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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 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. 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 Bibliography: 1. 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. 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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]]> 8.1.2024 Theoretic-experimental evaluation of the solid-propellant grain erosive burning https://journal.yuzhnoye.com/content_2024_1-en/annot_8_1_2024-en/ Mon, 17 Jun 2024 08:41:58 +0000 https://journal.yuzhnoye.com/?page_id=35027
2024, (1); 72-77 DOI: https://doi.org/10.33136/stma2024.01.072 Language: Ukrainian Annotation: The high demands for the flow rate and thrust characteristics specified for the modern solid-propellant rocket motors (SRM) under the strict mass and overall dimensions constraints require high level of mass fraction of propellant. This paper proposes a methodology for calculating the internal ballistic characteristics of a solid propellant rocket motor under erosive burning, which is relatively time and resource consuming. Key words: rocket motor , solid propellant , erosive burning , internal ballistic characteristics Bibliography: Arkhipov V. rocket motor , solid propellant , erosive burning , internal ballistic characteristics .
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8. Theoretic-experimental evaluation of the solid-propellant grain erosive burning

Автори: Taran M. V., Moroz V. G.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 72-77

DOI: https://doi.org/10.33136/stma2024.01.072

Language: Ukrainian

Annotation: The high demands for the flow rate and thrust characteristics specified for the modern solid-propellant rocket motors (SRM) under the strict mass and overall dimensions constraints require high level of mass fraction of propellant. And in the process of propellant grain combustion, erosive burning often takes place (increase of propellant burning rate depending on combustion products flow rate along the grain channel). This may play both negative (off-design increase of chamber pressure) and positive role (for example, increasing the launch thrust-to-weight ratio of the rocket). It is typical of the main SRMs of various rocket systems (multiple launch rocket systems, anti-aircraft guided missiles, tactical missiles, boosters). This paper proposes a methodology for calculating the internal ballistic characteristics of a solid propellant rocket motor under erosive burning, which is relatively time and resource consuming. The methodology is based on equidistant model of propellant grain combustion, where grain is divided lengthwise into a number of intervals. For any point of time during the engine operation, burning area and port area of each interval are calculated, taking into account erosive impact on each interval; total burning area is the sum of all intervals burning areas. Gas flow rate in each interval of the grain channel is calculated using gas-dynamic equations. The motor mass flow rate is a mass input sum of all the intervals; and the burning rate in each interval is estimated with proper erosion factor. The combustion chamber pressure had been calculated for four erosive burning models proposed by different authors. All the models showed convergence with the experimental SRM test data sufficient for engineering estimate (in particular, for maximum chamber pressure and combustion time). Selected as a result erosive burning model may be used to design new motors with solid propellants similar in chemical composition, and the model parameters are to be further customized using the test specimens.

Key words: rocket motor, solid propellant, erosive burning, internal ballistic characteristics

Bibliography:
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  5. Yanjie Ma, Futing Bao, Lin Sun, Yang Liu, and Weihua Hui. A New Erosive Burning Model of Solid Propellant Based on Heat Transfer Equilibrium at Propellant Surface. Hindawi International Journal of Aerospace Engineering, Vol. 2020, Article ID 8889333. https://doi.org/10.1155/2020/8889333
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  8. William Orvis. EXCEL dlya uchenykh, inzhenerov i studentov. Kiev: «Junior», 1999.

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8.1.2024 Theoretic-experimental evaluation of the solid-propellant grain erosive burning
8.1.2024 Theoretic-experimental evaluation of the solid-propellant grain erosive burning
8.1.2024 Theoretic-experimental evaluation of the solid-propellant grain erosive burning

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]]> 10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM https://journal.yuzhnoye.com/content_2020_1-en/annot_10_1_2020-en/ https://journal.yuzhnoye.com/?page_id=31037
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).
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10. Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

Authors:

Yenotov V. H., Pustovharova O. V.

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:
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3. Sorkin R. Е. Gasotermodinamika raketnykh dvigatelei na tverdom toplive. М, 1967. 368 s.

