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There were two conditions of plasma creation during the research: free location of samples on the surface of the cathode (configuration I) and inside the hollow cathode (configuration II). The results of the conducted research can be used to strengthen the surfaces of the steel parts in rocket and space technology, applying high-strength coatings. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
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12. Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge

Authors:

Nadtoka V. M.1, Shtapenko Ye. P.2, Kraeva V. S.1, Kraev M. V.1

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Ukrainian State University of Science and Technologies2

Page: Kosm. teh. Raket. vooruž. 2024, (1); 102-113

DOI: https://doi.org/10.33136/stma2024.01.102

Language: Ukrainian

Annotation: Steel hardening technology is considered, which implies modification of the steel surface with the method of ion-plasma nitriding in glow discharge. Ion-plasma nitriding is a multi-factor process, which requires the study of the influence of nitriding process conditions on the structure of modified layers, which, in its turn, determines their mechanical properties. The subjects of research included: austenitic steel 12X18Н10T, carbon steel Ст3 and structural steel 45. There were two conditions of plasma creation during the research: free location of samples on the surface of the cathode (configuration I) and inside the hollow cathode (configuration II). Optimal parameters of the ion-plasma nitriding process have been determined, which provide stability of the process and create conditions for intensive diffusion of nitrogen into the steel surface. Hydrogen was added to the argon-nitrogen gaseous medium to intensify the nitriding process. Working pressure in the chamber was maintained within the range of 250-300 Pa, the duration of the process was 120 minutes. Comparative characteristics of the structure and microhardness of the modified surfaces of the steels under study for two ion-plasma nitriding technologies are presented. Metallographic examination of the structure of the surface modified layers in the cross section showed the presence of the laminated nitrided layer, which consists of different phases and has different depths, depending on the material of the sample and treatment mode. Nitrided layer of 12Х18Н10Т steel consisted of four sublayers: upper “white” nitride layer, double diffuse layer and lower transition layer. The total depth of the nitrided layer after the specified treatment time reached 23 μm, use of hollow cathode increased it by 26% to 29 μm. The nitrided layers of steel Ст3 and steel 45 consisted of two sublayers – thick “white” nitride layer and general diffuse layer with a thickness of about 18 μm. The microhardness of the nitrided layer of steel Ст3 was 480 HV, increasing by 2,5 times, and for steel 45 was 440 HV, increasing by 1,7 times. The use of hollow cathode for these steels reduces the depth of the nitrided layer, but at the same time the microhardness increases due to the formation of a thicker and denser nitride layer on the surface. The results of the conducted research can be used to strengthen the surfaces of the steel parts in rocket and space technology, applying high-strength coatings.

Key words: ion nitriding, glow discharge, cross-sectional layer structure, hardening, microhardness

Bibliography:

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12.1.2024 Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge
12.1.2024 Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge
12.1.2024 Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge

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]]> 14.1.2024 EXPERIMENTAL STUDIES OF THE PERFORMANCE OF PYROTECHNIC DEVICES INSTALLED ON THE LAUNCH VEHICLE SEPARATION SYSTEMS https://journal.yuzhnoye.com/content_2024_1-en/annot_14_1_2024-en/ Mon, 17 Jun 2024 07:52:20 +0000 https://journal.yuzhnoye.com/?page_id=35004
2024, (1); 121-128 DOI: https://doi.org/10.33136/stma2024.01.121 Language: Ukrainian Annotation: Pyrotechnic devices are important elements in rocket and space technology, which to a large degree determine the flight success of the launch vehicles, since they enable instantaneous operations to separate spent stages, change configurations, ensure safety, etc.
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14. Experimental studies of the performance of pyrotechnic devices installed on the launch vehicle separation systems

Автори: Bolyubash Ye. S.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 121-128

