Search Results for “ground operations” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Thu, 25 Apr 2024 06:24:09 +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 “ground operations” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation https://journal.yuzhnoye.com/content_2020_1-en/annot_7_1_2020-en/ Wed, 13 Sep 2023 06:27:07 +0000 https://journal.yuzhnoye.com/?page_id=31031
ESA Operations. – Access mode: https://twitter.com/esaoperations/status/ 1168533241873260544 (Access date 12.09.2019). Orbital Debris: The Growing Threat to Space Operations / Advances in the Astronautical Sciences. Trajectory Error and Covariance Realism for Launch Cola Operations / Advances in the Astronautical Sciences. Recommended Risk Assessment Techniques and Thresholds for Launch Cola Operations / Advances in the Astronautical Sciences.
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7. Mechanics of a satellite cluster. Methods for estimating the probability of their maximal approach in flight

Authors:

Holubek O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 76-84

DOI: https://doi.org/10.33136/stma2020.01.076

Language: Russian

Annotation: The mathematic modeling was performed of the flight of light-class three-stage launch vehicle injecting a payload into sun-synchronous orbit of 700 km altitude and a cluster of observed space debris objects in the conditions of dynamically changing cataloged space situation. It is shown that as the launch moment becomes closer, the cataloged space situation is ascertained, which leads to the constant change of the quantity of hazardous space debris objects observed in the vicinity of launch vehicle trajectory and to the change of the parameters of their approach to the launch vehicle: minimal relative distance, relative velocity, rendezvous angle and launch moment for which hazardous approach is revealed. The hazardous approaches for the launch vehicle trajectory under consideration are more often observed with the relative velocities of more than 8 km/s and rendezvous angles less than 90 deg and their variations within the launch window do not exceed 1.2 m/s and 0.035 deg respectively. In this case, the histograms of distribution of relative distance, relative velocity, and rendezvous angle from catalog to catalog vary insignificantly. The distribution of hazardous approaches in launch time within launch window is not uniform, the regions are observed with low quantity of hazardous approaches and with high quantity. The hazard of launch vehicle collision with observed space debris objects in a launch is confirmed. In all, in the launch day time window under consideration, more than ten hazardous approaches are revealed, for two of them the approach to minimal distance of less than 1 km is predicted. This testifies to the necessity of taking measures to increase safety of launch vehicle flight through observed space debris cluster. In order to increase Ukrainian launch vehicles miss ion safety in the conditions of near space pollution, it is proposed to create the system of pre -flight space analysis, whose tasks are periodic analysis of space situation not less than once in a day, revealing of hazardous approaches, determination of their parameters, and preparation of data to make decision on launch time.

Key words: method of launch time planning, safety of flight through space debris cluster

