Keywords cloud
Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Key words: rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design. rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design.
]]>9. General-purpose thermostating module – new approach in development of up-to-date thermostating systems for rocket and space complexes
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 78-84
DOI: https://doi.org/10.33136/stma2024.01.078
Language: Ukrainian
Annotation: These days when creating any rocket space complex, it is important to ensure its advancement and competitive ability. To create such complex, the technical systems it consists of must be implemented with minimal economic and energy costs. Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Development of the competitive rocket and space complex also requires the new approach in the development of the thermostatting system. One of the main tasks is to create a system that can be mass-produced and used as part of any rocket and space complex. Solving this problem will significantly reduce the cost of creating and operating the thermostatting systems and the whole rocket and space complex. One of the ways to solve this task is to create a general-purpose thermostatting system. The modular principle for such thermostatting system would be optimal, which means making up a system from separate modules. It simplifies the all-round installation of various system options and simplifies its setup and operation. The paper demonstrates the possibility and prospects of creating modular thermostatting systems, which enable air supply with the required parameters to different consumers. Characteristics and design of the general-purpose thermostatting module are specified, which can be used as the main component without changing anything in the composition of stationary and mobile thermostatting systems.
Key words: rocket and space complex, launch vehicle, technological systems of the ground complex, thermostatting systems, open type system, versatility, modular design.
Bibliography:
- . Tsiklon-4M. URL: https://www. yuzhnoye.com.
- . KRK «Tsiklon-4M». C4M YZH SPS 090 02 Technicheskoe zadanie na sostavnuyu chast’ OKR «Sistema termostatirovaniya rakety-nositelya i golovnogo bloka» GP «KB «Yuzhnoye». 78 s.
- . KRK «Tsiklon-4M». C4M YZH SPS 119 02 Technicheskoe zadanie na sostavnuyu chast OKR «Transportnaya systema termostatirovaniya» GP «KB «Yuzhnoye». 2018. 40 s.
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Experimental studies of the performance of pyrotechnic devices installed on the launch vehicle separation systems Автори: Boliubash Ye. 2024, (1); 121-128 DOI: https://doi.org/10.33136/stma2024.01.121 Language: Ukrainian Annotation: Pyrotechnic devices are important elements in rocket and space technology, which to a large degree determine the flight success of the launch vehicles, since they enable instantaneous operations to separate spent stages, change configurations, ensure safety, etc. This type of linear shaped charge is one of the most common types of linear shaped charge, which are used in launch vehicle separation systems being developed in Ukraine. Based on the obtained results, it was established that the linear shaped charges under study are operational and meet the requirements for linear shaped charges, installed on launch vehicle separation systems. (2024) "Experimental studies of the performance of pyrotechnic devices installed on the launch vehicle separation systems" Космическая техника.
]]>14. Experimental studies of the performance of pyrotechnic devices installed on the launch vehicle separation systems
Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2024, (1); 121-128
DOI: https://doi.org/10.33136/stma2024.01.121
Language: Ukrainian
Annotation: Pyrotechnic devices are important elements in rocket and space technology, which to a large degree determine the flight success of the launch vehicles, since they enable instantaneous operations to separate spent stages, change configurations, ensure safety, etc. Pyrotechnic devices are subject to strict requirements for reliability, safety, security and efficiency. The article presents an experimental study of the performance of a linear shaped charge of a launch vehicle stage separation system. This type of linear shaped charge is one of the most common types of linear shaped charge, which are used in launch vehicle separation systems being developed in Ukraine. One of the main characteristics of the linear shaped charge, which determines the efficiency and reliability of the separation process, is the depth of penetration of the cumulative jet into the obstacle. The work studied the effect of a cumulative jet of a linear shaped charge with a semi-cylindrical cumulative part. An experimental confirmation of the performance of this type of linear shaped charge is presented, using the example of a linear shaped charge with a diameter of 5 mm, acting on an obstacle made of aluminum alloy grade 2219. The research methodology, experimental scenario, in particular, a description of the research object and a scheme for measuring test results are presented. Depth of cumulative jet penetration into the obstacle was measured in 60 points along the cut line of the samples under study. A statistical analysis of the experimental results was carried out, in particular, the average penetration depth was determined. An improved formula is proposed for the practical calculation of the penetration depth of a cumulative jet for a linear shaped charge with a semi-cylindrical cumulative part, using an additional correction factor. It is noted that the depth of penetration of a cumulative jet into an obstacle is significantly influenced by technological aspects. Taking into account this influence, the lower limit of the one-sided tolerance interval was determined. Recommendations are provided to improve future experimental procedures. Based on the obtained results, it was established that the linear shaped charges under study are operational and meet the requirements for linear shaped charges, installed on launch vehicle separation systems.
