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P., Selivanov Yu. R., Selivanov Yu.
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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
Turbopump Units of Rocket Engines Developed by DO-4 Authors: Ivanov Y. Centrifugal Pump: Patent 1021816 А, USSR: MPK 7F04D1/00, 7F04D29/04 / Ivanov Y. Content 2018 (2) Downloads: 38 Abstract views: 466 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Ashburn; San Antonio; Matawan; Baltimore; Plano; Columbus; Phoenix; Monroe; Ashburn; Seattle; Ashburn; Seattle; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn 23 Singapore Singapore; Singapore; Singapore; Singapore; Singapore 5 Unknown Hong Kong; 2 Finland Helsinki 1 The Republic of Korea Daejeon 1 Canada Monreale 1 Germany 1 Latvia Riga 1 Romania Voluntari 1 Netherlands Amsterdam 1 Ukraine Dnipro 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Ivanov Y.
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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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]]> 15.1.2018 The Results of Using Automated Methods to Solve Standardization Tasks in Yuzhnoye SDO Practice https://journal.yuzhnoye.com/content_2018_1-en/annot_15_1_2018-en/ Tue, 05 Sep 2023 07:04:10 +0000 https://journal.yuzhnoye.com/?page_id=30474
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15. The Results of Using Automated Methods to Solve Standardization Tasks in Yuzhnoye SDO Practice

Authors:

Shipko O. F., Matus G. V., Il’ina S. M., Fesenko E. Y.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 91-100

DOI: https://doi.org/10.33136/stma2018.01.091

Language: Russian

Annotation: The article presents the main results obtained when solving the standardization tasks in Yuzhnoye SDO practice. The specific ways are presented of reducing the periods of work performance and increasing the accuracy of results due to the use of automated methods. The article also presents the recommendations in respect of sequence and methods of creating the standard data arrays, which allows optimizing the work process performance.

Key words:

Bibliography:
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15.1.2018 The Results of Using Automated Methods to Solve Standardization Tasks in Yuzhnoye SDO Practice
15.1.2018 The Results of Using Automated Methods to Solve Standardization Tasks in Yuzhnoye SDO Practice
15.1.2018 The Results of Using Automated Methods to Solve Standardization Tasks in Yuzhnoye SDO Practice
]]> 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
R., Selivanov Yu.
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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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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.
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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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Analysis of Spacecraft Control Issues In Early Design Phases Authors: Ivanova G. Content 2019 (1) Downloads: 42 Abstract views: 505 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Columbus; Matawan; Baltimore; Redmond; Plano; Columbus; Monroe; Ashburn; Ashburn; Seattle; Tappahannock; Portland;; San Mateo; Boydton; Boydton; Boydton; Boydton; Boydton; Boydton; Des Moines; Boardman; Boardman; Ashburn 25 Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore 8 Romania ; Voluntari 2 Belgium Brussels 1 Unknown Sidney 1 Finland Helsinki 1 France 1 Canada Monreale 1 Netherlands Amsterdam 1 Ukraine Dnipro 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Ivanova G. Analysis of Spacecraft Control Issues In Early Design Phases Автори: Ivanova G.
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3. Analysis of Spacecraft Control Issues In Early Design Phases

Authors:

Ivanova G. A., Khoroshilov V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 15-20

DOI: https://doi.org/10.33136/stma2019.01.015

Language: Russian

Annotation: Mission control of the orbital space plane is one of the actual and complicated applied problems of the theory of mobile objects control. Dynamic configuration of this plane as an object of control is described by the system of non-linear differential equations of higher order. Research of stability of such system is a difficult problem. However, thanks to known theorems of Lyapunov, often stability of the real system can be estimated by the roots of the characteristic equation of the linearized system. Thereupon the stability analysis in the linear setting is the necessary link in the process of orbital space plane control system development. Among the methods of synthesis of the automatic control linear systems developed to date one can emphasize the trend, which has become widely-spread in the engineering area. According to this trend the issues of synthesis of the dynamic regulator, observability and controllability for the orbital space plane are considered. Procedure of selection of the dynamic regulator parameters at the early phase of development of the control system for the orbital space plane motion about the center of mass is suggested. Observability and controllability of the orbital space plane are considered. It is shown that the considered control system of the orbital space plane is observable and controllable, i.e. it is possible to develop the stable dynamic regulator, which provides the required speed and accuracy of the angular position of the orbital space plane during the orbital flight. Factors selection procedure is offered for the factors being the part of the control laws for the control system actuators.