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10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM
10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM
10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

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]]> 3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff https://journal.yuzhnoye.com/content_2020_1-en/annot_3_1_2020-en/ Fri, 29 Sep 2023 18:22:49 +0000 https://journal.yuzhnoye.com/?page_id=32230
Rocket motor exhaust thermal environment characterization. Analysis of composite rocket motor case using finite element method.
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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

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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
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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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15. Малинин Н. Н. Прикладная теория пластичности и ползучести. М., 1968. 400 с.

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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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The structure was tested in the process of fueling the solid rocket motor casing and during charge polymerization. Solid Rocket Motors Design / Under the editorship of L. Solid Rocket Motor Charged Case: Patent 2418187C1 Russian Federation: MPK F02K 9/34 (2006:01) /
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16. Design Solutions to Prevent Propellant Ingress into SRM Case Space behind Sealing Ring

Authors:

Motylyov S. O., Malyi L. P., Kolos O. M., Faryat’eva N. P., Badakva L. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 139-142

DOI: https://doi.org/10.33136/stma2018.02.139

Language: Russian

Annotation: The structure examined herein aims to keep fuel from entering the space behind the cuff, evacuate the space behind the cuff, reliably fasten the cuff to the thermal protective coating of the bottom in the process of charge forming, easily release the cuff after charge forming, and remove the support structure elements from the casing after charge polymerization when equipping. The structure was tested in the process of fueling the solid rocket motor casing and during charge polymerization. In order to comply with the specified requirements the cuff functions were identified, the structures previously developed were analyzed, and a new structure was designed and improved after testing. The improved structure ensured that fuel did not enter the space behind the cuff; it was removed easily after charge forming. Conclusions proved the suitability of this stricture.

Key words: insert, charge, ring, cuff

Bibliography:
1. Solid Rocket Motors Design / Under the editorship of L. N. Lavrov. М., 1993. 214 p.
2. Solid Rocket Motor Charged Case: Patent 2418187C1 Russian Federation: MPK F02K 9/34 (2006:01) / M. I. Sokolovsky, V. Z. Karimov, Y. B. Nelzin, N. N. Karmanov, B. A. Nesterov; Applicant and patent holder OJSC NPO Iskra. No. 2009146654; claimed 15.12.09; published 10.05.11, Bulletin No. 13.

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16.2.2018 Design Solutions to Prevent Propellant Ingress into SRM Case Space behind Sealing Ring
16.2.2018 Design Solutions to Prevent Propellant Ingress into SRM Case Space behind Sealing Ring
16.2.2018 Design Solutions to Prevent Propellant Ingress into SRM Case Space behind Sealing Ring

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]]> 12.2.2018 Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs https://journal.yuzhnoye.com/content_2018_2-en/annot_12_2_2018-en/ Thu, 07 Sep 2023 11:38:27 +0000 https://journal.yuzhnoye.com/?page_id=30770
2018 (2); 101-116 DOI: https://doi.org/10.33136/stma2018.02.101 Language: Russian Annotation: The main scientific and methodological propositions for designing single-stage guided missiles with main solid rocket motors that are intended for delivering payload to the given spatial point with required and specified kinematic motion parameters are defined. Key words: 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 object Bibliography: 1. On Problem of Optimization of Design Parameters and Control programs of a Rocket Object With Solid Rocket Motor. Theory and Calculation of Solid Rocket Motors. Gas Dynamics of Powder Rocket Motors. 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 object .
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12. Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs

Authors:

Aksyonenko A. V.1, Baranov E. Y.1, Hurskyi O. I.1, Klochkov A. S.1, Morozov A. S.1, Alpatov A. P.2, 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. 2018 (2); 101-116

DOI: https://doi.org/10.33136/stma2018.02.101

Language: Russian

Annotation: The main scientific and methodological propositions for designing single-stage guided missiles with main solid rocket motors that are intended for delivering payload to the given spatial point with required and specified kinematic motion parameters are defined. The aim of the article is to develop methodology for the early design phase to improve the basic characteristics of guided missiles, including formalization of complex problem to optimize design parameters, trajectory parameters and motion control programs for guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories. The task is defined as a problem of the optimal control theory with limitations in form of equality, inequality and differential constraints. 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 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 criterion functional that was used for optimization of design parameters, control programs and basic characteristics of the guided missile. The mathematical model of the guided missile provides adequate accuracy for design study to determine: overall dimensions and mass characteristics of the guided missile in general and its structural components and subsystems; power, thrust and consumption characteristics of the main engine; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by solving design problems. Applications of the developed program were studied to present the research results in a user-friendly form.

