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Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff Authors: Degtiarov М. Analysis of composite rocket motor case using finite element method. (2020) "Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff" Космическая техника. "Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff" Космическая техника. quot;Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff", Космическая техника.
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3. Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

Authors:

Degtiarov М. O.1, Avramov K. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2020, (1); 26-33

DOI: https://doi.org/10.33136/stma2020.01.026

Language: Russian

Annotation: The study of thermal strength of the hold-down bay is considered. The hold-down bay is a cylindrical shell with the load-bearing elements as the standing supports. The case of the hold-down bay consists of the following structural elements: four standing supports and the compound cylindrical shell with two frames along the top and bottom joints. The purpose of this study was the development of a general approach for the thermal strength calculation of the hold-down bay. This approach includes two parts. Firstly, the unsteady heat fields on the hold-down bay surface are calculated by means of the semi-empirical method, which is based on the simulated results of the combustion product flow of the main propulsion system. The calculation is provided by using Solid Works software. Then the unsteady stress-strain behavior of the hold-down bay is calculated, taking into consideration the plastoelastic deformations. The material strain bilinear diagram is used. The finiteelement method is applied to the stress-strain behavior calculation by using NASTRAN software. The thermal field is assumed to be constant throughout the shell thickness. As a result of the numerical simulation the following conclusions are made. The entire part of the hold-down bay, which is blown by rocket exhaust jet, is under stress-strain behavior. The stresses of the top frame and the shell are overridden the breaking strength that caused structural failure. The structure of the hold-down bay, which is considered in the paper, is unappropriated to be reusable. The hold-down bay should be reconstructed by reinforcement in order to provide its reusability.

Key words: stress-strain behavior, finite-element method, plastoelastic deformations, breaking strength, reusability

Bibliography:

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2. Perakis N., Haidn O. J. Inverse heat transfer method applied to capacitively cooled rocket thrust chambers. International Journal of Heat and Mass Transfer. 2019. № 131. P. 150–166. https://doi.org/10.1016/j.ijheatmasstransfer.2018.11.048
3. Yilmaz N., Vigil F., Height J., et. al. Rocket motor exhaust thermal environment characterization. Measurement. 2018. № 122. P. 312–319. https://doi.org/10.1016/j.measurement.2018.03.039
4. Jafari M. Thermal stress analysis of orthotropic plate containing a rectangular hole using complex variable method. European Journal of Mechanics A /Solids. 2019. № 73. P. 212–223. https://doi.org/10.1016/j.euromechsol.2018.08.001
5. Song J., Sun B. Thermal-structural analysis of regeneratively cooled thrust chamber wall in reusable LOX / Methane rocket engines. Chinese Journal of Aeronautics. 2017. № 30. P. 1043–1053.
6. Ramanjaneyulu V., Murthy V. B., Mohan R. C., Raju Ch. N. Analysis of composite rocket motor case using finite element method. Materials Today: Proceedings. 2018. № 5. P. 4920–4929.
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3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff
3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff
3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

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]]> 2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems https://journal.yuzhnoye.com/content_2020_1-en/annot_2_1_2020-en/ Fri, 29 Sep 2023 18:16:07 +0000 https://journal.yuzhnoye.com/?page_id=31001
Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems Authors: Aksenenko A. 2020, (1); 13-25 DOI: https://doi.org/10.33136/stma2020.01.013 Language: Russian Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. Key words: multiple launch rocket systems (MLRS) , Metodicheskoe obespechenie dlia vybora oblika, optimizatsii proektnykh parametrov i programm upravleniia poletom rakety-nositelia. Optimizatsiia proektnykh parametrov rakety-nositelia sverkhlegkogo klassa.
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2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

Authors:

Aksenenko A. V.1, Hurskyi O. I.1, Klochkov A. S.1, Kondratiuk Ye. A.1, Senkin V. S.2, Siutkina-Doronina S. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2020, (1); 13-25

