Search Results for “reduced mass” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 12:35:08 +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 “reduced mass” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 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

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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10.2.2019 Dynamic performance of the gas drive with jet motor
10.2.2019 Dynamic performance of the gas drive with jet motor
10.2.2019 Dynamic performance of the gas drive with jet motor

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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

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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7.1.2019 Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants
7.1.2019 Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants
7.1.2019 Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants

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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

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:

1. Lyashevskiy A. V., Mironov Ye. A., Vedernikov M. V. Prognozirovanie srokov prigodnosti tverdykh raketnykh topliv metodom Roentgen-computrnoy tomografii// Aviatsionnaya i raketno-kosmichaskaya technika. №2. 2015. P. 118-123.
2. Schubert H., Menke K. Service Life Determination of Rocket Motors by Comprehensive Property Analysis of Propellant Grain / Athens, Greece, May, 1996, Simposium. №41 P. 1-10.
3. Hufferd W. L. Service Life Assessment for Space Launch Vehicles / Athens, Greece, May, 1996, Simposium. №46. P. 1-9.
4. Faulkner G. S., Tod D. Service Life Prediction Methodologies Aspects of the TTCP KTA-14 UK Programme / Athens, Greece, May, 1996, Simposium. – №24. P. 1-13.
5. Francis E. C. (England), Busswell H. J. Improvements in Rocket Motor Service Life Prediction / Athens, Greece, May, 1996, Simposium. №27. P. 1-13.
6. Collingwood G. A., Dixon M. D., Clark L. M., Becker E. B. Solid Rocket Motor Service Life Prediction Using Nonlinear Viscoelastic Analysis and Probabilistic Approach / Athens, Greece, May, 1996, Simposium. №29. P. 1-8.
7. Zharkov A. S., Anisimov I. I., Maryash V. I. Physiko-chimichaskie process v izdeliyakh iz vysokoenergetycheskykh kondensirovannykh materialov pri dlitelnoy ekspluatatsii/ Physicheskaya mezomechanika. №9/4. 2006. P. 93-106.
8. Gul’ V. Ye. Struktura i prochnost’ polymerov. M.: Chimia, 1971. P. 10-23, 189-209.
9. Pavlov P. A. Osnovy engeneernykh raschetov elementov machin na ustalostnuyu i dlitelnuyu prochnost’. L.: Mashinostroenie, 1988. P. 65-70.
10. Ushkin N. P. Sposoby proektnoy otsenki resursa RDTT i obespechaniya ego dlitelnoy ekspluatatsii/ Kosmicheskaya technika. Raketnoye vooruzhenie: Sb. nauch.- techn. st. 2016. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 110-116.

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14.1.2019 Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins
14.1.2019 Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins
14.1.2019 Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins

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