Search Results for “launch complex” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 05 Nov 2024 20:32:02 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “launch complex” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 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/ 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. 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. Key words: multiple launch rocket systems (MLRS) ,
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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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]]> 9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes https://journal.yuzhnoye.com/content_2024_1-en/annot_9_1_2024-en/ Mon, 17 Jun 2024 08:48:18 +0000 https://journal.yuzhnoye.com/?page_id=35030
Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Key words: rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design. rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design.
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9. General-purpose thermostating module – new approach in development of up-to-date thermostating systems for rocket and space complexes

Authors:

Fateev D. M., Bikova G. M, Petukhov O. M., Pokataiev V. M.,Yelanskyi Yu. A.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 78-84

DOI: https://doi.org/10.33136/stma2024.01.078

Language: Ukrainian

Annotation: These days when creating any rocket space complex, it is important to ensure its advancement and competitive ability. To create such complex, the technical systems it consists of must be implemented with minimal economic and energy costs. Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Development of the competitive rocket and space complex also requires the new approach in the development of the thermostatting system. One of the main tasks is to create a system that can be mass-produced and used as part of any rocket and space complex. Solving this problem will significantly reduce the cost of creating and operating the thermostatting systems and the whole rocket and space complex. One of the ways to solve this task is to create a general-purpose thermostatting system. The modular principle for such thermostatting system would be optimal, which means making up a system from separate modules. It simplifies the all-round installation of various system options and simplifies its setup and operation. The paper demonstrates the possibility and prospects of creating modular thermostatting systems, which enable air supply with the required parameters to different consumers. Characteristics and design of the general-purpose thermostatting module are specified, which can be used as the main component without changing anything in the composition of stationary and mobile thermostatting systems.

Key words: rocket and space complex, launch vehicle, technological systems of the ground complex, thermostatting systems, open type system, versatility, modular design.

Bibliography:
  1. . Tsiklon-4M. URL: https://www. yuzhnoye.com.
  2. . KRK «Tsiklon-4M». C4M YZH SPS 090 02 Technicheskoe zadanie na sostavnuyu chast’ OKR «Sistema termostatirovaniya rakety-nositelya i golovnogo bloka» GP «KB «Yuzhnoye». 78 s.
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9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes
9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes
9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes

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]]> 16.1.2024 EDUCATIONAL TENDENCIES AS AN ELEMENT OF INNOVATIVE PROGRESS IN THE PERSONNEL TRAINING SYSTEM FOR THE STATE-OF-THE-ART ENTERPRISES https://journal.yuzhnoye.com/content_2024_1-en/annot_16_1_2024-en/ Mon, 17 Jun 2024 07:20:20 +0000 https://journal.yuzhnoye.com/?page_id=34966
The goal-oriented educational areas represent a complex of actions of several divisions at the enterprise, supervised by the scientific-educational center, which aim to provide the corresponding professional level of the employees busy with fulfilment of current job assignments. Among the most significant are the following areas: training of the executive personnel and its reserve; training in the postgraduate courses of the enterprise; learning computer technologies; preparation of the pre-launch processing personnel and its reserve; activities with intellectual property; involvement of the leading institutes of higher education both for training of young specialists and to obtain particular scientific results etc.
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16. Educational tendencies as an element of innovative progress in the personnel training system for the state-of-the-art enterprises

Автори: Zevako V. S.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 136-140.