Bibliography:
1. ESA Operations. For the first time ever, ESA has performed a ‘collision avoidance manoeuvre’ to protect one of its satellites from colliding with a ‘mega constellation’. Electronic resource. – Access mode: https://twitter.com/esaoperations/status/ 1168533241873260544 (Access date 12.09.2019).
2. Klinkrad H. Space Debris – Models and Risk Analysis. Chichester, UK: Praxis Publishing Ltd, 2006. 430 p.
3. Johnson N. L. Orbital Debris: The Growing Threat to Space Operations / Advances in the Astronautical Sciences. 2010. Vol. 137. P. 3-11.
4. Orbital Debris. A Technical Assessment. Washington, D.C.: National Academy Press, 1995. 210 p.
5. Bandyopadhyay P., Sharma R.K., Adimurthy V. Space debris proximity analysis in powered and orbital phases during satellite launch / Advances in Space Research. 2004. Vol. 34. P. 1125-1129. https://doi.org/10.1016/j.asr.2003.10.043
6. Adimurthy V., Ganeshan A. S. Space debris mitigation measures in India / Acta Astronautica. 2005. Vol. 58. P. 168-174. https://doi.org/10.1016/j.actaastro.2005.09.002
7. Schultz E. D., Schultz E. D., Wilde P. D. Mitigation of Collision Hazard for the International Space Station from Globally Launched Objects / 6th IAASS Conference Safety is Not an Option. 21-23 May 2013. Montreal, Canada. Electronic resource. Access mode: https://iaassconference2013.-space-safety.org/ wp-content/uploads/sites/-19/2013/06/ 1420_Shultz.pdf (Access date 12.09.2019).
8. Brevdik G. D., Strub J. E. Determination of acceptable launch windows for satellite collision avoidance / AAS/AIAA Astrodyna-mics Conference. 19-21 August 1991 Pt1. Durango USA. Astrodynamics. P. 345-356.
9. Hejduk M. D., Plakalovic D., New-man L. K., Ollivierre J. C., Hametz M. E., Beaver B. A., Thompson R. C. Trajectory Error and Covariance Realism for Launch Cola Operations / Advances in the Astronautical Sciences. 2013. Vol. 148. P. 2371-2390.
10. Hejduk M. D., Plakalovic D., New-man L. K., Ollivierre J. C., Hametz M. E., Beaver B. A., Thompson R. C. Recommended Risk Assessment Techniques and Thresholds for Launch Cola Operations / Advances in the Astronautical Sciences. 2014. Vol. 150. P. 3061-3080.
11. Handschuh D. A., Wang C., Vidal B. Operational Feedback on Four Years of Collision Risk Avoidance at Launch in Europe / 7th IAASS Conference Space Safety is No Accident, 20-22 October 2014. Fredrichschafen, Germany. P. 355-363. https://doi.org/10.1007/978-3-319-15982-9_42
12. Ihdalov I. М., Kuchma L. D., Poliakov N. V., Sheptun Yu. D. Dinamicheskoe proektirovanie raket. Zadachi dinamiki raket i ikh kosmicheskikh stupenei: mohografiia / pod red. akad. S. N. Koniukhova. Dnepropetrovsk, 2010. 264 s.
13. NIMA TR 8350.2. Department of Defense world geodetic system 1984: Its definition and relationships with local geodetic systems. 3-d ed. National Geospatial-Intelligence Agency, 2000. 174 p.
14. NGA EGM2008 – WGS 84 version. Electronic resource. Access mode to page: http://earth-info.nga.mil/GandG/ wgs84/gravitymod/egm2008/ gm08_wgs84.html. (Access date 12.09.2019).
15. Holubek А. V. Sblizheniie rakety-nositelia s katalogizirovannymi kosmicheskimi ob’ektami v processe vyvedeniia na orbity s nizkim nakloneniem / Izvestiia vysshikh uchebnykh zavadenii. Mashinostroenie. 2018. №2 (695). S. 86-98.

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7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation
7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation
7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation

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]]> 8.2.2018 Development of Nozzle Blocks New Manufacturing Technology without Blazing https://journal.yuzhnoye.com/content_2018_2-en/annot_8_2_2018-en/ Thu, 07 Sep 2023 11:21:51 +0000 https://journal.yuzhnoye.com/?page_id=30757
The laser welding and surfacing technology will allow avoiding the use of costly and unique equipment and will allow reducing and optimizing the technological manufacturing cycle rejecting the long –term and energy-consuming technological operations.
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8. Development of Nozzle Blocks New Manufacturing Technology without Blazing

Authors:

Kovalenko A. M.1, Kirsanov D. V.1, Mirosidi M. A.1, Shelyagin V. D.2, Bernatsky A. V.2, Siora O. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; STC «Paton Welding Institute», Kiev, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2018 (2); 68-75

DOI: https://doi.org/10.33136/stma2018.02.068

Language: Russian

Annotation: The article describes the problems of manufacturing large-size nozzle blocks by classical for Ukrainian space industry method of high-temperature brazing. The Yuzhnoye SDO-selected way of solving this problem and the first strides on the way to organization of new production using innovative technologies of laser welding and surfacing are presented. The step-by-step sequence and procedure of research work to develop and test a new technology of cooled nozzle block manufacturing are described. Four phases are identified, out of which the first two phases have already been successfully performed. The laser welding and surfacing technology will allow avoiding the use of costly and unique equipment and will allow reducing and optimizing the technological manufacturing cycle rejecting the long –term and energy-consuming technological operations. The scientific-and-technological works performed showed the principle feasibility of making connection between the external jacket and internal wall of a nozzle block using laser welding. The test samples manufactured confirmed the high strength characteristics, which had been preliminary obtained by the theoretical calculation methods. The sections obtained by surfacing demonstrate good metallurgical connection between the layers. On the test samples, the technique was tried-out allowing repairing defect areas in a welded seam obtained by laser welding method. This is especially important from the technological and economic viewpoints, as the technology of high-temperature brazing applied currently does not allow making guaranteed repair of brazed joints.