Key words: 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 object

Bibliography:
1. Degtyarev A. V. Rocket Engineering: Problems and Prospects. Selected scientific-technical publications. Dnepropetrovsk, 2014. 420 p.
2. Shcheverov D. N. Designing of Unmanned Aerial Vehicles. М., 1978. 264 p.
3. Sinyukov А. М. et al. Ballistic Solid-Propellant Rocket / Under the editorship of A. M. Sinyukov. М., 1972. 511 p.
4. Varfolomeyev V. I. Designing and Testing of Ballistic Rockets / Under the editorship of V. I. Varfolomeyev, M. I. Kopytov. М., 1970. 392 p.
5. Vinogradov V. A., Grushchansky V. A., Dovgodush S. I. et al. Effectiveness of Complex Systems. Dynamic Models. М., 1989. 285 p.
6. Il’ichyov A. V., Volkov V. D., Grushchansky V. A. Effectiveness of Designed Complex Systems’ Elements. М., 1982. 280 p.
7. Krotov V. F., Gurman V. I. Methods and Problems of Optimal Control. М., 1973. 446 p.
8. Pontryagin L. S. et al. Mathematical Theory of Optimal Processes. М., 1969. 385 p.
9. Tarasov E. V. Algorithms of Flying Vehicles Optimal Designing. М., 1970. 364 p.
10. Alpatov A. P., Sen’kin V. S. Complex Task of Optimization of Space Rocket Basic Design Parameters and Motion Control Programs. Technical Mechanics. 2011. No. 4. P. 98-113.
11. Alpatov A. P., Sen’kin V. S. Methodological Support for Selection of Launch Vehicle Configuration, Optimization of Design Parameters and Flight Control Programs. Technical Mechanics. 2013. No. 4. P. 146-161.
12. Sen’kin V. S. Optimization of Super-Light Launch Vehicle Design Parameters. Technical Mechanics. 2009. No. 1. P. 80-88.
13. Sen’kin V. S. Flight Control Optimization and Thrust Optimization of Controllable Rocket Object Main Propulsion System. Technical Mechanics. 2000. No. 1. P. 46-50.
14. Syutkina-Doronina S. V. On Problem of Optimization of Design Parameters and Control programs of a Rocket Object With Solid Rocket Motor. Aerospace Engineering and Technology. 2017. No. 2 (137). P. 44-59.
15. Lebedev А. А., Gerasyuta N. F. Rocket Ballistics. М., 1970. 244 p.
16. Razumov V. F., Kovalyov B. K. Design Basis of Solid-Propellant Ballistic Missiles. М., 1976. 356 p.
17. Yerokhin B. T. SRM Theoretical Design Basis. М., 1982. 206 p.
18. Abugov D. I., Bobylyov V. M. Theory and Calculation of Solid Rocket Motors. М., 1987. 272 p.
19. Shishkov А. А. Gas Dynamics of Powder Rocket Motors. М., 1974. 156 p.
20. Sen’kin V. S. Complex Task of Optimization of Super-Light Solid-Propellant Launch Vehicle Design Parameters and Control Programs. Technical Mechanics. 2012. No. 2. P. 106-121.
21. Methodological Support to Determine in Initial Designing Phase the Design Parameters, Control Programs, Ballistic, Power, and Mass-Dimensional Characteristics of Controllable Rocket Objects Moving In Aeroballistic Trajectory: R&D Report. ITM of NASU and SSAU, Yuzhnoye SDO. Inv. No. 40-09/2017. 2017. 159 p.