Key words: cumulative effect, shaped charge, linear shaped charge, separation systems, pyrotechnic separation devices, linear shaped charge parameters.
Bibliography:
- Petushkov V. G. Pod red. B.Ye.Patona, Priminenie vzryva v svarochnoy technike, K.: Nauk. dumka, 2005, 754 s.
- Physika vzryva. Izd. tretie, t. ІІ. Pod red. L. P. Orlenko. Nauka, 2004, 644 s.
- Baum F. A., Stanyukovich K. P., Shekhter B. I. Physika vzryva. Gos. izd. FM lit. M. 1959, 800 s.
- Kolesnikov K. S., Kozlov V. I., Kokushkin V. V. Dynamika razdeleniya stupeney letatelnykh apparatov. M.: Mashinostroenie. 1977, 224 s.
- Kumulyativniy efect ta iogo vykorystannya dlya rozdilennya raketno-kosmichnykh elementiv za dopomogou pyrotechnichnykh prystroiv. Ye. S. Bolyubash. Materialy XVII naukovykh chytan’ «Dniprovska orbita – 2022» (26–28 zhovtnya). Dnipro, 2022. 263 s.
- ISO 16269-6:2003 Statistical interpretation of data – Part 6: Determination of statistical tolerance intervals (IDT).
- Kobzar A. N. Prikladnaya matematicheskaya statistika. Dlya inzhenerov i nauchnykh rabotnikov. M.: Phizmatlit, 2006, 816 s.
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Keywords cloud
Educational tendencies as an element of innovative progress in the personnel training system for the state-of-the-art enterprises Автори: Zevako V. DOI: https://doi.org/10.33136/stma2024.01.136 Language: Ukrainian Annotation: Yuzhnoye SDO is one of the most state-of-the-art and hi-tech enterprises of the Ukraine’s space and rocket branch. To solve this problem there is personnel training system at the enterprise. ...the following areas: training of the executive personnel and its reserve; training in the postgraduate courses of the enterprise; learning computer technologies; preparation of the pre-launch processing personnel and its reserve; activities with intellectual property; involvement of the leading institutes of higher education both for training of young specialists and... Thus it can be concluded that the personnel training system is effective. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
]]>16. Educational tendencies as an element of innovative progress in the personnel training system for the state-of-the-art enterprises
Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2024, (1); 136-140.
DOI: https://doi.org/10.33136/stma2024.01.136
Language: Ukrainian
Annotation: Yuzhnoye SDO is one of the most state-of-the-art and hi-tech enterprises of the Ukraine’s space and rocket branch. To maintain its scientific and productive potential, among other things, the enterprise needs to have professional specialists, who are development-orientated and eager to enhance their professional skills. To solve this problem there is personnel training system at the enterprise. Responsibility to provide the Yuzhnoye SDO with the skilled specialists is shared, within their authority, between the staff department and the scientific-educational center of the enterprise, which directly report to the General Director. The goal-oriented educational areas, realized at the enterprise, occupy the special role in these activities. The goal-oriented educational areas represent a complex of actions of several divisions at the enterprise, supervised by the scientific-educational center, which aim to provide the corresponding professional level of the employees busy with fulfilment of current job assignments. Among the most significant are the following areas: training of the executive personnel and its reserve; training in the postgraduate courses of the enterprise; learning computer technologies; preparation of the pre-launch processing personnel and its reserve; activities with intellectual property; involvement of the leading institutes of higher education both for training of young specialists and to obtain particular scientific results etc. All these areas have already been proven and some of them run on continuing basis. Thus it can be concluded that the personnel training system is effective. It proves itself and can serve as an example of introduction at any manufacturing enterprise. Besides, orientation of training process at the individual goal-oriented educational areas involves and unites efforts of several interested enterprise divisions to reach particular and necessary results within certain timetable.