Key words: liquid rocket engine nozzles, laser, laser welding, laser surfacing

Bibliography:

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8.2.2018 Development of Nozzle Blocks New Manufacturing Technology without Blazing
8.2.2018 Development of Nozzle Blocks New Manufacturing Technology without Blazing

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]]> 2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop https://journal.yuzhnoye.com/content_2018_1-en/annot_2_1_2018-en/ Mon, 04 Sep 2023 12:45:06 +0000 https://journal.yuzhnoye.com/?page_id=30403
A comparison of nitrogen and time specific consumption in dehydration operations is done and recommendations are given for their use in the cosmodromes’ launch complexes fuel storage and preparation facilities. Space Rocketry Ground Infrastructure Technological Facilities: Engineering Manual.
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2. Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop

Authors:

Salo М. P., Tereschenko K. O., Ivanitsky G. М.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 6-12

DOI: https://doi.org/10.33136/stma2018.01.006

Language: Russian

Annotation: An alternative method of kerosene dehydration is proposed, which is based on application of cyclic technology of supersaturation decrease using dry nitrogen. A comparison of nitrogen and time specific consumption in dehydration operations is done and recommendations are given for their use in the cosmodromes’ launch complexes fuel storage and preparation facilities.

Key words:

Bibliography:

1. Zrelov V. N., Seryogin E. P. Liquid Rocket Propellants. М., 1975. 320 p.
2. Energy-Intensive Fuels for Aircraft and Rocket Engines / Under the editorship of L. S. Yanovsky. М., 2009. 400 p.
3. Soyuz-2. URL: https://ru.wikipedia.org/wiki/Soyuz-2_(launch vehicle family).
4. Angara. URL: https://ru.wikipedia.org/wiki/Angara_(launch vehicle).
5. Zenit-2. URL: https://ru.wikipedia.org/wiki/Zenit-2_(launch vehicle).
6. Leshchiner L. B., Ul’yanov I. E. Designing of Aircraft Fuel Systems. М., 1975. 344 p.
7. Zenit Space Launch System from the Eyes of its Developers / Under the editorship of e.d. professor V. N. Solov’yov, e.d. professor G. P. Biryukov, N. S. Kozhukhov, N. I. Kursenkova. М., 2003. 213 p.
8. Space Rocketry Ground Infrastructure Technological Facilities: Engineering Manual. Book 1. М., 2005. 416 p.
9. Investigation of Prospective Propellant Preparation Technologies: Scientific-Technical Report 21.18258.173ОТ / Yuzhnoye SDO. 2016. 115 p.
10. Shleifer A. A., Litvinov A. N. Prospective Technologies to Prepare Propellants with Improved Performance Properties. Ul’yanovsk, 1989. 215 p.
11. Englin B. A. Use of Liquid Propellants at Low Temperatures. 3-rd edition revised and enlarged. М., 1980. 207 p.
12. Volkov A. I., Zharsky I. M. Big Chemical Guide. Minsk, 2005. 608 p.
13. Calculated Evaluation and Experimental Check of RPC Degassing and Saturation by Helium for Filling Cyclone-4 LV: Technical Note Cyclone-4. 22.6849.123 СТ / Yuzhnoye SDO. 2005. 29 p.