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12.2.2018 Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs
12.2.2018 Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs
12.2.2018 Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs

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]]> 9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps https://journal.yuzhnoye.com/content_2018_2-en/annot_9_2_2018-en/ Thu, 07 Sep 2023 11:25:59 +0000 https://journal.yuzhnoye.com/?page_id=30763
Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent: Patent 6640536 USA: MPK F02K9/50, F02K9/48, F02K9/46, F02K9/72, F02K9/56 / Korey R.
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9. The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps

Authors:

Nazarenko G. V., Filippenko P. P., Strelchenko O. Y., Deshevykh S. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 76-82

DOI: https://doi.org/10.33136/stma2018.02.076

Language: Russian

Annotation: In the present-day rocket engineering, the liquid rocket engines with pump feed system have gained wide acceptance. As a rule, the pumps used in liquid rocket engines are screw-axifugal. The screw serves to increase pressure upstream of the axifugal wheel, thus ensuring its cavitation-free operation. The screws used in the screw-axifugal pumps of liquid rocket engines may be of two types: with constant and variable step. The screws with constant step are easier to calculate, profile and manufacture as compared to the screws with variable step. As known from the literature, the use of the screw with variable step increases power characteristics of the screw-axifugal pump. The purpose of investigation is comparative analysis of cavitation and power characteristics of the following high-speed low-consumption screw-axifugal pumps of liquid rocket engines with jointed screws, screws of constant and variable step:  RD868 engine oxidizer and fuel pumps;  RD859 engine fuel pumps;  RD861K engine fuel pumps. Besides, the analysis has been made of the impact of design features and geometrical dimensions of the screws with variable and constant step on power characteristics of the screw-axifugal high-speed lowconsumption pumps of liquid rocket engines. Special attention has been given to the analysis of anticavitation properties of the pumps with screws of variable step and pumps with jointed screws. Based on the results of investigation, it has been ascertained that when using the joint screws and screws with variable step instead of the screws with constant step in the high-speed low-consumption screw-axifugal pumps of liquid rocket engines, the pump delivery head increases from 0.65 to 3.83%, the efficiency increases up to 1.7%. The use of jointed screw and screw of variable step as compared with the screw of constant step does not have any impact on cavitation properties of low-consumption crew-axifugal pumps of liquid rocket engines.

Key words: pressure characteristic, cavitation characteristic, inducers of the variable-pitch, continuous-pitch inducers, pump efficiency

Bibliography:
1. Pre-burner operating method for rocket turbopump: Patent 6505463 USA: MPK F02K9/48 / William D. Kruse, Thomas J. Mueller, John J. Weede (USA); Northrop Grumman Corporation. No. 20020148215; claimed 17.01.2001; published 14.01.2003, Bulletin No. 09/761,957. 5 p.
2. Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent: Patent 6640536 USA: MPK F02K9/50, F02K9/48, F02K9/46, F02K9/72, F02K9/56 / Korey R. Kline, Kevin W. Smith, Eric E. Schmidt, Thomas O. Bales; Hy Pat Corporation (Miami, FL). No. 20030136111; claimed 22.01.2002; published 04.11.2003, Bulletin No. 10/054,646. – 11 p.
3. Chebayevsky V. F., Petrov V. I. Cavitation Characteristics of High-Speed Auger-Centrifugal Pumps. М., 1973. 152 p.
4. Petrov V. I., Chebayevsky V. F. Cavitation on High-Speed Impeller Pumps. М., 1982. 192 p.
5. Ovsyanikov V. B., Borovsky B. I. Theory and Calculation of Liquid Rocket Engines Generator Sets. М, 1986. 376 p.
6. Borovsky B. I. Power Parameters and Characteristics of High-Speed Impeller Pumps. М., 1989. 181 p.

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9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps
9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps
9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps

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]]> 8.1.2018 The Solid–Propellant Motors with Regulated Thrust https://journal.yuzhnoye.com/content_2018_1-en/annot_8_1_2018-en/ Tue, 05 Sep 2023 06:26:08 +0000 https://journal.yuzhnoye.com/?page_id=30458
Solid Rocket Motor Dynamics. Solid Rocket Motor Gas Thermodynamics.
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8. The Solid–Propellant Motors with Regulated Thrust

Authors:

Glazkov V. O., Yenotov V. H., Kozak L. R., Fomenko V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 46-52

DOI: https://doi.org/10.33136/stma2018.01.046

Language: Russian

Annotation: The paper considers the results of scientific research and experimental works performed by Yuzhnoye SDO on solid–propellant motors with controlled thrust. The possibility in principle is shown of creating such motors and stabilizing their characteristics in different operation modes due to the throat area regulation system and selection of relevant control algorithm.

