Search Results for “reduced mass” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Mon, 16 Mar 2026 00:20:10 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “reduced mass” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 5.2.2025 Analysis and minimization of resistive forces occurring during rocket stage separation. Possibility of using a single pneumatic pusher for stage separation https://journal.yuzhnoye.com/content_2025_2-en/annot_5_2_2025-en/ Tue, 27 Jan 2026 08:28:58 +0000 https://journal.yuzhnoye.com/?page_id=35828
For the fi rst time in the practice of launch vehicle design, the authors present a separation system that eliminates resistive forces through the use of an alternative complex of electrical disconnectors, featuring noncontact data transfer and allowing for reduced power losses and fewer elements that produce relative speed for the stage separation system, resulting in a signifi cantly lighter overall mass of the system.
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5. Analysis and minimization of resistive forces occurring during rocket stage separation. Possibility of using a single pneumatic pusher for stage separation

Date of receipt of the article for publication: 10.11.2025

Date of acceptance of the article for publication after review: 24.11.2025

Date of publication: 27.01.2026

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Udovychenko D. O., Makarenko A. O.

ORCID authors:

Udovychenko D. O. ORCID

Organization:

Yangel Yuzhnoye State Design Office

Page: Kosm. teh. Raket. vooruž. 2025 (2); 46-57

DOI: https://doi.org/10.33136/stma2025.02.046

Language: Ukrainian

Annotation: One of the primary objectives in designing separation systems for rocket stages is to create a system featuring minimal mass while ensuring the required relative speed of stage separation, achieving minimal thrust diff erence, and preventing contamination of spacecraft surfaces. Based on the results of resolving an optimization problem, the utilization of one pneumatic pusher for stage separation is one of the optimum scenarios, which will enable a several times lighter mass of the separation system due to the signifi cant reduction of the mass of pipelines, the overall mass of the pusher, and the mass of gas bottles and their fasteners. The preliminary analysis of the separation process and the possibility of using a single pneumatic pusher for stage separation was performed using a mathematical model in the form of a system of diff erential equations describing the stage separation process, and through a series of calculations. The calculation results demonstrate that using a single pneumatic pusher to minimize the risk of an emergency requires a substantial reduction of the resistive forces occurring during stage separation. The article reviews the results of ground development testing for the stage separation system utilized in the Cyclone launch vehicles. It simulates an emergency when an abnormal detachment of the structural elements of stages occurs due to a meshing of electrical disconnector covers, resulting in the adapter section rotation by an angle over the allowable value. The article outlines the method for the experimental determination of resistive forces, presents calculated values obtained during the design phase, and compares these values with experimental data. Resistive force components were identifi ed during testing, such as detachment forces for electrical connectors and sealing elements, and friction forces in guiding studs. For the fi rst time in the practice of launch vehicle design, the authors present a separation system that eliminates resistive forces through the use of an alternative complex of electrical disconnectors, featuring noncontact data transfer and allowing for reduced power losses and fewer elements that produce relative speed for the stage separation system, resulting in a signifi cantly lighter overall mass of the system. The article analyzes resistive forces induced by the detachment of sealants. It presents a procedure for the autonomous development testing of joint sealants, which identifi es the relation between their detachment force and layer thickness. A technique for sealant application to the attachment surface has been developed. The test results enabled determining the required thickness of attachment sealants and the optimum application technique. Therefore, the change in the sealant application technique resulted in a 2.3 times lower maximum resistive force during stage separation, which meets the maximum and design values. The results of experiments provide meaningful data for the engineers of stage and booster separation systems for spacecraft and launch vehicles. Furthermore, they confi rm the feasibility of using alternative electrical disconnectors for stage separation.

Key words: pneumatic pusher, non-contact electric connector, resistive force, stage separation system, minimum mass of the stage separation system, emergencies, transient dynamics, launch vehicle, materials properties, strength

Bibliography:

1. Hamand M. Yehia, Rigid body dynamics: A Lagrangian Approach. Boston, Birkhauser. 2022. 485 p.
2. Ahmed A. Shabana, Dinamic of Multibody Systems. Cambridge, Cambridge University Press. 2020. 420 p.
3. Beiko I. V., Bublyk B. M., Zinko P. M. Metody i alhorytmy rozviazannia zadach optymizatsii. Kyiv: Vyshcha shkola. 1983. 512 s.
4. Udovychenko D. O. Optymizatsiia parametriv pnevmatychnoi systemy rozdilennia stupeniv rakety-nosiia kosmichnoho pryznachennia. Visnyk DNU. 2025. 34 (3). S. 9-17.
5. Linnyk A. K. Konstruiuvannia korpusiv ridynnykh balistychnykh raket. Dnipro, Vyd-vo DDU. 1994. 220 s.
6. Joaquim A. Battle, Anna Barjam Condomines, Rigid body dynamics, Cambridge, Cambridge University Press. 2022. 596 p.

