Search Results for “Zenit LV” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 05 Nov 2024 20:24:28 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “Zenit LV” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system https://journal.yuzhnoye.com/content_2024_1-en/annot_7_1_2024-en/ Fri, 14 Jun 2024 11:36:31 +0000 https://journal.yuzhnoye.com/?page_id=34957
pneumatic pusher , spring pusher , SPRE , gas-reactive nozzles , Zenit LV , Dnepr LV , Falcon 9 rocket , Cyclone-4М LV. pneumatic pusher , spring pusher , SPRE , gas-reactive nozzles , Zenit LV , Dnepr LV , Falcon 9 rocket , Cyclone-4М LV.
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7. Selection of the functional units for the Cyclone-4M ILV separation system

Authors:

Logvinenko A. I., Makarenko A. O., Khomyak V. O., Olesiyuk A. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 61-71

DOI: https://doi.org/10.33136/stma2024.01.061

Language: Ukrainian

Annotation: Separation of the spent LV stages is one of the important problems of the rocket technology, which requires the comprehensive analysis of different types of systems, evaluation of their parameters and structural layouts. Basic requirements are specified that need to be taken into account when engineering the separation system: reliable and safe separation, minimal losses in payload capability, keeping sufficient distance between the stages at the moment of the propulsion system start. Detailed classification of their types («cold», «warm», «hot», «cold-launched» separation) is given and their technical substance with advantages and drawbacks is described. Certain types of «cold» and «warm» separation of the spent stages of such rockets as Dnepr, Zenit, Antares, Falcon-9 with different operating principle are introduced – braking with the spent stage and pushing apart two stages. Brief characteristics of these systems are given, based on the gas-reactive nozzle thrust, braking with solid-propellant rocket engines, separating with spring or pneumatic pushers. Development of the separation system for the advanced Cyclone-4M ILV is taken as an example and design sequence of stage separation is suggested: determination of the necessary separation velocity and capability of the separation units, determination of the number of active units, calculation of design and energy parameters of the separation units, analysis of the obtained results followed by the selection of the separation system. Use of empirical dependences is shown, based on the great scope of experimental and theoretical activities in the process of design, functional testing and flight operation of similar systems in such rockets as Cyclone, Dnepr and Zenit. According to the comparative analysis results, pneumatic separation system to separate Cyclone-4M Stages 1 and 2 was selected as the most effective one. Its basic characteristics, composition, overall view and configuration are specified. Stated materials are of methodological nature and can be used to engineer the separation systems for LV stages, payload fairings, spacecraft etc.

Key words: separation system, functional units of separation, «cold separation», «warm separation», pneumatic pusher, spring pusher, SPRE, gas-reactive nozzles, Zenit LV, Dnepr LV, Falcon 9 rocket, Cyclone-4М LV.

Bibliography:
  1. Pankratov Yu. , Novikov A. V., Tatarevsky K. E., Azanov I. B. Dynamika perekhodnykh processov. 2014.
  2. Sinyukov A. M., Morozov N. I. Konstruktsia upravlyaemykh ballisticheskykh raket. 1969.
  3. Kabakova Zh. V., Kuda S. A., Logvinenko A. I., Khomyak V. A. Opyt razrabotki pneumosystemy dlya otdelenita golovnogo aerodynamicheskogo obtekatelya. Kosmicheskaya technika. Raketnoe vooruzhenie. 2017. Vyp. 2 (114).
  4. Kolesnikov K. S., Kozlov V. V., Kokushkin V. V. Dynamika razdeleniya stupeney letatelnykh apparatov. 1977.
  5. Antares – Spaceflight Insider: web site. URL: https://www. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023).
  6. Falcon 9 – pexels: website. URL: https://www. pexels.com/Falcon 9 (data zvernennya 31.10.2023).
  7. Kolesnikov K. , Kokushkin V. V., Borzykh S. V., Pankova N. V. Raschet i proektirovanie system razdeleniya stupeney raket. 2006.
  8. Cyclone-4M – website URL: https://www.yuzhnote.com (data zvernennya 31.10.2023)
  9. Logvinenko A. Sozdanie gasoreaktivnykh system otdeleniya i uvoda otrabotavshykh stupeney – noviy shag v RKT. Kosmicheskaya tekhnika. Raketnoe vooruzhenie, KBU, NKAU, vyp. 1, 2001.
  10. Logvinenko A. I., Porubaimekh V. I., Duplischeva O. M. Sovremennye metody ispytaniy system i elementov konstruktsiy letatelnykh apparatov. Monografia. Dnepr, KBU, 2018.

