 120 p.

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7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays
7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays
7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays
]]> 9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source https://journal.yuzhnoye.com/content_2019_1-en/annot_9_1_2019-en/ Thu, 25 May 2023 12:09:50 +0000 https://journal.yuzhnoye.com/?page_id=27714
2019, (1); 64-71 DOI: https://doi.org/10.33136/stma2019.01.064 Language: Russian Annotation: During lift-off of integrated launch vehicles, the propulsion system jet generates acoustic field. The method was developed that allows modeling the acoustic fields during integrated launch vehicle lift-off based on determination of acoustic sources type. The modeling of integrated launch vehicle propulsion system (ILV PS) jet acoustic field as bulky radiation source was performed in the rocket flight leg where ILV ascent altitude does not exceed ~ 25 m. Key words: integrated launch vehicle , acoustic field , sound pressure Bibliography: 1. integrated launch vehicle , acoustic field , sound pressure .
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9. Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source

Authors:

Sirenko V. M.1, Sokol G. I.2, Savchuk V. M.1, Kotlov V. Y.2, Savchuk T. L.2

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2019, (1); 64-71

DOI: https://doi.org/10.33136/stma2019.01.064

Language: Russian

Annotation: During lift-off of integrated launch vehicles, the propulsion system jet generates acoustic field. Therewith, the loads can be created that are critical for the launching equipment, rocket body and especially for the spacecraft, which are under the fairing. To take into account the effects on these elements, it is necessary to determine the characteristics of generated acoustic field. The method was developed that allows modeling the acoustic fields during integrated launch vehicle lift-off based on determination of acoustic sources type. In particular, modeling of Cyclone-4M ILV jet acoustic radiation by bulky source was performed. This provided the possibility to calculate acoustic pressure amplitudes in ILV ambient medium and to evaluate acoustic effect on the rocket body at certain points. The method is expected to be used to investigate kR wave parameter. The modeling of integrated launch vehicle propulsion system (ILV PS) jet acoustic field as bulky radiation source was performed in the rocket flight leg where ILV ascent altitude does not exceed ~ 25 m. In this case, one should be based on the value of boundary frequency fb =150 Hz which separates two types of acoustic field: fb ˂ 150 Hz – front of acoustic wave of spherical type, fb > 150 Hz – front of acoustic wave of flat type. The algorithm and program of calculation of sound pressure levels were developed in JAVA language. The characteristics of acoustic fields sound pressure levels were calculated depending on radiation frequency taking into account environmental temperature. The maximal acoustic pressure level in 150 Hz frequency in the payload area outside the fairing – 155 dB, in the instrumentation bay area – 157 dB, in the intertank bay area – 172 dB, in the aft bay area – 182 dB. In the frequencies lower than 150 Hz, the sound pressure levels are lower. The calculation data are presented graphically.

Key words: integrated launch vehicle, acoustic field, sound pressure

Bibliography:

1. Dementiev V. K. O maximalnykh akusticheskykh nagruzkakh na rekety pri starte/ V. K. Dementiev, G. Ye. Dumnov, V. V. Komarov, D.A. Melnikov// Kosmonavtika I raketostroenie. 2000. Vyp. 19. P. 44-55.
2. Tsutsumi S., Ishii T., Ut K., Tokudone S., Chuuouku Y., Wado K. Acoustic Design of Launch Pad for Epsilon Launch Vehicle / Proceedings of AJCPP2014 . Asian Joint Conference on Propulsion and Power, March 5- 8, 2014, Jeju Island, Korea. AJCPP2014-090.
3. Panda J., Mosher R., Porter D.J. Identification of Noise Sources during Rocket Engine Test Firings and a Rocket Launch a Microphone Phased-Array // NASA / TM2013-216625, December 2013. P. 1-20.
4. Sokol G. I. Metod opredeleniya vida istochnikov akusticheskogo izlucheniya v pervye secundy starta raket kosmicheskogo naznacheniya/ G. I. Sokol// Systemne proektuvannya ta analiz characteristic aerokosmichoi techniki: Zb. nauk. pr. 2018. XXIV. Dnipro: Lira, 2018. P. 91-101.
5. Sokol G. I., Frolov V. P., Kotlov V. Yu. / Volnovoy parameter kak kriteriy v osnove metoda issledovaniya akusticheskikh istochnikov pro starte raket/ Aviatsionno-kosmicheskaya technika I technologia. 2018. 3 (147), May-June 2018. Kharkov: KhAI, 2018. P. 4-13. DОІ:http://doi.org /10.20535/0203- 3771332017119600.
6. Rzhevkin S. N. Kurs lektsiy po teorii zvuka/ S. N. Rzhevkin. M.: MGU, 1960. 261 p.
7. Tyulon V. N. Vvedenie v teoriyu izlucheniya I rasseyaniya zvuka / V. N. Tyulin. M.: Nauka, 1976. 253 p.
8. Sapozhkov M. A. Electroakustica/ M. A. Sapozhkov. M.: Svyaz, 1978. 272 p.
9. Grinchenko V. T., Vovk V. V., Matsipura V. T.. Osnovy akustiki. Kyiv: Nauk. dumka, 2007. 640 p.
10. Ultrazvuk: Malaya enciclopedia. M.: Nauka, 1983. 400 p.
11. Volkov K. N. Turbulentnye strui – staticheskie modeli i modelirovanie krupnykh vikhrey/ K. N. Volkov, V. N. Emelyanov, V. A. Zazimko. M.: Fizmatlit, 2013. 960 p.
12. Schildt G. Java 8. Polnoe rukovodstvo. 9-e izd. M.: Wiliams, 2015. 137 p.