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]]> 4.1.2024 The dynamics of servo drives https://journal.yuzhnoye.com/content_2024_1-en/annot_4_1_2024-en/ Wed, 12 Jun 2024 16:08:46 +0000 https://journal.yuzhnoye.com/?page_id=34978
Interaction of the motor with the multimass system of the reducer and load is presented in the form of force interaction of two masses – a reduced mass of the rotor and mass of the load through the certain equivalent rigidity of the kinematic chain.
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4. The dynamics of servo drives

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Degtiarov М. O., Karpenko V. Y., Kozak L. R.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 29-39

DOI: https://doi.org/10.33136/stma2024.01.029

Language: Ukrainian

Annotation: The article gives the analysis results for the servo drives dynamics, obtained from the theoretical calculations and during the development testing of the high power electric drives. Theoretical research was conducted, using the complete mathematical model of the servo drive, which included the equations of the control signal shaping path, electric motor, reducer and load. The equations of the control signal shaping network include only the characteristics of the compensating element in the assumption that all other delays in the transformation path are minimized. The electric motor equations are assumed in the classical form, taking into account the influence of the following main parameters on the motor dynamics: inductance and stator winding resistance, torque and armature reaction coefficients and rotor moment of inertia. Interaction of the motor with the multimass system of the reducer and load is presented in the form of force interaction of two masses – a reduced mass of the rotor and mass of the load through the certain equivalent rigidity of the kinematic chain. To describe the effect of gap in the kinematic connection the special computational trick, which considerably simplifies its mathematical description, is used. Efficiency of the reducer is presented in the form of the internal friction, proportional to the transmitted force. Calculation results with the application of the given mathematical model match well with the results of the full-scale testing of different specimens of servo drives, which makes it possible to use it for the development of new servomechanisms, as well as for the correct flight simulation when testing the aircraft control systems. In particular, based on the frequency response calculations of the closed circuit with the application of the given mathematical model, it is possible to define optimal parameters of the correcting circuit. Reaction on the step action with the various values of circular amplification coefficient in the circuit gives complete information on the stability regions of the closed circuit and influence of various drive parameters on these regions. Based on the conducted theoretical and experimental studies, the basic conclusions and recommendations were obtained and presented, accounting and implementation of which will provide high dynamic characteristics of the newly designed servo drives.

Key words: electric drive, servo drive, reducer, stability, mathematical model.

Bibliography:
  1. Kozak L. Dynamika servomechanismov raketnoy techniki. Inzhenernye metody issledovaniya. Izd-vo LAP LAMBERT Academic Publiching, Germania. 2022.
  2. Kozak L. R., Shakhov M. I. Matematicheskie modely hydravlicheskikh servomekhanismov raketno-kosmicheskoy techniki. Kosmicheskaya technika. Raketnoe vooruzhenie. 2019. Vyp. 1.

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]]> 10.2.2019 Dynamic performance of the gas drive with jet motor https://journal.yuzhnoye.com/content_2019_2-en/annot_10_2_2019-en/ Tue, 03 Oct 2023 11:52:15 +0000 https://journal.yuzhnoye.com/?page_id=32366
Using Lagrange transformation as applied to ball screw transmission, the expression for reduced mass of output element was derived. The reduced mass of load depends on the jet motor design and exerts basic influence on the drive’s natural frequencies. The evaluation is given of reduced mass change from the jet motor moment of inertia and reducer transmission coefficient. The drive has relatively low pass band, which is explained by the value of reduced mass of load. Key words: pneumatic drive , functional arrangement , hydrodynamic force , reduced mass , Lagrange transformations , ball screw transmission , transient process , frequency characteristic Bibliography: 1. pneumatic drive , functional arrangement , hydrodynamic force , reduced mass , Lagrange transformations , ball screw transmission , transient process , frequency characteristic .
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10. Dynamic performance of the gas drive with jet motor

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Oliinyk V. P., Kaluger L. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 71-79