DOI: https://doi.org/10.33136/stma2024.01.136

Language: Ukrainian

Annotation: Yuzhnoye SDO is one of the most state-of-the-art and hi-tech enterprises of the Ukraine’s space and rocket branch. To maintain its scientific and productive potential, among other things, the enterprise needs to have professional specialists, who are development-orientated and eager to enhance their professional skills. To solve this problem there is personnel training system at the enterprise. Responsibility to provide the Yuzhnoye SDO with the skilled specialists is shared, within their authority, between the staff department and the scientific-educational center of the enterprise, which directly report to the General Director. The goal-oriented educational areas, realized at the enterprise, occupy the special role in these activities. The goal-oriented educational areas represent a complex of actions of several divisions at the enterprise, supervised by the scientific-educational center, which aim to provide the corresponding professional level of the employees busy with fulfilment of current job assignments. Among the most significant are the following areas: training of the executive personnel and its reserve; training in the postgraduate courses of the enterprise; learning computer technologies; preparation of the pre-launch processing personnel and its reserve; activities with intellectual property; involvement of the leading institutes of higher education both for training of young specialists and to obtain particular scientific results etc. All these areas have already been proven and some of them run on continuing basis. Thus it can be concluded that the personnel training system is effective. It proves itself and can serve as an example of introduction at any manufacturing enterprise. Besides, orientation of training process at the individual goal-oriented educational areas involves and unites efforts of several interested enterprise divisions to reach particular and necessary results within certain timetable.

Key words: system of specialist training, goal-oriented educational area, training at the enterprise, professional training.

Bibliography:

1. Upravlenie personalom. Uchebnik dlya vuzov. Pod red. T.Yu. Bazarova, B.L. Yeremina.
2-e izd. peredel. i dop. M., YuNITI. 2002. 560 s.
2. Zevako V. S. Pidgotovka naukovo-pedagogichnykh kadriv dlya naukoemnogo pidpriemstva. Svit naukovykh doslidzhen’. Zbirnyk tez mizhnarodnoi naukovo-praktychnoi internet-conferentsii 24-25 bereznya 2022 r. Vyp. 7. S. 90 – 91.

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16.1.2024 EDUCATIONAL TENDENCIES AS AN ELEMENT OF INNOVATIVE PROGRESS IN THE PERSONNEL TRAINING SYSTEM FOR THE STATE-OF-THE-ART ENTERPRISES
16.1.2024 EDUCATIONAL TENDENCIES AS AN ELEMENT OF INNOVATIVE PROGRESS IN THE PERSONNEL TRAINING SYSTEM FOR THE STATE-OF-THE-ART ENTERPRISES
16.1.2024 EDUCATIONAL TENDENCIES AS AN ELEMENT OF INNOVATIVE PROGRESS IN THE PERSONNEL TRAINING SYSTEM FOR THE STATE-OF-THE-ART ENTERPRISES

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]]> 5.1.2024 Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight https://journal.yuzhnoye.com/content_2024_1-en/annot_5_1_2024-en/ Thu, 13 Jun 2024 06:00:42 +0000 https://journal.yuzhnoye.com/?page_id=34981
Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight Authors: Hladkyi E. 2024, (1); 40-50 DOI: https://doi.org/10.33136/stma2024.01.040 Language: English Annotation: Despite stringent environmental requirements, modern launch vehicles/integrated launch vehicles (LV/ILV) burn toxic propellants such as NTO and UDMH. The complexity of this lies in the need to take into account the characteristics of the atmosphere, primarily the wind. A zone dangerous for people was constructed using the proposed model for the case of the failure of the Dnepr launch vehicle, where the risks of toxic damage exceed the permissible level (10–6).
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5. Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight

Authors:

Hladkyi E. H., Sheiko А. F.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 40-50

