Search Results for “Mikhailov K. F.” – 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://wordpress.org/?v=6.2.2 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “Mikhailov K. F.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 12.1.2018 A Device for Soft Separation of Spacecraft from Launch Vehicle https://journal.yuzhnoye.com/content_2018_1-en/annot_12_1_2018-en/ Tue, 05 Sep 2023 06:45:35 +0000 https://journal.yuzhnoye.com/?page_id=30464
, Mikhailov K. Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm. Mikhailov, V. М., Mikhailov K. F., Porubaimekh V. М., Mikhailov K. F., Porubaimekh V. М., Mikhailov K. F., Porubaimekh V. М., Mikhailov K. F., Porubaimekh V. М., Mikhailov K. F., Porubaimekh V. М., Mikhailov K. F., Porubaimekh V.
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12. A Device for Soft Separation of Spacecraft from Launch Vehicle

Authors:

Bondar’ М. А., Voloshin V. V., Duplischeva О. М., Mikhailov K. F., Porubaimekh V. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 69-71

DOI: https://doi.org/10.33136/stma2018.01.069

Language: Russian

Annotation: The paper deals with the advantages and peculiarities of operation of a device for soft separation of spacecraft from launch vehicle.

Key words:

Bibliography:
1. Kolesnikov K. S., Kozlov V. I., Kokushkin V. V. Flying Vehicle Stages Separation Dynamics. М., 1977. 221 p.
2. Method of Satellite Separation from Launch Vehicle and Device to Implement the Method: Pat. 108515 Ukraine: MPK В64G1/64 (2006:01) / М. А. Bondar’, V. V. Voloshin, О. М. Duplishcheva, K. F. Mikhailov, V. I. Porubaimekh (Ukraine); applicant and patent holder is Yuzhnoye SDO. No. а201305544; appl. 29.04.13; publ. 12.05.16, Bull. No 9.

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12.1.2018 A Device for Soft Separation of Spacecraft from Launch Vehicle
12.1.2018 A Device for Soft Separation of Spacecraft from Launch Vehicle
12.1.2018 A Device for Soft Separation of Spacecraft from Launch Vehicle
]]> 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. Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm. 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. Such procedure has been developed based on Ansys software package. E., Mikhailov N. Primenimost’ modeley turbulentnosti, realizovannykh v Ansys CFX dlya issledovaniya gasodynamiki v schelevom kanale TNA ZhRD. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M. E., Mikhailov M.
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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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]]> 8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses https://journal.yuzhnoye.com/content_2023_1-en/annot_8_1_2023-en/ Fri, 12 May 2023 16:11:05 +0000 https://test8.yuzhnoye.com/?page_id=26992
Duplischeva O.M., Kononets P.I., Lisoviy A.M., Maschenko A.M., Mikhailov K.F., kand.
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8. Specificity of developing pyrobolts with low impact and vibration impulse responses

Authors:

Samoilenko I. D., Voloshin V. V., Bezkorsyi D. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 70-76

DOI: https://doi.org/10.33136/stma2023.01.070

Language: Ukrainian

Annotation: One of the systems in the integrated launch vehicle responsible for prelaunch processing and launch is a ground thermal conditioning system, which supplies the low-pressure air into the launch vehicle’s “dry” compartments. Thermal conditioning system is mated with the launch vehicle, using the mating interfaces, proper functioning of which enhances reliability of the ground support equipment, the launch vehicle and the entire space launch system. The article describes key requirements to the interfaces of the thermal conditioning system and the drawbacks of the existing designs. The article proposes a new design concept of the interface that connects the pipeline of the ground thermal conditioning system to the orifice of the launch vehicle using the corrugated rubber hose composed of three basic parts, attached with the help of a metal lock/release assembly. The proposed solution provides reliable leaktightness, ease of operation, providing multiple connections to the launch vehicle, including at various angles, and automatic disconnection by rocket motion or manual removal in case of launch abort. Using rubber as a high-elasticity structural material to manufacture the hoses, enabled minimization of efforts required to disconnect the interface from the launch vehicle. In its high-elasticity state, rubber can absorb and dissipate mechanical energy within a wide range of temperatures, which prevents transmission of engine vibrations to the ground thermal conditioning system. The article presents key properties of rubber used as a structural material and its peculiarities to be considered during design of similar products. Unlike metal showing two types of deformation (elastic and plastic), rubber can exhibit three types of deformation (elastic, superelastic and plastic). In the process of interface design, we took into account two types of deformations (elastic and superelastic ones). Experimental studies of the interface showed its full compliance with technical specification.

Key words: orifice of the launch vehicle, corrugated rubber hose, lock/release assembly, superelastic deformation, leaktightness

Bibliography:
1. Pat. Ukrainy na korycnu model «Pirobolt» №138414. Shevtsov E.I., Voloshin V.V., Samoilenko I.D. Onofrienko V.I., Bezkorsiy D.M. MPK F42B 15/36, F42В 15/38, B64G 1/22 zayavnik ta patentovlasnik KB «Pivdenne». Byul. №22, 2019 r.
2. Galuzeviy standart «Pyrozamky. Metodika rozrakhunku» OST 92-9594-82, 24 ark.
3. Duplischeva O.M., Kononets P.I., Lisoviy A.M., Maschenko A.M., Mikhailov K.F., kand. tekhn. nauk Porubaimekh V.I., Sviridov V.M. Znizhennya vibroimpulsnykh navantazhen, scho vynykaut pid chas spratsyuvannya pyromechanismu. Kosmichna technika. Raketne ozbroennya: Zb. nauk.-techn. st. 2009. Vyp. 2. Dnipro: DP «KB «Pivdenne». 100 ark.
4. Bement L. J. and Schimmel M. L. A Manual for Pyrotechnic Design, Development and Qualification, NASA, NASA Technical Memorandum 110172, 1995.
5. Yanhua Li, Yuan Li, Xiaogan Li, Yuquan Wen, Huina Mu and Zhiliang Li. Identification of Pyrotechnic Shock Sources for Shear Type Explosive Bolt, Shock and Vibration Vol. 2017, Article ID 3846236, 9 p. https://doi.org/10.1155/2017/3846236
6. Yanhua Li, Jingcheng Wang, Shihui Xiong, Li Cheng, Yuquan Wen, and Zhiliang Li Numerical Study of Separation Characteristics of Piston-Type Explosive Bolt, Shock and Vibration, Vol. 2019, Article ID 2092796, 18 p. https://doi.org/10.1155/2019/2092796

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8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses
8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses
8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses

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