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Content 2024 (1) Downloads: 14 Abstract views: 517 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Matawan; Phoenix; Ashburn; Ashburn; Des Moines; Boardman; Ashburn 7 Singapore Singapore; Singapore 2 China Shanghai 1 Finland Helsinki 1 Canada Monreale 1 Netherlands Amsterdam 1 Ukraine Dnipro 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Semenenko Ye.V., Biliaiev M. Parameters calculation of the lunar regolith transport system Автори: Semenenko Ye.V., Biliaiev M. Parameters calculation of the lunar regolith transport system Автори: Semenenko Ye.V., Biliaiev M. Parameters calculation of the lunar regolith transport system Автори: Semenenko Ye.V., Biliaiev M. Parameters calculation of the lunar regolith transport system Автори: Semenenko Ye.V., Biliaiev M.
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11. Parameters calculation of the lunar regolith transport system

Authors:

Semenenko Ye. V.1, Biliaiev M. M.2, Semenenko P. V.3

Organization:

National Academy of Sciences of Ukraine, M.S. Poliakov Institute of geotechnical mechanics1; Ukrainian State University of Science and Technologies2; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2024, (1); 93-101

Language: Ukrainian

Annotation: The objective of this article is to develop a scientifically proven method of calculation of the auger conveyor parameters, such as the conveyor capacity and the corresponding power of the electrical motor, for different densities and porosities of conveyed materials, the geometrical parameters of the auger, and the specificity of the gravitational fields at the place of transportation. Another objective is to investigate potential limitations of the auger parameters when transporting lunar regolith. To reach these objectives, the known relations for calculating the auger conveyor parameters were applied, as well as the fundamental laws of the granular media mechanics, the principal equations of asynchronous motor electrodynamics, and the behavior of granular media when moving it with the auger conveyor, experimentally studied by the domestic authors. It gave the possibility, for the first time for the lunar environment, to suggest a procedure to calculate the auger conveyor parameters, such as the conveyor capacity and the corresponding power of the electric motor, using known geometrical parameters of the mainline and pipeline, the auger conveyor filling ratio and the parameters of the selected electrical motor. It gave the possibilities to study how the filling ratio of the auger conveyor influences its principal performance parameters and determine potential limitations of the geometrical parameters and the filling ratios of auger conveyors according to the parameters and features of the selected electrical motor. The allowable transportation distances, diameters, other geometrical parameters of auger conveyors, and conveyor filling ratios with the selected electrical motor have been determined. It has been proven that the solutions based on using auger conveyors would be most rational for transporting loose lunar regolith over the Moon’s surface because the auger conveyors are compact and adaptable, and they can be placed inside tubes and laid under the day surface, thereby ensuring the continuous transportation process. Furthermore, they are capable of autonomous operation and can use the electricity produced by solar arrays.

Key words: Moon, regolith, auger, electric motor, capacity, power

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11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM
11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM
11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM

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]]> 19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles https://journal.yuzhnoye.com/content_2018_2-en/annot_19_2_2018-en/ Thu, 07 Sep 2023 12:23:58 +0000 https://journal.yuzhnoye.com/?page_id=30801
V., Semenenko P.
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19. Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles

Authors:

Aksiuta О. А., Balyayev O. A., Konstantinov G. I., Sidoruk V. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 157-172

DOI: https://doi.org/10.33136/stma2018.02.157

Language: Russian

Annotation: The measurement errors upon conducting flight tests for launch vehicles are evaluated by considering the interferences and uncertainties in the measurement system procedure. Formal use of this approach can lead to unpredictable consequences. More reliable evaluation of errors upon conducted measurements can be achieved if the measurement process is regarded as a procedure of successive activities for designing, manufacturing, and testing the measurement system and the rocket including measurements and their processing during the after-flight analysis of the received data. The sampling rates of the main controlled parameters are three to ten times higher than the frequency range of their changing. Therefore, it is possible to determine the characteristics of the random error components directly on the basis of registered data. The unrevealed systematic components create the basic uncertainty in the evaluation of the examined parameter’s total measurement error. To evaluate the precision and measurement accuracy of a particular launch, the article suggests specifying the preliminary data on measurement error components determined during prelaunch processing and launch. Basic structures of algorithms for evaluation of precision and measurement accuracy for certain mathematical models that form the measured parameters were considered along with the practical case when static correlation existed among the measured parameters.

Key words: flight tests, sensor, measurement error, mathematical model

Bibliography:
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19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles
19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles
19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles

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]]> 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
Fundamentals of Spacecraft Launch Vehicles Designing / Under the editorship of V. Flying Vehicles Stages Separation Dynamics. Semenenko, E. Petrushevsky et al. (2017) "Development Test of Payload Fairing Separation Dynamics under Ground Conditions" Космическая техника. "Development Test of Payload Fairing Separation Dynamics under Ground Conditions" Космическая техника. quot;Development Test of Payload Fairing Separation Dynamics under Ground Conditions", Космическая техника. More Citation Formats Harvard Chicago IEEE AIP ДСТУ 8302:2015 ДСТУ ГОСТ 7.1:2006 (ВАК) ISO 690:2010 BibTeX на сайт ДП «КБ «Південне»
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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
V., Semenenko P. V., Semenenko P. V., Semenenko P. V., Semenenko P. V., Semenenko P. V., Semenenko P.
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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:
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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
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