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Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period Authors: Oglikh V. Content 2016 (2) Downloads: 39 Abstract views: 819 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Matawan; Baltimore; Plano; Miami; Miami; Dublin; Dublin; Ashburn; Columbus; Phoenix; Monroe; Ashburn; Ashburn; Boardman; Seattle; Seattle; Tappahannock; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Ashburn 24 Singapore Singapore; Singapore; Singapore; Singapore; Singapore 5 Germany ; Falkenstein 2 Ukraine Dnipro; Dnipro 2 Canada Toronto; Monreale 2 Finland Helsinki 1 Unknown 1 Romania Voluntari 1 Netherlands Amsterdam 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Oglikh V. Oglikh V. Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period Автори: Oglikh V.
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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
, Oglikh V. K., Oglikh V. K., Oglikh V. K., Oglikh V. K., Oglikh V. K., Oglikh V. K., Oglikh V.
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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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]]> 14.1.2016 Development of Powder Pressure Accumulators for Rocket Cold Start – the Most Important Condition of its Successful Realization https://journal.yuzhnoye.com/content_2016_1/annot_14_1_2016-en/ Tue, 23 May 2023 13:10:10 +0000 https://journal.yuzhnoye.com/?page_id=27629
Development of Powder Pressure Accumulators for Rocket Cold Start - the Most Important Condition of its Successful Realization Authors: Oglikh V. Content 2016 (1) Downloads: 45 Abstract views: 286 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Baltimore; Los Angeles; Columbus; Detroit; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Columbus; Ashburn; Boardman; Seattle; Seattle; Tappahannock; San Mateo; San Mateo; San Mateo; Ashburn; Des Moines; Boardman; Boardman; Ashburn; Boardman; Ashburn 26 Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore 9 Germany Frankfurt am Main; Falkenstein 2 Ukraine Dnipro; Dnipro 2 Unknown 1 Great Britain London 1 India Tiruchchirappalli 1 Canada Toronto 1 Romania Voluntari 1 Netherlands Amsterdam 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Oglikh V.
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14. Development of Powder Pressure Accumulators for Rocket Cold Start - the Most Important Condition of its Successful Realization

Authors:

Oglikh V. V., Vakhromov V. O., Kirichenko A. S., Kosenko M. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 88-92

Language: Russian

Annotation: The basic design solutions are considered that were adopted in developing the powder pressure accumulators with highly-progressive flow characteristic due to which the pop-up rocket launch became possible.

Key words:

Bibliography:

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14.1.2016 Development of Powder Pressure Accumulators for Rocket Cold Start – the Most Important Condition of its Successful Realization
14.1.2016 Development of Powder Pressure Accumulators for Rocket Cold Start – the Most Important Condition of its Successful Realization
14.1.2016 Development of Powder Pressure Accumulators for Rocket Cold Start – the Most Important Condition of its Successful Realization
]]> 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
, Oglikh V. O., Oglikh V. O., Oglikh V. O., Oglikh V. O., Oglikh V. O., Oglikh V. O., Oglikh V.
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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:

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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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