DOI: https://doi.org/10.33136/stma2024.01.040

Language: English

Annotation: Despite stringent environmental requirements, modern launch vehicles/integrated launch vehicles (LV/ILV) burn toxic propellants such as NTO and UDMH. Typically, such propellants are used in the LV/ILV upper stages, where a small amount of propellant is contained; however, some LV/ILV still use such fuel in all sustainer propulsion stages. For launch vehicles containing toxic rocket propellants, flight accidents may result in the failed launch vehicle falling to the Earth’s surface, forming large zones of chemical damage to people (the zones may exceed blast and fire zones). This is typical for accidents occurring in the first stage flight segment, when an intact launch vehicle or its components (usually individual stages) with rocket propellants will reach the Earth’s surface. An explosion and fire following such an impact will most likely lead to a massive release of toxicant and contamination of the surface air. An accident during the flight segment of the LV/ILV first stage with toxic rocket propellants, equipped with a flight termination system that implements emergency engine shutdown in case of detection of an emergency situation, has been considered. To assess the risk of toxic damage to a person located at a certain point, it is necessary to mathematically describe the zone within which a potential impact of the failed LV/ILV will entail toxic damage to the person (the so-called zone of dangerous impact of the failed LV/ILV). The complexity of this lies in the need to take into account the characteristics of the atmosphere, primarily the wind. Using the zone of toxic damage to people during the fall of the failed launch vehicle, which is proposed to be represented by a combination of two figures: a semicircle and a half-ellipse, the corresponding zone of dangerous impact of the failed LV/ILV is constructed. Taking into account the difficulties of writing the analytical expressions for these figures during the transition to the launch coordinate system and further integration when identifying the risk, in practical calculations we propose to approximate the zone of dangerous impact of the failed LV/ILV using a polygon. This allows using a known procedure to identify risks. A generalization of the developed model for identifying the risk of toxic damage to people involves taking into account various types of critical failures that can lead to the fall of the failed LV/ILV, and blocking emergency engine shutdown during the initial flight phase. A zone dangerous for people was constructed using the proposed model for the case of the failure of the Dnepr launch vehicle, where the risks of toxic damage exceed the permissible level (10–6). The resulting danger zone significantly exceeds the danger zone caused by the damaging effect of the blast wave. Directions for further improvement of the model are shown, related to taking into account the real distribution of the toxicant in the atmosphere and a person’s exposure to a certain toxic dose.

Key words: launch vehicle, critical failure, flight accident, zone of toxic damage to people, zone of dangerous impact of the failed launch vehicle, risk of toxic damage to people.

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  9. 9 GOST 12.1.005-88. Systema standartov bezopasnosti truda. Obschie sanitarno-gigienicheskie trebovaniya k vozdukhu rabochei zony. [GOST 12.1.005-88. Labor safety standards system. General sanitary and hygienic requirements to air of working zone].
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  11. 11 Kolichestvennaya otsenka riska chimicheskykh avariy. Kolodkin V. M., Murin A. V., Petrov A. K., Gorskiy V. G. Pod red. Kolodkina V. M. Izhevsk: Izdatelskiy dom «Udmurtskiy universitet», 2001. 228 s. [Quantitative risk assessment of accident at chemical plant. Kolodkin V., Murin A., Petrov A., Gorskiy V. Edited by Kolodkin V. Izhevsk: Udmurtsk’s University. Publish house, 2001. 228 p. (in Russian)].

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5.1.2024 Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight
5.1.2024 Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight
5.1.2024 Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight

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]]> 11.2.2017 Remote Monitoring Method of Pneudraulic System Structural Elements Integrity https://journal.yuzhnoye.com/content_2017_2/annot_11_2_2017-en/ Thu, 30 May 2024 12:33:16 +0000 https://journal.yuzhnoye.com/?page_id=29781
2017 (2); 57-59 Language: Russian Annotation: The remote control method of launch vehicle hydrosystem detachable joints airtightness by mass spectrometer at the Launch Complex in conditions of limited access to hydrosystem elements is under consideration.
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11. Remote Monitoring Method of Pneudraulic System Structural Elements Integrity

Authors:

Babii H. M., Tishchenko Y. S., Mogilevtsev O. А.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 57-59

Language: Russian

Annotation: The remote control method of launch vehicle hydrosystem detachable joints airtightness by mass spectrometer at the Launch Complex in conditions of limited access to hydrosystem elements is under consideration. The additional design development of hydrosystems prior to article roll-out to the launch side is provided for control.

Key words:

Bibliography:
1. Volkov V. P., Kulik A. V. et al. Technological Processes of Strength and Leak Tests in Space Rocketry Production / Under the editorship of L. D. Kuchma. Dnepropetrovsk, 2014. 264 p.
2. Sanin F. P. et al. Leak-Tightness in Space Rocketry: Tutorial / F. P. Sanin, E. O. Dzhur, L. D. Kuchma, V. A. Naidyonov. Dnipropetrovsk, 1995. 168 p.
3. Babkin V. T., Zaichenko A. A. et al. Leak-Tightness of Hydraulic Systems Fixed Connections. М., 1977. 120 p.
4. OST 92-1527-89. Leak Tests of Products Using Mass-Spectrometer Helium Leak Detectors. Test Methods. 138 p.