DOI: https://doi.org/10.33136/stma2020.01.013

Language: Russian

Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. The guided missiles of multiple launch rocket system are intended for delivering munitions to the given spatial point with required and specified kinematic motion parameters at the end of flight. The aim of the article is an analysis of the development trends of the guided missiles with the solid rocket motors for the multiple launch rocket systems, identifying the characteristics and requirements for the flight trajectories, design parameters, control programs, overall dimensions and mass characteristics, structural layout and aerodynamic schemes of missiles. The formalization of the complex task to optimize design parameters, trajectory parameters and motion control programs for the guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories is given. The complex task belongs to a problem of the optimal control theory with limitations in form of equa lity, inequality and differential constraints. To simplify the problem, an approach to program forming is proposed for motion control in the form of polynomial that brings the problem of the optimal control theory to a simpler problem of nonlinear mathematical programming. When trajectory parameters were calculated the missile was regarded as a material point of variable mass and the combined equations for center-of-mass motion of the guided missile with projections on axes of the terrestrial reference system were used. The structure of the mathematical model was given along with the calculation sequence of the criterion function that was used for determination of the optimal parameters, programs and characteristics. The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.

Key words: multiple launch rocket systems (MLRS), complex problem of the optimal control theory, problem of nonlinear mathematical programming, main solid rocket motor, limitations for motion parameters and basic characteristics of the guided missiles

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2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems
2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems
2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

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]]> 9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials https://journal.yuzhnoye.com/content_2020_1-en/annot_9_1_2020-en/ Wed, 13 Sep 2023 10:43:08 +0000 https://journal.yuzhnoye.com/?page_id=31035
Experimental investigation of a liner-free propellant tank made from polymer composite materials Authors: Sidoruk А. 2020, (1); 90-98 DOI: https://doi.org/10.33136/stma2020.01.090 Language: Russian Annotation: The exploratory and experimental investigations were conducted into design of propellant tank made of composite polymer materials for work in cryogenic environment at operating pressure of 7.5 kgf/cm2 . The materials used and propellant tank manufacturing technologies ensure leak-tightness of load-bearing shell at liquid nitrogen operating pressure of 7.5 kgf/cm2 and strength at excess pressure of 15 kgf/cm2 and allow conducting approbation of prospective stage of the integrated launch vehicle. Composite fuel tank for ILV, Dnipro, Yuzhnoye SDO, 2019.
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9. Experimental investigation of a liner-free propellant tank made from polymer composite materials

Authors:

Sidoruk А. V., Popov D. А., Zadoia А. S., Kalinichenko D. S., Aksenenko O. V., Husarova I. O., Derevianko I. I., Kharchenko V. M., Litot O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 90-98

DOI: https://doi.org/10.33136/stma2020.01.090

Language: Russian

Annotation: The exploratory and experimental investigations were conducted into design of propellant tank made of composite polymer materials for work in cryogenic environment at operating pressure of 7.5 kgf/cm2 . When determining the configuration of a liner-free composite propellant tank, the main requirement was ensuring its leak-tightness at internal excess pressure and cryogenic temperature effect. The world experience of creating similar designs was analyzed and the requirements were defined imposed on configuration of propellant tank load-bearing shells. Before defining the final configuration, the types of materials, reinforcing patterns, and possible ways to ensure leak-tightness were analyzed, and preliminary tests were conducted of physical and mechanical characteristics of thin-wall samples of composite materials and tubular structures with different reinforcing patterns. The tests of carbon plastic samples were conducted at different curing modes to determine the most effective one from the viewpoint of strength characteristics and the tests for permeability by method of mouthpiece were conducted. The tests of pilot propellant tank showed that the calculated values of deformations and displacements differ from the experimental values by no more than 10 %. Using the parameters measurement results from the tests on liquid nitrogen, the empirical formulas were obtained to calculate linear thermal expansion coefficient of the package of materials of load -bearing shell. The empirical dependences were constructed of relative ring deformations at load-bearing shell middle section on pressure and temperature. The tests confirmed correctness of adopted solutions to ensure strength and leak-tightness of propellant tank load-bearing shell at combined effect on internal excess pressure and cryogenic temperature, particularly at cyclic loading. The materials used and propellant tank manufacturing technologies ensure leak-tightness of load-bearing shell at liquid nitrogen operating pressure of 7.5 kgf/cm2 and strength at excess pressure of 15 kgf/cm2 and allow conducting approbation of prospective stage of the integrated launch vehicle.