DOI: https://doi.org/10.33136/stma2024.01.121

Language: Ukrainian

Annotation: Pyrotechnic devices are important elements in rocket and space technology, which to a large degree determine the flight success of the launch vehicles, since they enable instantaneous operations to separate spent stages, change configurations, ensure safety, etc. Pyrotechnic devices are subject to strict requirements for reliability, safety, security and efficiency. The article presents an experimental study of the performance of a linear shaped charge of a launch vehicle stage separation system. This type of linear shaped charge is one of the most common types of linear shaped charge, which are used in launch vehicle separation systems being developed in Ukraine. One of the main characteristics of the linear shaped charge, which determines the efficiency and reliability of the separation process, is the depth of penetration of the cumulative jet into the obstacle. The work studied the effect of a cumulative jet of a linear shaped charge with a semi-cylindrical cumulative part. An experimental confirmation of the performance of this type of linear shaped charge is presented, using the example of a linear shaped charge with a diameter of 5 mm, acting on an obstacle made of aluminum alloy grade 2219. The research methodology, experimental scenario, in particular, a description of the research object and a scheme for measuring test results are presented. Depth of cumulative jet penetration into the obstacle was measured in 60 points along the cut line of the samples under study. A statistical analysis of the experimental results was carried out, in particular, the average penetration depth was determined. An improved formula is proposed for the practical calculation of the penetration depth of a cumulative jet for a linear shaped charge with a semi-cylindrical cumulative part, using an additional correction factor. It is noted that the depth of penetration of a cumulative jet into an obstacle is significantly influenced by technological aspects. Taking into account this influence, the lower limit of the one-sided tolerance interval was determined. Recommendations are provided to improve future experimental procedures. Based on the obtained results, it was established that the linear shaped charges under study are operational and meet the requirements for linear shaped charges, installed on launch vehicle separation systems.

Key words: cumulative effect, shaped charge, linear shaped charge, separation systems, pyrotechnic separation devices, linear shaped charge parameters.

Bibliography:
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  2. Physika vzryva. Izd. tretie, t. ІІ. Pod red. L. P. Orlenko. Nauka, 2004, 644 s.
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  6. ISO 16269-6:2003 Statistical interpretation of data – Part 6: Determination of statistical tolerance intervals (IDT).
  7. Kobzar A. N. Prikladnaya matematicheskaya statistika. Dlya inzhenerov i nauchnykh rabotnikov. M.: Phizmatlit, 2006, 816 s.

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14.1.2024 EXPERIMENTAL STUDIES OF THE PERFORMANCE OF PYROTECHNIC DEVICES INSTALLED ON THE LAUNCH VEHICLE SEPARATION SYSTEMS
14.1.2024 EXPERIMENTAL STUDIES OF THE PERFORMANCE OF PYROTECHNIC DEVICES INSTALLED ON THE LAUNCH VEHICLE SEPARATION SYSTEMS
14.1.2024 EXPERIMENTAL STUDIES OF THE PERFORMANCE OF PYROTECHNIC DEVICES INSTALLED ON THE LAUNCH VEHICLE SEPARATION SYSTEMS

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]]> 7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system https://journal.yuzhnoye.com/content_2024_1-en/annot_7_1_2024-en/ Fri, 14 Jun 2024 11:36:31 +0000 https://journal.yuzhnoye.com/?page_id=34957
Its basic characteristics, composition, overall view and configuration are specified. Stated materials are of methodological nature and can be used to engineer the separation systems for LV stages, payload fairings, spacecraft etc. Antares – Spaceflight Insider: web site. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023). Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
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7. Selection of the functional units for the Cyclone-4M ILV separation system

Authors:

Logvinenko A. I., Makarenko A. O., Khomyak V. O., Olesiyuk A. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 61-71

