Search Results for “lifetime” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 12:52:05 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “lifetime” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel https://journal.yuzhnoye.com/content_2019_2-en/annot_9_2_2019-en/ Tue, 03 Oct 2023 11:48:27 +0000 https://journal.yuzhnoye.com/?page_id=27211
The boundaries of the region of equal velocities, within which the condition of quasistatic supersonic flow is satisfied, and the lifetime of the operating mode for the selected nozzle type were determined.
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9. Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

Authors:

Sirenko V. M., Zhivotov O. Yu.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 63-70

DOI: https://doi.org/10.33136/stma2019.02.063

Language: Russian

Annotation: A promising experimental bench – a shock wind tunnel was put into operation at Yuzhnoye SDO. The shock wind tunnel is designed to simulate the incident flow during rocket flight at high supersonic and hypersonic velocities. To solve actual design problems facing Yuzhnoye SDO, it was necessary to expand the range of velocities under investigation in a shock wind tunnel by low supersonic Mach numbers (Mа=1.5; 2; 3). As a result of this work, a modernized configuration of the shock wind tunnel was developed, which allows simulating flow parameters at low supersonic velocities. The results of aerodynamic experiment performed in the modernized shock wind tunnel, which are close to full scale ones, can be obtained using as much data on peculiarities of supersonic flow formation in it as possible. Therefore, the study of the distribution of Mach numbers profiles in the working section of the modernized shock wind tunnel at low and high supersonic velocity was chosen as the main line of research. The results of the research presented in the article are based on the use of numerical simulation methods, as well as data obtained experimentally. As a result of gasdynamic simulation of a supersonic flow conducted for the nozzle Mа=4 and the nozzle Mа=2, the calculated and experimental data on the distribution pattern and field values of Mach numbers in the working section of the tunnel were obtained. A comparative analysis was carried out. The boundaries of the region of equal velocities, within which the condition of quasistatic supersonic flow is satisfied, and the lifetime of the operating mode for the selected nozzle type were determined. At the flow from the nozzle Mа=2, a peculiarity was revealed in the distribution pattern of Mach numbers fields associated with the appearance of “blocking” effect of the supersonic flow. The methods for eliminating the effect of flow “blocking” at low supersonic velocities are proposed.

Key words: incident flow modeling, velocity fields in the wind tunnel working section, aerodynamic experiment

Bibliography:
1. Zvegintsev V. I. Gasodynamicheskie ustanovki kratkovremennogo deistviya. V dvuh chastyakh. Ch. 1. Ustanovki dlya nauchnykh issledovaniy. Novosibirsk, 2014. 551 s.
2. Computerno-vymiryuvalni tekhnologii kontrolu ta upravlinnya raketno-kosmichnoi techniki / monogr. pid zagal. red. prof. V. P. Malaichuka. Dnipro, 2018. 344 s.
3. «Sirius-18». Systema izmereniya i upravleniya impulsnoi aerodynamicheskoi truboi. Rukovodstvo po ekspluatatsii. ELVA4.044.901 RE. 2018. 45 s.
4. Abramovich G.N. Prikladnaya gazovaya dynamika. M., 1978. 888 s.
5. Raschet vnutrennego davlenia v otsekakh RN. YSF YZH UMN 041 01. Rukovodstvo operatora. 2016. 138 s.
6. Issledovania characteristic hyperzvukovoi aerodynamicheskoi truby AT-303. Ch. 1. Polya skorostey / A. M. Kharitonov at al. Teplophysika i aeromekhanika. 2006. T. 13, № 1. S. 1–17.