Key words: load-bearing shell, permeability, cryogenic propellant, relative deformations, linear thermal expansion coefficient

Bibliography:
1. Frantsevich I. М., Karpinos D. М. Kompozitsionnye materialy voloknistogo stroeniia. K., 1970.
2. TSM YZH ANL 009 00. Composite fuel tank for ILV, Dnipro, Yuzhnoye SDO, 2019.
3. Zheng H., Zeng X., Zhang J., Sun H. The application of carbon fiber composites in cryotank. Solidification. 2018. https://doi.org/10.5772/intechopen.73127

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9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials
9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials
9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials

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]]> 7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation https://journal.yuzhnoye.com/content_2020_1-en/annot_7_1_2020-en/ Wed, 13 Sep 2023 06:27:07 +0000 https://journal.yuzhnoye.com/?page_id=31031
2020, (1); 76-84 DOI: https://doi.org/10.33136/stma2020.01.076 Language: Russian Annotation: The mathematic modeling was performed of the flight of light-class three-stage launch vehicle injecting a payload into sun-synchronous orbit of 700 km altitude and a cluster of observed space debris objects in the conditions of dynamically changing cataloged space situation. The hazard of launch vehicle collision with observed space debris objects in a launch is confirmed. Access mode: https://iaassconference2013.-space-safety.org/ wp-content/uploads/sites/-19/2013/06/ 1420_Shultz.pdf (Access date 12.09.2019). Sblizheniie rakety-nositelia s katalogizirovannymi kosmicheskimi ob’ektami v processe vyvedeniia na orbity s nizkim nakloneniem / Izvestiia vysshikh uchebnykh zavadenii.
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7. Mechanics of a satellite cluster. Methods for estimating the probability of their maximal approach in flight

Authors:

Holubek O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 76-84

DOI: https://doi.org/10.33136/stma2020.01.076

Language: Russian

Annotation: The mathematic modeling was performed of the flight of light-class three-stage launch vehicle injecting a payload into sun-synchronous orbit of 700 km altitude and a cluster of observed space debris objects in the conditions of dynamically changing cataloged space situation. It is shown that as the launch moment becomes closer, the cataloged space situation is ascertained, which leads to the constant change of the quantity of hazardous space debris objects observed in the vicinity of launch vehicle trajectory and to the change of the parameters of their approach to the launch vehicle: minimal relative distance, relative velocity, rendezvous angle and launch moment for which hazardous approach is revealed. The hazardous approaches for the launch vehicle trajectory under consideration are more often observed with the relative velocities of more than 8 km/s and rendezvous angles less than 90 deg and their variations within the launch window do not exceed 1.2 m/s and 0.035 deg respectively. In this case, the histograms of distribution of relative distance, relative velocity, and rendezvous angle from catalog to catalog vary insignificantly. The distribution of hazardous approaches in launch time within launch window is not uniform, the regions are observed with low quantity of hazardous approaches and with high quantity. The hazard of launch vehicle collision with observed space debris objects in a launch is confirmed. In all, in the launch day time window under consideration, more than ten hazardous approaches are revealed, for two of them the approach to minimal distance of less than 1 km is predicted. This testifies to the necessity of taking measures to increase safety of launch vehicle flight through observed space debris cluster. In order to increase Ukrainian launch vehicles miss ion safety in the conditions of near space pollution, it is proposed to create the system of pre -flight space analysis, whose tasks are periodic analysis of space situation not less than once in a day, revealing of hazardous approaches, determination of their parameters, and preparation of data to make decision on launch time.

Key words: method of launch time planning, safety of flight through space debris cluster

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7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation
7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation
7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation

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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. Test and launch control technology for launch vehicles. Development of the normative framework methodology for justifying the launcher structures resource of launch vehicles. Vliianie vyrezov na prochnost tsilindricheskikh otsekov raket-nositelei pri neuprugom deformirovanii materiala.
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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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]]> 20.2.2018 The Use of Special Devices during Launch Pad Development Testing https://journal.yuzhnoye.com/content_2018_2-en/annot_20_2_2018-en/ Thu, 07 Sep 2023 12:27:24 +0000 https://journal.yuzhnoye.com/?page_id=30805
The tests are carried out after the launch pad was manufactured and assembled on-site as well as during the whole operating period (if necessary). Advantages of the pad loading device include low materials consumption, low cost in comparison with composite weights (with large load values), provision of the required modes for applying and removing the test load, controlled separate loading of each support of the launch pad, high mobility, short duration of testing, possibility of using launch pads of other rocket complexes with lower or equal test load values for testing. Ground support equipment for use at launch, landing or retrieval sites.
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20. The Use of Special Devices during Launch Pad Development Testing

Authors:

Fedenko B. R., Onischenko S. M., Yerofeyev S. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 173-177

