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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Main Authors: Gligorijević Nikola, Antonović Saša, Živković Saša, Pavković Bojan, Rodić Vesna
Format: Article
Language:English
Published: Military Technical Institute, Belgrade 2016-01-01
Series:Scientific Technical Review
Subjects:
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.
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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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AT antonovicsasa thermalandaccelerationloadanalysisofnew122mmrocketpropellantgrain
AT zivkovicsasa thermalandaccelerationloadanalysisofnew122mmrocketpropellantgrain
AT pavkovicbojan thermalandaccelerationloadanalysisofnew122mmrocketpropellantgrain
AT rodicvesna thermalandaccelerationloadanalysisofnew122mmrocketpropellantgrain