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2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop
2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop
2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop
]]> 8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation https://journal.yuzhnoye.com/content_2019_1-en/annot_8_1_2019-en/ Thu, 25 May 2023 12:09:45 +0000 https://journal.yuzhnoye.com/?page_id=27713
For the specified loading conditions during the ground operations with the warhead, the most dangerous computational cases are determined which have been implemented during the virtual tests. Key words: computer modelling , computational models , ground operations , mechanical condition , performance Bibliography: 1. computer modelling , computational models , ground operations , mechanical condition , performance .
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8. Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation

Authors:

Tonkonozhenko A. M.1, Kozharin V. Y.1, Martynenko G. Y.3, Chernobryvko M. V.2, Avramov K. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine2; National Technical University “Kharkiv Polytechnic Institute”, Kharkiv, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2019, (1); 54-63

DOI: https://doi.org/10.33136/stma2019.01.054

Language: Russian

Annotation: This paper describes the effective approach for the technology of the rocket airframe development testing, based on the method of numerical modelling, which enables the virtual experimental runs prior to the beginning of the development testing to check the performance of the standard airframes and predict issues of concern. The method is realized based on the computer models developed in the ANSYS Workbench environment. Based on the offered method the complex mechanical system, which attaches the cluster projectiles in the conditions of the temperature exposure and heat cycling, underwent the virtual tests. Computational models, criteria and test procedures necessary for the analysis of the mechanical condition and prediction of the performance of the actual airframe of the warhead were developed. Moreover, computational models consider all the design and technological features of the airframe: layout of the projectiles attachments, initial stress-strain state of the system after the tightening of the threaded connections, friction between the components of the system and their mutual displacement, temperature dependence of the physical and mechanical characteristics and ultimate stress of materials. For the specified loading conditions during the ground operations with the warhead, the most dangerous computational cases are determined which have been implemented during the virtual tests. Test results were used to conduct the static analysis of the mechanical condition, strength and conditions for performance of the actual structure of the attachment under the impact of the operating levels of temperature exposure and heat cycling. Results of the virtual tests confirm the performance of the projectiles attachment system and are introduced into production in the phase of engineering development.

Key words: computer modelling, computational models, ground operations, mechanical condition, performance

Bibliography:

1. Birger I. A., Iosilevich G. B. Rezbovye i flantsevye soedineniya. M.: Mashinostroenie, 1990. 368 p.
2. Kukhling Ch. Spravochnik po phisike. M.: Mir, 1985. 520 p.
3. Nikolskiy B. P., Rabinovich V. A. Spravochnil chimika. T. 6. L.: Chimiya, 1967. 1009 p.
4. Stali I splavy. Marochnik: Sprav. izd. / pod red. V. G. Sorokina, M. A. Gervasieva. M.: Intermet Engineering, 2001. 608 p.
5. Numerical simulation of missile warhead operation / G. Martynenko, M. Chernobryvko, K. Avramov, V. Martynenko, A. Tonkonozhenko, V. Kozharin, D. Klymenko / Advances in Engineering Software. 2018. Vol. 123. P. 93-103. https://doi.org/10.1016/j.advengsoft.2018.07.001

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8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation
8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation
8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation

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]]> 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
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.
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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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]]> 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

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.
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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.
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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
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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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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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]]> 13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight https://journal.yuzhnoye.com/content_2019_1-en/annot_13_1_2019-en/ Wed, 24 May 2023 16:00:19 +0000 https://journal.yuzhnoye.com/?page_id=27718
Based on the statistical processing of the deviations of the predicted time of solid fuel burn-out versus the realized one it was determined that the forecast based on the results of apparent acceleration measurement has the greatest accuracy with the minimal number of operations.
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13. Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

Authors:

Holubek O. V., Filippenko I. M., Tatarevsky K. E.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 87-94

DOI: https://doi.org/10.33136/stma2019.01.088

Language: Russian

Annotation: This article considers the problem of determination of propulsion system solid fuel burn-out time in the extraatmospheric flight segment taking the apparent acceleration and apparent speed measured by the inertial navigation system. Correlation analysis of the realized and nominal dependencies of the apparent acceleration and apparent speed of the launch vehicle on relative operating time of the propulsion system is suggested to be used to forecast the fuel burn-out time. In order to improve the accuracy of the forecast, and to decrease the amplitude and vibration rate of its results several channels simultaneously are suggested to be used for calculations with subsequent majority voting and digital filtration. As a result of the study, the procedure to forecast the time of solid fuel burn-out in the launch vehicle propulsion system in flight has been developed. Operability of the suggested procedure has been verified using the mathematical simulation of the launch vehicle flight for two operating modes of the propulsion system different from the nominal ones. Based on the statistical processing of the deviations of the predicted time of solid fuel burn-out versus the realized one it was determined that the forecast based on the results of apparent acceleration measurement has the greatest accuracy with the minimal number of operations. Suggested procedure is easily realized as the multistage adaptive algorithm and can be used in the guidance system of the solid-propellant launch vehicle in the extra-atmospheric flight segment for the numerical forecast of the reachable terminal parameters of flight, definition of command vector and development of the relevant thrust vector control commands.

