Search Results for “thrust measurement” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Mon, 16 Mar 2026 00:46:07 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “thrust measurement” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 3.2.2025 Electric thrusters utilizing metal plasma https://journal.yuzhnoye.com/content_2025_2-en/annot_3_2_2025-en/ Tue, 27 Jan 2026 08:12:56 +0000 https://journal.yuzhnoye.com/?page_id=35821
Flight Metal Plasma Thruster (MPT) Development, Qualification, and Thrust Measurement Campaign.
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3. Electric thrusters utilizing metal plasma

Date of receipt of the article for publication: 24.10.2025

Date of acceptance of the article for publication after review: 07.11.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Spirin Ye. V., Nadtoka V. M.

ORCID authors:

Spirin Ye. V. ORCID, Nadtoka V. M. ORCID

Organization:

Yangel Yuzhnoye State Design Office

Page: Kosm. teh. Raket. vooruž. 2025 (2); 24-34

DOI: https://doi.org/10.33136/stma2025.02.024

Language: Ukrainian

Annotation: The article provides an overview of modern research on the problem of creating electric jet engines based on metal plasma. Electric jet engines have long attracted the attention of specialists working in the fi eld of creating space technology. One type of electric rocket engines is electric engines that use a metal plasma fl ow. A metal plasma rocket engine (Vacuum Arc Thruster, VAT) is a new class of electric propulsion systems in which metal converted into a plasma state using an electric discharge and an accelerated metal plasma fl ow creates jet thrust. A metal plasma engine does not require gas or liquid fuel, neutralizers, heaters, highvoltage electronics, or strong electric or magnetic fi elds to operate. Metal plasma engines use metal to create a plasma fl ow, so their design is very compact. Since the cathode material is in the solid phase, there can be no fuel loss due to leakage. No gases are required, so such engines do not threaten the spacecraft with a possible explosion of the pressurized container. In addition, there are no valves and fl ow sensors (components that increase the complexity and cost of the system). The purpose of this work is to analyze the level of development of vacuum-arc jet engines on metal plasma based on the generalization and systematization of publications. Particular attention paid to the analysis of works that consider metal plasma engines with a thrust level of the order of millinewtons. Based on the analysis, conclusions drawn regarding the relevance of the development of vacuum-arc jet engines. In March 2024, a satellite successfully launched in the USA, in which the Xantus X4 vacuum-arc jet engine developed by Alameda Applied Sciences Co. and Benchmark Space Systems was installed. Currently, leading companies in the space industry continue to improve the technology of metal plasma rocket engines with an emphasis on reliability, increased thrust and service life. The article intended for specialists in the fi eld of rocket engine engineering.

Key words: electric thruster, vacuumarc discharge, metal plasma

Bibliography:

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15. Qi N., Gensler S., Prasad R., Krishnan M., Vizir A. & Brown I. A vacuum arc ion thruster for space propulsion. Technical report, AASC. SBIR Phase-I Final Report F49620-97-C-0024, 31 MARCH 1998. https://doi.org/10.21236/ADA342818
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https://doi.org/10.1063/1.1428784

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]]> 3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff https://journal.yuzhnoye.com/content_2020_1-en/annot_3_1_2020-en/ Fri, 29 Sep 2023 18:22:49 +0000 https://journal.yuzhnoye.com/?page_id=32230
Inverse heat transfer method applied to capacitively cooled rocket thrust chambers. Measurement. https://doi.org/10.1016/j.measurement.2018.03.039 4. Thermal-structural analysis of regeneratively cooled thrust chamber wall in reusable LOX / Methane rocket engines.
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3. Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Degtiarov М. O.1, Avramov K. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2020, (1); 26-33

DOI: https://doi.org/10.33136/stma2020.01.026

Language: Russian

Annotation: The study of thermal strength of the hold-down bay is considered. The hold-down bay is a cylindrical shell with the load-bearing elements as the standing supports. The case of the hold-down bay consists of the following structural elements: four standing supports and the compound cylindrical shell with two frames along the top and bottom joints. The purpose of this study was the development of a general approach for the thermal strength calculation of the hold-down bay. This approach includes two parts. Firstly, the unsteady heat fields on the hold-down bay surface are calculated by means of the semi-empirical method, which is based on the simulated results of the combustion product flow of the main propulsion system. The calculation is provided by using Solid Works software. Then the unsteady stress-strain behavior of the hold-down bay is calculated, taking into consideration the plastoelastic deformations. The material strain bilinear diagram is used. The finiteelement method is applied to the stress-strain behavior calculation by using NASTRAN software. The thermal field is assumed to be constant throughout the shell thickness. As a result of the numerical simulation the following conclusions are made. The entire part of the hold-down bay, which is blown by rocket exhaust jet, is under stress-strain behavior. The stresses of the top frame and the shell are overridden the breaking strength that caused structural failure. The structure of the hold-down bay, which is considered in the paper, is unappropriated to be reusable. The hold-down bay should be reconstructed by reinforcement in order to provide its reusability.