Key words: system of specialist training, goal-oriented educational area, training at the enterprise, professional training.
Bibliography:
1. Upravlenie personalom. Uchebnik dlya vuzov. Pod red. T.Yu. Bazarova, B.L. Yeremina.
2-e izd. peredel. i dop. M., YuNITI. 2002. 560 s.
2. Zevako V. S. Pidgotovka naukovo-pedagogichnykh kadriv dlya naukoemnogo pidpriemstva. Svit naukovykh doslidzhen’. Zbirnyk tez mizhnarodnoi naukovo-praktychnoi internet-conferentsii 24-25 bereznya 2022 r. Vyp. 7. S. 90 – 91.
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Keywords cloud
Stated materials are of methodological nature and can be used to engineer the separation systems for LV stages, payload fairings, spacecraft etc. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023).
]]>7. Selection of the functional units for the Cyclone-4M ILV separation system
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2024, (1); 61-71
DOI: https://doi.org/10.33136/stma2024.01.061
Language: Ukrainian
Annotation: Separation of the spent LV stages is one of the important problems of the rocket technology, which
requires the comprehensive analysis of different types of systems, evaluation of their parameters and
structural layouts. Basic requirements are specified that need to be taken into account when engineering
the separation system: reliable and safe separation, minimal losses in payload capability, keeping sufficient
distance between the stages at the moment of the propulsion system start. Detailed classification of their
types («cold», «warm», «hot», «cold-launched» separation) is given and their technical substance with
advantages and drawbacks is described. Certain types of «cold» and «warm» separation of the spent stages
of such rockets as Dnepr, Zenit, Antares, Falcon-9 with different operating principle are introduced – braking
with the spent stage and pushing apart two stages. Brief characteristics of these systems are given, based
on the gas-reactive nozzle thrust, braking with solid-propellant rocket engines, separating with spring or
pneumatic pushers. Development of the separation system for the advanced Cyclone-4M ILV is taken as an
example and design sequence of stage separation is suggested: determination of the necessary separation
velocity and capability of the separation units, determination of the number of active units, calculation of
design and energy parameters of the separation units, analysis of the obtained results followed by the
selection of the separation system. Use of empirical dependences is shown, based on the great scope of
experimental and theoretical activities in the process of design, functional testing and flight operation of
similar systems in such rockets as Cyclone, Dnepr and Zenit. According to the comparative analysis results,
pneumatic separation system to separate Cyclone-4M Stages 1 and 2 was selected as the most effective
one. Its basic characteristics, composition, overall view and configuration are specified. Stated materials
are of methodological nature and can be used to engineer the separation systems for LV stages, payload
fairings, spacecraft etc.
Key words: separation system, functional units of separation, «cold separation», «warm separation», pneumatic pusher, spring pusher, SPRE, gas-reactive nozzles, Zenit LV, Dnepr LV, Falcon 9 rocket, Cyclone-4М LV.
Bibliography:
- Pankratov Yu. , Novikov A. V., Tatarevsky K. E., Azanov I. B. Dynamika perekhodnykh processov. 2014.
- Sinyukov A. M., Morozov N. I. Konstruktsia upravlyaemykh ballisticheskykh raket. 1969.
- Kabakova Zh. V., Kuda S. A., Logvinenko A. I., Khomyak V. A. Opyt razrabotki pneumosystemy dlya otdelenita golovnogo aerodynamicheskogo obtekatelya. Kosmicheskaya technika. Raketnoe vooruzhenie. 2017. Vyp. 2 (114).