Key words: guidance system, correlation analysis, procedure, mathematical simulation

Bibliography:

1. Osnovy teorii avtomaticheskogo upravleniya raketnymi dvigatelnymi ustanovkami / A. I. Babkin, S. I. Belov, N.B. Rutovskiy i dr. – M.: Mashinostroenie, 1986. – 456 s.
2. Proektirovanie system upravleniya obiektov raketno-kosmicheskoy techniki. T. 1. Proektirovanie system upravlenia raket-nositeley: Uchebnik/Yu. S. Alekseev, Yu. Ye. Balabey, T. A. Baryshnikova i dr.; Pod obshey red. Yu. S. Alekseeva, Yu. M. Zlatkina, V. S. Krivtsova, A. S. Kulika, V. I. Chumachenko. – Kh.: NAU «KhAI», NPP «Khartron-Arkos», 2012. – 578 s.
3. Sikharulidze Yu. G. Ballistika letatelnykh apparatov. – M.: Nauka, 1982. – 352 s.
4. Lysenko L. N. Navedenie I navigatsia ballisticheskykh raket: Ucheb. posobie. – M.: Izd-vo MGTU im. N. E. Baumana, 2007. – 672 s.
5. Systemy upravleniya letatelnymi apparatami (ballisticheskimi raketami I ikh golovnymi chastyami): Uchebnik dlya VUZov/ G. N. Razorenov, E. A. Bakhramov, Yu. F. Titov; Pod red. G. N. Razorenova. – M.: Mashinostroenie, 2003. – 584 s.
6. Siouris G. M. Missile guidance and control systems. – New York: Springer-Verlag New York, Inc., 2004. – 666 p. https://doi.org/10.1115/1.1849174
7. Zarchan P. Tactical and Strategic missile guidance. – American Institute of Aeronautics and Astronautics, Inc., 2012. – 989 p. https://doi.org/10.2514/4.868948
8. Balakrishnan S. N. Advances in missile guidance, control, and estimation / S. N. Balakrishnan, A. Tsourdos, B.A. White. – New York: CRC Press, Taylor & Francis Group. 2013. – 682 p.
9. Shneydor N. A. Missile guidance and pursuit: kinematics, dynamics and control. – Horwood Publishing Chichester, 1998. – 259 p. https://doi.org/10.1533/9781782420590
10. Yanushevsky R. Modern missile guidance. – CRC Press, Taylor & Francis Group, 2008. – 226 p. https://doi.org/10.1201/9781420062281

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13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight
13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight
13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

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]]> 9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software https://journal.yuzhnoye.com/content_2023_1-en/annot_9_1_2023-en/ Fri, 12 May 2023 16:11:14 +0000 https://test8.yuzhnoye.com/?page_id=26993
Based on this, as well as taking into account the sharp increase in the cost of weaponry, the considered problem is classified as an optimization one that should be solved through the theory of operations research. The classification of mathematical models has been indicated according to the scale of reproduced operations, purpose, and goal orientation. The first is implemented through modeling of the combat operations.
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9. Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software

Authors:

Yenotov V. H., Kushnir B. I., Pustovharova O. V., Chubarov A. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 77-87

