Search Results for “ANSYS CFX” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 12:23:50 +0000 en-GB hourly 1 https://wordpress.org/?v=6.2.2 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “ANSYS CFX” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 21.1.2019 Optimization of Geometrical Shape of Isolation Valve Blading Position https://journal.yuzhnoye.com/content_2019_1-en/annot_21_1_2019-en/ Wed, 24 May 2023 16:00:50 +0000 https://journal.yuzhnoye.com/?page_id=27726
Four options of the valve design were calculated using numerical methods of ANSYS CFX software. Key words: automation devices , valve , launch vehicle , design optimization , ANSYS CFX Bibliography: 1. Ansys CFX Solver Theory Guide [Electronniy resurs] / Rezhim dostupa: http://www1.ansys.com/customer/content/ documentation/180/cfx_thry.pdf. automation devices , valve , launch vehicle , design optimization , ANSYS CFX .
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21. Optimization of Geometrical Shape of Isolation Valve Blading Position

Authors:

Veskov E. V., Nazarenko O. P., Rabotilov V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 144-148

DOI: https://doi.org/10.33136/stma2019.01.144

Language: Russian

Annotation: One of the main design parameters of the automatic equipment in the launch vehicle’s pneumohydraulic systems is the flow friction characteristic, which represents the proportionality factor between the automatic equipment pressure differential and velocity head. The flow friction characteristic of the completely open automatic device should have very small value with required dimensions and mass. With decrease of the pressure losses, the required upstream pressure of the propulsion system is ensured with smaller pressurization of the tanks. It results in the decrease of the required pressurization gas volume, which boosts reduction of the performance of the launch vehicle as a whole. This paper describes the method of reduction of the flow friction characteristic of the dividing valve, optimizing the geometric shape of the flow passage. The problem of minimization of the valve’s flow friction characteristic is considered with the specified mass and design dimensions restrictions. The initial design of the valve was developed, taking into account the specified requirements, literature references and parameters of the analogue units. With the goal of optimization various options of valve design were considered, different from the initial design in configuration of the inlet and discharge nozzles, notably various angle sizes, forming the stream profile, and lengths of the direct-flow sections. Four options of the valve design were calculated using numerical methods of ANSYS CFX software. Navier – Stokes equations and k-ω SST turbulence model were used. Based on the calculations results the optimal design was selected. Initial design of the valve was compared with the optimal one. The flow friction characteristic of the optimal valve design decreased by 26 % in comparison with initial design with insignificant change of mass and dimensions. The design of the developed dividing valve can be involved in the design of the new launch vehicles.

Key words: automation devices, valve, launch vehicle, design optimization, ANSYS CFX

Bibliography:
1. Gurevich D. F. Raschet i konstruirovanie truboprovodnoi armatury: Raschet truboprovodnoi armatuty. 5-e izd. M.: Izd-vo LKI, 2008. 480 p.
2. Yanshin B. I. Hydrodynamicheskie characteristiki zatvorov i elementov truboprovodov. M.: Mashinostroenie, 1965. 259 p.
3. Idelchik I. Ye. Spravochnik po hydrovlicheskim soprotivleniyam / Pod red. M. O. Steinberga. 3-e izd., pererab. i dop. M.: Mashinostroenie, 1992. 672 p.
4. Ansys CFX Solver Theory Guide [Electronniy resurs] / ANSYS Inc., 2012. Rezhim dostupa: http://www1.ansys.com/customer/content/ documentation/180/cfx_thry.pdf.

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21.1.2019 Optimization of Geometrical Shape of Isolation Valve Blading Position
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]]> 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
Opredelenie coeffitsientov teplootdachi pri modelirovanii zadach v Ansys CFX // Primenimost’ modeley turbulentnosti, realizovannykh v Ansys CFX dlya issledovaniya gasodynamiki v schelevom kanale TNA ZhRD.
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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
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]]> 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
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.
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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
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