- Kolesnikov K. S., Kozlov V. V., Kokushkin V. V. Dynamika razdeleniya stupeney letatelnykh apparatov. 1977.
- Antares – Spaceflight Insider: web site. URL: https://www. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023).
- Falcon 9 – pexels: website. URL: https://www. pexels.com/Falcon 9 (data zvernennya 31.10.2023).
- Kolesnikov K. , Kokushkin V. V., Borzykh S. V., Pankova N. V. Raschet i proektirovanie system razdeleniya stupeney raket. 2006.
- Cyclone-4M – website URL: https://www.yuzhnote.com (data zvernennya 31.10.2023)
- Logvinenko A. Sozdanie gasoreaktivnykh system otdeleniya i uvoda otrabotavshykh stupeney – noviy shag v RKT. Kosmicheskaya tekhnika. Raketnoe vooruzhenie, KBU, NKAU, vyp. 1, 2001.
- Logvinenko A. I., Porubaimekh V. I., Duplischeva O. M. Sovremennye metody ispytaniy system i elementov konstruktsiy letatelnykh apparatov. Monografia. Dnepr, KBU, 2018.
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Keywords cloud
Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 417 – Launch Safety, 2023 [Internet resource]. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 420 License to Operate a Launch Site. ISO 14620-1:2018 Space systems – Safety requirements.
]]>5. Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 40-50
DOI: https://doi.org/10.33136/stma2024.01.040
Language: English
Annotation: Despite stringent environmental requirements, modern launch vehicles/integrated launch vehicles (LV/ILV)
burn toxic propellants such as NTO and UDMH. Typically, such propellants are used in the LV/ILV upper
stages, where a small amount of propellant is contained; however, some LV/ILV still use such fuel in all
sustainer propulsion stages. For launch vehicles containing toxic rocket propellants, flight accidents may result
in the failed launch vehicle falling to the Earth’s surface, forming large zones of chemical damage to people
(the zones may exceed blast and fire zones). This is typical for accidents occurring in the first stage flight
segment, when an intact launch vehicle or its components (usually individual stages) with rocket propellants
will reach the Earth’s surface. An explosion and fire following such an impact will most likely lead to a massive
release of toxicant and contamination of the surface air. An accident during the flight segment of the LV/ILV
first stage with toxic rocket propellants, equipped with a flight termination system that implements emergency
engine shutdown in case of detection of an emergency situation, has been considered. To assess the risk
of toxic damage to a person located at a certain point, it is necessary to mathematically describe the zone
within which a potential impact of the failed LV/ILV will entail toxic damage to the person (the so-called zone
of dangerous impact of the failed LV/ILV). The complexity of this lies in the need to take into account the
characteristics of the atmosphere, primarily the wind. Using the zone of toxic damage to people during the fall
of the failed launch vehicle, which is proposed to be represented by a combination of two figures: a semicircle
and a half-ellipse, the corresponding zone of dangerous impact of the failed LV/ILV is constructed. Taking into
account the difficulties of writing the analytical expressions for these figures during the transition to the launch
coordinate system and further integration when identifying the risk, in practical calculations we propose to
approximate the zone of dangerous impact of the failed LV/ILV using a polygon. This allows using a known
procedure to identify risks. A generalization of the developed model for identifying the risk of toxic damage
to people involves taking into account various types of critical failures that can lead to the fall of the failed
LV/ILV, and blocking emergency engine shutdown during the initial flight phase. A zone dangerous for people
was constructed using the proposed model for the case of the failure of the Dnepr launch vehicle, where the
risks of toxic damage exceed the permissible level (10–6). The resulting danger zone significantly exceeds the
danger zone caused by the damaging effect of the blast wave. Directions for further improvement of the model
are shown, related to taking into account the real distribution of the toxicant in the atmosphere and a person’s
exposure to a certain toxic dose.