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9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel
9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel
9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

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]]> 5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep https://journal.yuzhnoye.com/content_2020_1-en/annot_5_1_2020-en/ Wed, 13 Sep 2023 06:15:53 +0000 https://journal.yuzhnoye.com/?page_id=31026
The problems of determining the lifetime of space launch vehicles and launching facilities should be noted separately, as it is connected with damages that arise at alternating-sign thermomechanical loads of high intensity. The main approach in lifetime determination is one that is based on the theory of low-cycle and high-cycle fatigue. Plasticity and creeping of material are the fundamental factors in lifetime substantiation. Key words: shell structures , stress and strain state , structural and technological inhomogeneity , thermomechanical loads , low-cycle and high-cycle fatigue , lifetime Bibliography: 1. shell structures , stress and strain state , structural and technological inhomogeneity , thermomechanical loads , low-cycle and high-cycle fatigue , lifetime .
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5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

Authors:

Hudramovych V. S.2, Sirenko V. M.1, Klimenko D. V.1, Hart Ye. L.3

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2; Oles Honchar Dnipro National University, Dnipro, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2020, (1); 44-56

DOI: https://doi.org/10.33136/stma2020.01.044

Language: Russian

Annotation: The shell structures widely used in space rocket hardware feature, along with decided advantage in the form of optimal combination of mass and strength, inhomogeneities of different nature: structural (different thicknesses, availability of reinforcements, cuts-holes et al.) and technological (presence of defects arising in manufacturing process or during storage, transportation and unforseen thermomechanical effects). The above factors are concentrators of stress and strain state and can lead to early destruction of structural elements. Their different parts are deformed according to their program and are characterized by different levels of stress and strain state. Taking into consideration plasticity and creeping of material, to determine stress and strain state, the approach is effective where the calculation is divided into phases; in each phase the parameters are entered that characterize the deformations of plasticity and creeping: additional loads in the equations of equilibrium or in boundary conditions, additional deformations or variable parameters of elasticity (elasticity modulus and Poisson ratio). Then the schemes of successive approximations are constructed: in each phase, the problem of elasticity theory is solved with entering of the above parameters. The problems of determining the lifetime of space launch vehicles and launching facilities should be noted separately, as it is connected with damages that arise at alternating-sign thermomechanical loads of high intensity. The main approach in lifetime determination is one that is based on the theory of low-cycle and high-cycle fatigue. Plasticity and creeping of material are the fundamental factors in lifetime substantiation. The article deals with various aspects of solving the problem of strength and stability of space rocket objects with consideration for the impact of plasticity and creeping deformations.

Key words: shell structures, stress and strain state, structural and technological inhomogeneity, thermomechanical loads, low-cycle and high-cycle fatigue, lifetime

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5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep
5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep
5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep

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]]> 4.2.2018 Turbopump Units of Rocket Engines Developed by DO-4 https://journal.yuzhnoye.com/content_2018_2-en/annot_4_2_2018-en/ Thu, 07 Sep 2023 10:54:18 +0000 https://journal.yuzhnoye.com/?page_id=30735
The design evolution allowed increasing the unit’s lifetime dozens times. For example, the lifetime of the first turbopump units developed by DO did not exceed 150 s. Currently, the DO has in stock the engines with lifetime of ~19000 s.
]]>

4. Turbopump Units of Rocket Engines Developed by DO-4

Authors:

Ivanov Y. N., Badun O. P., Deshevykh S. O., Ivchenko L. F.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 25-33

DOI: https://doi.org/10.33136/stma2018.02.025

Language: Russian

Annotation: The article presents the experience of creating LRE turbopump units by the Rocket Engines Design Office (DO-4) at Yuzhnoye SDO. The best known turbopump units designs developed by DO are described. Both earlier developments of DO and the turbopump unit being now in final testing phase are considered. The design evolution of both separate assemblies and of entire unit is shown. The design evolution allowed increasing the unit’s lifetime dozens times. For example, the lifetime of the first turbopump units developed by DO did not exceed 150 s. Currently, the DO has in stock the engines with lifetime of ~19000 s. The information is presented on the problems that the designers faced in testing the turbopumop unit and the ways to solve them. The unique achievement are presented. At present, there are no analogs of some units in the world. The article presents the information on the latest achievements of DO, such as the face seal on pump vane discs whose use fully excludes unwanted leaks. Having analyzed the data presented, one may conclude that the Rocket Engines Design Office and Yuzhnoye SDO as a whole accumulated sufficient experience and knowledge allowing solving any problems that may arise when developing a new LRE turbopump unit, and successfully operating LRE with turbopump units, including those in the engines with generator gas afterburning created in recent years testify to a great value of accumulated experience.