Key words: stress-strain behavior, finite-element method, plastoelastic deformations, breaking strength, reusability

Bibliography:

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2. Perakis N., Haidn O. J. Inverse heat transfer method applied to capacitively cooled rocket thrust chambers. International Journal of Heat and Mass Transfer. 2019. № 131. P. 150–166. https://doi.org/10.1016/j.ijheatmasstransfer.2018.11.048
3. Yilmaz N., Vigil F., Height J., et. al. Rocket motor exhaust thermal environment characterization. Measurement. 2018. № 122. P. 312–319. https://doi.org/10.1016/j.measurement.2018.03.039
4. Jafari M. Thermal stress analysis of orthotropic plate containing a rectangular hole using complex variable method. European Journal of Mechanics A /Solids. 2019. № 73. P. 212–223. https://doi.org/10.1016/j.euromechsol.2018.08.001
5. Song J., Sun B. Thermal-structural analysis of regeneratively cooled thrust chamber wall in reusable LOX / Methane rocket engines. Chinese Journal of Aeronautics. 2017. № 30. P. 1043–1053.
6. Ramanjaneyulu V., Murthy V. B., Mohan R. C., Raju Ch. N. Analysis of composite rocket motor case using finite element method. Materials Today: Proceedings. 2018. № 5. P. 4920–4929.
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12. Лойцянский Л. Г. Механика жидкости и газа. М., 2003. 840 с.
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]]> 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
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). Key words: firing rig tests of the engine , thrust measurement , engine thrust and displacement – time diagrams Bibliography: Full text (PDF) || firing rig tests of the engine , thrust measurement , engine thrust and displacement – time diagrams .
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16. Oscillation Processes in Rig at the Moment of SRM Transfer to Main Operation Mode

ISSN: 2617-5525

e-ISSN: 2617-5533

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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]]> 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
Key words: elastic oscillations , motor starting operation , sudden loading , measurement of thrust , principle of superposition , initial thrust Bibliography: 1. elastic oscillations , motor starting operation , sudden loading , measurement of thrust , principle of superposition , initial thrust .
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15. Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test

ISSN: 2617-5525

e-ISSN: 2617-5533

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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]]> 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
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.
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13. Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

ISSN: 2617-5525

e-ISSN: 2617-5533

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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]]> 7.1.2016 Updated Design of SRM Test Rig https://journal.yuzhnoye.com/content_2016_1/annot_7_1_2016-en/ Tue, 23 May 2023 13:02:04 +0000 https://journal.yuzhnoye.com/?page_id=27612
2016 (1); 52-54 Language: Russian Annotation: The advanced design of SRM test rig is considered the use of which improves the quality of measurement of motor power parameters and increases the amount of test data. The technique is proposed for assessment of rig operation stability when measuring the lateral thrust.
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7. Updated Design of SRM Test Rig

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Bezkrovny І. B., Tregubenko О. О., Krivsun R. Y.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 52-54

Language: Russian

Annotation: The advanced design of SRM test rig is considered the use of which improves the quality of measurement of motor power parameters and increases the amount of test data. It is shown, due to which this was achieved. The technique is proposed for assessment of rig operation stability when measuring the lateral thrust.

Key words:

Bibliography:

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]]> 14.2.2019 Selection of the validation algorithm for the solid rocket motor trust measurement procedure https://journal.yuzhnoye.com/content_2019_2-en/annot_14_2_2019-en/ Mon, 15 May 2023 15:46:10 +0000 https://journal.yuzhnoye.com/?page_id=27216
2019, (2); 103-108 DOI: https://doi.org/10.33136/stma2019.02.103 Language: Russian Annotation: The solid rocket motors thrust is measured according to the developed measurement procedure; fulfilment of its requirements guarantees obtaining the results with required accuracy parameters. The proposed article deals with two validation algorithms of measurement procedure for solid rocket motor thrust up to 30 tf – end-to-end and link-by-link validation methods. The comparative analysis of the results of validation procedure of solid rocket motor thrust measurement procedure obtained during metrological investigations of thrust measurement channel by end-to-end and link-by-link validation methods shows that to ensure the required measurement accuracy, the algorithms of end-to-end method is preferable, at which the lower values of reduced error can be obtained as compared with the algorithm of link-by-link validation.
]]>

14. Selection of the validation algorithm for the solid rocket motor trust measurement procedure

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Voloshina M. O., Gergel V. G., Yeres L. O., Kurako I. М., Oliinyk O. O., Rohulin V. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 103-108

DOI: https://doi.org/10.33136/stma2019.02.103

Language: Russian

Annotation: The solid rocket motors thrust is measured according to the developed measurement procedure; fulfilment of its requirements guarantees obtaining the results with required accuracy parameters. Compliance of this procedure with the measurement accuracy requirements is confirmed by way of its validation that can be performed according to different algorithms. The proposed article deals with two validation algorithms of measurement procedure for solid rocket motor thrust up to 30 tf – end-to-end and link-by-link validation methods. The composition of measurement channel, the experimental works performed at each validation algorithm are described, the calculation formulas to evaluate the limits of absolute measurement error and the obtained numerical values of the latter are presented. The comparative analysis of the results of validation procedure of solid rocket motor thrust measurement procedure obtained during metrological investigations of thrust measurement channel by end-to-end and link-by-link validation methods shows that to ensure the required measurement accuracy, the algorithms of end-to-end method is preferable, at which the lower values of reduced error can be obtained as compared with the algorithm of link-by-link validation.

Key words: measurement channel, reduced error, calibration characteristic, electric signal.

Bibliography:
1. Kotsyuba A. M., Zgurya V. I. Otsinyuvannya prydantosti (validatsiya) metodik vyprobuvannya ta calibruvannya: detalizatsia vymog. Metrologia ta prylady. 2013. № 6. S. 22–24.
2. Kotsyuba A. M., Domnytska V. K., Kotsyuba L. G. Validatsia metodik calibruvannya. Standartizatsia, certifikatsia, yakist’. 2016. № 1. S. 41–45.
3. Kotsyuba A. M. Validatsia metodik calibruvannya mir fizichnykh velichin. Systemy obrobky informatsii. 2015. № 2 (127). S. 35–39.

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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
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”. 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. Key words: vibrating system , plane vibrations , forward vibrations , rotary vibrations , resonance , thrust measurement Bibliography: 1. vibrating system , plane vibrations , forward vibrations , rotary vibrations , resonance , thrust measurement .
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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

ISSN: 2617-5525

e-ISSN: 2617-5533

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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