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11.2.2017 Remote Monitoring Method of Pneudraulic System Structural Elements Integrity
11.2.2017 Remote Monitoring Method of Pneudraulic System Structural Elements Integrity
11.2.2017 Remote Monitoring Method of Pneudraulic System Structural Elements Integrity
]]> 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
Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff Authors: Degtiarov М. Thermal stress analysis of orthotropic plate containing a rectangular hole using complex variable 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:

1. Elhefny A., Liang G. Stress and deformation of rocket gas turbine disc under different loads using finite element modeling. Propulsion and Power Research. 2013. № 2. P. 38–49. https://doi.org/10.1016/j.jppr.2013.01.002
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.
7. Xu F., Abdelmoula R., Potier-Ferry M. On the buckling and post-buckling of core-shell cylinders under thermal loading. International Journal of Solids and Structures. 2017. № 126–127. P. 17–36.
8. Wang Z., Han Q., Nash D. H., et. al. Thermal buckling of cylindrical shell with temperature-dependent material properties: Conventional theoretical solution and new numerical method. Mechanics Research Communications. 2018. № 92. P. 74–80.
9. Duc N. D. Nonlinear thermal dynamic analysis of eccentrically stiffened S-FGM circular cylindrical shells surrounded on elastic foundations using the Reddy’s third-order shear de-formation shell theory. European Journal of Mechanics A /Solids. 2016. № 58. P. 10–30.
10. Trabelsi S., Frikha A., Zghal S., Dammak F. A modified FSDT-based four nodes finite shell element for thermal buckling analysis of functionally graded plates and cylindrical shells. Engineering Structures. 2019. № 178. P. 444–459.
11. Trinh M. C., Kim S. E. Nonlinear stability of moderately thick functionally graded sandwich shells with double curvature in thermal environment. Aerospace Science and Technology. 2019. № 84. P. 672–685.
12. Лойцянский Л. Г. Механика жидкости и газа. М., 2003. 840 с.
13. Launder B. E., Sharma B. I. Application of the energy dissipation model of turbulence to the calculation of flow near a spinning disc. International Journal of Heat and Mass Transfer. 1974. № 1. P. 131–138.
14. Михеев М. А., Михеева И. М. Основы теплопередачи. М., 1977. 345 с.
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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]]> 13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses https://journal.yuzhnoye.com/content_2017_1/annot_13_1_2017-en/ Fri, 22 Sep 2023 15:13:28 +0000 https://journal.yuzhnoye.com/?page_id=29483
By calculation method, high reliability level was confirmed of hoses of joints being an interface elements of launch vehicle launch complexes.
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13. Reliability Evaluation of ILV Thermostating System Mating Hoses

Authors:

Bigun S. O.1, Khorolskyi M. S.2, Skokov O. I.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; State Enterprise DINTEM Ukrainian Research Design-Technological Institute of Elastomer Materials and Products2

Page: Kosm. teh. Raket. vooruž. 2017 (1); 84-87

Language: Russian

Annotation: The technique is proposed of reliability evaluation of space launch vehicle low pressure air thermostating system joints hoses. By calculation method, high reliability level was confirmed of hoses of joints being an interface elements of launch vehicle launch complexes.

Key words:

Bibliography:
1. Development of Single Action Units’ Hoses of Cyclone-4 Space Launch System Thermostating System: SOW for R&D 2G40.12.8599.608TЗ/Yuzhnoye SDO. 2009. 41 p.
2. Abramov E. I., Kolesnichenko K. A., Maslov V. T. Hydraulic Actuator Elements (Guide). Kyiv, 1969. 320 p.
3. Shor Y. B., Kuzmin F. I. Tables for Reliability Analysis and Control. М, 1968. 286 p.
4. Ventsel E. S. Theory of Probability. М., 1964. 576 p.

