Search Results for “solid propellant charge mass” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 30 Jun 2026 12:57:39 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “solid propellant charge mass” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 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/ Wed, 12 Jun 2024 14:58:34 +0000 https://journal.yuzhnoye.com/?page_id=31037
Key words: solid propellant charge mass , propellant combustion rate , combustion chamber pressure , operation time in starting and cruise modes , combustion chamber pressure difference Bibliography: 1. solid propellant charge mass , propellant combustion rate , combustion chamber pressure , operation time in starting and cruise modes , combustion chamber pressure difference .
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10. Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

ISSN: 2617-5525

e-ISSN: 2617-5533

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 99-106

DOI: https://doi.org/10.33136/stma2020.01.099

Language: Russian

Annotation: The main solid rocket motors of surface-to-air missiles and some short-range missiles have, as a rule, two operation modes – starting (augmented rating) and cruise (with decreased propellant consumption level). The methods to calculate intraballistic characteristics of such motors have a number of peculiarities, which set them apart from the methods of determining the characteristics of motors with constant propellant consumption level. The purpose of this article is to analyze such peculiarities, design methods, to find interrelation between the parameters of propellant consumption diagram, to determine the impact on the latter of motor design features and propellant characteristics. To achieve this goal, the method of analytical dependencies was developed. The equations obtained show that the required parameters of diagrams (including consumption-thrust characteristics difference between the starting and cruise modes) can be ensured due to varying either case diameter or propellant combustion rate or due to combined variation of these values. In practice, the cases are possible when for some reasons it does not seem possible to vary the case diameter or propellant combustion rate and the requirements to consumption diagram cannot be satisfied to the full extent. The task of motor developer in that case consists in determination of acceptable (alternative) propellant consumption diagrams that would be closest to required. The proposed method is based on calculation and construction of nomograms of dependencies of relative propellant consumption in cruse mode on relative time of starting leg at different propellant combustion rates and constant (required) case diameter and vice versa, at different values of case diameter and constant (available) propellant combustion rate. Using these nomograms, the rocket developer can determine the propellant consumption diagram acceptable for the rocket. In a number of cases, design limitations for separate main motor assemblies are imposed on consumption characteristic diagram that have an impact on its required parameters. The presented materials allow evaluating that impact and contain the proposals to remove it. The presented method allows quickly determining the conditions needed to fulfill required propellant combustion products consumption diagrams and in case of nonfulfillment of these conditions – allow presenting alternative options for selection of most acceptable one.

Key words: solid propellant charge mass, propellant combustion rate, combustion chamber pressure, operation time in starting and cruise modes, combustion chamber pressure difference

Bibliography:
1. K vyboru velichiny davliniia v kamere sgoraniia marshevykh RDTT: tekhn. otchet / GP “KB “Yuzhnoye”. Dnipro, 2017. 19 s.
2. Enotov V. G., Kushnir B. I., Pustovgarova Е. V. Avtomatizirovannaia proektnaia otsenka kharakteristik marshevykh dvigatelei na tverdom toplive s korpusom iz vysokoprochnykh metallicheskikh materialov takticheskikh i operativno-takticheskikh raket: ucheb.-metod. posobie / pod red. А. S. Kirichenko. Dnepropetrovsk, 2014. 72 s.
3. Sorkin R. Е. Gasotermodinamika raketnykh dvigatelei na tverdom toplive. М, 1967. 368 s.
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14.1.2019 Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins https://journal.yuzhnoye.com/content_2019_1-en/annot_14_1_2019-en/ Wed, 24 May 2023 16:00:23 +0000 https://journal.yuzhnoye.com/?page_id=27719
...the estimation of safety margins in all phases of storage and operation of the device, consideration of the impact of the active factors (mass, temperature, loading, process of material aging), performance of calculations for the chosen specific zones of the device. Analysis of experimental and computation data as applied to solid-propellant rocket engine shows that the most dangerous zones, which define the service life, are the fuel charge channel (deformations at launch), a fuel-body coupling zone (breakaway coupling stress) and a “lock” zone of the release collar (concentration of shear and breakaway stresses and deformations).
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14. Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins

ISSN: 2617-5525

e-ISSN: 2617-5533

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 95-101

DOI: https://doi.org/10.33136/stma2019.01.096

Language: Russian

Annotation: Service life (resource) of the device (system, structure, material) is one of the major factors, which defines the reliable performance of the device or necessity of its replacement. The purpose of this paper is to develop the engineering methodology to estimate the service life of the device to support the well-founded design decision-making. The methodology of estimation of the service life of material or structure is based on the generalization of great amount of Yuzhnoye SDO experimental data and theoretical research on the impact of various factors (properties of materials, loads, storage and operation conditions) on their service life on the ground of strength analysis. At the same time, service life definition is based on the results of stress and deformation analyses and their comparison with strength properties of the applied material (tensile strength and deformation properties). Strength properties of the material should be reduced to test conditions in terms of temperature, pressure, rate of loading, degrees of material aging etc. Methodology provides the estimation of safety margins in all phases of storage and operation of the device, consideration of the impact of the active factors (mass, temperature, loading, process of material aging), performance of calculations for the chosen specific zones of the device. It is shown that the service life estimation is in general case a probabilistic observation because of the random combination of the influencing factors (strength properties, storage and operation conditions, loads). Analysis of experimental and computation data as applied to solid-propellant rocket engine shows that the most dangerous zones, which define the service life, are the fuel charge channel (deformations at launch), a fuel-body coupling zone (breakaway coupling stress) and a “lock” zone of the release collar (concentration of shear and breakaway stresses and deformations). Developed methodological guidelines of the engineering estimate of the service life can be used as the computational basis for the service life of materials and structures in the phase of system design and updating of the assumed design solutions.

Key words: stress, deformation, service life, aging, load

Bibliography:

1. Lyashevskiy A. V., Mironov Ye. A., Vedernikov M. V. Prognozirovanie srokov prigodnosti tverdykh raketnykh topliv metodom Roentgen-computrnoy tomografii// Aviatsionnaya i raketno-kosmichaskaya technika. №2. 2015. P. 118-123.
2. Schubert H., Menke K. Service Life Determination of Rocket Motors by Comprehensive Property Analysis of Propellant Grain / Athens, Greece, May, 1996, Simposium. №41 P. 1-10.
3. Hufferd W. L. Service Life Assessment for Space Launch Vehicles / Athens, Greece, May, 1996, Simposium. №46. P. 1-9.
4. Faulkner G. S., Tod D. Service Life Prediction Methodologies Aspects of the TTCP KTA-14 UK Programme / Athens, Greece, May, 1996, Simposium. – №24. P. 1-13.
5. Francis E. C. (England), Busswell H. J. Improvements in Rocket Motor Service Life Prediction / Athens, Greece, May, 1996, Simposium. №27. P. 1-13.
6. Collingwood G. A., Dixon M. D., Clark L. M., Becker E. B. Solid Rocket Motor Service Life Prediction Using Nonlinear Viscoelastic Analysis and Probabilistic Approach / Athens, Greece, May, 1996, Simposium. №29. P. 1-8.
7. Zharkov A. S., Anisimov I. I., Maryash V. I. Physiko-chimichaskie process v izdeliyakh iz vysokoenergetycheskykh kondensirovannykh materialov pri dlitelnoy ekspluatatsii/ Physicheskaya mezomechanika. №9/4. 2006. P. 93-106.
8. Gul’ V. Ye. Struktura i prochnost’ polymerov. M.: Chimia, 1971. P. 10-23, 189-209.
9. Pavlov P. A. Osnovy engeneernykh raschetov elementov machin na ustalostnuyu i dlitelnuyu prochnost’. L.: Mashinostroenie, 1988. P. 65-70.
10. Ushkin N. P. Sposoby proektnoy otsenki resursa RDTT i obespechaniya ego dlitelnoy ekspluatatsii/ Kosmicheskaya technika. Raketnoye vooruzhenie: Sb. nauch.- techn. st. 2016. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 110-116.

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12.1.2016 Increasing Effectiveness of Meteorological Rockets when Using Hybrid Motors https://journal.yuzhnoye.com/content_2016_1/annot_12_1_2016-en/ Tue, 23 May 2023 13:07:28 +0000 https://journal.yuzhnoye.com/?page_id=27624
2016 (1); 76-81 Language: Russian Annotation: A comparative assessment of effectiveness of usage of hybrid rocket motors and solid rocket motors for meteorological rocket with propellant mass of 540 kg is made. Based on the results of investigation, an assessment is given of ballistic effectiveness of hybrid rocket motors, the peculiarities of combustion process and of selection and designing of solid propellant charge shape are analyzed.
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12. Increasing Effectiveness of Meteorological Rockets when Using Hybrid Motors

ISSN: 2617-5525

e-ISSN: 2617-5533

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 76-81

Language: Russian

Annotation: A comparative assessment of effectiveness of usage of hybrid rocket motors and solid rocket motors for meteorological rocket with propellant mass of 540 kg is made. Different combinations of oxidizer and fuel are considered based on which the power characteristics of hybrid rocket motors were determined. Based on the results of investigation, an assessment is given of ballistic effectiveness of hybrid rocket motors, the peculiarities of combustion process and of selection and designing of solid propellant charge shape are analyzed.

