Keywords cloud
B., Kirichenko A. Space Technology. Space technology. Available at: https://doi.org/10.33136/stma2018.01.027 . Space technology. https://doi.org/10.33136/stma2018.01.027 . Space technology. September.2018, doi: https://doi.org/10.33136/stma2018.01.027 . Space technology. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 27—30.doi: https://doi.org/10.33136/stma2018.01.027 . Space technology. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 27—30.doi: https://doi.org/10.33136/stma2018.01.027 . Space technology. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 27—30.doi: https://doi.org/10.33136/stma2018.01.027 . Space technology.
]]>5. Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2018 (1); 27-30
DOI: https://doi.org/10.33136/stma2018.01.027
Language: Ukrainian
Annotation: The paper gives reasons for conducting experimental works to determine lateral force caused by eccentricity and skew of SRM thrust vector, considers the configuration of fixed test stand for respective experimental works with vertical position of motor axis and describes the fixed test stand operation principle.
Key words:
Bibliography:
1. Volkov V. T., Yagodnikov D. A. Investigations and Bench Testing of Solid Rocket Motors. М., 2007. 296 p.
2. Beskrovny I. B., Kirichenko A. S., Balitsky I. P. et al. The Company’s Experience in Designing and Operation of SRM Test Rigs. Space Technology. Missile Armaments: Collected book of scientific-technical articles / Yuzhnoye SDO. Dnepropetrovsk, 2008. Issue 1. P. 119-127.
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Comparison of Payload Fairings of Existing and Prospective Domestic Launch Vehicles and their Foreign Analogs / А. Creation of Space Rocketry Units with Specified Quality of Polymer Composite Materials / A. Kirichenko, A. Design and Technological Solution and Carrying Capacity of Cyclone-4 Launch Vehicle Interstage Bay Made of Polymer Composite Materials / А. Kushnar’ov, V. Space Technology. Kushnar’ov, А. Static Tests of Cyclone-4 Launch Vehicle Experimental Interstage Bay Made of Carbon Plastic / А. Kushnar’ov, А. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
]]>20. Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Kharkiv Aviation Institute, Kharkiv, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2017 (2); 112-120
Language: Russian
Annotation: Some main results of scientific support of development of launch vehicle head module composite loadbearing bays are presented. The methodology is proposed for developing these units. By the example of payload fairing and interstage bay of Cyclone-4 launch vehicle, high efficiency is shown of proposed methodology implementation when selecting their rational design and technological parameters.
Key words:
Bibliography:
1. Degtyarev A. V. Rocket Technology. Problems and Prospects. Selected scientific-technical publications. Dnepropetrovsk, 2014. 420 p.
2. Kovalenko V. A., Kondrat’yev A. V. Use of Polymer Composite Materials in Space Rockets as Reserve of Increasing their Mass and Functional Effectiveness. Aerospace Engineering and Technology. 2011. No. 5 (82). P. 14-20.
3. Kondrat’yev A. V. et al. Analysis of Nomenclature of Type Composite Units of Space Rockets and Structural Schemes Applied for them / A. V. Kondrat’yev, A. G. Dmitrenko, K. D. Stenile, А. А. Tsaritsynsky. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 3 (79). Kharkiv, 2014. P. 19 – 30.
4. Potapov A. M. et al. Comparison of Payload Fairings of Existing and Prospective Domestic Launch Vehicles and their Foreign Analogs / А. М. Potapov, V. A. Kovalenko, A. V. Kondrat’yev. Aerospace Engineering and Technology. 2015. No. 1(118). P. 35 – 43.
5. Gaidachuk A. V. et al. Methodology of Developing Effective Design and Technological Solutions of Space Rocketry Composite Units: Monography in 2 volumes. Vol. 2. Synthesis of Space Rocketry Composite Units Parameters at Heterogeneous Loading / A. V. Gaidachuk, V. E. Gaidachuk, A. V. Kondrat’yev, V. A. Kovalenko, V. V. Kirichenko, А. M. Potapov / Under the editorship of A. V. Gaidachuk. Kharkiv, 2016. 250 p.
6. Gaidachuk A. V. et al. Methodology of Developing Effective Design and Technological Solutions of Space Rocketry Composite Units: Monography in 2 volumes. Vol. 1. Creation of Space Rocketry Units with Specified Quality of Polymer Composite Materials / A. V. Gaidachuk, V. E. Gaidachuk, A. V. Kondrat’yev, V. A. Kovalenko, V. V. Kirichenko, А. M. Potapov / Under the editorship of A. V. Gaidachuk. Kharkiv, 2016. 263 p.
7. Smerdov A. A. Development of Methods to Design Space Rocketry Composite Materials and Structures: Dissertation of Doctor of Engineering Science: 05.07.02, 05.02.01. М., 2007. 410 p.