DOI: https://doi.org/10.33136/stma2019.02.071

Language: Russian

Annotation: The use of servo drives on flying vehicles determines the requirements to their dynamic characteristics. The problems of dynamics of drive with jet motor are not practically covered in publications. The task arises of selection of structure and parameters of devices consisting of several subsystems whose dynamic characteristics must be brought into agreement with each other in optimal way. The purpose of this work is to develop mathematical dependences for calculation of dynamic characteristics. The functional arrangement of the drive is considered consisting of jet motor based on Segner wheel with de Laval nozzle, mechanical transmission, pneumatic distributing device – jet pipe controlled by electromechanical converter. The layout is presented of mechanical segment of servo drive with jet motor with screw-nut transmission. The dynamic model is presented and the algebraic relations to determine natural frequencies of the drive are given. The motion equations of output rod at full composition of load are given. Using Lagrange transformation as applied to ball screw transmission, the expression for reduced mass of output element was derived. The reduced mass of load depends on the jet motor design and exerts basic influence on the drive’s natural frequencies. The evaluation is given of reduced mass change from the jet motor moment of inertia and reducer transmission coefficient. Based on the proposed algorithms, the dynamic characteristics of servo drive were constructed: transient process and amplitude-frequency characteristic. The drive has relatively low pass band, which is explained by the value of reduced mass of load.

Key words: pneumatic drive, functional arrangement, hydrodynamic force, reduced mass, Lagrange transformations, ball screw transmission, transient process, frequency characteristic

Bibliography:
1. Pnevmoprivod system upravleniya letatelnykh apparatov /V. A. Chaschin, O. T. Kamladze, A. B. Kondratiev at al. M., 1987. 248 s.
2. Berezhnoy A. S. Sovershenstvovanie rabochikh characteristic struino-reaktivnogo pnevmoagregata na osnove utochneniya modeli rabochego processa: dis. cand. techn. nauk: 05.05.17. Zaschischena 03.10.14. Sumy, 2014. 157 s.
3. Oleinik V. P., Yelanskiy Yu. A., Kovalenko V. N. et al. Staticheskie characteristiki gazovogo privoda so struinym dvigatelem /Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2016. Vyp. 2. S. 21-27.
4. Abramovich G. N. Prikladnaya gazovaya dynamika. M., 1976. 888 s.
5. Strutinskiy V. B. Matematichne modelyuvannya processiv ta system mechaniki. Zhitomir, 2001. 612 s.
6. Shalamov A. V., Mazein P. G. Dynamicheskaya model’ sharikovintovoi pary/ Izv. Chelyabinskogo nauchnogo centra UrO RAN. №4. Chelyabinsk, 2002. S.161-170.
7. Kripa K.Varanasi, Samir A. Nayfer. The Dynamics of Lead-Screw Drivers: Low-Order Modeling and Experiments /Journal of Dynamic System, Measurement and Control. June 2004. Vol. 126. P. 388-395. https://doi.org/10.1115/1.1771690

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]]> 7.1.2019 Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants https://journal.yuzhnoye.com/content_2019_1-en/annot_7_1_2019-en/ Thu, 25 May 2023 12:09:38 +0000 https://journal.yuzhnoye.com/?page_id=27712
Replacement of gas bottle pressurization systems with generating ones on such launch vehicles as 15A14, 15A15, 11K68 (8K67), 15A18M substantially simplified operation, reduced the pneumohydraulic feed system mass at least twice and its cost – by five times.
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7. Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Voloshin M. L., Kuda S. А., Logvinenko A. I., Mashchenko O. M., Shevtsov E. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 45-53

DOI: https://doi.org/10.33136/stma2019.01.045

Language: Russian

Annotation: Long-term experience in development, development testing and use of generating systems of fuel tanks pressurization for rockets powered by nitrogen tetroxide and unsymmetrical dimethylhydrazine is summarized. Replacement of gas bottle pressurization systems with generating ones on such launch vehicles as 15A14, 15A15, 11K68 (8K67), 15A18M substantially simplified operation, reduced the pneumohydraulic feed system mass at least twice and its cost – by five times. Typical stages of development and introduction of the pressurization generating systems are shown: development of generators, their development testing, study of the composition and parameters of gas. The important steps were the development of methodology for pressurization system parameters calculation, which enabled achievement of the substantial improvements of their characteristics, appearance of the high-performance hightemperature (up to ~ 1000o C) unsymmetrical dimethylhydrazine tank pressurization system, study of the degree of impact of each of the pressurization system parameters on the tank pressure. Accounting of the correlation between the flow rate and the generator gas temperature improved the output performance, as well as simplified and reduced the amount of development testing of the pressurization system. Important role of the gas sprayer design in pressurization system parametric configuration is described, and the advanced versions are shown taking into account g-loads, changes in temperature, pressure and propellant level inside the tank. Significant phase in the development of the generating pressurization system was the effective use of the high-temperature pressurization of the fuel tank with submerged propulsion system. Besides for the first time the effect of mechanical temperature destratification of the propellant in the tanks was observed, which occurs during the propulsion systems shutdown. Due to this effect, the Dnepr LV payload capability enhanced. Successful engineering solutions in the design of the pressurization system were defended by ~80 copyright certificates and patents of invention, ~40 of which were successfully implemented.