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12.1.2016 Increasing Effectiveness of Meteorological Rockets when Using Hybrid Motors
12.1.2016 Increasing Effectiveness of Meteorological Rockets when Using Hybrid Motors
12.1.2016 Increasing Effectiveness of Meteorological Rockets when Using Hybrid Motors
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11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation https://journal.yuzhnoye.com/content_2016_1/annot_11_1_2016-en/ Tue, 23 May 2023 13:06:36 +0000 https://journal.yuzhnoye.com/?page_id=27621
It is shown that thrust behavior in the leg of deep decay is determined by two main processes: afterburning of solid propellant charge residues within the first 3-5 s and mass input of internal thermal protection coating destruction products within the following several tenths of second.
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11. Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation

ISSN: 2617-5525

e-ISSN: 2617-5533

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 68-75

Language: Russian

Annotation: The factors are considered that have an impact on the value and behavior of SRM flow rate and thrust characteristics after stage separation (in the leg of deep decay). It is shown that thrust behavior in the leg of deep decay is determined by two main processes: afterburning of solid propellant charge residues within the first 3-5 s and mass input of internal thermal protection coating destruction products within the following several tenths of second. The dependences are proposed for design evaluation of SRM intra-ballistic and flow rate/thrust characteristics.

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11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
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Сollected book of scientific-technical articles https://journal.yuzhnoye.com/ Thu, 04 May 2023 07:56:30 +0000 https://enovathemes.com/samatex2/?page_id=41
Design and development of components of space launch vehicles and combat missiles (liquid-propellant and solid-propellant rocket engines, propulsion systems, control systems, separation systems, payload equipment, etc.) Design and development of components for ground-based systems (facilities, fueling systems, prelaunch processing systems, etc.) Design and development of spacecraft and their components. Problems of aerodynamics, heat and mass transfer, flight theory, loading, and structural strength. Publications in the Collection are provided free of charge for both authors and users (Diamond Open Access). No fees are charged to authors for the processing, peer review, or publication of the articles in the Collection or on its website.
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The collection of scientific and technical articles Space Technology. Missile Armaments is a specialized professional publication that publishes new results of theoretical and experimental research and development in the field of aviation and space rocket technology.

The subject area of the Collection corresponds to the Mechanical Engineering and Machine-Building cluster (G8 Materials Science, G9 Applied Mechanics, G10 Metallurgy, G11 Industrial Engineering, and G12 Aviation, Rocket, and Space Technology).

The scope of the Collection covers the development and operation of state-of-the-art military missile and space launch systems, spacecraft, and satellite systems, as well as their components, including:

  • Design and development of missile and ground-based systems.
  • Design and development of components of space launch vehicles and combat missiles (liquid-propellant and solid-propellant rocket engines, propulsion systems, control systems, separation systems, payload equipment, etc.)
  • Design and development of components for ground-based systems (facilities, fueling systems, prelaunch processing systems, etc.)
  • Design and development of spacecraft and their components.
  • Problems of aerodynamics, heat and mass transfer, flight theory, loading, and structural strength.
  • Problems of efficiency, reliability, safety, and economic feasibility of space launch systems.
  • Other aspects that are directly related to the development and operation of space launch systems.
  • Other topics corresponding to the Mechanical Engineering and Manufacturing

 

The target audience is scientists, postgraduate students, and specialists whose scientific interests include achievements in aviation, rocket, and space technology (G12) and other specialties within the Mechanical Engineering and Machine-Building cluster (G8, G9, G10, and G11).

The Collection is included in the List of Scientific Professional Publications of Ukraine (category B) in accordance with Order No. 928 of the Ministry of Education and Science, dated June 11, 2026 (Appendix 5).

The Collection is registered in the unified open scientific identification system ROR (Research Organization Registry).

The collection of scientific and technical articles Space Technology. Missile Armaments has been published since April 1979. It is currently published in printed (ISSN 2617-5525) and identical in content, full-text electronic forms (e-ISSN 2617 5533).

Publications in the Collection are provided free of charge for both authors and users (Diamond Open Access). No fees are charged to authors for the processing, peer review, or publication of the articles in the Collection or on its website.

About the collected articles

ISSN 2617-5525 (Print); e-ISSN 2617-5533 (Online)

obl1

ISSN 2617-5525 (Print);
e-ISSN 2617-5533 (Online)

Publisher and founder: Yuzhnoye State Design Office, EDRPOU code 14308304.

Publication DOI: 10.33136/stma

Publication languages: Ukrainian, English.

Periodicity: twice a year.
In 2023-2024, taking into account the announcement of martial law in Ukraine, the Collection was issued once a year.
In 2025, the editorial and publication process was stabilized, and the Collection resumed publication every six months.

State registration of the printed media in the National Council of Ukraine on Television and Radio Broadcasting: media identifier – R30-01817 of 04.12.2023.

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