DOI: https://doi.org/10.33136/stma2024.01.061

Language: Ukrainian

Annotation: Separation of the spent LV stages is one of the important problems of the rocket technology, which requires the comprehensive analysis of different types of systems, evaluation of their parameters and structural layouts. Basic requirements are specified that need to be taken into account when engineering the separation system: reliable and safe separation, minimal losses in payload capability, keeping sufficient distance between the stages at the moment of the propulsion system start. Detailed classification of their types («cold», «warm», «hot», «cold-launched» separation) is given and their technical substance with advantages and drawbacks is described. Certain types of «cold» and «warm» separation of the spent stages of such rockets as Dnepr, Zenit, Antares, Falcon-9 with different operating principle are introduced – braking with the spent stage and pushing apart two stages. Brief characteristics of these systems are given, based on the gas-reactive nozzle thrust, braking with solid-propellant rocket engines, separating with spring or pneumatic pushers. Development of the separation system for the advanced Cyclone-4M ILV is taken as an example and design sequence of stage separation is suggested: determination of the necessary separation velocity and capability of the separation units, determination of the number of active units, calculation of design and energy parameters of the separation units, analysis of the obtained results followed by the selection of the separation system. Use of empirical dependences is shown, based on the great scope of experimental and theoretical activities in the process of design, functional testing and flight operation of similar systems in such rockets as Cyclone, Dnepr and Zenit. According to the comparative analysis results, pneumatic separation system to separate Cyclone-4M Stages 1 and 2 was selected as the most effective one. Its basic characteristics, composition, overall view and configuration are specified. Stated materials are of methodological nature and can be used to engineer the separation systems for LV stages, payload fairings, spacecraft etc.

Key words: separation system, functional units of separation, «cold separation», «warm separation», pneumatic pusher, spring pusher, SPRE, gas-reactive nozzles, Zenit LV, Dnepr LV, Falcon 9 rocket, Cyclone-4М LV.

Bibliography:
  1. Pankratov Yu. , Novikov A. V., Tatarevsky K. E., Azanov I. B. Dynamika perekhodnykh processov. 2014.
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  5. Antares – Spaceflight Insider: web site. URL: https://www. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023).
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  8. Cyclone-4M – website URL: https://www.yuzhnote.com (data zvernennya 31.10.2023)
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7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system
7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system
7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system

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]]> 23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body https://journal.yuzhnoye.com/content_2018_2-en/annot_23_2_2018-en/ Thu, 07 Sep 2023 12:35:25 +0000 https://journal.yuzhnoye.com/?page_id=30813
configuration space of the body and corresponding metric lines of the space are considered. ~ in every point of the configuration space and is expressed as   As a result metric lines of the configuration space under conditions of beam acceleration become polarized lines, generating vector information inertia field. Interaction of mechanical particles with the information inertia field in the configuration space generates physical inertia field of force, providing the real inertia under accelerated motion of the beam. Key words: configuration space , modified method of sections , information and vacuum environment , metric lines , property of space reflection , polarization , scalar information field , vector information field Bibliography: 1. configuration space , modified method of sections , information and vacuum environment , metric lines , property of space reflection , polarization , scalar information field , vector information field .
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23. On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

Authors:

Muliar Yu. M., Fedorov V. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 190-206

DOI: https://doi.org/10.33136/stma2018.02.190

Language: Russian

Annotation: Presented is the theoretical justification of the phenomenon of the inertia initiation under accelerated motion of the body, and gravity origin in the circumterrestrial space. There is no description of the physical nature of the inertia and gravity in the scientific publications. In the phenomenological approach under study, allowing for reflection properties of the space, earlier unknown interdependent information-physical link of the body and its mechanical particles with space under the accelerated motion was determined in the state of rest of the gravitation field as well as in the state of weightlessness. Alongside with the environment, eigenspace, i.e. configuration space of the body and corresponding metric lines of the space are considered. Idea of metric lines agrees with the concept of F. Wilczek, the American physicist, Nobel-Prize laureate, on the existence of the unobservable metric field in the real space. Solution of the problem rests on the example of the cantilever beam and mathematical model of the information reflection process, which for the first time takes into consideration previously unknown property of space reflection. Under the accelerated motion of the body reflection gains the acceleration vector dt d а     . In this case reflection manifests itself in the initiation of the beam of polarization vector under study   ~ in every point of the configuration space and is expressed as     ~ а . Value of the polarization vector equals the value of acceleration vector with negative sign. As a result metric lines of the configuration space under conditions of beam acceleration become polarized lines, generating vector information inertia field. Interaction of mechanical particles with the information inertia field in the configuration space generates physical inertia field of force, providing the real inertia under accelerated motion of the beam. (Relatively slow motion of bodies is studied as compared to the speed of light). According to the set forth unconventional approach the nature of the earth gravity is conditioned by the polarization of the radial metric lines of the circumterrestrial space. And polarization vector is directed to the center of the Earth and equals acceleration vector of the free fall with the same sign. Interaction of the body with specific mass with the vector information field of the Earth generates the physical force field of gravity. Article deals with the fundamental issues of theoretical physics and other fields of natural science. Materials of the conducted research are regarded as a potential scientific discovery.