Key words: gas generator, sprayer, propulsion system, tank, gas pressure, gas temperature

Bibliography:

1. Belyaev N. M. Systemy nadduva toplivnykh bakov raket. M.: Mashinostroenie, 1976. 336 p.
2. Logvinenko A. I. Osnovnyie napravlenia sovershenstvovania PGS sovremennykh RN / Dokl. Mezhd. astronavt. kongress. IAA. C4.1 IAC-63. Naples, Italia, 2012.
3. Kozlov A. A., Novikov V. N., Soloviev Ye. V. Systemy pitania i upravlenia zhidkostnykh raketnykh dvigatelnykh ustanovok. M.: Mashinostroenie, 1988. 352 p.
4. Logvinenko A. I. Tendentsii razvitia system nadduva toplivnykh bakov RN// Tez. dokl. Mezhdunar. astronavt. congressa IAC–05–C4.1.10, IAC-56. Fukuoka, Japan, 2005.
5. Logvinenko A. Gas-generation pressurization system experimental development method of the LV propellant tanks / Acta Astronautica. 2009. AA3161. №64. Р. 84-87. https://doi.org/10.1016/j.actaastro.2008.06.008
6. Ivanitskiy G. M., Logvinenko A. I., Tkachev V. A. K voprosu rascheta temperatury gazanadduva v bakakh raket / Systemne proektuvannya aerokosmichnoi techniki. 2001. T. III. P. 44-47.
7. Pat. 72330 Ukraina, MPK (2006) F02K 9/44 (2006.1), F02K 11/00, В64Д 37/00. Sposib vyroblennya zalyshku palyva v rushiniy ustanovtsi riddinoi rakety/ Ivanitskiy G. M., Kubanov S. M., Logvinenko A. I., Yushin G. I.; zayavnil I vlasnyk DP KB “Pivdenne”. №20021210267; zayvl. 18.12.2002; opubl. 15.02.2005, Bul. №2/2005.
8. Voloshin M. L., Kuda S. A., Mikhalchishin R. V. Complex meropriyatiy po povysheniyu energeticheskykh kharakteristic RN// Kosmicheskaya technika. Raketnoye vooruzhenie: Sb. nauch.-techn. st. Dnepr: GP KB «Yuzhnoye». 2017. Vyp. 2. P. 29-34.

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]]> 14.1.2019 Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins https://journal.yuzhnoye.com/content_2019_1-en/annot_14_1_2019-en/ Wed, 24 May 2023 16:00:23 +0000 https://journal.yuzhnoye.com/?page_id=27719
Strength properties of the material should be reduced to test conditions in terms of temperature, pressure, rate of loading, degrees of material aging etc. Methodology provides the estimation of safety margins in all phases of storage and operation of the device, consideration of the impact of the active factors (mass, temperature, loading, process of material aging), performance of calculations for the chosen specific zones of the device.
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14. Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Ushkin M. P.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 95-101

DOI: https://doi.org/10.33136/stma2019.01.096

Language: Russian

Annotation: Service life (resource) of the device (system, structure, material) is one of the major factors, which defines the reliable performance of the device or necessity of its replacement. The purpose of this paper is to develop the engineering methodology to estimate the service life of the device to support the well-founded design decision-making. The methodology of estimation of the service life of material or structure is based on the generalization of great amount of Yuzhnoye SDO experimental data and theoretical research on the impact of various factors (properties of materials, loads, storage and operation conditions) on their service life on the ground of strength analysis. At the same time, service life definition is based on the results of stress and deformation analyses and their comparison with strength properties of the applied material (tensile strength and deformation properties). Strength properties of the material should be reduced to test conditions in terms of temperature, pressure, rate of loading, degrees of material aging etc. Methodology provides the estimation of safety margins in all phases of storage and operation of the device, consideration of the impact of the active factors (mass, temperature, loading, process of material aging), performance of calculations for the chosen specific zones of the device. It is shown that the service life estimation is in general case a probabilistic observation because of the random combination of the influencing factors (strength properties, storage and operation conditions, loads). Analysis of experimental and computation data as applied to solid-propellant rocket engine shows that the most dangerous zones, which define the service life, are the fuel charge channel (deformations at launch), a fuel-body coupling zone (breakaway coupling stress) and a “lock” zone of the release collar (concentration of shear and breakaway stresses and deformations). Developed methodological guidelines of the engineering estimate of the service life can be used as the computational basis for the service life of materials and structures in the phase of system design and updating of the assumed design solutions.

Key words: stress, deformation, service life, aging, load

Bibliography:

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