Search Results for “Lysenko M. T.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Fri, 19 Apr 2024 06:44:26 +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 “Lysenko M. T.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew https://journal.yuzhnoye.com/content_2018_1-en/annot_5_1_2018-en/ Tue, 05 Sep 2023 06:16:22 +0000 https://journal.yuzhnoye.com/?page_id=30421
, Lysenko M. B., Lysenko M. Available at: https://doi.org/10.33136/stma2018.01.027 . https://doi.org/10.33136/stma2018.01.027 . B., Lysenko M. September.2018, doi: https://doi.org/10.33136/stma2018.01.027 . B., Lysenko M. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 27—30.doi: https://doi.org/10.33136/stma2018.01.027 . B., Lysenko M. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 27—30.doi: https://doi.org/10.33136/stma2018.01.027 . B., Lysenko M. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 27—30.doi: https://doi.org/10.33136/stma2018.01.027 . B., Lysenko M. Missile armaments Том: 2018 Випуск: 2018 (1) Рік: 2018 Сторінки: 27—30.doi: https://doi.org/10.33136/stma2018.01.027 .
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5. Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew

Authors:

Bezkrovny І. B., Lysenko M. T., Tregubenko О. О.

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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5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew
5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew
5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew
]]> 16.1.2019 Oscillation Processes in Rig at the Moment of SRM Transfer to Main Operation Mode https://journal.yuzhnoye.com/content_2019_1-en/annot_16_1_2019-en/ Wed, 24 May 2023 16:00:31 +0000 https://journal.yuzhnoye.com/?page_id=27721
, Lysenko M. B., Lysenko M. Available at: https://doi.org/10.33136/stma2019.01.110 . https://doi.org/10.33136/stma2019.01.110 . B., Lysenko M. March.2019, doi: https://doi.org/10.33136/stma2019.01.110 . B., Lysenko M. Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 110—113.doi: https://doi.org/10.33136/stma2019.01.110 . B., Lysenko M. Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 110—113.doi: https://doi.org/10.33136/stma2019.01.110 . B., Lysenko M. Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 110—113.doi: https://doi.org/10.33136/stma2019.01.110 . B., Lysenko M. Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 110—113.doi: https://doi.org/10.33136/stma2019.01.110 .
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16. Oscillation Processes in Rig at the Moment of SRM Transfer to Main Operation Mode

Authors:

Bezkrovny І. B., Lysenko M. T., Gergel V. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 110-113

DOI: https://doi.org/10.33136/stma2019.01.110

Language: Ukrainian

Annotation: This paper describes the configuration of the rig, designed to fasten the solid-propellant rocket engine (hereunder referred to engine) during their testing, with engine thrust measurements by force transducers. It is determined that rig is the important link in the measurement chain, which directly impacts the thrust measurements, values of which will be used for calculation of the most important engine characteristics (for example, total burn). It was observed that when engine starts the basic mode of operation the thrust-measuring system of the rig is impacted by the dynamic loading caused by the engine thrust, which results in the occurrence of the oscillating processes in the rig, therefore it is important to know the behavior of these oscillating processes to estimate their impact on the thrust measurement during the design of the rigs and their thrustmeasuring systems. It is shown that if there is no procedure in the design practice to define the mode of oscillations in the rig it is rational to do it analyzing experimental thrust – time curves when different engines start the basic mode of operation. Number of experimental thrust (displacement of the engine/rig moving part) – time curves are provided for analysis when four different engines with different ballistic characteristic and capabilities start the basic mode of operation. Oscillating processes in the rig distort the physical behavior of the thrust, which requires additional analysis of the data following the tests, but since the oscillations subside rapidly, they will not significantly affect the calculation of the total burn. It is also observed that frequency of oscillations of the moving part of the rig, registered by the motion sensor, coincides with oscillation frequency, registered by the force transducer, moreover stable behavior of the oscillating processes, registered by the force transducer of the same engines, when they started the basic mode of operation, indicate the stable behavior of those engines and stable performance of the rig.

Key words: firing rig tests of the engine, thrust measurement, engine thrust and displacement – time diagrams

Bibliography:

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16.1.2019 Oscillation Processes in Rig at the Moment of SRM Transfer to Main Operation Mode
16.1.2019 Oscillation Processes in Rig at the Moment of SRM Transfer to Main Operation Mode
16.1.2019 Oscillation Processes in Rig at the Moment of SRM Transfer to Main Operation Mode

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]]> 15.1.2019 Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test https://journal.yuzhnoye.com/content_2019_1-en/annot_15_1_2019-en/ Wed, 24 May 2023 16:00:27 +0000 https://journal.yuzhnoye.com/?page_id=27720
Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test Authors: Lysenko M. Content 2019 (1) Downloads: 19 Abstract views: 423 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Baltimore; Plano; Monroe; Ashburn; Seattle; Ashburn; Boardman; Seattle; Portland; San Mateo; Boardman; Ashburn 13 Singapore Singapore; Singapore; Singapore; Singapore; Singapore 5 Ukraine Dnipro 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Lysenko M. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test Автори: Lysenko M. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test Автори: Lysenko M. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test Автори: Lysenko M. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test Автори: Lysenko M.
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15. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test

Authors:

Lysenko M. T., Rohulin V. V., Bezkrovny І. B., Kalnysh R. V.

