As a kind of solid fuel,HTPB propellant is widely used due to its high energy,high density,light weight and good comprehensive performance.In order to provide the reference for solid rocket motor propellant grain structural integrity analysis and optimal design method.The mechanical properties and constitutive model of the composite propellant was researched.In this work,HTPB propellant selects as the research object,and the main research contents and corresponding results include the following ... 

【文章來源】：南京理工大學江蘇省 211工程院校

【文章頁數(shù)】：79 頁

【學位級別】：碩士

【文章目錄】：
ABSTRACT
1 INTRODUCTION
    1.1 RESEARCH BACKGROUND, PURPOSE AND SIGNIFICANCE
    1.2 RESEARCH STATUS HOME AND ABROAD
        1.2.1 Research on high strain rate: experimental technology
        1.2.2 Research on mechanical properties of HTPB propellant
        1.2.3 Research on thermal effect of deformation at high strain rates
        1.2.4 Application of high strain rate constitutive model with propellant materials
    1.3 RESEARCH BACKGROUND,PURPOSE AND MEANING
2 EXPERIMENTAL METHODS, RESULTS AND DISCUSSION
    2.1 EXPERIMENTAL METHODOLOGIES
        2.1.1 Split Hopkinson pressure bar (SHPB)
        2.1.2 Working principle of SHPB
    2.2 EXPERIMENTAL PROCEDURE
        2.2.1 Material and specimen
        2.2.2 Experimental results and analysis
    2.3 SUMMARY
3 STUDY ON LOW STRAIN RATE CONSTITUTIVE MODEL OFHTPB PROPELLANT MATERIAL
    3.1 SHERWOOD-FROST CONSTITUTIVE RELATIONSHIP
    3.2 SHERWOOD-FROST CONSTITUTIVE MODEL OF HTPB PROPELLANT
        3.2.1 The establishment of constitutive model
        3.2.2 Fitting of model parameters
        3.2.3 Validation of constitutive model
    3.3 SUMMARY
4 STUDY ON HIGH STRAIN RATE CONSTITUTIVE MODEL OFHTPB PROPELLANT
    4.1 STUDY ON HIGH STRAIN RATE COMPRESSIVE MECHANICAL PROPERTIES OFHTPB PROPELLANT
    4.2 MODIFIED ZWT CONSTITUTIVE MODELS
        4.2.1 Determination of model parameters
        4.2.2 Validation
    4.3 SUMMARY
5 STUDY ON DEFORMATION-INDUCED HEAT GENERATION
    5.1 THERMAL EFFECT OF PROPELLANT MATERIAL AT HIGH STRAIN RATE
    5.2 TEMPERATURE MEASUREMENT OF HTPB PROPELLANT
        5.2.1 Specimen and experimental device
        5.2.2 Experimental methods and experimental results
    5.3 HTPB PROPELLANT MATERIAL DEFORMATION OF HEAT GENERATIONCALCULATION
        5.3.1 Calculation method of thermal temperature rise of deformation generation
        5.3.2 Calculation of thermal temperature rise of HTPB propellant material
    5.4 STUDY ON TEMPERATURE RISE OF HTPB PROPFLLANT MATERIAL
        5.4.1 Comparison of experimental results of temperature rise and theoretical calculation
        5.4.2 Temperature rises function of HTPB in deformation of generating heat
    5.5 STUDY ON A CONSTITUTIVE MODEL OF HTPB PROPELLANT CONSIDERING THETHERMAL EFFECT OF DEFORMATION GENERATION
        5.5.1 The thermal softening function of thermal effect generated by deformation
        5.5.2 Modification of constitutive model of HTPB propellant material
        5.5.3 Parameter fitting and validation of constitutive model
    5.6 SUMMARY
6 CONCLUSION
ACKNOWLEDGEMENTS
REFERENCES
PUBLICATIONS


【參考文獻】：
期刊論文
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本文編號：3345227