Key words:

Bibliography:
1. Petrenko V. I., Sokoovsky M. I. et al. Control of Solid-Propellant Propulsion Systems. М., 2003. 463 p.
2. Presnyakov V. F. Solid Rocket Motor Dynamics. М., 1984. 248 p.
3. Sorokin R. E. Solid Rocket Motor Gas Thermodynamics. М., 1967. 368 p.

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8.1.2018 The Solid–Propellant Motors with Regulated Thrust
8.1.2018 The Solid–Propellant Motors with Regulated Thrust
8.1.2018 The Solid–Propellant Motors with Regulated Thrust
]]> 5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew https://journal.yuzhnoye.com/content_2018_1-en/annot_5_1_2018-en/ Tue, 05 Sep 2023 06:16:22 +0000 https://journal.yuzhnoye.com/?page_id=30421
Investigations and Bench Testing of Solid Rocket Motors.
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5. Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew

Authors:

Bezkrovny І. B., Lysenko M. T., Tregubenko О. О.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 27-30

DOI: https://doi.org/10.33136/stma2018.01.027

Language: Ukrainian

Annotation: The paper gives reasons for conducting experimental works to determine lateral force caused by eccentricity and skew of SRM thrust vector, considers the configuration of fixed test stand for respective experimental works with vertical position of motor axis and describes the fixed test stand operation principle.

Key words:

Bibliography:
1. Volkov V. T., Yagodnikov D. A. Investigations and Bench Testing of Solid Rocket Motors. М., 2007. 296 p.
2. Beskrovny I. B., Kirichenko A. S., Balitsky I. P. et al. The Company’s Experience in Designing and Operation of SRM Test Rigs. Space Technology. Missile Armaments: Collected book of scientific-technical articles / Yuzhnoye SDO. Dnepropetrovsk, 2008. Issue 1. P. 119-127.

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5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew
5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew
5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew
]]> 11.1.2017 Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors https://journal.yuzhnoye.com/content_2017_1/annot_11_1_2017-en/ Wed, 28 Jun 2023 12:21:35 +0000 https://journal.yuzhnoye.com/?page_id=29442
Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors Authors: Sokolov O. (2017) "Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors" Космическая техника. "Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors" Космическая техника. quot;Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors", Космическая техника. Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors Автори: Sokolov O. Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors Автори: Sokolov O. Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors Автори: Sokolov O. Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors Автори: Sokolov O.
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11. Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors

Authors:

Sokolov O. V., Sheiko А. F., Fomenko V. S., Kirichenko A. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 70-77

Language: Russian

Annotation: The mathematical models are presented and the calculations are made of lower atmosphere contamination with solid propellant combustion products, noise and thermal effects on environment in the test bench area. Based on earlier field investigations and on the results obtained, the assessment is given of ecological safety of the tests.

Key words:

Bibliography:
1. Noise Control in Industry: Guide / Under the editorship of E. Y. Yudin. М., 1985.
2. Maximum Permissible Concentrations and Approximate Safe Levels of Contaminating Substances Effect in Atmospheric Air of Populated Areas. Donetsk, 2000.
3. GOST 12.1.005-88. System of Labor Safety Standards. General Sanitary-Hygienic Requirements to Working Area Air / Collection of GOSTs. М., 1988.
4. Gusev N. G., Belyayev V. A. Radioactive Emissions in Biosphere: Guide. 2nd edition. M., 1991. 256 p.
5. Investigation of Environment Pollution during Tests of 365-Type Article on PMZ Site: Report on research work / MPO Technokhim, NPO GIPH. Leningrad, 1991.
6. Assessment of Hygienic Situation in the Area of Pavlograd Mechanical Plant during Tests of 15D365 Articles. Report by Agreement No48-6/91-429 YuR-1/Ministry of Health Protection of the USSR. M., 1991.

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11.1.2017 Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors
11.1.2017 Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors
11.1.2017 Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors
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