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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15.1.2019 Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test
15.1.2019 Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test
15.1.2019 Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test

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]]> 13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight https://journal.yuzhnoye.com/content_2019_1-en/annot_13_1_2019-en/ Wed, 24 May 2023 16:00:19 +0000 https://journal.yuzhnoye.com/?page_id=27718
Lysenko L. Available at: https://doi.org/10.33136/stma2019.01.088 . https://doi.org/10.33136/stma2019.01.088 . March.2019, doi: https://doi.org/10.33136/stma2019.01.088 . Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 87—94.doi: https://doi.org/10.33136/stma2019.01.088 . Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 87—94.doi: https://doi.org/10.33136/stma2019.01.088 . Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 87—94.doi: https://doi.org/10.33136/stma2019.01.088 . Missile armaments Том: 2019 Випуск: 2019, (1) Рік: 2019 Сторінки: 87—94.doi: https://doi.org/10.33136/stma2019.01.088 .
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13. Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

Authors:

Holubek O. V., Filippenko I. M., Tatarevsky K. E.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 87-94

DOI: https://doi.org/10.33136/stma2019.01.088

Language: Russian

Annotation: This article considers the problem of determination of propulsion system solid fuel burn-out time in the extraatmospheric flight segment taking the apparent acceleration and apparent speed measured by the inertial navigation system. Correlation analysis of the realized and nominal dependencies of the apparent acceleration and apparent speed of the launch vehicle on relative operating time of the propulsion system is suggested to be used to forecast the fuel burn-out time. In order to improve the accuracy of the forecast, and to decrease the amplitude and vibration rate of its results several channels simultaneously are suggested to be used for calculations with subsequent majority voting and digital filtration. As a result of the study, the procedure to forecast the time of solid fuel burn-out in the launch vehicle propulsion system in flight has been developed. Operability of the suggested procedure has been verified using the mathematical simulation of the launch vehicle flight for two operating modes of the propulsion system different from the nominal ones. Based on the statistical processing of the deviations of the predicted time of solid fuel burn-out versus the realized one it was determined that the forecast based on the results of apparent acceleration measurement has the greatest accuracy with the minimal number of operations. Suggested procedure is easily realized as the multistage adaptive algorithm and can be used in the guidance system of the solid-propellant launch vehicle in the extra-atmospheric flight segment for the numerical forecast of the reachable terminal parameters of flight, definition of command vector and development of the relevant thrust vector control commands.

Key words: guidance system, correlation analysis, procedure, mathematical simulation

Bibliography:

1. Osnovy teorii avtomaticheskogo upravleniya raketnymi dvigatelnymi ustanovkami / A. I. Babkin, S. I. Belov, N.B. Rutovskiy i dr. – M.: Mashinostroenie, 1986. – 456 s.
2. Proektirovanie system upravleniya obiektov raketno-kosmicheskoy techniki. T. 1. Proektirovanie system upravlenia raket-nositeley: Uchebnik/Yu. S. Alekseev, Yu. Ye. Balabey, T. A. Baryshnikova i dr.; Pod obshey red. Yu. S. Alekseeva, Yu. M. Zlatkina, V. S. Krivtsova, A. S. Kulika, V. I. Chumachenko. – Kh.: NAU «KhAI», NPP «Khartron-Arkos», 2012. – 578 s.
3. Sikharulidze Yu. G. Ballistika letatelnykh apparatov. – M.: Nauka, 1982. – 352 s.
4. Lysenko L. N. Navedenie I navigatsia ballisticheskykh raket: Ucheb. posobie. – M.: Izd-vo MGTU im. N. E. Baumana, 2007. – 672 s.
5. Systemy upravleniya letatelnymi apparatami (ballisticheskimi raketami I ikh golovnymi chastyami): Uchebnik dlya VUZov/ G. N. Razorenov, E. A. Bakhramov, Yu. F. Titov; Pod red. G. N. Razorenova. – M.: Mashinostroenie, 2003. – 584 s.
6. Siouris G. M. Missile guidance and control systems. – New York: Springer-Verlag New York, Inc., 2004. – 666 p. https://doi.org/10.1115/1.1849174
7. Zarchan P. Tactical and Strategic missile guidance. – American Institute of Aeronautics and Astronautics, Inc., 2012. – 989 p. https://doi.org/10.2514/4.868948
8. Balakrishnan S. N. Advances in missile guidance, control, and estimation / S. N. Balakrishnan, A. Tsourdos, B.A. White. – New York: CRC Press, Taylor & Francis Group. 2013. – 682 p.
9. Shneydor N. A. Missile guidance and pursuit: kinematics, dynamics and control. – Horwood Publishing Chichester, 1998. – 259 p. https://doi.org/10.1533/9781782420590
10. Yanushevsky R. Modern missile guidance. – CRC Press, Taylor & Francis Group, 2008. – 226 p. https://doi.org/10.1201/9781420062281