Key words: launch vehicle, critical failure, flight accident, zone of toxic damage to people, zone of dangerous impact of the failed launch vehicle, risk of toxic damage to people.
Bibliography:
- Hladkiy E. H. Protsedura otsenky poletnoy bezopasnosti raket-nositeley, ispolzuyuschaya geometricheskoe predstavlenie zony porazheniya obiekta v vide mnogougolnika. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2015. Vyp. 3. S. 50 – 56. [Hladkyi E. Procedure for evaluation of flight safety of launch vehicles, which uses geometric representation of object lesion zone in the form of a polygon. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2015. Issue 3. Р. 50 – 56. (in Russian)].
- Hladkiy E. H., Perlik V. I. Vybor interval vremeni blokirovki avariynogo vyklucheniya dvigatelya na nachalnom uchastke poleta pervoy stupeni. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-tech. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2011. Vyp. 2. s. 266 – 280. [Hladkyi E., Perlik V. Selection of time interval for blocking of emergency engine cut off in the initial flight leg of first stage. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2011. Issue 2. Р. 266 – 280. (in Russian)].
- Hladkiy E. H., Perlik V. I. Matematicheskie modeli otsenki riska dlya nazemnykh obiektov pri puskakh raket-nositeley. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2010. Vyp. 2. S. 3 – 19. [Hladkyi E., Perlik V. Mathematic models for evaluation of risk for ground objects during launches of launch-vehicles. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2010. Issue 2. P. 3 – 19. (in Russian)].
- NPAOP 0.00-1.66-13. Pravila bezpeki pid chas povodzhennya z vybukhovymy materialamy promyslovogo pryznachennya. Nabrav chynnosti 13.08.2013. 184 s [Safety rules for handling explosive substances for industrial purposes. Consummated 13.08.2013. 184 p.
(in Ukranian)]. - AFSCPMAN 91-710 RangeSafetyUserRequirements. Vol. 1. 2016 [Internet resource]. Link : http://static.e-publishing.af.mil/production/1/afspc/publicating/
afspcman91-710v1/afspcman91-710. V. 1. pdf. - 14 CFR. Chapter III. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 417 – Launch Safety, 2023 [Internet resource]. Link: http://law.cornell.edu/cfr/text/14/part-417.
- 14 CFR. Chapter III. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 420 License to Operate a Launch Site. 2022 [Internet resource]. Link: http://law.cornell.edu/cfr/text/14/part-420.
- ISO 14620-1:2018 Space systems – Safety requirements. Part 1: System safety.
- 9 GOST 12.1.005-88. Systema standartov bezopasnosti truda. Obschie sanitarno-gigienicheskie trebovaniya k vozdukhu rabochei zony. [GOST 12.1.005-88. Labor safety standards system. General sanitary and hygienic requirements to air of working zone].
- 10 Rukovodyaschiy material po likvidatsii avarijnykh bolshykh prolivov okislitelya АТ (АК) i goruchego NDMG. L.:GIPKh, 1981, 172 s. [Guidelines on elimination of large spillages of oxidizer NTO and fuel UDMH. L.:GIPH, 1981, 172 p. (in Russian)].
- 11 Kolichestvennaya otsenka riska chimicheskykh avariy. Kolodkin V. M., Murin A. V., Petrov A. K., Gorskiy V. G. Pod red. Kolodkina V. M. Izhevsk: Izdatelskiy dom «Udmurtskiy universitet», 2001. 228 s. [Quantitative risk assessment of accident at chemical plant. Kolodkin V., Murin A., Petrov A., Gorskiy V. Edited by Kolodkin V. Izhevsk: Udmurtsk’s University. Publish house, 2001. 228 p. (in Russian)].
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Keywords cloud
2024, (1); 9-18 DOI: https://doi.org/10.33136/stma2024.01.009 Language: Ukrainian Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Within the framework of extensive cooperation with foreign space companies, on a contract basis, Yuzhnoye propulsion experts are working on the design and development testing of the liquid rocket engines, as well as their components. Space technology. Space technology. Space technology. Space technology.
