Search Results for “Popkov V. M.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 12:09:48 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “Popkov V. M.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 4.2.2016 Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period https://journal.yuzhnoye.com/content_2016_2-en/annot_4_2_2016-en/ Tue, 06 Jun 2023 11:49:59 +0000 https://journal.yuzhnoye.com/?page_id=28308
Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period Authors: Oglikh V. 1 , Mikhailov M. 1 , Popkov V. 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. E., Mikhailov M. S., Popkov V. E., Mikhailov M. S., Popkov V. Missile armaments, vol. E., Mikhailov M. S., Popkov V. E., Mikhailov M. S., Popkov V. E., Mikhailov M. S., Popkov V. E., Mikhailov M. S., Popkov V. More Citation Formats Harvard Chicago IEEE AIP ДСТУ 8302:2015 ДСТУ ГОСТ 7.1:2006 (ВАК) ISO 690:2010 BibTeX на сайт ДП «КБ «Південне»
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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
, Mikhailov M. V., Vakhromov V. Proektirovanie zenitnykh upravlyaemykh raket. M.: Izd-vo MAH, 2001. S., PopkovV. Gazodynamicheskie i teplophysicheskie process v raketnykh dvigatelyakh na tverdom toplive. Scherbakov M. Primenimost’ modeley turbulentnosti, realizovannykh v Ansys CFX dlya issledovaniya gasodynamiki v schelevom kanale TNA ZhRD. Tverdotoplivnaya dvigatelnaya ustanovka orientatsii I stabilizatsii descretnogo deistviya dlya upravleniya kosmicheskimi obiektami / Vestn. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M. More Citation Formats Harvard Chicago IEEE AIP ДСТУ 8302:2015 ДСТУ ГОСТ 7.1:2006 (ВАК) ISO 690:2010 BibTeX Keywords cloud Your browser doesn't support the HTML5 CANVAS tag.
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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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