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9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source
9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source
9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source

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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
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.
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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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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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]]> 12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing https://journal.yuzhnoye.com/content_2019_1-en/annot_12_1_2019-en/ Wed, 24 May 2023 16:00:15 +0000 https://journal.yuzhnoye.com/?page_id=27717
Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing Authors: Stetsenko V. (2019) "Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing" Космическая техника. "Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing" Космическая техника. quot;Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing", Космическая техника. Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing Автори: Stetsenko V. Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing Автори: Stetsenko V. Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing Автори: Stetsenko V.
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12. Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing

Authors:

Stetsenko V. Y., Davydenko S. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 81-86

DOI: https://doi.org/10.33136/stma2019.01.082

Language: Russian

Annotation: Under the Sea Launch program when developer of the Zenit-3SL ILV control system issued the permission to launch in the conditions of drift from the design launch point of the Odyssey launch platform, the problem of drift parameters monitoring at the Sea Launch Commander ACS appeared. To ensure the payload orbiting accuracy the following maximum permissible values of platform drift parametres were determined: • maximum velocity of platform drift – no more than 0,32 m/s; • maximum acceleration of platform drift – no more than ±0,05 m/s2; • maximum distance of platform drift from design launch point – no more than 1950 m. The article includes the computation algorithm of the platform drift parametres to calculate velocity and acceleration of the drift, as well as distance from the design launch point to the actual point of the platform location. Geographical coordinates – latitude and longitude of the platform according to the GPS sensor, installed on the platform are used for calculations. These values during prelaunch processing of the ILV are transmitted to the assembly and command ship’s workstation for calculation of loads in the ILV root section at the rate of once in a second. During one of the Sea Launch missions, C++ program was developed and installed on the loads calculation workstation, realizing the computation algorithm offered by the authors of this article. This program displayed in real time the monitored parametres of the platform drift, and monitored the tolerable limits. During the same mission, the correctness of the developed algorithm and program were confirmed during the special experiment on the launch platform drift in the launch point. In future, they were used during the subsequent missions of the Sea Launch program.

Key words: Sea Launch, latitude, longitude, algorithm, velocity, acceleration

Bibliography:

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12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing
12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing
12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing

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]]> 8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses https://journal.yuzhnoye.com/content_2023_1-en/annot_8_1_2023-en/ Fri, 12 May 2023 16:11:05 +0000 https://test8.yuzhnoye.com/?page_id=26992
2023 (1); 70-76 DOI: https://doi.org/10.33136/stma2023.01.070 Language: Ukrainian Annotation: One of the systems in the integrated launch vehicle responsible for prelaunch processing and launch is a ground thermal conditioning system, which supplies the low-pressure air into the launch vehicle’s “dry” compartments.
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8. Specificity of developing pyrobolts with low impact and vibration impulse responses

Authors:

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

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 70-76

DOI: https://doi.org/10.33136/stma2023.01.070

Language: Ukrainian

Annotation: One of the systems in the integrated launch vehicle responsible for prelaunch processing and launch is a ground thermal conditioning system, which supplies the low-pressure air into the launch vehicle’s “dry” compartments. Thermal conditioning system is mated with the launch vehicle, using the mating interfaces, proper functioning of which enhances reliability of the ground support equipment, the launch vehicle and the entire space launch system. The article describes key requirements to the interfaces of the thermal conditioning system and the drawbacks of the existing designs. The article proposes a new design concept of the interface that connects the pipeline of the ground thermal conditioning system to the orifice of the launch vehicle using the corrugated rubber hose composed of three basic parts, attached with the help of a metal lock/release assembly. The proposed solution provides reliable leaktightness, ease of operation, providing multiple connections to the launch vehicle, including at various angles, and automatic disconnection by rocket motion or manual removal in case of launch abort. Using rubber as a high-elasticity structural material to manufacture the hoses, enabled minimization of efforts required to disconnect the interface from the launch vehicle. In its high-elasticity state, rubber can absorb and dissipate mechanical energy within a wide range of temperatures, which prevents transmission of engine vibrations to the ground thermal conditioning system. The article presents key properties of rubber used as a structural material and its peculiarities to be considered during design of similar products. Unlike metal showing two types of deformation (elastic and plastic), rubber can exhibit three types of deformation (elastic, superelastic and plastic). In the process of interface design, we took into account two types of deformations (elastic and superelastic ones). Experimental studies of the interface showed its full compliance with technical specification.

Key words: orifice of the launch vehicle, corrugated rubber hose, lock/release assembly, superelastic deformation, leaktightness

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5. Yanhua Li, Yuan Li, Xiaogan Li, Yuquan Wen, Huina Mu and Zhiliang Li. Identification of Pyrotechnic Shock Sources for Shear Type Explosive Bolt, Shock and Vibration Vol. 2017, Article ID 3846236, 9 p. https://doi.org/10.1155/2017/3846236
6. Yanhua Li, Jingcheng Wang, Shihui Xiong, Li Cheng, Yuquan Wen, and Zhiliang Li Numerical Study of Separation Characteristics of Piston-Type Explosive Bolt, Shock and Vibration, Vol. 2019, Article ID 2092796, 18 p. https://doi.org/10.1155/2019/2092796

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8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses
8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses
8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses

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