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7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system
7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system
7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system

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]]> 2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop https://journal.yuzhnoye.com/content_2018_1-en/annot_2_1_2018-en/ Mon, 04 Sep 2023 12:45:06 +0000 https://journal.yuzhnoye.com/?page_id=30403
Zenit-2. URL: https://ru.wikipedia.org/wiki/Zenit-2_(launch vehicle) . Zenit Space Launch System from the Eyes of its Developers / Under the editorship of e.d. Calculated Evaluation and Experimental Check of RPC Degassing and Saturation by Helium for Filling Cyclone-4 LV: Technical Note Cyclone-4.
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2. Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop

Authors:

Salo М. P., Tereschenko K. O., Ivanitsky G. М.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 6-12

DOI: https://doi.org/10.33136/stma2018.01.006

Language: Russian

Annotation: An alternative method of kerosene dehydration is proposed, which is based on application of cyclic technology of supersaturation decrease using dry nitrogen. A comparison of nitrogen and time specific consumption in dehydration operations is done and recommendations are given for their use in the cosmodromes’ launch complexes fuel storage and preparation facilities.

Key words:

Bibliography:

1. Zrelov V. N., Seryogin E. P. Liquid Rocket Propellants. М., 1975. 320 p.
2. Energy-Intensive Fuels for Aircraft and Rocket Engines / Under the editorship of L. S. Yanovsky. М., 2009. 400 p.
3. Soyuz-2. URL: https://ru.wikipedia.org/wiki/Soyuz-2_(launch vehicle family).
4. Angara. URL: https://ru.wikipedia.org/wiki/Angara_(launch vehicle).
5. Zenit-2. URL: https://ru.wikipedia.org/wiki/Zenit-2_(launch vehicle).
6. Leshchiner L. B., Ul’yanov I. E. Designing of Aircraft Fuel Systems. М., 1975. 344 p.
7. Zenit Space Launch System from the Eyes of its Developers / Under the editorship of e.d. professor V. N. Solov’yov, e.d. professor G. P. Biryukov, N. S. Kozhukhov, N. I. Kursenkova. М., 2003. 213 p.
8. Space Rocketry Ground Infrastructure Technological Facilities: Engineering Manual. Book 1. М., 2005. 416 p.
9. Investigation of Prospective Propellant Preparation Technologies: Scientific-Technical Report 21.18258.173ОТ / Yuzhnoye SDO. 2016. 115 p.
10. Shleifer A. A., Litvinov A. N. Prospective Technologies to Prepare Propellants with Improved Performance Properties. Ul’yanovsk, 1989. 215 p.
11. Englin B. A. Use of Liquid Propellants at Low Temperatures. 3-rd edition revised and enlarged. М., 1980. 207 p.
12. Volkov A. I., Zharsky I. M. Big Chemical Guide. Minsk, 2005. 608 p.
13. Calculated Evaluation and Experimental Check of RPC Degassing and Saturation by Helium for Filling Cyclone-4 LV: Technical Note Cyclone-4. 22.6849.123 СТ / Yuzhnoye SDO. 2005. 29 p.

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2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop
2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop
2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop
]]> 18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions https://journal.yuzhnoye.com/content_2017_2/annot_18_2_2017-en/ Wed, 09 Aug 2023 12:19:09 +0000 https://journal.yuzhnoye.com/?page_id=29858
2017 (2); 102-106 Language: Russian Annotation: The paper presents the original test methods with simulation of axial loads nx＜＜ 1 and nx ＞＞1 and the test stands which were used on testing the Zenit-2 ILV large-sized nose fairing.
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18. Development Test of Payload Fairing Separation Dynamics under Ground Conditions

Authors:

Shevtsov E. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 102-106

Language: Russian

Annotation: The paper presents the original test methods with simulation of axial loads nx＜＜ 1 and nx ＞＞1 and the test stands which were used on testing the Zenit-2 ILV large-sized nose fairing.

Key words:

Bibliography:
1. Fundamentals of Spacecraft Launch Vehicles Designing / Under the editorship of V. P. Mishin. М., 1991. 415 p.
2. Kolesnikov K. S., Kozlov V. V., Kokushkin V. V. Flying Vehicles Stages Separation Dynamics. М., 1977. 224 p.
3. Аuthor’s Certificate 285792. Stand for Testing Rocket Fairing Separation in Ground Conditions / O. A. Semenenko, E. I. Shevtsov, V. A. Gontarovsky, V. A. Petrushevsky et al. Claimed 10.05.1989.
4. Аuthor’s Certificate 323879. Method of g-Loads Simulation during Testing of Separation Systems of Cylindrical-Conical Fairing that Separates into Doors / E. I. Shevtsov, V. A. Gontarovsky et al. Claimed 07.02.1989.

