1. 北京理工大学 爆炸科学与技术国家重点实验室, 北京 100081
2. 北京理工大学 宇航学院, 北京 100081
*邮箱: wuyqing@bit.edu.cn
收稿:2022-08-26,
网络出版:2024-01-12,
纸质出版:2023-12-30
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王贵军, 吴艳青, 侯晓, 等. 基于细观结构的复合固体推进剂含损伤黏弹性本构模型[J]. 兵工学报, 2023,44(12):3696-3706.
Guijun WANG, Yanqing WU, Xiao HOU, et al. Research on the Viscoelastic Constitutive Model of Composite Solid Propellant Containing Damage Based on Mesostructure[J]. Acta Armamentarii, 2023, 44(12): 3696-3706.
王贵军, 吴艳青, 侯晓, 等. 基于细观结构的复合固体推进剂含损伤黏弹性本构模型[J]. 兵工学报, 2023,44(12):3696-3706. DOI: 10.12382/bgxb.2022.0747.
Guijun WANG, Yanqing WU, Xiao HOU, et al. Research on the Viscoelastic Constitutive Model of Composite Solid Propellant Containing Damage Based on Mesostructure[J]. Acta Armamentarii, 2023, 44(12): 3696-3706. DOI: 10.12382/bgxb.2022.0747.
复合固体推进剂的宏观力学性能与其细观组分及损伤密切相关
基于复合固体推进剂变形过程中细观结构的演化
开发复合固体推进剂含孔洞损伤的宏细观本构模型。该模型考虑了推进剂温度和应变率的相关性
并能够描述推进剂拉伸和压缩状态下不同的力学响应。通过不同温度和不同应变率下的拉伸和压缩试验
验证本构模型的有效性。基于有限元分析软件提供的用户材料子程序接口UMAT
对非线性黏弹性本构模型进行二次开发
并应用于低温点火工况下药柱结构完整性分析
结果表明药柱在低温点火条件下安全系数为2.56
结构完整性满足要求。与基于Prony级数的线性黏弹性本构模型进行对比分析
表明新建立的本构模型能够更准确地进行复合固体推进剂药柱的结构分析。
The macroscopic mechanical properties of composite solid propellant are inseparably linked to its mesoscopic components and damage. A macro and mesoscopic constitutive model of composite solid propellant with void damage was developed based on the evolution of the mesostructure during the deformation process of composite solid propellants. The model takes into account the dependence of propellant temperature and strain rate
and is able to describe the different mechanical responses of propellant in tension and compression. The validity of the constitutive model is verified by tensile and compressive tests at different temperatures and strain rates. The macro and mesoscopic constitutive model is re-developed based on the user material subroutine interface UMAT provided by the finite element software
and applied to the structural integrity analysis of grain under low temperature ignition conditions
indicating that the safety factor of grain under low-temperature ignition conditions is 2.56
and the structural integrity of grain meets the requirements. Finally
compared with the linear viscoelastic constitutive model based on Prony series
the proposed constitutive model can be used to more accurately analyze the structure of composite solid propellant grains.
DOUGLASS H W , COLLINS J H , NOEL J S , et al . Solid propellant grain structural integrity analysis:NASA SP-8073 [J ] . Washington, DC , US:NASA Space Vehicle Design Criteria (Chemical Propulsion) , 1973 .
ZHOU D M , LIU X Y , SUI X , et al . Accelerated aging and structural integrity analysis approach to predict the service life of solid rocket motor [C ] //Proceedings of the 51st AIAA/SAE/ASEE Joint Propulsion Conference.Orlando,FL, US:AIAA , 2015 : 4240 .
DENG B , TANG G J , SHEN Z B . Structural analysis of solid rocket motor grain with aging and damage effects [J ] . Journal of Spacecraft and Rockets , 2015 , 52 ( 2 ): 331 - 339 . DOI: 10.2514/1.A32843 http://doi.org/10.2514/1.A32843 https://arc.aiaa.org/doi/10.2514/1.A32843 https://arc.aiaa.org/doi/10.2514/1.A32843
WANG Z J , QIANG H F , WANG T J , et al . A thermovisco-hyperelastic constitutive model of HTPB propellant with damage at intermediate strain rates [J ] . Mechanics of Time-Dependent Materials , 2018 , 22 ( 3 ): 291 - 314 . DOI: 10.1007/s11043-017-9357-9 http://doi.org/10.1007/s11043-017-9357-9
CHYUAN S W . Dynamic analysis of solid propellant grains subjected to ignition pressurization loading [J ] . Journal of Sound and Vibration , 2003 , 268 ( 3 ): 465 - 483 . DOI: 10.1016/S0022-460X(02)01554-7 http://doi.org/10.1016/S0022-460X(02)01554-7 https://linkinghub.elsevier.com/retrieve/pii/S0022460X02015547 https://linkinghub.elsevier.com/retrieve/pii/S0022460X02015547
王佳奇 , 贺绍飞 , 申志彬 , 等 . 低温点火条件下药柱结构完整性分析与试验 [J ] . 固体火箭技术 , 2019 , 42 ( 3 ): 356 - 360 .