]]>2. New and advanced liquid rocket engines of the Yuzhnoye SDO
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 9-18
DOI: https://doi.org/10.33136/stma2024.01.009
Language: Ukrainian
Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Moreover, liquid engines design office was assigned with manufacturing and testing of the main rocket engines, developed by NPO Energomash and to be installed on Yuzhnoye-developed launch vehicles. Over the past 66 years Yuzhnoye SDO has developed more than 40 liquid rocket engines (LRE) of various purpose, designed both to gas-generator cycle and to staged combustion cycle. Seventeen of them were commercially produced by Yuzhmash PA and installed on launch vehicles. Nowadays Yuzhnoye propulsion experts keep working on development of the advanced liquid rocket engines powered both by cryogenic and hypergolic propellants, which satisfy the majority of launch service market demands. Within the framework of extensive cooperation with foreign space companies, on a contract basis, Yuzhnoye propulsion experts are working on the design and development testing of the liquid rocket engines, as well as their components. The accumulated vast experience in the development of liquid rocket engines nowadays enables high scientific and technical level in the creation of up-to-date engines, demanded in the world market. Significant steps in this area have been made by the experts from the Yuzhnoye propulsion division and then subsequent manufacture and delivery by Yuzhmash PA of the engine intended for the European rocket Vega Stage 4; and designing the individual components for the engines with thrusts ranging from 500 kgf to 200 tf ordered by foreign customers. This article provides the review of current and scheduled activities of the Yuzhnoye SDO to develop the liquid rocket engines within the thrust ranges from ~ 40 kgf to ~ 500 tf.
Key words: LOX-kerosene liquid rocket engines, hypergolic propellant liquid rocket engines, staged combustion cycle, main rocket engine, thrust, specific thrust impulse.
Bibliography:
- Zhidkostnye raketnye dvigateli, dvigatelnye ustanovki, bortovye istochniki moschnosti, razrabotannye KB dvigatelnykh ustanovok GP«KB «Yuzhnoye». Za nauk. red. akad. NAN Ukrainy S.M. Konyukhova, kand. tekhn. nauk V.M. Shnyakina. Dnipropetrovsk: DP «KB «Pivdenne», 2008. 466 ark.
- Prokopchyuk O. O., Shulga V. A., Khromyuk D. S., Sintyuk V. O. Zhidkostnye raketnye dvigateli GP«KB «Yuzhnoye»: nauk.-tekhn. zbirnyk. Za nauk. red. akademika NAN Ukrainy
O. V. Degtyareva. Dnipro: ART-PRES, 2019. 440 ark.
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2017 (1); 84-87 Language: Russian Annotation: The technique is proposed of reliability evaluation of space launch vehicle low pressure air thermostating system joints hoses. Development of Single Action Units’ Hoses of Cyclone-4 Space Launch System Thermostating System: SOW for R&D 2G40.12.8599.608TЗ/Yuzhnoye SDO.
]]>13. Reliability Evaluation of ILV Thermostating System Mating Hoses
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; State Enterprise DINTEM Ukrainian Research Design-Technological Institute of Elastomer Materials and Products2
Page: Kosm. teh. Raket. vooruž. 2017 (1); 84-87
Language: Russian
Annotation: The technique is proposed of reliability evaluation of space launch vehicle low pressure air thermostating system joints hoses. By calculation method, high reliability level was confirmed of hoses of joints being an interface elements of launch vehicle launch complexes.
Key words:
Bibliography:
1. Development of Single Action Units’ Hoses of Cyclone-4 Space Launch System Thermostating System: SOW for R&D 2G40.12.8599.608TЗ/Yuzhnoye SDO. 2009. 41 p.