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13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses
13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses
13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses
]]> 21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV https://journal.yuzhnoye.com/content_2020_1-en/annot_21_1_2020-en/ Wed, 13 Sep 2023 12:05:46 +0000 https://journal.yuzhnoye.com/?page_id=31081
The main task of presented works was approbation of new approaches to improvement of space launch systems operation quality and operation process effectiveness by the example of prospective Cyclone-4M space rocket complex.
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21. Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV

Authors:

Hlechkov V. H.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 184-192

DOI: https://doi.org/10.33136/stma2020.01.184

Language: Russian

Annotation: The article deals with the problems of applying new approaches to formation and improvement of operation system. Turning of space hardware and services into marketable commodity requires their new qualities that determine competitiveness. The main task of presented works was approbation of new approaches to improvement of space launch systems operation quality and operation process effectiveness by the example of prospective Cyclone-4M space rocket complex. The works to form and improve its operation system were performed using the methods based on general theory of space systems operation and the pocedures based on the results of research work conducted by Yuzhnoye SDO in 2015 for analytical evaluation of launch services costs. The topicality of the article is confirmed by the results of practical application of new approaches in main directions of Cyclone-4M space rocket complex operation system improvement, which allowed increasing commercial attractibility of Yuzhnoye SDO-developed systems due to reduction of direct recurring costs and annual expenses. The article describes the course of development of operation model of a created object; based on investigation of the processes of this model, the object’s performance characteristics are detemined. The basis of the article are the organizational-and-technical decisions used herewith and the results obtained for Cyclone-4M space rocket complex. The article is of practical interest for specialists involved in creation of space rocket complexes and other sophisticated systems where the operation system is a multi-level organizational-technical system.

Key words: space hardware, launch services, performance characteristics, operation model, organizational-and-technical decisions

Bibliography:
1. Analiticheskaia otsenka ob’ema rabot i zatrat na puskovye uslugi i napravleniia rabot dlia ikh snizheniia v perspektivnykh RKK razrabotki GP “KB “Yuzhnoye”: tekhn. otchet / GP “KB “Yuzhnoye”. Dnepropetrovsk, 2015. 344 s.
2. Teoriia i praktika ekspluatatsii ob’ektov kosmicheskoi infrastruktury: monografiia / N. D. Anikeichik i dr. SPb., 2006. Т. 1: Ob’ekty kosmicheskoi infrastruktury. 400 s.
3. Ispytaniia i ekspluatatsiia raketnykh kompleksov: kurs lektsii / А. V. Agarkov i dr.; pod red. А. V. Degtyareva. GP “KB “Yuzhnoye”. Dnipro, 2016. Kn. 1. 505 s.

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21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV
21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV
21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV

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]]> 17.1.2020 Acoustic problems of rocket launch https://journal.yuzhnoye.com/content_2020_1-en/annot_17_1_2020-en/ Wed, 13 Sep 2023 11:36:44 +0000 https://journal.yuzhnoye.com/?page_id=31054
Acoustic problems of rocket launch Authors: Hrinchenko V. 2020, (1); 155-159 DOI: https://doi.org/10.33136/stma2020.01.155 Language: Russian Annotation: Due to an increase of power of rocket engines, the high intensity sound field generated by the exhaust jets have become an important factor, which determines the success rate of a rocket launch. Ensuring a successful launch of a rocket system became harder due to new engineering problems. Identification and definition of acoustic sources structure within a complex supersonic jet, being a one of the most important scientific problems, which have to be solved to find the ways to control accoustic radiation. It is recommended to use big amounts of water-air mix to protect the launch pad from damage.
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17. Acoustic problems of rocket launch

Authors:

Hrinchenko V. T.