DOI: https://doi.org/10.33136/stma2018.02.173

Language: Russian

Annotation: One of the tasks of the development tests conducted on a launch pad is verification of its strength properties. The tests are carried out after the launch pad was manufactured and assembled on-site as well as during the whole operating period (if necessary). Load mode was chosen in consideration of cost and possibility of providing the required loading conditions. Two modes of creating the required test load were examined: usage of weights with corresponding mass (load simulators) or special devises (which have smaller mass as compared with load simulators). The descriptions, basic characteristics, advantages and disadvantages of composite and bulk weights and pad loading device are given. This article studies the pad loading device under development. This device enables to conduct static nondestructive tests on the launch pad in order to check its strength after manufacturing and during the whole operating period. The device consists of the load-bearing frame, hydraulic system, locks, control system and measurement system. Advantages of the pad loading device include low materials consumption, low cost in comparison with composite weights (with large load values), provision of the required modes for applying and removing the test load, controlled separate loading of each support of the launch pad, high mobility, short duration of testing, possibility of using launch pads of other rocket complexes with lower or equal test load values for testing. Therefore, the pad loading device enables to achieve the required test load values while having considerably smaller dimensions and mass as compared with composite weights and bigger functional possibilities as compared with bulk weights. Small overall dimensions and operability reduce the number of needed personnel and equipment.

Key words: weight for testing, test load, loading device

Bibliography:
1. ISO 14625:2007. Space systems. Ground support equipment for use at launch, landing or retrieval sites. General requirement. Brought in 01.11.2007. 32 p.
2. Launch Vehicle Mass Dummy: Patent RU2491211 RF: MPK B64G 5/00, B64G 7/00, F42B 15/00 / Dneprotyazhmash. Published 27.08.2013. 12 p.
3. Method of Poles Static Testing and Poles Static Test Device: Patent RU2173747: RF E02D 33/00 / NPSF Fundamentspetstroy. Published 20.09.2001. 10 p.
4. ISO 16290:2013. Space systems. Definition of the Technology Readiness Levels (TRLs) and their criteria of assessment. Brought in 14.10.2013. 20 p.

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]]> 13.1.2018 On Selection of Materials for Creation of Modern LV Thermostating System Mating Hoses https://journal.yuzhnoye.com/content_2018_1-en/annot_13_1_2018-en/ Tue, 05 Sep 2023 06:52:56 +0000 https://journal.yuzhnoye.com/?page_id=30469
The topical issues are considered of materials designing with consideration for specific features of the hoses as special industrial rubber articles of launch vehicle launch sites.
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13. On Selection of Materials for Creation of Modern LV Thermostating System Mating Hoses

Authors:

Bigun S. O.1, Yevchik V. S.2, Khorolskyi M. S.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; State Enterprise “Ukrainian Research Design-Technological Institute of Elastomer Materials and Products”, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2018 (1); 72-84

DOI: https://doi.org/10.33136/stma2018.01.072

Language: Russian

Annotation: A series of materials is proposed for creation of space launch vehicle low-pressure air thermostating systems joints hoses. The topical issues are considered of materials designing with consideration for specific features of the hoses as special industrial rubber articles of launch vehicle launch sites.

Key words:

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17. Blokh G. A. Organic Rubber Vulcanization Accelerators. М.,1964. 156 p.
18. Big Reference Book of Rubber Industry Worker in 2 parts. Part 1. Rubbers and Ingredients / Under the general editorship of S. V. Reznichenko and Y. L. Morozov. М., 2012. 740 p.
19. Polyurethane Chemistry and Technology: Collection of conference papers. Manchester, 1967. 254 p.
20. Degteva T. G. et al. The Impact of Additives on Thermal Ageing of Rubbers and Model Gaskets Made of SKEP. Caoutchouc and Rubber. М., 1984. No. 8. P. 17-19.
21. Lepetov V. A. Rubber Products. L., 1976. 440 p.
22. Lepetov V. A., Yurtsev L. N. Calculations and Designing of Rubber Products and Production Accessories. М., 2009. 417 p.
23. New Prospective Hoses and Scarce and Commercially Inviable Rubbers, Ingredients and Materials: Recommendation No. 51-РМ-22/38/57/50-1050-83. М., 1983. 42 p.
24. Kornev A. E. et al. Technology of Elastomer Materials. М., 2009. 504 p.
25. Gerasimenko A. А. Protection of Machines from Biological Damages. M., 1984. 92 p.
26. Principles of Constructing Formulations and Using Rubbers for Rubber Products of Tropical Version: Recommendation No. 51-РМ-26-48-66. М., 1966. 56 p.
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28. Increasing Rubber Products Service Life in Conditions of Tropical Climate: Recommendation No. 51-РМ-4-697-76. М., 1976. 23 p.
29. Assessment of Rubber Resistance to Mould: Recommendation No. 51-РМ-4-407-73. М., 1976. 42 p.