Key words: vector, matrix, dynamic regulator, observability, controllability, stability

Bibliography:

1. Isenberg Ya. Ye., Sukhorebriy V. G. Proektirovanie sistem stabilizatsii nositeley kosmicheskikh apparatov. M.: Mashinostroenie, 1986. 220 p.
2. Kuzovkov N. T. Modalnoe upravlenie i nabludauschie ustroistva. M.: Mashinostroenie, 1976. 184 p.
3. Krasovskiy N. N. Teoria upravlenia dvizheniem. M.: Nauka, 1968. 475 p.
4. Larson Wiley J. and Wertz James R. (editors). Space mission analysis and design. Published Jointly by Microcosm, Inc. (Torrance, California) Kluwer Academic Publishers (Dordrecht / Boston / London), 1992. 865 p.
5. Sidi Marcel J. Spececraft Dynamics and Control. A Practical Engineering Approach. Israel Aircraft Industries Ltd. and Tel Aviv University. Cambridge University press, 1997. 409 p.

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]]> 24.1.2019 Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware https://journal.yuzhnoye.com/content_2019_1-en/annot_24_1_2019-en/ Wed, 24 May 2023 16:01:02 +0000 https://journal.yuzhnoye.com/?page_id=27729
Porous Cast Materials (Gasars). , Ivanov A. To obtain various structures, along with directed crystallization process, the pressure in crystallization chamber is an important factor, which drives the gasar morphology. Subsequent processing of the gasars does not differ from analogous non-porous materials, which is also an advantage over conventional porous materials. At present, the gasars have already found application as light and strong structural materials, filters, heat exchangers, dampers, slide bearings, catalyst elements, friction materials, etc. O., Ivanov A. (2019) "Porous Cast Materials (Gasars). O., Ivanov A. O., Ivanov A. O., Ivanov A. O., Ivanov A. Space technology. O., Ivanov A. Space technology.
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24. Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware

Authors:

Naiden O. O., Ivanov A. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 163-170

DOI: https://doi.org/10.33136/stma2019.01.163

Language: Russian

Annotation: Gasars is a new type of porous cast materials manufactured on the basis of metals and their alloys, some types of ceramics. The basis of the process is gas-eutectic conversion in the system metal-hydrogen. The process of investigation and creation of gasars was commenced in 1979 in the National Metallurgical Academy of Ukraine and is currently continued in Ukraine, the USA, China, Japan, South Korea, Poland and others. The gasars production technological process consists in melting the specified material (metal, alloy, ceramics) in hydrogen (or other active gas) atmosphere at a certain pressure. After the melt is saturated with active gas to a certain concentration, the crystallization process begins at which the pore formation process is launched. As the pores growth occurs perpendicular to crystallization front, the orientation of heat withdrawal influences pores location. So, for example, to obtain radial porosity, radial heat withdrawal is required. To obtain various structures, along with directed crystallization process, the pressure in crystallization chamber is an important factor, which drives the gasar morphology. The porous structure of gasars is diverse, there are the gasars with longitudinal, cylindrical, spherical, conical pores. It is possible to alternate the porosity layers and monolithic metal layers. The dimensions of gasars pores are in the limits from 10 μm to 10 mm at total porosity from 7 to 55 (75%). However, there is a possibility to obtain the pores with smaller diameter. The mechanical properties of gasars have a number of advantages as compared with conventional porous materials produced by different methods. Subsequent processing of the gasars does not differ from analogous non-porous materials, which is also an advantage over conventional porous materials. And in case when the diameter of pores is less than 50 μm, the exceedance of mechanical properties of gasars as compared with monolithic materials of the same chemical composition is observed. This is caused by the fact that the pores were formed during crystallization and at the action of pressure on a gasar, local hardening occurs. At present, the gasars have already found application as light and strong structural materials, filters, heat exchangers, dampers, slide bearings, catalyst elements, friction materials, etc. The use of gasars in space hardware will help to considerably reduce the mass of launch vehicle structural elements without worsening strength properties. The possibility of welding and soldering the gasars allows finding their application in the structure of propellant systems, compressed gas and propellants supply systems, creating filtering elements based on the gasars, including propellant spraying and mixing systems.