Organization:

Institute of Hydromechanics of National Academy of Sciences of Ukraine, Kyiv, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 155-159

DOI: https://doi.org/10.33136/stma2020.01.155

Language: Russian

Annotation: Due to an increase of power of rocket engines, the high intensity sound field generated by the exhaust jets have become an important factor, which determines the success rate of a rocket launch. Ensuring a successful launch of a rocket system became harder due to new engineering problems. Identification and definition of acoustic sources structure within a complex supersonic jet, being a one of the most important scientific problems, which have to be solved to find the ways to control accoustic radiation. A three components of acoustic sources can be defined here – broadband signals from large and small components of of turbulent jet and tonal signals which usually being overlooked during the estimation of overall sound pressure level. The paper considers various aspects of acoustics of the launch of rocket systems, which includes characteristics of acoustic sources in supersonic jets, possibilities and physical limitation factors, under which it is possible to control the sound radiation. Among the possible ways to control the process of sound generation by a jet, a method of water injection in a jet is being studied. While saving the general thrust of the engine this method can not greatly reduce the sound radiation by a jet. It is recommended to use big amounts of water-air mix to protect the launch pad from damage. Significant progress on the topic of understanding the process of sound generation by supersonic jets can be achieved via mathematical modeling of sound radiation. The latest achievements of mathematical modeling of sound generation by supersonic jets being presented.

Key words: Acoustics of rocket launch, acoustic efficiency of a jet, semi-empirical models of of jet acoustics, numeric-computational methods in aeroacoustics, control of jet-generated acoustic levels

Bibliography:
1. Lighthill M. J. On Sound Generated Aerodynamically: I. General Theory. Proc. Roy. Soc. London Ser. A, 211. 1952. Р. 564–581. https://doi.org/10.1098/rspa.1952.0060
2. Tam C. K. W. Jet noise. Theoretical Computftional Fluid Dynamics. 1998. No 10. Р. 393–405. https://doi.org/10.1007/s001620050072
3. Lubert C. P. Sixty years of launch vehicle acoustics. Proc.Mtgs.Acoust. Vol. 31. 2017. https://doi.org/10.1121/2.0000704
4. Ask the Astronaut: What does launch feel like? URL: https://www.airspacemag. com/ask-astronaut/ask-astronaut-what-does-launch-feel-what-thoughts-and-emotions-run-through-your-mind-180959920/
5. Tim P. Ask an Astronaut: My Guide to Life in Space. 2018. 272 p.
6. Saucer B. What’s the Deal with Rocket Vibration? MIT Technology Review. July 15, 2009. URL: https://www.technology-review.com/s/414364https:/whats-the-deal-with-rocket-vibrations/
7. Ross D. Mechanics of Underwater noise. 1976. 266 p.
8. Varnier J. Experimental study and simulation of rocket engine free jet noise. AIAA J. 2001. Vol. 39, Nо 10. P. 1851–1859. https://doi.org/10.2514/2.1199
9. Eldred K. M. Acoustic loads generated by the propulsion system. NASA SP-8072, 1971. 49 p.
10. Balakrishnan P., Srinivason K. Impinging get noise reduction using non-circular jets. Applied Acoustics. 2019. Vol. 143. Р. 19-30. https://doi.org/10.1016/j.apacoust.2018.08.016
11. Tsutsumi S. Acoustic generation mechanism of a supersonic jet impinging on deflectors / S. Tsutsumi, R. Takaki, Y. Nakanishi, K. Okamoto, S. Teramoto 52th AIAA Aerospace Sci. Meet. AIAA Pap. 2014-0882. 2014. 12 p. https://doi.org/10.2514/6.2014-0882
12. Ahuja K. K., Manes J. P., Massey K. C., Calloway A. B. An Evaluation of various concepts of Reducing Supersonic Jet Noise, AIAA-90-3982. AIAA 13th Aeroacoustic Conference, 1990. Р. 1-21. https://doi.org/10.2514/6.1990-3982
13. Krathapalli A., Lenkatakrishnan L., Elovarsan R., Laurenco L. Supersonic Jet Noise Suppression by Water Injection. AIAA 2000-2025. 6th AIAA/CEAS Aeroacoustic Conference, 2000. Р. 1-25.
14. Moratilla-Vega M. A., Lackhole K., Janicka J., Xia H., Page C. J. Jet Noise Analysis using an Efficient LES/ High-Order Acoustic Coupling Method. Computer and Fluid. 2020. https://doi.org/10.1016/j.compfluid.2020.104438