8. Slyvyns’kyy V. et al. Basic parameters’ optimization concept for composite nose fairings of launchers / V. Slyvyns’kyy, V. Gajdachuk, V. Kirichenko, A. Kondratiev. 62nd International Astronautical Congress, IAC 2011 (Cape Town, 3-7 October 2011). Red Hook, NY: Curran, 2012. Vol. 9. P. 5701-5710.
9. Gaidachuk V. E. et al. Optimization of Cyclone-4 Launch Vehicle Payload Fairing Design Parameters / V. E. Gaidachuk, V. I. Slivinsky, A. V. Kondrat’yev, A. P. Kushnar’ov, Effectiveness of Honeycomb Structures in Aerospace Products: Proceedings of III International Scientific-Practical Conference (Dnepropetrovsk, 27-29 May 2009). Dnepropetrovsk, 2009. P. 88 – 95.
10. Zinov’yev A. M. et al. Design and Technological Solution and Carrying Capacity of Cyclone-4 Launch Vehicle Interstage Bay Made of Polymer Composite Materials / А. М. Zinov’yev, А. P. Kushnar’ov, A. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Aerospace Engineering and Technology. 2013. No. 3 (100). P. 46-53.
11. Karpov Y. S. Connection of Parts and Units Made of Composite Materials: Monography. Kharkiv, 2006. 359 p.
12. Kondrat’yev A. V. Mass Optimization of Launch Vehicle Payload Fairing Irregular Zones. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 47 (4). Kharkiv, 2006. P. 126 – 133.
13. Degtyarev A. V. et al. Evaluation of Carrying Capacity of Launch Vehicle Bays Separation System Composite Fitting / A. V. Degtyarev, A. P. Kushnar’ov, V. V. Gavrilko, V. A. Kovalenko, А. V. Kondrat’yev, А. М. Potapov. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2013. Issue 1. P. 18-21.
14. Patent 81537 UA, MPK (2013.01) F42B 15/36 (2006.01) B64D 1/00 Fitting of Rocket’s Three-Layer Shell / О. М. Zinov’yev, О. P. Kuznetsov, V. V. Gavrilko, О. М. Potapov, V. O. Kovalenko et al.; Applicant and patent holder NVF Dniprotechservice, Yuzhnoye SDO. No. u 2012 11210; Claimed 27.09.2012; Published 10.07.13, Bulletin 13. 4 p.
15. Zinov’yev A. M. et al. Manufacturing Technology of Cyclone-4 Launch Vehicle Experimental Large-Sized Interstage Bay Made of Carbon Plastics / А. M. Zinov’yev, А. P. Kushnar’ov, А. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 2 (74). Kharkiv, 2013. P. 7 – 17.
16. Zinov’yev A. M. et al. Static Tests of Cyclone-4 Launch Vehicle Experimental Interstage Bay Made of Carbon Plastic / А. М. Zinov’yev, А. P. Kushnar’ov, А. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Aerospace Engineering and Technology. 2013. No. 4(101). P. 28-35.
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S., Kirichenko A. S., Kirichenko A. S., Kirichenko A. S., Kirichenko A. S., Kirichenko A. S., Kirichenko A.
]]>11. Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2017 (1); 70-77
Language: Russian
Annotation: The mathematical models are presented and the calculations are made of lower atmosphere contamination with solid propellant combustion products, noise and thermal effects on environment in the test bench area. Based on earlier field investigations and on the results obtained, the assessment is given of ecological safety of the tests.
Key words:
Bibliography:
1. Noise Control in Industry: Guide / Under the editorship of E. Y. Yudin. М., 1985.
2. Maximum Permissible Concentrations and Approximate Safe Levels of Contaminating Substances Effect in Atmospheric Air of Populated Areas. Donetsk, 2000.
3. GOST 12.1.005-88. System of Labor Safety Standards. General Sanitary-Hygienic Requirements to Working Area Air / Collection of GOSTs. М., 1988.
4. Gusev N. G., Belyayev V. A. Radioactive Emissions in Biosphere: Guide. 2nd edition. M., 1991. 256 p.
5. Investigation of Environment Pollution during Tests of 365-Type Article on PMZ Site: Report on research work / MPO Technokhim, NPO GIPH. Leningrad, 1991.
6. Assessment of Hygienic Situation in the Area of Pavlograd Mechanical Plant during Tests of 15D365 Articles. Report by Agreement No48-6/91-429 YuR-1/Ministry of Health Protection of the USSR. M., 1991.
