Keywords cloud
G., <b>Kushnirb> B.
]]>10. Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2020, (1); 99-106
DOI: https://doi.org/10.33136/stma2020.01.099
Language: Russian
Annotation: The main solid rocket motors of surface-to-air missiles and some short-range missiles have, as a rule, two operation modes – starting (augmented rating) and cruise (with decreased propellant consumption level). The methods to calculate intraballistic characteristics of such motors have a number of peculiarities, which set them apart from the methods of determining the characteristics of motors with constant propellant consumption level. The purpose of this article is to analyze such peculiarities, design methods, to find interrelation between the parameters of propellant consumption diagram, to determine the impact on the latter of motor design features and propellant characteristics. To achieve this goal, the method of analytical dependencies was developed. The equations obtained show that the required parameters of diagrams (including consumption-thrust characteristics difference between the starting and cruise modes) can be ensured due to varying either case diameter or propellant combustion rate or due to combined variation of these values. In practice, the cases are possible when for some reasons it does not seem possible to vary the case diameter or propellant combustion rate and the requirements to consumption diagram cannot be satisfied to the full extent. The task of motor developer in that case consists in determination of acceptable (alternative) propellant consumption diagrams that would be closest to required. The proposed method is based on calculation and construction of nomograms of dependencies of relative propellant consumption in cruse mode on relative time of starting leg at different propellant combustion rates and constant (required) case diameter and vice versa, at different values of case diameter and constant (available) propellant combustion rate. Using these nomograms, the rocket developer can determine the propellant consumption diagram acceptable for the rocket. In a number of cases, design limitations for separate main motor assemblies are imposed on consumption characteristic diagram that have an impact on its required parameters. The presented materials allow evaluating that impact and contain the proposals to remove it. The presented method allows quickly determining the conditions needed to fulfill required propellant combustion products consumption diagrams and in case of nonfulfillment of these conditions – allow presenting alternative options for selection of most acceptable one.
Key words: solid propellant charge mass, propellant combustion rate, combustion chamber pressure, operation time in starting and cruise modes, combustion chamber pressure difference
Bibliography:
1. K vyboru velichiny davliniia v kamere sgoraniia marshevykh RDTT: tekhn. otchet / GP “KB “Yuzhnoye”. Dnipro, 2017. 19 s.
2. Enotov V. G., Kushnir B. I., Pustovgarova Е. V. Avtomatizirovannaia proektnaia otsenka kharakteristik marshevykh dvigatelei na tverdom toplive s korpusom iz vysokoprochnykh metallicheskikh materialov takticheskikh i operativno-takticheskikh raket: ucheb.-metod. posobie / pod red. А. S. Kirichenko. Dnepropetrovsk, 2014. 72 s.
3. Sorkin R. Е. Gasotermodinamika raketnykh dvigatelei na tverdom toplive. М, 1967. 368 s.
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Key words: shell structures , stress and strain state , structural and technological inhomogeneity , thermomechanical loads , low-cycle and high-cycle fatigue , lifetime Bibliography: 1. Plastic buckling. Ustoichivost uprugo-plasticheskikh obolochek / otv. Ob odnom sposobe linearizatsii uravnenii teorii obolochek srednego izgiba. Prochnost i dolgovechnost elementov konstruktsii: sb. Izbrannye Trudy / otv. Ustoichivost i nesushchaia sposobnost plasticheskikh obolochek. Prochnost i dolgovechnost konstruktsii: sb. Budnik. <b>Kushnirb> R. Predelnyi analiz – effektivnyi sposob otsenki konstruktsionnoi prochnosti obolochechnykh system. Budnik. S., Dziuba A.
]]>5. Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep
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
Bibliography:
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Keywords cloud
, <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B.
]]>1. Solid Rocket Motors Developed by DO-5
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 4-12.
Language: Russian
Annotation: The main phases of formation and development of solid motor engineering are presented. The basic technical problems are considered, solution of which allowed building the main motors and dispensing motors with high performance level and highly-effective rocket systems on their basis
Key words:
Bibliography:
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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. 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: 1. <b>Kushnirab>. Bigus G. Technicheskaya diagnostica opasnykh proizvodstvennykh obiektov/ G. Bigus, Yu. Bigus G. M.: Librokom, 2008. posibn.
]]>5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime
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
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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.
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, <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B. S., <b>Kushnirb> B.
]]>2. Experience of Testing SRM Thrust Vector Controls
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2016 (1); 13-18
Language: Russian
Annotation: The design peculiarities and basic characteristics of thrust vector controls of main SRM developed by Yuzhnoye SDO DO-5 beginning from 1966 are presented. The basic design and design-theoretical problems solved during thrust vector controls development are considered.
Key words:
Bibliography:
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, <b>Kushnirb> B. G., <b>Kushnirb> B. S., <b>Kushnirb> B. H., <b>Kushnirb> B. H., <b>Kushnirb> B. H., <b>Kushnirb> B. H., <b>Kushnirb> B. H., <b>Kushnirb> B. H., <b>Kushnirb> B.
]]>9. Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2023 (1); 77-87
DOI: https://doi.org/10.33136/stma2023.01.077
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
Bibliography:
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2. Nikolaev Yu. M., Solomonov Yu. S. Inzhenernoe proektirovanie upravlyaemykh ballisticheskikh raket s RDTT. M., 1979. 240 s.
3. Enotov V. G., Kirichenko A. S., Pustovgarova Ye. V. Osobennosti rascheta i vybora raskhodnoy diagrammy dvukhrezhimnykh marshevykh RDTT: ucheb.-metod. posobie. Pod red. akadem. A. V. Degtyreva. Dnepr, 2019. 68 s.
4. Enotov V. G., Kushnir B. I., Pustovgarova Ye. V. Metodika-programma proektnoy otsenki characteristic marshevykh dvigateley na tverdom toplive s korpusami iz vysokoprochnykh metallicheskikh materialov, statsionarnymi soplami i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. A. S. Kirichenko. Dnep, 2019. 91 s.
5. Enotov V. G., Kirichenko A. S., Kushnir B. I., Pustovgarova Ye. V. Metodika proektnoy otsenki characteristic marshevykh dvigatelnykh ustanovok na tverdom toplive s povorotnymi upravlyayuschimi soplami, plastikovymi tselnomotannymi korpusamy i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. akadem. A. V. Degtyareva. Dnepr. 2019. 149 s.
6. Alemasov V. Ye., Dregalin A. F., Tishin A. P. Teoriya raketnykh dvigateley. M., 1980. 55 s.
7. Raschetnye materialy dlya podgotovki i vydachi iskhodnykh dannykh na razrabotku uzlov marshevykh dvigatelnykh ustanovok na tverdom toplive. Raschet ID metodom avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: inzhenern. zapiska 553-376 IZ. GP «KB «Yuzhnoye». Dnepropetrovsk, 2017. 30 s.
8. Metodika avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: nauch.-tekhn. Otchet 03-453/32 NTO. GP «KB «Yuzhnoye». Dnepropetrovsk, 2010. 127 s.
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