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17.1.2020 Acoustic problems of rocket launch
17.1.2020 Acoustic problems of rocket launch
17.1.2020 Acoustic problems of rocket launch

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]]> 16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations https://journal.yuzhnoye.com/content_2020_1-en/annot_16_1_2020-en/ Wed, 13 Sep 2023 11:18:27 +0000 https://journal.yuzhnoye.com/?page_id=31052
A source of increased risk is the intense thermal and pressure impact of rocket propulsion jet on launch complex elements and on rocket itself. Therefore, a numerical simulation of processes is quite helpful in the design of launch complexes. The presented work contains simulation of liquid rocket engine combustion products jet flowing into the gas duct at the rocket lift-off, taking into account the following input data: the parameters of propulsion system, geometric parameters of launch complex elements, propulsion systems nozzles and gas duct. A three-dimensional geometric model of the launch complex, including rocket and gasduct, was constructed.
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16. Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

Authors:

Furkalo S. A., Stelmakh K. L., Lazarev T. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 149-154

DOI: https://doi.org/10.33136/stma2020.01.149

Language: Russian

Annotation: Launch vehicle lift-off is one of the most critical phases of the whole mission requiring special technical solutions to ensure trouble-free and reliable launch. A source of increased risk is the intense thermal and pressure impact of rocket propulsion jet on launch complex elements and on rocket itself. The most accurate parameters of this impact can be obtained during bench tests, which are necessary to confirm the operability of the structure, as well as to clarify the parameters and configuration of the equipment and systems of complex. However, full-scale testing is expensive and significantly increases the development time of the complex. Therefore, a numerical simulation of processes is quite helpful in the design of launch complexes. The presented work contains simulation of liquid rocket engine combustion products jet flowing into the gas duct at the rocket lift-off, taking into account the following input data: the parameters of propulsion system, geometric parameters of launch complex elements, propulsion systems nozzles and gas duct. A three-dimensional geometric model of the launch complex, including rocket and gasduct, was constructed. The thermodynamic parameters of gas in the engine nozzle were verified using NASA CEA code and ANSYS Fluent. When simulating a multicomponent jet, the equations of conservation of mass, energy, and motion were solved taking into account chemical kinetics. The three-dimensional problem was solved in ANSYS Fluent in steady-state approach, using Pressure-based solver and RANS k-omega SST turbulence model. The calculation results are the gas-dynamic and thermodynamic parameters of jets, as well as distribution of gas-dynamic parameters at nozzle exit, in flow and in boundary layer at gas duct surface. The methodology applied in this work makes it possible to qualitatively evaluate the gas-dynamic effect of combustion products jets on gas duct for subsequent optimization of its design.

Key words: liquid rocket engine, combustion products, multicomponent flow, ANSYS Fluent

Bibliography:
1. Bonnie J. McBride, Sanford Gordon. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications. II. Users Manual and Program Descriptions: NASA Reference Publication 1311. 1996.
2. Ten-See Wang. Thermophysics Characterization of Kerosene Combustion. Journal of Thermophysics and Heat Transfer. 2001. № 2, Vol. 15. P. 140–147. https://doi.org/10.2514/2.6602
3. Maas U., Warnatz J. Ignition Processes in Carbon-Monoxide-Hydrogen-Oxygen Mixtures: Twenty-Second Symposium (International) on Combustion. The Combustion Institute, 1988. P. 1695–1704. https://doi.org/10.1016/S0082-0784(89)80182-1
4. Timoshenko V. I. Teoreticheskiie osnovy tekhnicheskoj gazovoj dinamiki. Kiev, 2013. S. 154–155.

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16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations
16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations
16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

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