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2 Organization: Yangel Yuzhnoye State Design Office 1 , Dnipro, Ukraine; SSRI, Shostka, Ukraine 2 Page: Kosm. Content 2016 (2) Downloads: 17 Abstract views: 342 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Baltimore; Plano; Dublin; Monroe; Ashburn; Ashburn; Boardman; Seattle; Seattle; San Mateo; Boardman 12 Singapore Singapore; Singapore; Singapore 3 Ukraine Dnipro; Dnipro 2 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Oglikh V. Space technology.
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4. Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period

Authors:

Oglikh V. V.1, Toloch’yants G. E.1, Mikhailov M. S.1, Popkov V. M.2

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:

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4.2.2016 Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period
4.2.2016 Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period
4.2.2016 Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period
]]> 17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type https://journal.yuzhnoye.com/content_2019_1-en/annot_17_1_2019-en/ Wed, 24 May 2023 16:00:35 +0000 https://journal.yuzhnoye.com/?page_id=27722
, 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

Authors:

Toloch’yants G. E., Mikhailov M. S., Magdin E. K., Oglikh V. V.

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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17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type
17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type
17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type

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]]> 15.1.2016 Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems https://journal.yuzhnoye.com/content_2016_1/annot_15_1_2016-en/ Tue, 23 May 2023 13:10:58 +0000 https://journal.yuzhnoye.com/?page_id=27631
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

Authors:

Toloch’yants G. E., Lepsky A. V.

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:

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15.1.2016 Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems
15.1.2016 Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems
15.1.2016 Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems
]]> 13.1.2016 The Impact of Diaphragm’s Shape on Gas Dynamic Flow Characteristics in Small-Size SRM Combustion Chamber https://journal.yuzhnoye.com/content_2016_1/annot_13_1_2016-en/ Tue, 23 May 2023 13:08:28 +0000 https://journal.yuzhnoye.com/?page_id=27627
, 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

Authors:

Vakhromov V. O., Oglikh V. V., Toloch’yants G. E., Magdin E. K.

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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13.1.2016 The Impact of Diaphragm’s Shape on Gas Dynamic Flow Characteristics in Small-Size SRM Combustion Chamber
13.1.2016 The Impact of Diaphragm’s Shape on Gas Dynamic Flow Characteristics in Small-Size SRM Combustion Chamber
13.1.2016 The Impact of Diaphragm’s Shape on Gas Dynamic Flow Characteristics in Small-Size SRM Combustion Chamber
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