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Study on Creep Mechanical Properties of HTPB Solid Propellant.

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Title: Study on Creep Mechanical Properties of HTPB Solid Propellant.
Authors: Jin, Li1 (AUTHOR), Jia, Siqi1,2 (AUTHOR), Zhang, Ze1 (AUTHOR), An, Zicong1,2 (AUTHOR), Lu, Zhenkun2 (AUTHOR) luzhk123@163.com
Source: Materials (1996-1944). May2026, Vol. 19 Issue 10, p1951. 17p.
Subjects: Creep (Materials), Solid propellants, Viscoelastic materials, Finite element method, Adhesives, Creep testing
Abstract: Solid rocket propellants based on hydroxyl-terminated polybutadiene (HTPB), in which HTPB acts as the polymeric binder and fuel matrix, are widely used in aerospace propulsion. During storage, transport, and service, these composite energetic materials are exposed to sustained mechanical loads as well as environmental variations, which may induce time-dependent inelastic deformation. Such creep deformation can alter the grain geometry, affect combustion stability, and reduce the structural reliability of rocket motors. In this work, room-temperature tensile creep tests were conducted on an HTPB-based solid propellant under different stress levels. Several viscoelastic and power-law constitutive models were compared, and a composite time-hardening creep model was established to describe the experimental strain–time response. The model was further implemented in Abaqus through a Fortran user subroutine for finite element simulation. The results provide a useful basis for creep deformation assessment, formulation optimization, and structural reliability analysis of HTPB-based propellants. [ABSTRACT FROM AUTHOR]
Copyright of Materials (1996-1944) is the property of MDPI and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
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Header DbId: egs
DbLabel: Engineering Source
An: 194116787
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
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  Data: Study on Creep Mechanical Properties of HTPB Solid Propellant.
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  Data: <searchLink fieldCode="JN" term="%22Materials+%281996-1944%29%22">Materials (1996-1944)</searchLink>. May2026, Vol. 19 Issue 10, p1951. 17p.
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  Data: <searchLink fieldCode="DE" term="%22Creep+%28Materials%29%22">Creep (Materials)</searchLink><br /><searchLink fieldCode="DE" term="%22Solid+propellants%22">Solid propellants</searchLink><br /><searchLink fieldCode="DE" term="%22Viscoelastic+materials%22">Viscoelastic materials</searchLink><br /><searchLink fieldCode="DE" term="%22Finite+element+method%22">Finite element method</searchLink><br /><searchLink fieldCode="DE" term="%22Adhesives%22">Adhesives</searchLink><br /><searchLink fieldCode="DE" term="%22Creep+testing%22">Creep testing</searchLink>
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  Data: Solid rocket propellants based on hydroxyl-terminated polybutadiene (HTPB), in which HTPB acts as the polymeric binder and fuel matrix, are widely used in aerospace propulsion. During storage, transport, and service, these composite energetic materials are exposed to sustained mechanical loads as well as environmental variations, which may induce time-dependent inelastic deformation. Such creep deformation can alter the grain geometry, affect combustion stability, and reduce the structural reliability of rocket motors. In this work, room-temperature tensile creep tests were conducted on an HTPB-based solid propellant under different stress levels. Several viscoelastic and power-law constitutive models were compared, and a composite time-hardening creep model was established to describe the experimental strain–time response. The model was further implemented in Abaqus through a Fortran user subroutine for finite element simulation. The results provide a useful basis for creep deformation assessment, formulation optimization, and structural reliability analysis of HTPB-based propellants. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
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  Data: <i>Copyright of Materials (1996-1944) is the property of MDPI and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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RecordInfo BibRecord:
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    Identifiers:
      – Type: doi
        Value: 10.3390/ma19101951
    Languages:
      – Code: eng
        Text: English
    PhysicalDescription:
      Pagination:
        PageCount: 17
        StartPage: 1951
    Subjects:
      – SubjectFull: Creep (Materials)
        Type: general
      – SubjectFull: Solid propellants
        Type: general
      – SubjectFull: Viscoelastic materials
        Type: general
      – SubjectFull: Finite element method
        Type: general
      – SubjectFull: Adhesives
        Type: general
      – SubjectFull: Creep testing
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      – TitleFull: Study on Creep Mechanical Properties of HTPB Solid Propellant.
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            NameFull: Jin, Li
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            NameFull: Jia, Siqi
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            NameFull: Zhang, Ze
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            NameFull: An, Zicong
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            NameFull: Lu, Zhenkun
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            – D: 15
              M: 05
              Text: May2026
              Type: published
              Y: 2026
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              Value: 19
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              Value: 10
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