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13.1.2018 On Selection of Materials for Creation of Modern LV Thermostating System Mating Hoses
13.1.2018 On Selection of Materials for Creation of Modern LV Thermostating System Mating Hoses
13.1.2018 On Selection of Materials for Creation of Modern LV Thermostating System Mating Hoses
]]> 20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments https://journal.yuzhnoye.com/content_2017_2/annot_20_2_2017-en/ Wed, 09 Aug 2023 12:26:27 +0000 https://journal.yuzhnoye.com/?page_id=29866
Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments Authors: Potapov O. 2017 (2); 112-120 Language: Russian Annotation: Some main results of scientific support of development of launch vehicle head module composite loadbearing bays are presented. Basic parameters’ optimization concept for composite nose fairings of launchers / V. (2017) "Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments" Космическая техника. "Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments" Космическая техника. quot;Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments", Космическая техника. Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments Автори: Potapov O. Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments Автори: Potapov O.
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20. Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments

Authors:

Potapov O. М.1, Kovalenko V. O.1, Kondrat’ev А. V.2, Gaidachuk V. Е.2

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2017 (2); 112-120

Language: Russian

Annotation: Some main results of scientific support of development of launch vehicle head module composite loadbearing bays are presented. The methodology is proposed for developing these units. By the example of payload fairing and interstage bay of Cyclone-4 launch vehicle, high efficiency is shown of proposed methodology implementation when selecting their rational design and technological parameters.

Key words:

Bibliography:
1. Degtyarev A. V. Rocket Technology. Problems and Prospects. Selected scientific-technical publications. Dnepropetrovsk, 2014. 420 p.
2. Kovalenko V. A., Kondrat’yev A. V. Use of Polymer Composite Materials in Space Rockets as Reserve of Increasing their Mass and Functional Effectiveness. Aerospace Engineering and Technology. 2011. No. 5 (82). P. 14-20.
3. Kondrat’yev A. V. et al. Analysis of Nomenclature of Type Composite Units of Space Rockets and Structural Schemes Applied for them / A. V. Kondrat’yev, A. G. Dmitrenko, K. D. Stenile, А. А. Tsaritsynsky. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 3 (79). Kharkiv, 2014. P. 19 – 30.
4. Potapov A. M. et al. Comparison of Payload Fairings of Existing and Prospective Domestic Launch Vehicles and their Foreign Analogs / А. М. Potapov, V. A. Kovalenko, A. V. Kondrat’yev. Aerospace Engineering and Technology. 2015. No. 1(118). P. 35 – 43.
5. Gaidachuk A. V. et al. Methodology of Developing Effective Design and Technological Solutions of Space Rocketry Composite Units: Monography in 2 volumes. Vol. 2. Synthesis of Space Rocketry Composite Units Parameters at Heterogeneous Loading / A. V. Gaidachuk, V. E. Gaidachuk, A. V. Kondrat’yev, V. A. Kovalenko, V. V. Kirichenko, А. M. Potapov / Under the editorship of A. V. Gaidachuk. Kharkiv, 2016. 250 p.
6. Gaidachuk A. V. et al. Methodology of Developing Effective Design and Technological Solutions of Space Rocketry Composite Units: Monography in 2 volumes. Vol. 1. Creation of Space Rocketry Units with Specified Quality of Polymer Composite Materials / A. V. Gaidachuk, V. E. Gaidachuk, A. V. Kondrat’yev, V. A. Kovalenko, V. V. Kirichenko, А. M. Potapov / Under the editorship of A. V. Gaidachuk. Kharkiv, 2016. 263 p.
7. Smerdov A. A. Development of Methods to Design Space Rocketry Composite Materials and Structures: Dissertation of Doctor of Engineering Science: 05.07.02, 05.02.01. М., 2007. 410 p.
8. Slyvyns’kyy V. et al. Basic parameters’ optimization concept for composite nose fairings of launchers / V. Slyvyns’kyy, V. Gajdachuk, V. Kirichenko, A. Kondratiev. 62nd International Astronautical Congress, IAC 2011 (Cape Town, 3-7 October 2011). Red Hook, NY: Curran, 2012. Vol. 9. P. 5701-5710.
9. Gaidachuk V. E. et al. Optimization of Cyclone-4 Launch Vehicle Payload Fairing Design Parameters / V. E. Gaidachuk, V. I. Slivinsky, A. V. Kondrat’yev, A. P. Kushnar’ov, Effectiveness of Honeycomb Structures in Aerospace Products: Proceedings of III International Scientific-Practical Conference (Dnepropetrovsk, 27-29 May 2009). Dnepropetrovsk, 2009. P. 88 – 95.
10. Zinov’yev A. M. et al. Design and Technological Solution and Carrying Capacity of Cyclone-4 Launch Vehicle Interstage Bay Made of Polymer Composite Materials / А. М. Zinov’yev, А. P. Kushnar’ov, A. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Aerospace Engineering and Technology. 2013. No. 3 (100). P. 46-53.
11. Karpov Y. S. Connection of Parts and Units Made of Composite Materials: Monography. Kharkiv, 2006. 359 p.
12. Kondrat’yev A. V. Mass Optimization of Launch Vehicle Payload Fairing Irregular Zones. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 47 (4). Kharkiv, 2006. P. 126 – 133.
13. Degtyarev A. V. et al. Evaluation of Carrying Capacity of Launch Vehicle Bays Separation System Composite Fitting / A. V. Degtyarev, A. P. Kushnar’ov, V. V. Gavrilko, V. A. Kovalenko, А. V. Kondrat’yev, А. М. Potapov. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2013. Issue 1. P. 18-21.
14. Patent 81537 UA, MPK (2013.01) F42B 15/36 (2006.01) B64D 1/00 Fitting of Rocket’s Three-Layer Shell / О. М. Zinov’yev, О. P. Kuznetsov, V. V. Gavrilko, О. М. Potapov, V. O. Kovalenko et al.; Applicant and patent holder NVF Dniprotechservice, Yuzhnoye SDO. No. u 2012 11210; Claimed 27.09.2012; Published 10.07.13, Bulletin 13. 4 p.
15. Zinov’yev A. M. et al. Manufacturing Technology of Cyclone-4 Launch Vehicle Experimental Large-Sized Interstage Bay Made of Carbon Plastics / А. M. Zinov’yev, А. P. Kushnar’ov, А. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works of N. E. Zhukovsky Aerospace University “KhAI”. Issue 2 (74). Kharkiv, 2013. P. 7 – 17.
16. Zinov’yev A. M. et al. Static Tests of Cyclone-4 Launch Vehicle Experimental Interstage Bay Made of Carbon Plastic / А. М. Zinov’yev, А. P. Kushnar’ov, А. V. Kondrat’yev, А. М. Potapov, А. P. Kuznetsov, V. A. Kovalenko. Aerospace Engineering and Technology. 2013. No. 4(101). P. 28-35.

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20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments
20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments
20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments
]]> 5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle https://journal.yuzhnoye.com/content_2017_2/annot_5_2_2017-en/ Tue, 08 Aug 2023 12:36:28 +0000 https://journal.yuzhnoye.com/?page_id=29750
Launch Sites.
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5. Structural Perfection of Cyclone-4 Integrated Launch Vehicle

Authors:

Zhuk N. P., Makarenko A. O., Shevtsov E. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 25-28

Language: Russian

Annotation: The comparison of Integrated Launch Vehicles structural perfection coefficients shows that Yuzhnoyedeveloped Cyclone-4 launch vehicle has structural perfection at the best world rocket model level

Key words:

Bibliography:
1. Fundamentals of Spacecraft Launch Vehicles Designing / Under the editorship of V. P. Mishin. М., 1991. 415 p.
2. Kobelev V. N., Milovanov A. G. Launch vehicles: Tutorial. М., 1993. 185 p.
3. Umansky S. P. Launch Vehicles. Launch Sites. М., 2001. 216 p.
4. Kobelev V. N., Milovanov A. G. Spacecraft Injection Means. М., 2009. 528 p.

