Search Results for “propellant combustion rate” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 13:03:08 +0000 en-GB hourly 1 https://wordpress.org/?v=6.2.2 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “propellant combustion rate” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 20.1.2020 Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility https://journal.yuzhnoye.com/content_2020_1-en/annot_20_1_2020-en/ Wed, 13 Sep 2023 12:04:53 +0000 https://journal.yuzhnoye.com/?page_id=31078
The advantages of thermal neutralization units are considered, their operating principle is described, by the example of high-temperature toxic rocket propellants, the chemical reactions that take place in combustion chamber are formulated. The findings are presented that confirm practical feasibility of using integrated supply assemblies.
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20. Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 177-183

DOI: https://doi.org/10.33136/stma2020.01.177

Language: Russian

Annotation: The possibility is considered of using rocket propellant thermal neutralization units for decontamination of dangerous industrial wastes. The advantages of thermal neutralization units are considered, their operating principle is described, by the example of high-temperature toxic rocket propellants, the chemical reactions that take place in combustion chamber are formulated. The combustion chamber is a component of the neu tralization unit, it is in the combustion chamber, in the environment of created high temperatures, that the process of elimination of dangerous substances takes place. Taking into consideration the high cost of neutralization units, which will be a factor hindering the wide-scale introduction of neutralization units to decrease technogenic load on environment of Ukraine, the option is proposed of reducing the costs during the use of thermal neutralization units by way of combining the function of oxidizer neutralization unit and fuel neutralization unit in a single universal neutralization unit. The article substantiates the topicality and necessity of works to create the universal thermal neutralization unit from the viewpoint of economic and ecological aspects. The article presents a generalized description of technology and methodology of research tests of pilot samples of assemblies for high-temperature rocket propellants vapor and industrial wastewater supply into the neutralization unit. The assemblies for high-temperature rocket propellants vapor and industrial wastewater supply are considered as most critical components of the universal neutralization unit from the viewpoint of neutralized substance changing. The experiments were conducted on water solutions of rocket propellants that in this case simulated the contact of internal cavities of supply assemblies with aggressive toxic media. The conditions were created at which the probability existed of interaction of rocket propellants residues in stagnation zones at the moment of changing the supplied propellant component. In the frameworks of research tests of pilot samples, the obtained results were considered and analyzed. The findings are presented that confirm practical feasibility of using integrated supply assemblies.

Key words: neutralization unit, supply assemblies, alternate supply, rocket propellants interaction, universal thermal neutralization unit

Bibliography:
1. Kolesnikov S. V. Okislenie nesimmetrichnogo dimetilgidrazina (geptila) i identifikatsiia produktov ego prevrashcheniia pri prolivakh. Monografiia. NP “SibAK”, Novosibirsk, 2014.
2. Zhidkoe raketnoe toplivo v regione OBSE: obzor aspektov utilizatsii. FSC.DEL/443/07/Rev. 2. 23 okt. 2008 g.
3. Egorychev V. S., Kondrusev V. S. Topliva khimicheskikh raketnykh dvigatelei. Samara, 2007.
4. Kasimov А. М., Semenov V. Т., Shcherban’ N. H., Miasoedov V. V. Sovremennye problemy i resheniia v sisteme upravleniia opasnymi otkhodami. Kharkiv, 2008.
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20.1.2020  Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility
20.1.2020  Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility
20.1.2020  Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility

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10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM https://journal.yuzhnoye.com/content_2020_1-en/annot_10_1_2020-en/ Wed, 13 Sep 2023 10:47:53 +0000 https://journal.yuzhnoye.com/?page_id=31037
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 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. 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.
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10. Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

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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Downloads geography
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USA Boardman; Baltimore; Plano; Los Angeles; Monroe; Ashburn; Seattle; Boardman; Seattle; San Mateo; Boardman; Ashburn; Boardman13
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Ukraine Dnipro1
10.1.2020  Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM
10.1.2020  Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM
10.1.2020  Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

Keywords cloud

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