DOI: https://doi.org/10.33136/stma2023.01.077

Language: Ukrainian

Annotation: Substantiation of the research tools has been performed as a part of methodology development for the air and missile defense system. The problem under consideration is very complex due to the multifactorial nature of the research object, its qualitative variety and manifold structure, incomplete definition of the problem statement. Furthermore, the ability of modern technologies to produce different arms systems, which are capable of carrying out same class tasks, considerably increases the risk of making not the best decisions. Based on this, as well as taking into account the sharp increase in the cost of weaponry, the considered problem is classified as an optimization one that should be solved through the theory of operations research. In this theory, such task is viewed as a mathematical problem, and mathematical simulation is the basic method of research. The main types of mathematical models, their areas of application have been considered as a part of the analysis. The classification of mathematical models has been indicated according to the scale of reproduced operations, purpose, and goal orientation. Quantitative and qualitative correlation of forces has been accepted as the efficiency criterion, which determines a goal orientation of the model. The problems related to this have been shown. In particular, searching for the compromise between simplicity of the mathematical model and its adequacy to the research object is among these problems. Two of the basic approaches to principles of the military operation model construction and its assessment have been considered. The first is implemented through modeling of the combat operations. The second approach is based on the assumption that different armament types can be compared based on their contribution to the outcome of the operation, and on the possibility to assign «a weighting coefficient» named as a combat potential to each of these types. The modern level of problem solving related to this method has been shown. The reasonability of its application in the considered task, including the definition of forces correlation of the opposing parties, has been substantiated. The basic regulations of the construction concept of the required mathematical model and tools for its research have been formulated based on the analysis results: the assigned problem should be solved by analytical methods through the theory of operations research; the analytical model is the most acceptable conception of the analyzed level of the military operation; the synthesis of the model should be based on the idea of a combat potential. At the same time, it should be taken into account that the known approach to the definition of forces correlation, which uses the combat potential method, has a number of essential limitations, including the methodological ones. Therefore, within the bounds of further research, this approach requires the development both in terms of improving the reliability of the single assessment and in terms of giving the system qualities to the synthesized mathematical model.

Key words: multifunctional system, mathematical model, military unit, combat potential, correlation of forces, defensive sufficiency

Bibliography:

1. Pavlyuk Yu. S. Ballisticheskoe proektirovanie raket: ucheb.-metod, posobie dlya vuzov. UDK623.451.8. Izd-vo ChGTU, Chelyabinsk, 1996. 92 s.
2. Nikolaev Yu. M., Solomonov Yu. S. Inzhenernoe proektirovanie upravlyaemykh ballisticheskikh raket s RDTT. M., 1979. 240 s.
3. Enotov V. G., Kirichenko A. S., Pustovgarova Ye. V. Osobennosti rascheta i vybora raskhodnoy diagrammy dvukhrezhimnykh marshevykh RDTT: ucheb.-metod. posobie. Pod red. akadem. A. V. Degtyreva. Dnepr, 2019. 68 s.
4. Enotov V. G., Kushnir B. I., Pustovgarova Ye. V. Metodika-programma proektnoy otsenki characteristic marshevykh dvigateley na tverdom toplive s korpusami iz vysokoprochnykh metallicheskikh materialov, statsionarnymi soplami i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. A. S. Kirichenko. Dnep, 2019. 91 s.
5. Enotov V. G., Kirichenko A. S., Kushnir B. I., Pustovgarova Ye. V. Metodika proektnoy otsenki characteristic marshevykh dvigatelnykh ustanovok na tverdom toplive s povorotnymi upravlyayuschimi soplami, plastikovymi tselnomotannymi korpusamy i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. akadem. A. V. Degtyareva. Dnepr. 2019. 149 s.
6. Alemasov V. Ye., Dregalin A. F., Tishin A. P. Teoriya raketnykh dvigateley. M., 1980. 55 s.
7. Raschetnye materialy dlya podgotovki i vydachi iskhodnykh dannykh na razrabotku uzlov marshevykh dvigatelnykh ustanovok na tverdom toplive. Raschet ID metodom avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: inzhenern. zapiska 553-376 IZ. GP «KB «Yuzhnoye». Dnepropetrovsk, 2017. 30 s.
8. Metodika avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: nauch.-tekhn. Otchet 03-453/32 NTO. GP «KB «Yuzhnoye». Dnepropetrovsk, 2010. 127 s.