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13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight
13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight
13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

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]]> 6.1.2023 Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests https://journal.yuzhnoye.com/content_2023_1-en/annot_6_1_2023-en/ Fri, 12 May 2023 16:10:51 +0000 https://test8.yuzhnoye.com/?page_id=26990
Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests Authors: Lysenko M. Content 2023 (1) Downloads: 27 Abstract views: 378 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Baltimore; Plano; Monroe; Ashburn; Ashburn; Mountain View; Boydton; Boydton; Boydton; Boydton; San Mateo; San Mateo; Boydton; Boydton; Boydton; Boardman; Ashburn 18 Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore 6 Sri Lanka Colombo; Colombo 2 Ukraine Dnipro 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Lysenko M. Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests Автори: Lysenko M.
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6. Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests

Authors:

Lysenko M. T., Rohulin V. V., Demchenko A. V., Bezkrovny І. B., Kalnysh R. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 56-62

DOI: https://doi.org/10.33136/stma2023.01.056

Language: Ukrainian

Annotation: This article dwells on results of firing bench testing of the solid-propellant rocket engine (SPRE), fastened to the thrust-measuring assembly stand. It is shown that when engine enters the steady-state mode of operation, plane (forward and rotation) vibrations of the SPRE can take place in the assembly stand due to the sudden pattern of thrust generation and displacement of the center of mass of the vibrating system from the engine axis. These vibrations distort measured values of engine thrust and pattern of its change versus time. The purpose of this work is to simulate the oscillating processes of the engine atop the assembly stand to single out in the distorted values of the measured thrust the components related to the processes in the engine and components, which are introduced into the thrust measurement by the oscillating processes in the system “assembly stand – engine”. Model of vibrating system is suggested, which consists of two rigidly connected bodies, containing elastic links, enabling forward and rotary motion and limited by the rigidity of the links. Mathematical model of the vibrating system is developed. Internal forces and moments acting in oscillatory system are defined. Method of numerical simulation of plane vibrations within the limits of the developed model is suggested. Plane vibrating motion and elastic force curve (curve based on force sensor readings) were simulated in thrust-measuring system for different cases of thrust curve and values of vibrating system parameters. Resonance condition was simulated and mutual influence of elastic parametrical link between forward and rotary vibrations was established. Impact of thrust-measuring system rigidity on peak values of force sensor readings was found out. Elastic force vibrations in thrust-measuring system with vibrating system parameters were simulated including variant of thrust change versus time, implemented during firing bench tests of one of the SPRE. It is shown that registered simulation results recreate thrust measurement results in pattern and values obtained by the force sensor during the firing bench tests, and owing to this, it was concluded that oscillating process parameters, assumed in the model, meet the actual ones. It is concluded that simulation provides objective interpretation of the thrust curve, reliable and comprehensive analysis of engine run during firing bench tests, more detailed and exact design of the assembly stand.

Key words: vibrating system, plane vibrations, forward vibrations, rotary vibrations, resonance, thrust measurement

Bibliography:

1. Beskrovniy I. B., Kirichenko A. S., Balitskiy I. P. i dr. Opyt predpriyatia po proektirovaniyu i ekspluatatsii stapeley dlya ispytaniy RDTT. Kosmicheskays technika. Raketnoye vooruzhennie: Sb. nauch.-techn. st. 2008. Vyp. 1. Dnepropetrovsk: GP «KB «Yuzhnoye». S. 119–127.
2. Lysenko M. T., Rogulin V. V., Beskrovniy I. B., Kalnysh R. V. Modelyuvannya kolyvann RDTP u stapeli, scho vynykaut pid chas VSV. Kosmicheskays technika. Raketnoye vooruzhennie: Sb. nauch.-techn. st. 2019. Vyp. 1. Dnepropetrovsk: GP «KB «Yuzhnoye».
3. Beskrovniy I. B., Lysenko M. T., Gergel V. G. Kolyvalnni processy u stapeli v moment vyhodu RDTP na ustalenniy rezhim roboty. Kosmicheskay technika. Raketnoye vooruzhennie: Sb. nauch.-techn. st. 2019. Vyp. 1. Dnepropetrovsk: GP «KB «Yuzhnoye».

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6.1.2023 Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests
6.1.2023 Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests
6.1.2023 Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests

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