Key words: gasars, gas-eutectic conversion, eutectics, porosity

Bibliography:
1. Shapovalov V. I. Legirovanie vodorodom. D.: Zhurfond, 2013. 385 p.
2. Shapovalov V. TERMEC 2006 // International Conference on Processing and Manufacturing of Advanced Materials, July 4–8, 2006, Vancouver, Canada. Р. 529.
3. Komissarchuk Olga, Xu Zhengbin, Hao Hai, Zhang Xinglu, Karpov V. Pore structure and mechanical properties of directionally solidified porous aluminum alloys / Research & Development. Vol. 11, No.1, January 2014.
4. Karpov V. V., Karpov V. Yu. Vliyanie poristosti na teploprovodnost’ gazov/ Teoriya I praktica metallurgii. 2003. № 4.

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24.1.2019 Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware
24.1.2019 Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware
24.1.2019 Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware

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]]> 4.1.2023 On control of spacecraft orientation to the ground data acquisition station https://journal.yuzhnoye.com/content_2023_1-en/annot_4_1_2023-en/ Fri, 12 May 2023 16:10:38 +0000 https://test8.yuzhnoye.com/?page_id=26988
On control of spacecraft orientation to the ground data acquisition station Authors: Ivanova G. Ivanova G.A., Ostapchuk S.V. Content 2023 (1) Downloads: 28 Abstract views: 348 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Boardman; Matawan; Monroe; Ashburn; Seattle; Seattle; Ashburn; Boardman; Mountain View; Tappahannock; Portland; San Mateo; Des Moines; Boardman; Boardman; Ashburn 16 Singapore Singapore; Singapore; Singapore; Singapore; Singapore 5 Ukraine Dnipro; Dnipro 2 Finland Helsinki 1 Mongolia 1 Canada Monreale 1 Romania Voluntari 1 Netherlands Amsterdam 1 Downloads, views for all articles Articles, downloads, views by all authors Articles for all companies Geography of downloads articles Ivanova G. On control of spacecraft orientation to the ground data acquisition station Автори: Ivanova G. On control of spacecraft orientation to the ground data acquisition station Автори: Ivanova G.
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4. On control of spacecraft orientation to the ground data acquisition station

Authors:

Ivanova G. A., Khoroshilov V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 41-47

DOI: https://doi.org/10.33136/stma2023.01.041

Language: English

Annotation: The article dwells on the spacecraft attitude control to point the onboard antenna to the ground data acquisition station during the communication session. Antenna is fixed relative to the spacecraft body. Pur-pose of the antenna is to receive the flight task aboard the spacecraft and to downlink the telemetry infor-mation. When orbiting, the spacecraft position relative to the ground data acquisition station changes contin-uously. It is due to the diurnal rotation of the Earth, spacecraft orbital motion and angular motion of the spacecraft relative to the center of mass under the impact of the disturbing and control moments. To tilt the spacecraft uses reaction wheels, installed in axes of coordinate system coupled with spacecraft center of mass. Electromagnets are used to unload the reaction wheels. The reaction wheels control law is suggested, which tilts the spacecraft to point the antenna to the ground data acquisition station. Mathematical model of the spacecraft dynamics relative to center of mass is given, using the suggested reaction wheels control law. The following external disturbing moments, acting on the spacecraft in flight, are taken into consideration: gravitational, magnetic, aerodynamic moments and solar radiation moment of forces. Dipole model of the magnetic field of the Earth is used to calculate the magnetic moments. Software was developed and space-craft dynamics was simulated on the personal computer with the specified initial data. Simulation initial con-ditions correspond to the attitude control mode of the spacecraft relative to the orbital coordinate system with the specified accuracy. Simulation results verify the applicability of the suggested reaction wheel control law.

