Thermal and acceleration load analysis of new 122 mm rocket propellant grain
In order to achieve very strong inter-ballistic requirements, a unusual free standing rocket motor propellant grain was designed, with variable channel diameter. Due to its very high length, it was expected for the grain to be exposed to dangerous combination of different loads during the design pha...
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Format: | Article |
Language: | English |
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Military Technical Institute, Belgrade
2016-01-01
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Series: | Scientific Technical Review |
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Online Access: | https://scindeks-clanci.ceon.rs/data/pdf/1820-0206/2016/1820-02061603003G.pdf |
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author | Gligorijević Nikola Antonović Saša Živković Saša Pavković Bojan Rodić Vesna |
author_facet | Gligorijević Nikola Antonović Saša Živković Saša Pavković Bojan Rodić Vesna |
author_sort | Gligorijević Nikola |
collection | DOAJ |
description | In order to achieve very strong inter-ballistic requirements, a unusual free standing rocket motor propellant grain was designed, with variable channel diameter. Due to its very high length, it was expected for the grain to be exposed to dangerous combination of different loads during the design phase. Structural analysis of viscoelastic propellant grain is always very complex and it differs substantially from an elastic analysis, because the propellant mechanical properties depend on temperature and strain rate. The most complex case in the analysis occurs when multiple loads operate simultaneously. In this paper, the structural analysis has been done during the initial period of rocket flight, when the grain is under very fast load due to acceleration and at the same time under a slow load due to surface pressure, created as a result of temperature dilatation. In the absence of data on mechanical properties of the new propellant composition, the properties over the whole time-temperature range were estimated comparing by a similar composition that have been completely tested earlier. Using finite element method (ANSYS program) two different design solutions were examined and the more reliable one was adopted. |
first_indexed | 2024-04-12T09:16:07Z |
format | Article |
id | doaj.art-6db64d20f3b74f66acb1a7558b55d371 |
institution | Directory Open Access Journal |
issn | 1820-0206 2683-5770 |
language | English |
last_indexed | 2024-04-12T09:16:07Z |
publishDate | 2016-01-01 |
publisher | Military Technical Institute, Belgrade |
record_format | Article |
series | Scientific Technical Review |
spelling | doaj.art-6db64d20f3b74f66acb1a7558b55d3712022-12-22T03:38:49ZengMilitary Technical Institute, BelgradeScientific Technical Review1820-02062683-57702016-01-016633111820-02061603003GThermal and acceleration load analysis of new 122 mm rocket propellant grainGligorijević Nikola0https://orcid.org/0000-0001-8604-4618Antonović Saša1Živković Saša2Pavković Bojan3Rodić Vesna4Military Technical Institute (VTI), BelgradeMilitary Technical Institute (VTI), BelgradeMilitary Technical Institute (VTI), BelgradeMilitary Technical Institute (VTI), BelgradeMilitary Technical Institute (VTI), BelgradeIn order to achieve very strong inter-ballistic requirements, a unusual free standing rocket motor propellant grain was designed, with variable channel diameter. Due to its very high length, it was expected for the grain to be exposed to dangerous combination of different loads during the design phase. Structural analysis of viscoelastic propellant grain is always very complex and it differs substantially from an elastic analysis, because the propellant mechanical properties depend on temperature and strain rate. The most complex case in the analysis occurs when multiple loads operate simultaneously. In this paper, the structural analysis has been done during the initial period of rocket flight, when the grain is under very fast load due to acceleration and at the same time under a slow load due to surface pressure, created as a result of temperature dilatation. In the absence of data on mechanical properties of the new propellant composition, the properties over the whole time-temperature range were estimated comparing by a similar composition that have been completely tested earlier. Using finite element method (ANSYS program) two different design solutions were examined and the more reliable one was adopted.https://scindeks-clanci.ceon.rs/data/pdf/1820-0206/2016/1820-02061603003G.pdfrocket122 mm calibrerocket enginepropellant grainthermal loadaccelerationviscoelasticitystructural analysistensile strenghtdamagereliabilityfinite elements method |
spellingShingle | Gligorijević Nikola Antonović Saša Živković Saša Pavković Bojan Rodić Vesna Thermal and acceleration load analysis of new 122 mm rocket propellant grain Scientific Technical Review rocket 122 mm calibre rocket engine propellant grain thermal load acceleration viscoelasticity structural analysis tensile strenght damage reliability finite elements method |
title | Thermal and acceleration load analysis of new 122 mm rocket propellant grain |
title_full | Thermal and acceleration load analysis of new 122 mm rocket propellant grain |
title_fullStr | Thermal and acceleration load analysis of new 122 mm rocket propellant grain |
title_full_unstemmed | Thermal and acceleration load analysis of new 122 mm rocket propellant grain |
title_short | Thermal and acceleration load analysis of new 122 mm rocket propellant grain |
title_sort | thermal and acceleration load analysis of new 122 mm rocket propellant grain |
topic | rocket 122 mm calibre rocket engine propellant grain thermal load acceleration viscoelasticity structural analysis tensile strenght damage reliability finite elements method |
url | https://scindeks-clanci.ceon.rs/data/pdf/1820-0206/2016/1820-02061603003G.pdf |
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