Key words: liquid rocket engine, turbopump unit, pump, turbine

Bibliography:
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4. End Seal of High-Speed Shaft: Patent 48248, Ukraine: MPK F16J15/54, F04D29/10 / Ivanov Y. N., Steblovtsev A. A., Gameberger Y. A., Peredarenko V. M.; Applicant and patent holder Yuzhnoye State Design Office. No. 99031442; claimed 16.03.1999, published 15.08.2002.
5. Centrifugal Pump. Patent 84023, Ukraine: MPK F04D1/00 / Ivanov Y. N., Ivchenko L. F., Deshevykh S. A., Dan’kevich D. S.; Applicant and patent holder Yuzhnoye State Design Office. No. а200601399; claimed 13.02.2006, published 10.09.2008.

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Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems Authors: Zemlyanoy K. (2018) "Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems" Космическая техника. "Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems" Космическая техника. quot;Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems", Космическая техника. Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems Автори: Zemlyanoy K. Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems Автори: Zemlyanoy K. Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems Автори: Zemlyanoy K.
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11. Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems

Authors:

Zemlyanoy K. M.1, Reva V. S.1, Frolov V. P.1, Bezruchko K. V.2, Kharchenko А. А.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Kharkiv Aviation Institute, Kharkiv, Ukraine2 .

Page: Kosm. teh. Raket. vooruž. 2018 (1); 63-68

DOI: https://doi.org/10.33136/stma2018.01.063

Language: Russian

Annotation: Several measures to ensure long service life of electrochemical batteries are proposed: electrochemical battery performance evaluation, study of theoretical basis for improvement and building of experimental bench equipment.

Key words:

Bibliography:
1. Davidov А. О. Development of Technique of Alkaline Nickel-Cadmium Accumulators Recovery to Prolong their Service Life. Aerospace Hardware and Technology. 2009. No. 8 (65). P. 132-137.
2. Bezruchko K. V., Vasilenko A. S., Davidov A. О., Kharchenko А. А. Recovery of Open-Type Nickel-Cadmium Accumulators Capacity by Acting on Active Mass of Oxide-Nickel Electrode. Problems and Chemistry and Chemical Technology. 2002. No. 2. P. 66-70.
3. Azarnov A. L. et al. Express-Diagnostics Technique for Electrochemical Accumulators. The ХII International Scientific-Practical Youth Conference “Man and Space”: Collection of abstracts. Dnepropetrovsk, 2010. P. 78.
4. Bezruchko K. V., Davidov A. O. Express-Diagnostics Method for Electrochemical Energy Storage Units of Space Rocketry Power Systems. Space Technologies: Present and Future: The III International Conference: Collection of Abstracts (Dnepropetrovsk, 20-22 April, 2011). Dnepropetrovsk, 2011. P. 5-6.
5. Bezruchko K. V., Davidov A. O., Sinchenko S. V. Pulse Diagnostics Method for Nickel-Cadmium Accumulators. The V Scientific–Technical Conference “Present-Day Problems of Space Rocketry and Space Technologies”: Collection of abstracts. Kharkiv, 2010. P. 13.
6. Bezruchko K. V., Davidov A. O., Katorgina J. G., Sinchenko S. V., Shirinsky S. V. Method of Predicting the Performance of Electrochemical Batteries Working during Long Time in Space Rocketry Power Systems. Electrical and Electronic Engineering. 2013. Vol. 3 (3). P. 81-85.
7. Bezruchko K. V. et al. Development and Approbation of Mathematical Model to Predict the Characteristics of Electrochemical Accumulators of Space Rocketry Power Systems. MAI News. 2013, Vol. 20, No. 1. P. 38-49.