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18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions
18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions
18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions
]]> 7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays https://journal.yuzhnoye.com/content_2017_1/annot_7_1_2017-en/ Tue, 27 Jun 2023 12:14:44 +0000 https://journal.yuzhnoye.com/?page_id=29425
By the example of Zenit LV it is shown that when using the statistic assessment, it is possible to considerably expand the launch vehicles application field from the viewpoint of ensuring required conditions in the spacecraft area. Calculation of Venting Parameters in Zenit-3SL ILV Bays PLB, US and IB in Injection Leg.
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7. Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays

Authors:

Sirenko V. M., Il’enko P. V., Semenenko P. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 43-47

Language: Russian

Annotation: The methodology is proposed of probabilistic assessment of fulfilment of the requirements to gas dynamic parameters in launch vehicle vented bays in the cases when it is impossible to categorically ensure satisfaction of all limitations. By the example of Zenit LV it is shown that when using the statistic assessment, it is possible to considerably expand the launch vehicles application field from the viewpoint of ensuring required conditions in the spacecraft area.

Key words:

Bibliography:
1. Calculation of Venting Parameters in Zenit-3SL ILV Bays PLB, US and IB in Injection Leg. Zenit-3SL 21.13651.122 ОТ: Technical Report. Dnipropetrovsk, 1998. 104 p.
2. Verification of Gas Dynamic and Design Parameters of Thermostating System and Globalstar SC X-Panels Local Blow off System: Report on research work / NASU ITM No12-12/97. 1997. 79 p.
3. Idelchik I. E. Guide on Hydraulic Resistances / Under the editorship of M. O. Steinberg. 3rd edition revised and enlarged. М., 1992. 672 p.
4. Kremer N. Sh. Theory of Probability and Mathematical Statistics: Tutorial. М., 2010. 551 p.
5. Zenit-3SL Integrated Launch Vehicle. Zenit-2S Launch Vehicle. Aerodynamic Analysis. P. 1. Materials on Aero Gas Dynamics. Book 5. Zenit-2S / Thuraya Р01.05: RBD Materials. Dnipropetrovsk, 2000. 120 p.

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7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays
7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays
7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays
]]> 12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing https://journal.yuzhnoye.com/content_2019_1-en/annot_12_1_2019-en/ Wed, 24 May 2023 16:00:15 +0000 https://journal.yuzhnoye.com/?page_id=27717
2019, (1); 81-86 DOI: https://doi.org/10.33136/stma2019.01.082 Language: Russian Annotation: Under the Sea Launch program when developer of the Zenit-3SL ILV control system issued the permission to launch in the conditions of drift from the design launch point of the Odyssey launch platform, the problem of drift parameters monitoring at the Sea Launch Commander ACS appeared.
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12. Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing

Authors:

Stetsenko V. Y., Davydenko S. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 81-86

DOI: https://doi.org/10.33136/stma2019.01.082

Language: Russian

Annotation: Under the Sea Launch program when developer of the Zenit-3SL ILV control system issued the permission to launch in the conditions of drift from the design launch point of the Odyssey launch platform, the problem of drift parameters monitoring at the Sea Launch Commander ACS appeared. To ensure the payload orbiting accuracy the following maximum permissible values of platform drift parametres were determined: • maximum velocity of platform drift – no more than 0,32 m/s; • maximum acceleration of platform drift – no more than ±0,05 m/s2; • maximum distance of platform drift from design launch point – no more than 1950 m. The article includes the computation algorithm of the platform drift parametres to calculate velocity and acceleration of the drift, as well as distance from the design launch point to the actual point of the platform location. Geographical coordinates – latitude and longitude of the platform according to the GPS sensor, installed on the platform are used for calculations. These values during prelaunch processing of the ILV are transmitted to the assembly and command ship’s workstation for calculation of loads in the ILV root section at the rate of once in a second. During one of the Sea Launch missions, C++ program was developed and installed on the loads calculation workstation, realizing the computation algorithm offered by the authors of this article. This program displayed in real time the monitored parametres of the platform drift, and monitored the tolerable limits. During the same mission, the correctness of the developed algorithm and program were confirmed during the special experiment on the launch platform drift in the launch point. In future, they were used during the subsequent missions of the Sea Launch program.

Key words: Sea Launch, latitude, longitude, algorithm, velocity, acceleration

Bibliography:

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12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing
12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing
12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing

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