Key words: configuration space, modified method of sections, information and vacuum environment, metric lines, property of space reflection, polarization, scalar information field, vector information field

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23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body
23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body
23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

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]]> 17.2.2018 Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine https://journal.yuzhnoye.com/content_2018_2-en/annot_17_2_2018-en/ Thu, 07 Sep 2023 12:17:39 +0000 https://journal.yuzhnoye.com/?page_id=30796
Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine Authors: Usichenko V. Such configuration can be of interest because turbojets have considerably smaller rate of flow in comparison to rocket engines. Korolev Samara State Aerospace University (National Research University). Spacecraft Earth Descent Dynamics М., 1970. (2018) "Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine" Космическая техника. Space technology. "Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine" Космическая техника. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
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17. Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine

Authors:

Usichenko V. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 143-150

DOI: https://doi.org/10.33136/stma2018.02.143

Language: Russian

Annotation: Basic dynamic properties of the reentry part of the aircraft-type first stage were examined when turbojet engine is used in the recovery phase. Such configuration can be of interest because turbojets have considerably smaller rate of flow in comparison to rocket engines. Moreover, they are launched in the lower stratosphere or in the troposphere so that there is no need to place oxidizer supply on board. This recovery plan differs from an alternative rocket recovery system and, from our point of view, provides more efficient usage of the fuel stores because it doesn’t require the main propulsion to be started in the recovery phase. Besides the analysis of qualitative characteristics of the descend phase for this stage, the efficiency of a wing with moderate values of maximum aerodynamic characteristics and a turbojet was studied. In this case three ways for stage recovery were investigated. The first one implied unguided descend with zero angle of attack assuming that the stage is statically stable. This descend trajectory was considered as standard and was used to evaluate the efficiency of the wing and turbojet with relatively small propulsion. The second and the third design cases offered the gliding guided descend with turbojet being started only in the lower stratosphere. The last two cases used the same program for the angle of attack. The possibility to ensure permissible overload values at the critical points of the descend trajectory and acceptable values of kinematic characteristics at the earth surface tangency point are also of great interest. Thereby the program for the angle of attack was developed in a way that allowed kinematic characteristics on touchdown be as close as possible to the corresponding values, shown by civil and/or military-transport heavy aircraft. Simulation was conducted on Microsoft Visual Studio 2010.

Key words: guided descent, turbojet, kinematic characteristics, tangency point, civil aviation

Bibliography:
1. Kuznetsov Y. L., Ukraintsev D. S. Analysis of Impact of Flight Scheme of Stage with Rocket-Dynamic Recovery System on Payload Capability of Medium-Class Two-Stage Launch Vehicle. New of S. P. Korolev Samara State Aerospace University (National Research University). 2016. Vol. 15, No. 1. P. 73-80. https://doi.org/10.18287/2412-7329-2016-15-1-73-80
2. Andreyevsky V. V. Spacecraft Earth Descent Dynamics М., 1970. 230 p.

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17.2.2018 Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine
17.2.2018 Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine
17.2.2018 Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine

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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
Complex Task of Optimization of Space Rocket Basic Design Parameters and Motion Control Programs. Methodological Support for Selection of Launch Vehicle Configuration, Optimization of Design Parameters and Flight Control Programs. Aerospace Engineering and Technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology. Space technology.
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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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]]> 4.1.2019 Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays https://journal.yuzhnoye.com/content_2019_1-en/annot_4_1_2019-en/ Thu, 25 May 2023 12:09:18 +0000 https://journal.yuzhnoye.com/?page_id=27709
As a result of analysis of the current situation with the stress-strain state studies of the complex configuration shell structures and mathematical support of the load-bearing capacity calculation of the aerospace structures, the following actual research trends can be singled out: 1) improvement of the methods of analytical estimation of the thin-walled structures’ strength and resistance; 2) improvement of the numerical methods of composite materials mechanical properties analysis; 3) development or application of the existing software packages and ADE-systems, automatizing stress-strain state analysis with visualization of the processes under study.
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4. Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays

Authors:

Akimov D. V.1, Larionov I. F.1, Klimenko D. V.1, Gryshchak V. Z.2, Gomenyuk S. I.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Zaporizhzhia National University, Zaporizhzhia, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2019, (1); 21-27

DOI: https://doi.org/10.33136/stma2019.01.021

Language: Russian

Annotation: This paper presents the overview and features of the stress-strain state analysis of the multilayer shell structures widely used in the design of the missile compartments. As a result of analysis of the current situation with the stress-strain state studies of the complex configuration shell structures and mathematical support of the load-bearing capacity calculation of the aerospace structures, the following actual research trends can be singled out: 1) improvement of the methods of analytical estimation of the thin-walled structures’ strength and resistance; 2) improvement of the numerical methods of composite materials mechanical properties analysis; 3) development or application of the existing software packages and ADE-systems, automatizing stress-strain state analysis with visualization of the processes under study. One of the most important steps of the third research trend is development of the initial data input media (setting the model parameters) and presentation of analysis results with account of the user interface visualization. The description of the mathematical simulation and experimental studies of the stress-strain state of the interstage bay made of carbon fiber sandwich structure is presented and short description of the structure condition after the tests is provided. Based on the analysis it can be concluded that development of the geometric simulation methods, taking into account the manufacturing deviations, is an independent problem from the point of view of practical applications in the aerospace technology.

Key words: sandwich structure, interstage bay, finite-element model, manufacturing deviations, test loads

Bibliography:

1. Vorovich I. I., Shlenev M. A. Plastiny I obolochki // Itogi nauki. Mechanika: Sbornik obzorov. M.: Nauka, 1963. P. 91–176.
2. Grigolyuk E. I., Kogan F. A. Sovremennoe sostoyanie teorii mnogosloynykh obolochek/ Prikladnaya mechanika. 972. T. 8, № 6. P. 3–17.
3. Grigolyuk E. I., Kulikov G.M. Razvitie obschego napravlenia v teorii mnogo – р max=630…651 kg/cm2/ Kosmicheskay technika. Raketnoe vooruzhenie. Space Technology. Missile Armaments. 2019. Vyp. 1 (117) 27 sloinykh obolochek/ Mechanika compositnykh materialov. 1972. T. 8, № 6. P. 3–17.
4. Grigorenko Ya. M., Vasilenko A. T., Pankratova N. D. K otsenke dopuscheniy teorii trekhsloinykh obolochek s zapolnitelem // Prikladnaya mechanika. 1984. T. 20, № 5. P. 19–25.
5. Dudchenko A. A., Lurie S. A., Obraztsov I. F. Anizotropnye mnogosloynye plastiny I obolochki / Itogi nauki I techniki. Mechanika deformiruemogo tverdogo tela. T. 15. M.: VINITI, 1983. P. 3–68.
6. Kurshin L. M. Obzor rabot po raschetu trekhsloynykh plastin I obolochek / Raschet prostranstvennykh konstruktsiy. Vyp. 1. M.: Gosstroyizdat, 1962. P. 163–192.
7. Noor A. K., Burton W. S., Bert C. W. Computational Models for Sandwich Panels and Shells / Applied Mechanics Reviews. 1996. Vol. 49, No 3. P. 155–199.
8. Piskunov V. G., Rasskazov A. O. Razvitie teorii cloistykh plastin I obolochek // Prikladnaya mechanika. 2002. T. 38, № 2. P. 22–56.
9. Grigorenko Ya. M., Budak V. D., Grigorenko O. Ya. Rozvyazannya zadach teorii bolonok na osnovi disrento –continualnykh metodiv: Navch. posib. Mykolaiv: Ilion, 2010. 294 p.
10. Carrera Е., Brischetto S. A Survey With Numerical Assessment of Classical and Refined Theories for the Analysis of Sandwich Plates // Applied Mechanics Reviews. 2009. Vol. 62, No 1. P. 1–17.
11. Grigolyuk E. I. Uravnenia trekhsloinykh obolochek s legkim zapolnitelem // Izv. AN SSSR. Otdelenie tekhnicheskikh nauk. 1957. № 1. P. 77–84.
12. Ambartsumyan S. A. Teoria anizotropnykh plastin: Prochnost’, ustoichivost’ i kolebania. M.: Nauka, 1987. 360 p.
13. Carrera Е. Historical review of Zig-Zag theories for multilayered plates and shells / Applied Mechanics Reviews. 2003. Vol. 56, No 3. P. 287–308.
14. Teichman F. K., Wang C.-T. Finite deflections of Curved Sandwich Cylinders. Sherman M. Fairchild Publ. Fund. Inst. Aero. Sci. Paper FF-4. Institute of the Astronautical Sciences, 1951. P. 14.
15. Teichman F. K., Wang C.-T., Gerard G. Buckling of Sandwich Cylinders under Axial Compression / Journal of the Aeronautical Sciences. 1951. Vol. 18, No 6. P. 398–406.
16. Vinson J. R. Sandwich Structures / Applied Mechanics Reviews. 2001. Vol. 54, No 4. P. 201–214.
17. Lin J., Fei Y., Zhihua W., Longmao Z. A numerical simulation of metallic cylindrical sandwich shells subjected to air blast loading / Latin American Journal of Solids and Structures. 2013. Vol. 10. P. 631–645.
18. Wu J., Pan L. Nonlinear theory of multilayer sandwich shells and its application (I) – general theory // Applied Mathematics and Mechanics. 1997. Vol. 18, No 1. P. 19–27.
19. Xu J., Wang C., Liu R. Nonlinear stability of truncated shallow conical sandwich shell with variable thickness / Applied Mathematics and Mechanics. 2000. Vol. 21, No 9. P. 977–986.
20. Komissarova G. L., Klyuchnikova V. G., Nikitenko V. N. K otsenke predelov primenimosti priblizhennykh teoriy sloistykh plastin// Prikladnaya mechanika. 1979. T. 15, № 6. P. 131–134.
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22. Kien T. N., Tai H. T., Thuc P. V. A refined higher-order shear deformation theory for bending, vibration and buckling analysis of functionally graded sandwich plates / Steel and Composite Structures. 2015. Vol. 18, No 1. P. 91–120.
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24. Chumachenko Ye. N., Polyakova T. V., Aksenov A. S. i dr. Matematicheskoe modelirovanie v nelineinoy mechanike: Obzor programmnykh complexov dlya resheniya zadach modelirovania slozhnykh system, Pr-2155. M.: Institut kosmicheskykh issledovaniy RAN, 2009. 44 p.
25. Opyt i novye tekhnologii inzhenernogo analiza v interesakh kosmosa: press-reliz / I. Novikov / GNKTs im. M. V. Khrunicheva. Rezhim dostupa: www.khrunichev.ru/ main.php?id=18mid=2132.

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4.1.2019 Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays
4.1.2019 Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays
4.1.2019 Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays

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Analysis of Spacecraft Control Issues In Early Design Phases Authors: Ivanova G. 2019, (1); 15-20 DOI: https://doi.org/10.33136/stma2019.01.015 Language: Russian Annotation: Mission control of the orbital space plane is one of the actual and complicated applied problems of the theory of mobile objects control. Dynamic configuration of this plane as an object of control is described by the system of non-linear differential equations of higher order. Thereupon the stability analysis in the linear setting is the necessary link in the process of orbital space plane control system development.
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3. Analysis of Spacecraft Control Issues In Early Design Phases

Authors:

Ivanova G. A., Khoroshilov V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

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

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

Language: Russian

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

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

Bibliography:

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

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3.1.2019 Analysis of Spacecraft Control Issues In Early Design Phases
3.1.2019 Analysis of Spacecraft Control Issues In Early Design Phases
3.1.2019 Analysis of Spacecraft Control Issues In Early Design Phases

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