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11.1.2018 Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems
11.1.2018 Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems
11.1.2018 Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems
]]> 6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability https://journal.yuzhnoye.com/content_2017_2/annot_6_2_2017-en/ Tue, 08 Aug 2023 12:39:31 +0000 https://journal.yuzhnoye.com/?page_id=29754
2017 (2); 29-34 Language: Russian Annotation: The paper presents a complex of analytical calculation measures that allow increasing tanks useful volume and ensure engines’ additional operational lifetime by the example of a launch vehicle, one of Yuzhnoye SDO developments.
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6. Set of Actions on Enhancement of Launch Vehicle Payload Capability

Authors:

Voloshin M. L., Kuda S. А., Mikhalchishin R. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 29-34

Language: Russian

Annotation: The paper presents a complex of analytical calculation measures that allow increasing tanks useful volume and ensure engines’ additional operational lifetime by the example of a launch vehicle, one of Yuzhnoye SDO developments. The calculated-experimental confirmation is set forth of the operability of pneumohydraulic supply system in the changed conditions that ensure considerable increase of launch vehicle power and mass characteristics.

Key words:

Bibliography:
1. Logvinenko A. I. Development Prospects of Modern LV Pneumohydraulic Systems. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2014. Issue 1. Dnepropetrovsk.
2. Increasing Dnepr LV 1 and 2 Stages Propellant Filling Doses due to Decrease of their Temperature, Initial Gas Volumes in Tanks and Change of Filling Technology: Technical Report 21.16850.123 ОТ / Yuzhnoye SDO. 54 p.
3. Determination of 2 Stage PHSS Operability Limits at Increased RE Autonomous Operation Mode Time (after ME Shutdown): Technical Report 21.16234.123 ОТ / Yuzhnoye SDO. 75 p.
4. Ostoslavsky I. V. Flight Dynamics. Flying Vehicles Trajectories / I. V. Ostoslavsky, I. V. Strazheva. М., 1969. 499 p.

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6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability
6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability
6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability
]]> 5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime https://journal.yuzhnoye.com/content_2019_1-en/annot_5_1_2019-en/ Thu, 25 May 2023 12:09:25 +0000 https://journal.yuzhnoye.com/?page_id=27710
Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime Authors: Hudramovych V. (2019) "Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime" Космическая техника. "Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime" Космическая техника. quot;Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime", Космическая техника. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime Автори: Hudramovych V. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime Автори: Hudramovych V. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime Автори: Hudramovych V.
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5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

Authors:

Hudramovych V. S.1, Sirenko V. M.2, Klimenko D. V.2, Daniyev Y. F.1, Hart Ye. L.3

Organization:

The Institute of Technical Mechanics, Dnipro, Ukraine1; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine2; Oles Honchar Dnipro National University, Dnipro, Ukraine3

Page: Kosm. teh. Raket. vooruž. 2019, (1); 28-37

DOI: https://doi.org/10.33136/stma2019.01.028

Language: Russian

Annotation: This article contains results of methodology and standards development for life prediction of launch site structures to launch various types’ launch vehicles into near-earth orbit. Launch sites have been built in various countries of the world (European Union, India, China, Korea, Russia, USA, Ukraine, France, Japan, etc.). In different countries they have their own characteristics, depending on the type and performance of the launch vehicles, infrastructure features (geography of the site, nomenclature of the space objects, development level of rocket and space technology), problems that are solved during launches, etc. Solution of various issues, arising in the process of development of the standards for justification of launch site life is associated with the requirement to consider complex problems of strength and life of nonuniform structural elements of launch sites and structures of rocket and space technology. Launch sites are the combination of technologically and functionally interconnected mobile and fixed hardware, controls and facilities, designed to support and carry out all types of operations with integrated launch vehicles. Launch pad, consisting of the support frame, flue duct lining and embedded elements for frame mounting, is one of the principal components of the launcher and to a large extent defines the life of the launch site. Main achievements of Ukrainian scientists in the field of strength and life are specified, taking into account the specifics of various branches of technology. It is noted that the physical nonlinearity of the material and statistical approaches determine the strength analysis of useful life. Main methodological steps of launch site structures life prediction are defined. Service limit of launch site is suggested to be the critical time or the number of cycles (launches) over this period, after which the specified limiting states are achieved in the dangerous areas of the load-bearing elements: critical cracks, destruction, formation of unacceptable plastic deformations, buckling failure, corrosion propagation, etc. Classification of loads acting on the launch sites is given. The useful life of launch site is associated with estimation of the number of launches. Concept of low and multiple-cycle fatigue is used. Developing strength standards and useful life calculation basis, it is advisable to use modern methods of engineering diagnostics, in particular, holographic interferometry and acoustic emission, and to develop the high-speed circuits of numerical procedures for on-line calculations when testing the designed systems.