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Solid Rocket Motors Developed by DO-5 Authors: Kirichenko A. San Mateo; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Boardman; Ashburn 39 Ukraine Kyiv; Kyiv; Boryspil; Kyiv; Kharkiv; Kyiv; Kyiv; Dnipro; Pavlohrad; Kyiv; Kyiv; Kharkiv; Kremenchuk; Dnipro 14 Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore 7 Canada Toronto; Toronto; Toronto; Toronto; Monreale 5 Sweden Linköping; Linköping 2 Germany Falkenstein; Hamburg 2 Finland Helsinki 1 France Paris 1 Mongolia 1 Romania Voluntari 1 Netherlands Amsterdam 1 Bulgaria Plovdiv 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Kirichenko A. Solid Rocket Motors Developed by DO-5 Автори: Kirichenko A. Solid Rocket Motors Developed by DO-5 Автори: Kirichenko A. Solid Rocket Motors Developed by DO-5 Автори: Kirichenko A.
]]>1. Solid Rocket Motors Developed by DO-5
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 4-12.
Language: Russian
Annotation: The main phases of formation and development of solid motor engineering are presented. The basic technical problems are considered, solution of which allowed building the main motors and dispensing motors with high performance level and highly-effective rocket systems on their basis
Key words:
Bibliography:
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Development of Prospective Small-Size Auxiliary SMR of New Type Authors: Toloch’yants G. A., Kirichenko A. statey. Space technology. Available at: https://doi.org/10.33136/stma2019.01.114 . Space technology. https://doi.org/10.33136/stma2019.01.114 . Toloch’yants G. Space technology. March.2019, doi: https://doi.org/10.33136/stma2019.01.114 . Development of Prospective Small-Size Auxiliary SMR of New Type Автори: Toloch’yants G. Space technology. Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 114—121.doi: https://doi.org/10.33136/stma2019.01.114 . Development of Prospective Small-Size Auxiliary SMR of New Type Автори: Toloch’yants G. Space technology. Space technology. Space technology.
]]>17. Development of Prospective Small-Size Auxiliary SMR of New Type
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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This procedure simulates different time variations of thrust as motor enters the steady-state mode. Application of the suggested procedure of motor oscillations simulation in the phase of rig design will enable more detailed prediction of the occurring processes as well as the estimation of parameters of the individual elements, units and rig as a whole. B., Kirichenko A. Posobie dlya studentov VUZov. Space technology. Space technology. Space technology. March.2019, doi: https://doi.org/10.33136/stma2019.01.103 . Space technology. Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 102—108.doi: https://doi.org/10.33136/stma2019.01.103 . Space technology. Space technology. Space technology.
]]>15. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 102-108
DOI: https://doi.org/10.33136/stma2019.01.103
Language: Ukrainian
Annotation: This paper describes the firing rig test of the solid rocket motor, fastened to the rig in order to measure the thrust level. It is shown that when the motor enters the steady-state mode, the rig with solid rocket motor starts experiencing mechanical oscillations due to the sudden thrust build-up. Motion of the oscillating system is studied under the impact of the linearly or suddenly increasing impulse load. Mechanical oscillations damping is considered on the basis of the viscous friction model. Procedure of the analytical modeling of the damped oscillations is suggested for the complex pattern of the loading variations, based on the fundamental principle of superposition, according to which the motor displacement during the oscillating motion is considered as sum of displacements due to the impact of the impulsive, sudden and linearly increasing loadings. This procedure simulates different time variations of thrust as motor enters the steady-state mode. Oscillating motion with parameters of the oscillating system and thrust change with time option have been simulated as they were realized during the firing rig tests of one of the solid rocket motors. Simulated and experimental (thrust sensor readings) curves of the elastic force were compared, which showed the qualitative and quantitative conformity of the suggested model of oscillations to the actual oscillations of the solid rocket motor, installed in the rig during the firing rig test. Values of the initial thrust, initial impulse and other simulation parameters were updated, adjusting the simulated curve of the elastic force to the experimental one. It was concluded that simulation of the elastic oscillations of the solid rocket motor in the rig using the suggested analytical model will enable more reliable definition of the initial thrust of the motor and its time behavior, impulse loading due to the separation of the plug and used elements that separate with it. Application of the suggested procedure of motor oscillations simulation in the phase of rig design will enable more detailed prediction of the occurring processes as well as the estimation of parameters of the individual elements, units and rig as a whole.
Key words: elastic oscillations, motor starting operation, sudden loading, measurement of thrust, principle of superposition, initial thrust
Bibliography:
1. Beskrovniy I. B., Kirichenko A. S., Balitskiy I. P. i dr. Opyt predpriyatiya po proektirovaniyu i ekspluatatsii stapeley dlya ispytaniy RDTT / Kosmicheskaya technika. Raketnoye vooruzhenie: Sb. nauch.- techn. st. 2008. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 119–127.
2. Bidermann V. L. Teoria mechanicheskykh kolebaniy: Uchebnik dlya VUZov. M.: Vyssh. shk., 1980. 408 p.
3. Yablonskiy A. A., Noreyko S. S. Kurs teorii kolebaniy. Ucheb. Posobie dlya studentov VUZov. Izd. 3-e, ispr. i dop. M.: Vyssh. shk., 1975. 248 p.
