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Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period Authors: Oglikh V. 2 Organization: Yangel Yuzhnoye State Design Office 1 , Dnipro, Ukraine; SSRI, Shostka, Ukraine 2 Page: Kosm. 2016 (2); 30-34 Language: Russian Annotation: The paper considers possible ways of the development of impulse SRM with operating time from 0.02 to 0.05 s. It is suggested to use the existing gunpowders as a charge for impulse SRM. Key words: Bibliography: Full text (PDF) || Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
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]]>4. Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period
Organization:
Yangel Yuzhnoye State Design Office1, Dnipro, Ukraine; SSRI, Shostka, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2016 (2); 30-34
Language: Russian
Annotation: The paper considers possible ways of the development of impulse SRM with operating time from 0.02 to 0.05 s. The tests of prototype motor show the development capability of such motor. It is suggested to use the existing gunpowders as a charge for impulse SRM.
Key words:
Bibliography:
Full text (PDF) || Content 2016 (2)
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, Magdin E. Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm. Such procedure has been developed based on Ansys software package. The article describes areas of further design and experimental activities, fulfilment of which will provide development of production models of the described engines. Golubev K. Dnepr: GP KB «Yuzhnoye». Gubertov A. Energoatomizdat, 1990. Magdin E. dvigatelestroiteley. S., Magdin E. Space technology. Space technology. S., Magdin E. Space technology. S., Magdin E. Space technology. S., Magdin E. Space technology. S., Magdin E. Space technology. S., Magdin E. Space technology.
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]]>17. Development of Prospective Small-Size Auxiliary SMR of New Type
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 114-121
DOI: https://doi.org/10.33136/stma2019.01.114
Language: Russian
Annotation: This article considers essentially new versions of small-sized solid propellant rocket engines (SRE), designed for rocket and spacecraft flight control with serial artillery pyroxiline powder taken as grain and solidpropellant gas generators discretely operating into the receiver. Preliminary results of design and experimental activities, performed in Yuzhnoye SDO, showed the possibility in principle and practicability to develop two new types of advanced small-sized SRE. Testing SRE with pyroxiline powder grain showed that the optimum design of the engine can be developed only with the application of the specially developed design procedure of the gas-dynamic flow pattern of powder gases in the engine chamber with definition of field of pressure and velocity. Such procedure has been developed based on Ansys software package. The article describes areas of further design and experimental activities, fulfilment of which will provide development of production models of the described engines. Intraballistic characteristics design procedure, mentioned in the article, can be used to design new type of micropulse SRE with less than 0.1 s burn time. This article will also facilitate definition of the application area for discrete solid-propellant propulsion systems, where they get the edge over the cold gas gas-jet systems.
Key words: procedure, microSRE, gas-jet system, heat-transfer factor
Bibliography:
1. Kovalenko N. D., Kukushkin V. I. Triumph I tragediya systemy upravleniya vektorom tyagi dvigatelya ZD65 vduvom kamernogo gaza v soplo// Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2014. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 97-106.
2. Oglykh V. V., Vakhromov V. A., Kirichenko A. S., Kosenko M. G. Razrabotka porokhovykh accumulyatorov davlenia dlya minometnogo starta raket – vazhneishee uslovie ego uspeshnoy realizatsii / Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2016. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 88-92.
3. Golubev K. S., Svetlov V. G. Proektirovanie zenitnykh upravlyaemykh raket. M.: Izd-vo MAH, 2001. 730 p.
4. Oglykh V. V., Tolochyants G. E., Mikhailov N. S., PopkovV. N. Eksperimentalnye issledovania vozmozhnosti sozdania impulsnogo RDTT s malym vremenem raboty/ Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauchn.-techn. st. 2016. Vyp. 2. Dnepr: GP KB «Yuzhnoye». P. 30-34.
5. Belyaev N. M., Belik N. P., Uvarov Ye. I. Reaktyvnye systemy upravleniya kosmicheskykh letatelnykh apparatov. M.: Mashinostroenie, 1979. 232 p.
6. Gubertov A. M., Mironov V. V., Borisov D. M. Gazodynamicheskie i teplophysicheskie process v raketnykh dvigatelyakh na tverdom toplive. M.: Mashinostroenie, 2004.
7. Kutateladze S. S. Teploperedacha i hydrodynamicheskoe soprotivlenie. Energoatomizdat, 1990. 368 p.
8. Scherbakov M. A. Opredelenie coeffitsientov teplootdachi pri modelirovanii zadach v Ansys CFX // Dvigateli i energoustanovki aerokosmicheskykh letatelnykh apparatov: Sb. nauch. statey. M.: Nauch.- techn. Centr im. A. Lyulki, 2014.
9. Moskvichev A. V. Primenimost’ modeley turbulentnosti, realizovannykh v Ansys CFX dlya issledovaniya gasodynamiki v schelevom kanale TNA ZhRD. Voronezhskiy gosudarstvenniy technicheskiy universitet, 2015.
10. Magdin E. K., Oglykh V. V., Rozlivan A. B. Tverdotoplivnaya dvigatelnaya ustanovka orientatsii I stabilizatsii descretnogo deistviya dlya upravleniya kosmicheskimi obiektami / Vestn. dvigatelestroiteley. 2017. Vyp. 2. P. 108-111.
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Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm. Key words: Bibliography: Full text (PDF) || (2016) "Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems" Космическая техника. Space technology. "Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems" Космическая техника. Space technology. quot;Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems", Космическая техника. Space technology. Space technology. Space technology. Space technology. Space technology.
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]]>15. Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 93-96
Language: Russian
Annotation: Different methods of calculation of burning surface are considered. The technique of burning surface calculation with the use of automated 3D modeling systems is described. The proposed technique allows simplifying and accelerating the burning surface calculation process.
Key words:
Bibliography:
Full text (PDF) || Content 2016 (1)
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, Magdin E. Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm. 2016 (1); 82-87 Language: Russian Annotation: By way of example of small-size motor with one-grain charge, the possibilities are shown that open up for a designer when selecting the optimal configuration of diaphragm using the Ansys (CFX) software package. The calculation results are compared with the experimental data obtained during hot-fire bench tests of experimental SRM. Key words: Bibliography: Full text (PDF) || E., Magdin E. Space technology. Space technology. E., Magdin E. Space technology. E., Magdin E. Space technology. E., Magdin E. Space technology. E., Magdin E. Space technology. E., Magdin E. Space technology.
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]]>13. The Impact of Diaphragm’s Shape on Gas Dynamic Flow Characteristics in Small-Size SRM Combustion Chamber
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 82-87
Language: Russian
Annotation: By way of example of small-size motor with one-grain charge, the possibilities are shown that open up for a designer when selecting the optimal configuration of diaphragm using the Ansys (CFX) software package. The calculation results are compared with the experimental data obtained during hot-fire bench tests of experimental SRM.
Key words:
Bibliography:
Full text (PDF) || Content 2016 (1)
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