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9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software
9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software
9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software

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]]> 5.1.2023 Fueling-neutralization stations. New developments and applications https://journal.yuzhnoye.com/content_2023_1-en/annot_5_1_2023-en/ Fri, 12 May 2023 16:10:44 +0000 https://test8.yuzhnoye.com/?page_id=26989
2023 (1); 48-55 DOI: https://doi.org/10.33136/stma2023.01.048 Language: Ukrainian Annotation: The article dwells on development and study of the multifunctional operations while preparing propellant components for launch vehicle tank filling by high-boiling propellant components at the neutralization stations. This article studies multifunctional operations, where the propellant is simultaneously drained from delivery vehicles, saturated with helium and denitrogenated.
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5. Fueling-neutralization stations. New developments and applications

Authors:

Pozdieiev H. L., Litau Ye. E.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 48-55

DOI: https://doi.org/10.33136/stma2023.01.048

Language: Ukrainian

Annotation: The article dwells on development and study of the multifunctional operations while preparing propellant components for launch vehicle tank filling by high-boiling propellant components at the neutralization stations. The article considers the preparation of propellant for filling the launch vehicle stages with high-boiling propellant components of nitrogen tetroxide (oxidizer) and unsymmetrical dimethyl hydrazine (fuel) in terms of propellant saturation with helium and denitrogenation. Usually these issues refer to the common technology of propellant preparation and are tackled sequentially: first, propellant is drained into the filling tank of the filling system, then the propellant is denitrogened, for example purging the propellant by helium under atmospheric pressure in the tank, then propellant is saturated with helium to the given concentration by bubbling helium in the propellant, maintaining the set pressure of helium in the tank. This technology significantly complicates the process of propellant preparation, increases helium consumption, as well as the amount of the generated vapor, which requires recycling in the neutralization units. This article studies multifunctional operations, where the propellant is simultaneously drained from delivery vehicles, saturated with helium and denitrogenated. Amount of residual nitrogen in the propellant and the main direction of deep denitrogenation of the propellant are calculated. Amount of generated vapor and consumed helium are determined. The process of propellant draining by extrusion, maintaining the given pressure in the tank and alternating the propellant drain on the closed vent device (compression) and open vent device (decompression) is studied. As a result, the theoretical justification of multifunctional operations in preparation of high–boiling propellant components to fill the launch-vehicle stages is presented.

Key words: saturation with helium and denitrogenation of the propellant, drain with closed vent device, excessive pressure draining, gas-vapor mixture, neutralization system

Bibliography:

1. Pozdeev G. L., Kucherenko R. A., Kucherenko T. V. Issledovanie osobennostey dostavki na kosmodrom komponentov raketnogo topliva s zadannym gazonasyschenniem. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. / GP «KB «Yuzhnoye». Dnepr, 2019. Vyp. 1. S. 38–44. https://doi.org/10.33136/stma2019.01.038
2. Pozdeev G. L. Razrabotka I issledovanie metodov obespecheniya zadannyh parametrov pri zapravke: dis. na soiskanie kand. tehn. nauk. GP «KB «Yuzhnoye», 1978. Dnepropetrovsk. 123 s.
3. KRK «Tsiklon-4M». Zapravochno-neitralizatsionnaya stantsia. Tehnicheskiy proekt. С4М YZH-ANL 02802. GP «KB «Yuzhnoye». 2017. 108 s.
4. KRK «Tsiklon-4M». Predlozheniya po helirovaniyu komponentov topliva dlya zapravki 2-oy stupeni rakety-nositelya na ZNS s uchetom osobennostey dostavki topliva v hermetichnyh konteynerah-tsisternah. Nauchno-tehnicheskiy otchet. Tsiklon-4M. 21.18668.174 OT. GP «KB «Yuzhnoye», 2019. 33 s.
5. Sposob zakrytoy zapravki toplivnogo baka zhidkim toplivom i systema dlya ego osuschestvlenniya: pat. RU 2489327. В64F1/28.

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5.1.2023 Fueling-neutralization stations. New developments and applications
5.1.2023 Fueling-neutralization stations. New developments and applications
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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
The integral component of this problem along with the safety of operations during launch vehicle ground pre-launch processing is organization of flight safety.
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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.
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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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