Key words: classification of loads and failures; shock wave, acoustic and thermal loads; low-cycle fatigue; hierarchical approach in classification; projection-iterative schemes of numerical procedur

Bibliography:

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3. Prochnost’ materialov I konstruktsiy / Pod obsch. red. acad. NANU V. T. Troschenko. K.: Academperiodika, 2005.1088 p.
4. Bigus G. A. Technicheskaya diagnostica opasnykh proizvodstvennykh obiektov/ G. A. Bigus, Yu. F. Daniev. М.: Nauka, 2010. 415 p.
5. Bigus G. A., Daniev Yu. F., Bystrova N. A., Galkin D. I. Osnovy diagnostiki technicheskykh ustroistv I sooruzheniy. M.: Izdatelstvo MVTU, 2018. 445 p.
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10. Hudramovich V. S., Pereverzev Ye. S. Nesuschaya sposobnost’ sposobnost’ i dolgovechnost’ elementov konstruktsiy. K.: Nauk. dumka, 1981. 284 p.
11. Hudramovich V. S., SIrenko V. N., Klimenko D. V., Daniev Yu. F. Stvorennya metodologii nornativnykh osnov rozrakhunku resursu konstruktsii startovykh sporud ksomichnykh raket-nosiiv / Teoria ta practika ratsionalnogo proektuvannya, vygotovlennya i ekspluatatsii machinobudivnykh konstruktsiy: materialy 6-oy Mizhnar. nauk.-techn. conf. (Lvyv, 2018). Lvyv: Kinpatri LTD, 2018. P. 5–7.
12. Hudramovich V. S., Skalskiy V. R., Selivanov Yu. M. Golografichne ta akustico-emissine diagnostuvannya neodnoridnykh konstruktsiy i materialiv: monografia/Za red. akad. NANU Z. T. Nazarchuka. Lvyv: Prostir-M, 2017. 492 p.
13. Daniev Y. F. Kosmicheskie letatelnye apparaty. Vvedenie v kosmicheskuyu techniku/ Pod obsch. red. A. N. Petrenko. Dnepropetrovsk: ArtPress, 2007. 456 p.
14. O klassifikatsii startovogo oborudovania raketno-kosmicheskykh kompleksov pri obosnovanii norm prochnosti/ A. V. Degtyarev, O. V. Pilipenko, V.S. Hudramovich, V. N. Sirenko, Yu. F. Daniev, D. V. Klimenko, V. P. Poshivalov// Kosmichna nauka i technologia. 2016. T. 22, №1. P. 3–13. https://doi.org/10.15407/knit2016.01.003
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5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

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]]> 18.1.2016 Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation https://journal.yuzhnoye.com/content_2016_1/annot_18_1_2016-en/ Tue, 23 May 2023 13:14:12 +0000 https://journal.yuzhnoye.com/?page_id=27637
Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation Authors: Ushkin M. (2016) "Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation" Космическая техника. "Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation" Космическая техника. quot;Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation", Космическая техника. Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation Автори: Ushkin M. Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation Автори: Ushkin M. Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation Автори: Ushkin M. Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation Автори: Ushkin M.
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18. Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation

Authors:

Ushkin M. P.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 110-116

Language: Russian

Annotation: Based on generalization and analysis of Yuzhnoye SDO’s extensive experience of developing the SRM of various types, the dependences of their service life on main operative factors are determined. The techniques of engineering evaluation of operability margin of newly developed SRM are considered based on the methods of taking into account the breaking stresses and accumulation of damages (breaking deformations). An algorithm of engineering evaluation of SRM service life is proposed and the recommendations were elaborated to ensure long operation of the motors.

Key words:

Bibliography:

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18.1.2016 Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation
18.1.2016 Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation
18.1.2016 Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation
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