2. Abramov E. I., Kolesnichenko K. A., Maslov V. T. Hydraulic Actuator Elements (Guide). Kyiv, 1969. 320 p.
3. Shor Y. B., Kuzmin F. I. Tables for Reliability Analysis and Control. М, 1968. 286 p.
4. Ventsel E. S. Theory of Probability. М., 1964. 576 p.
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Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV Authors: Hlechkov V. (2020) "Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV" Космическая техника. "Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV" Космическая техника. quot;Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV", Космическая техника. Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV Автори: Hlechkov V. Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV Автори: Hlechkov V. Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV Автори: Hlechkov V.
]]>21. Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 184-192
DOI: https://doi.org/10.33136/stma2020.01.184
Language: Russian
Annotation: The article deals with the problems of applying new approaches to formation and improvement of operation system. Turning of space hardware and services into marketable commodity requires their new qualities that determine competitiveness. The main task of presented works was approbation of new approaches to improvement of space launch systems operation quality and operation process effectiveness by the example of prospective Cyclone-4M space rocket complex. The works to form and improve its operation system were performed using the methods based on general theory of space systems operation and the pocedures based on the results of research work conducted by Yuzhnoye SDO in 2015 for analytical evaluation of launch services costs. The topicality of the article is confirmed by the results of practical application of new approaches in main directions of Cyclone-4M space rocket complex operation system improvement, which allowed increasing commercial attractibility of Yuzhnoye SDO-developed systems due to reduction of direct recurring costs and annual expenses. The article describes the course of development of operation model of a created object; based on investigation of the processes of this model, the object’s performance characteristics are detemined. The basis of the article are the organizational-and-technical decisions used herewith and the results obtained for Cyclone-4M space rocket complex. The article is of practical interest for specialists involved in creation of space rocket complexes and other sophisticated systems where the operation system is a multi-level organizational-technical system.
Key words: space hardware, launch services, performance characteristics, operation model, organizational-and-technical decisions
Bibliography:
1. Analiticheskaia otsenka ob’ema rabot i zatrat na puskovye uslugi i napravleniia rabot dlia ikh snizheniia v perspektivnykh RKK razrabotki GP “KB “Yuzhnoye”: tekhn. otchet / GP “KB “Yuzhnoye”. Dnepropetrovsk, 2015. 344 s.
2. Teoriia i praktika ekspluatatsii ob’ektov kosmicheskoi infrastruktury: monografiia / N. D. Anikeichik i dr. SPb., 2006. Т. 1: Ob’ekty kosmicheskoi infrastruktury. 400 s.
3. Ispytaniia i ekspluatatsiia raketnykh kompleksov: kurs lektsii / А. V. Agarkov i dr.; pod red. А. V. Degtyareva. GP “KB “Yuzhnoye”. Dnipro, 2016. Kn. 1. 505 s.
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Ensuring a successful launch of a rocket system became harder due to new engineering problems. The paper considers various aspects of acoustics of the launch of rocket systems, which includes characteristics of acoustic sources in supersonic jets, possibilities and physical limitation factors, under which it is possible to control the sound radiation. URL: https://www.airspacemag. Ask an Astronaut: My Guide to Life in Space. Teramoto 52th AIAA Aerospace Sci. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
]]>17. Acoustic problems of rocket launch
Organization:
Institute of Hydromechanics of National Academy of Sciences of Ukraine, Kyiv, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 155-159
DOI: https://doi.org/10.33136/stma2020.01.155
Language: Russian
Annotation: Due to an increase of power of rocket engines, the high intensity sound field generated by the exhaust jets have become an important factor, which determines the success rate of a rocket launch. Ensuring a successful launch of a rocket system became harder due to new engineering problems. Identification and definition of acoustic sources structure within a complex supersonic jet, being a one of the most important scientific problems, which have to be solved to find the ways to control accoustic radiation. A three components of acoustic sources can be defined here – broadband signals from large and small components of of turbulent jet and tonal signals which usually being overlooked during the estimation of overall sound pressure level. The paper considers various aspects of acoustics of the launch of rocket systems, which includes characteristics of acoustic sources in supersonic jets, possibilities and physical limitation factors, under which it is possible to control the sound radiation. Among the possible ways to control the process of sound generation by a jet, a method of water injection in a jet is being studied. While saving the general thrust of the engine this method can not greatly reduce the sound radiation by a jet. It is recommended to use big amounts of water-air mix to protect the launch pad from damage. Significant progress on the topic of understanding the process of sound generation by supersonic jets can be achieved via mathematical modeling of sound radiation. The latest achievements of mathematical modeling of sound generation by supersonic jets being presented.