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5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle
5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle
5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle
]]> 6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing https://journal.yuzhnoye.com/content_2019_1-en/annot_6_1_2019-en/ Thu, 25 May 2023 12:09:32 +0000 https://journal.yuzhnoye.com/?page_id=27711
2019, (1); 38-44 DOI: https://doi.org/10.33136/stma2019.01.038 Language: Russian Annotation: This article considers the issue of achievement of the specified value of propellants saturation by helium after their delivery from the manufacturers to the launch site. In order to solve this problem number of factors have been considered, which determine the value of gas saturation in the propellants delivered to the launch site and procedure to control the value of gas saturation by the fuel manufacturer has been developed. This procedure implies that shipping tank container is pressurized after being fueled with propellants at the manufacturer’s, the pressure is characterized by the value of the known initial deficit or excess of gas in the propellants, following which tank container is delivered to the launch site. Based on this fuel saturation by helium procedure, the complex technology is suggested, providing controlled gas saturation during fuel delivery and subsequent adjustment of gas saturation using launch site equipment.
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6. Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing

Authors:

Pozdieiev H. L., Kucherenko R. A., Kucherenko T. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 38-44

DOI: https://doi.org/10.33136/stma2019.01.038

Language: Russian

Annotation: This article considers the issue of achievement of the specified value of propellants saturation by helium after their delivery from the manufacturers to the launch site. Knowing the fact that propellants gas saturation or gas separation processes are labour-consuming and costly this issue is of immediate interest. In order to solve this problem number of factors have been considered, which determine the value of gas saturation in the propellants delivered to the launch site and procedure to control the value of gas saturation by the fuel manufacturer has been developed. This procedure implies that shipping tank container is pressurized after being fueled with propellants at the manufacturer’s, the pressure is characterized by the value of the known initial deficit or excess of gas in the propellants, following which tank container is delivered to the launch site. During transportation tank container is subjected to various kinds of mechanical actions (vibration, rolling and pitching in the sea, braking, transshipment), therefore intensive mixing of propellants occur. As propellants mix, process of propellant saturation occurs when certain amount of gas transits from tank container’s gas volume into the liquid, therefore certain gas saturation is reached. Article includes the measuring results of the gas liquid medium parameters inside the tank containers with fuel in the process of fuel transportation to Ukraine from PRC factories and estimations of the measuring results using the developed model which confirmed the quantitative nature of the mass exchange processes, included in the model, going on in the gas liquid medium during transportation of the tank container with fuel equipment. It has been determined that due to inevitable errors in the measuring of the specified parameters by the tank container, the achievement of the specified gas saturation with high precision is problematic. In spite of the fact that this procedure does not provide exact value of the specified gas saturation, its application will accelerate and make cheaper the process of fuel preparation for filling operations at the launch site, which is especially relevant in case of fuel saturation by helium. Based on this fuel saturation by helium procedure, the complex technology is suggested, providing controlled gas saturation during fuel delivery and subsequent adjustment of gas saturation using launch site equipment. Therefore, this article develops and studies the original model of the controlled gas saturation of the fuel during its delivery to the consumer. Alternative of the practical use of the study results is suggested in the form of the complex technology of fuel saturation by helium, delivered in the tank containers from the manufacturer to the launch site.

Key words: oxidizer, fuel, saturation by helium, tank container, transportation

Bibliography:

1. Volskiy A. P. Kosmodrom. M.: Voenizdat, 1977. 311 p.
2. Stepanov A. N., Vorobiev A. M., Grankin B. K. Kompleksy zapravki raket I kosmicheskikh apparatov. SPB:OM-PRESS, 2004. 26 p.
3. Kiriyanova A. N., Matveeva O. P. Opredelenie kolebania davlenia v gazovoy polosti hermetychikh emkostey transportnozapravochnykh containerov dlya raketnykh topliv pri temperaturnykh vozdeistviyakh/ Nauka i innovatsii. 2016. Vyp. 7.
4. Berezhkovskiy M. I. Khranenie i transportirovka khimicheskykh produktov. – M.: Khimia, 1973. – 272 s.
5. Perepelkin K. Ye., Matveev V. S. Gazovye emulsii. L.:Khimia, 1979. 200 p.
6. Issledovanie protsessov degazirovaniya komponentov topliva v conteinere-tsisterne pri dostavke topliva potrebitelyu. Cyclone4M 21.18425.174 OT: Techn. report. Dnepropetrovsk: Yuzhnoye SDO, 2017. 39 p.

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6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing
6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing
6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing

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