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Keywords cloud
Development of Powder Pressure Accumulators for Rocket Cold Start - the Most Important Condition of its Successful Realization Authors: Oglikh V. , Kirichenko A. O., Kirichenko A. Space technology. Missile armaments , ( Space technology. Missile armaments , no. O., Kirichenko A. Space technology. Missile armaments, vol. O., Kirichenko A. Space technology. Missile armaments Том: 2016 Випуск: 2016 (1) Рік: 2016 Сторінки: 88—92.doi: . O., Kirichenko A. Space technology. Missile armaments Том: 2016 Випуск: 2016 (1) Рік: 2016 Сторінки: 88—92.doi: . O., Kirichenko A. Space technology. Missile armaments Том: 2016 Випуск: 2016 (1) Рік: 2016 Сторінки: 88—92.doi: . O., Kirichenko A. Space technology. Missile armaments Том: 2016 Випуск: 2016 (1) Рік: 2016 Сторінки: 88—92.doi: .
]]>14. Development of Powder Pressure Accumulators for Rocket Cold Start - the Most Important Condition of its Successful Realization
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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, Kirichenko A. 2016 (1); 55-58 Language: Russian Annotation: In the phase of designing and developmental testing of short-range missiles with main solid rocket motors, the necessity arises of quick evaluation of propulsion system power characteristics, in particular, determination of specific thrust pulse value and scatter. V., Kirichenko A. Space technology. Space technology. V., Kirichenko A. Space technology. Assessment of Validity of Hypothesis of Constancy of Specific Vacuum Thrust Pulse during SRM Designing and Testing Автори: Kalnysh R. V., Kirichenko A. Space technology. V., Kirichenko A. Space technology. V., Kirichenko A. Space technology. Assessment of Validity of Hypothesis of Constancy of Specific Vacuum Thrust Pulse during SRM Designing and Testing Автори: Kalnysh R. V., Kirichenko A. Space technology.
]]>8. Assessment of Validity of Hypothesis of Constancy of Specific Vacuum Thrust Pulse during SRM Designing and Testing
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 55-58
Language: Russian
Annotation: In the phase of designing and developmental testing of short-range missiles with main solid rocket motors, the necessity arises of quick evaluation of propulsion system power characteristics, in particular, determination of specific thrust pulse value and scatter. The use of hypothesis of specific thrust constancy (weak dependence of vacuum thrust pulse on pressure and temperature) allows to considerably simplify the procedure of SRM specific thrust pulse evaluation, thus increasing the efficiency of SRM design calculations and the speed of test results processing, and in some cases, even to considerably reduce the test scope.
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The Company’s Experience in Designing and Operating Special Bench Equipment for SRM Ground Tests Authors: Kirichenko A. Content 2016 (1) Downloads: 48 Abstract views: 283 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Matawan; Columbus; Columbus; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Ashburn; Seattle; Ashburn; Boardman; Ashburn; Ashburn; Seattle; Tappahannock; San Mateo; San Mateo; Des Moines; Boardman; Ashburn; Ashburn; Ashburn 28 Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore 7 Canada Toronto; Toronto; Toronto; Toronto; Monreale 5 Ukraine Dnipro; Dnipro; Odessa 3 Finland Helsinki 1 Unknown Hong Kong 1 Germany Falkenstein 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 Kirichenko A.
]]>4. The Company’s Experience in Designing and Operating Special Bench Equipment for SRM Ground Tests
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 26-33
Language: Russian
Annotation: The information on Yuzhnoye SDO experience in designing and operation of special equipment for testing of SRM of various classes is presented, the description and analysis of results of this equipment operation are given.
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On Peculiarities of Life Testing and Safe Storage of Solid Rocket Motors Authors: Kirichenko A. Falkenstein 4 Canada Toronto; Toronto; Toronto; Monreale 4 Ukraine Dnipro; Dnipro; 3 Finland Helsinki 1 France 1 India Tiruchchirappalli 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 Kirichenko A. On Peculiarities of Life Testing and Safe Storage of Solid Rocket Motors Автори: Kirichenko A. On Peculiarities of Life Testing and Safe Storage of Solid Rocket Motors Автори: Kirichenko A. On Peculiarities of Life Testing and Safe Storage of Solid Rocket Motors Автори: Kirichenko A. On Peculiarities of Life Testing and Safe Storage of Solid Rocket Motors Автори: Kirichenko A.
]]>3. On Peculiarities of Life Testing and Safe Storage of Solid Rocket Motors
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 19-25
Language: Russian
Annotation: The results of experimental verification of solid rocket motors warranty periods are presented. Some peculiarities and methods of tests with simulation of rocket motor operational mechanical and environmental loads are considered.
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