Key words: Acoustics of rocket launch, acoustic efficiency of a jet, semi-empirical models of of jet acoustics, numeric-computational methods in aeroacoustics, control of jet-generated acoustic levels
Bibliography:
1. Lighthill M. J. On Sound Generated Aerodynamically: I. General Theory. Proc. Roy. Soc. London Ser. A, 211. 1952. Р. 564–581. https://doi.org/10.1098/rspa.1952.0060
2. Tam C. K. W. Jet noise. Theoretical Computftional Fluid Dynamics. 1998. No 10. Р. 393–405. https://doi.org/10.1007/s001620050072
3. Lubert C. P. Sixty years of launch vehicle acoustics. Proc.Mtgs.Acoust. Vol. 31. 2017. https://doi.org/10.1121/2.0000704
4. Ask the Astronaut: What does launch feel like? URL: https://www.airspacemag. com/ask-astronaut/ask-astronaut-what-does-launch-feel-what-thoughts-and-emotions-run-through-your-mind-180959920/
5. Tim P. Ask an Astronaut: My Guide to Life in Space. 2018. 272 p.
6. Saucer B. What’s the Deal with Rocket Vibration? MIT Technology Review. July 15, 2009. URL: https://www.technology-review.com/s/414364https:/whats-the-deal-with-rocket-vibrations/
7. Ross D. Mechanics of Underwater noise. 1976. 266 p.
8. Varnier J. Experimental study and simulation of rocket engine free jet noise. AIAA J. 2001. Vol. 39, Nо 10. P. 1851–1859. https://doi.org/10.2514/2.1199
9. Eldred K. M. Acoustic loads generated by the propulsion system. NASA SP-8072, 1971. 49 p.
10. Balakrishnan P., Srinivason K. Impinging get noise reduction using non-circular jets. Applied Acoustics. 2019. Vol. 143. Р. 19-30. https://doi.org/10.1016/j.apacoust.2018.08.016
11. Tsutsumi S. Acoustic generation mechanism of a supersonic jet impinging on deflectors / S. Tsutsumi, R. Takaki, Y. Nakanishi, K. Okamoto, S. Teramoto 52th AIAA Aerospace Sci. Meet. AIAA Pap. 2014-0882. 2014. 12 p. https://doi.org/10.2514/6.2014-0882
12. Ahuja K. K., Manes J. P., Massey K. C., Calloway A. B. An Evaluation of various concepts of Reducing Supersonic Jet Noise, AIAA-90-3982. AIAA 13th Aeroacoustic Conference, 1990. Р. 1-21. https://doi.org/10.2514/6.1990-3982
13. Krathapalli A., Lenkatakrishnan L., Elovarsan R., Laurenco L. Supersonic Jet Noise Suppression by Water Injection. AIAA 2000-2025. 6th AIAA/CEAS Aeroacoustic Conference, 2000. Р. 1-25.
14. Moratilla-Vega M. A., Lackhole K., Janicka J., Xia H., Page C. J. Jet Noise Analysis using an Efficient LES/ High-Order Acoustic Coupling Method. Computer and Fluid. 2020. https://doi.org/10.1016/j.compfluid.2020.104438
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Keywords cloud
Mathematical models of hydraulic servomechanisms of space technologynt Authors: Kozak L. 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. Gidravlicheskii privod system upravleniia. (2020) "Mathematical models of hydraulic servomechanisms of space technologynt" Космическая техника. Space technology. "Mathematical models of hydraulic servomechanisms of space technologynt" Космическая техника.
]]>13. Mathematical models of hydraulic servomechanisms of space technologynt
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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Keywords cloud