Key words: electrical axis of the antenna, mathematical model, coordinate system, transformation matrix, vector

Bibliography:

1. Ivanova G.A., Ostapchuk S.V. Matematich-eskaya model magnitno-gravitatsionnoy sys-temy orientatsii dlya eksperimentalnogo mi-crosputnika. Kosmicheskaya technika. Raketnoye vooruzhennie: Nauch.-techn. sb. 2009. S. 192 -202.
2. Branets V.N., Shmyglevskiy I.P. Primenenie quoternionov v zadachah orientatsii tverdogo tela. M.: Nauka, 1973. 320 s.
3. Problemy orientatsii iskusstvennyh sputnikov Zemli. M.: Nauka, 1966. 350 s.

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]]> 1.1.2023 On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism https://journal.yuzhnoye.com/content_2023_1-en/annot_1_1_2023-en/ Thu, 11 May 2023 15:25:30 +0000 https://test8.yuzhnoye.com/?page_id=26682
Based on this, as well as taking into account the sharp increase in the cost of weaponry, the considered problem is classified as an optimization one that should be solved through the theory of operations research. Katasonov Yu.  Razvitie matemaicheskogo modelirovaniya boevyh deistviy v armii SShA.  Issledovanie operatsiy v voennom dele. K voprosu metodologii matematicheskogo modelirovaniya operatsii.  I., Ivanov V.  Nekotoye voprosy otsenki sootnosheniya sil i sredstv v operatsii.  O metodike rascheta sootnosheniya sil v operatsii.  Metod boevyh potentsialov. Istoria i nastoyaschee.  S., Gorchitsa G.  44-48 Ostankov V.  Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
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1. On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism

Authors:

Perkov V. M., Herasimov A. P., Degtyarev O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 3-13

DOI: https://doi.org/10.33136/stma2023.01.003

Language: Ukrainian

Annotation: Substantiation of the research tools has been performed as a part of methodology development for the air and missile defense system. The problem under consideration is very complex due to the multifactorial nature of the research object, its qualitative variety and manifold structure, incomplete definition of the problem statement. Furthermore, the ability of modern technologies to produce different arms systems, which are capable of carrying out same class tasks, considerably increases the risk of making not the best decisions. Based on this, as well as taking into account the sharp increase in the cost of weaponry, the considered problem is classified as an optimization one that should be solved through the theory of operations research. In this theory, such task is viewed as a mathematical problem, and mathematical simulation is the basic method of research. The main types of mathematical models, their areas of application have been considered as a part of the analysis. The classification of mathematical models has been indicated according to the scale of reproduced operations, purpose, and goal orientation. Quantitative and qualitative correlation of forces has been accepted as the efficiency criterion, which determines a goal orientation of the model. The problems related to this have been shown. In particular, searching for the compromise between simplicity of the mathematical model and its adequacy to the research object is among these problems. Two of the basic approaches to principles of the military operation model construction and its assessment have been considered. The first is implemented through modeling of the combat operations. The second approach is based on the assumption that different armament types can be compared based on their contribution to the outcome of the operation, and on the possibility to assign «a weighting coefficient» named as a combat potential to each of these types. The modern level of problem solving related to this method has been shown. The reasonability of its application in the considered task, including the definition of forces correlation of the opposing parties, has been substantiated. The basic regulations of the construction concept of the required mathematical model and tools for its research have been formulated based on the analysis results: the assigned problem should be solved by analytical methods through the theory of operations research; the analytical model is the most acceptable conception of the analyzed level of the military operation; the synthesis of the model should be based on the idea of a combat potential. At the same time, it should be taken into account that the known approach to the definition of forces correlation, which uses the combat potential method, has a number of essential limitations, including the methodological ones. Therefore, within the bounds of further research, this approach requires the development both in terms of improving the reliability of the single assessment and in terms of giving the system qualities to the synthesized mathematical model.

Key words: multifunctional system, mathematical model, military unit, combat potential, correlation of forces, defensive sufficiency

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1.1.2023 On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism
1.1.2023 On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism
1.1.2023 On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism

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