WANG J Q , HE S F , SHEN Z B , et al . Analysis and experiment on grain structural integrity under low temperature ignition [J ] . Journal of Sound and Vibration , 2019 , 42 ( 3 ): 356 - 360 . (in Chinese)
WANG C G , TIAN W P . The influence factors of grain integrity under the internal pressure condition in SRM [J ] . International Journal of Aerospace Engineering , 2021 , 2021 : 5521455 .
王哲君 , 强洪夫 , 王广 , 等 . 固体推进剂力学性能和本构模型的研究进展 [J ] . 含能材料 , 2016 , 24 ( 4 ): 403 - 416 .
WANG Z J , QIANG H F , WANG G , et al . Review on the mechanical properties and constitutive models of solid propellants [J ] . Chinese Journal of Energetic Materials , 2016 , 24 ( 4 ): 403 - 416 . (in Chinese)
SCHAPERY R A . Analysis of damage growth in particulate composites using a work potential [J ] . Composites Engineering , 1991 , 1 ( 3 ): 167 - 182 . DOI: 10.1016/0961-9526(91)90017-M http://doi.org/10.1016/0961-9526(91)90017-M https://linkinghub.elsevier.com/retrieve/pii/096195269190017M https://linkinghub.elsevier.com/retrieve/pii/096195269190017M
SCHAPERY R A . Nonlinear viscoelastic and viscoplastic constitutive equations with growing damage [J ] . International Journal of Fracture , 1999 , 97 ( 1 ): 33 - 66 . DOI: 10.1023/A:1018695329398 http://doi.org/10.1023/A:1018695329398 http://link.springer.com/10.1023/A:1018695329398 http://link.springer.com/10.1023/A:1018695329398
张建彬 . 双基推进剂屈服准则及粘弹塑性本构模型研究 [D ] . 南京 : 南京理工大学 , 2013 .
ZHANG J B . Study on yield criteria and visco-elastoplastic constitutive model of the double-base propellant [D ] . Nanjing : Nanjing University of Science and Technology , 2013 . (in Chinese)
XU J S , CHEN X , WANG H L , et al . Thermo-damage-viscoelastic constitutive model of HTPB composite propellant [J ] . International Journal of Solids and Structures , 2014 , 51 ( 18 ): 3209 - 3217 . DOI: 10.1016/j.ijsolstr.2014.05.024 http://doi.org/10.1016/j.ijsolstr.2014.05.024 https://linkinghub.elsevier.com/retrieve/pii/S0020768314002182 https://linkinghub.elsevier.com/retrieve/pii/S0020768314002182
XU J S , HAN L , ZHENG J , et al . Finite element implementation of a thermo-damage-viscoelastic constitutive model for hydroxyl-terminated polybutadiene composite propellant [J ] . Mechanics of Time-Dependent Materials , 2017 , 21 ( 4 ): 577 - 595 . DOI: 10.1007/s11043-017-9343-2 http://doi.org/10.1007/s11043-017-9343-2 http://link.springer.com/10.1007/s11043-017-9343-2 http://link.springer.com/10.1007/s11043-017-9343-2
MA H , SHEN Z B , LI D K . A viscoelastic constitutive model of composite propellant considering dewetting and strain‐rate and its implementation [J ] . Propellants, Explosives, Pyrotechnics , 2019 , 44 ( 6 ): 759 - 768 . DOI: 10.1002/prep.v44.6 http://doi.org/10.1002/prep.v44.6 https://onlinelibrary.wiley.com/toc/15214087/44/6 https://onlinelibrary.wiley.com/toc/15214087/44/6
ZHANG J F , ZHENG J , CHEN X , et al . A thermovisco-hyperelastic constitutive model of NEPE propellant over a large range of strain rates [J ] . Journal of Engineering Materials and Technology , 2014 , 136 ( 3 ): 031002 . DOI: 10.1115/1.4027291 http://doi.org/10.1115/1.4027291 https://asmedigitalcollection.asme.org/materialstechnology/article/doi/10.1115/1.4027291/372140/A-ThermoviscoHyperelastic-Constitutive-Model-of https://asmedigitalcollection.asme.org/materialstechnology/article/doi/10.1115/1.4027291/372140/A-ThermoviscoHyperelastic-Constitutive-Model-of The uniaxial compressive mechanical curves of nitrate ester plasticized polyether (NEPE) propellant under different temperatures and strain rates have been obtained with a universal testing machine and modified split Hopkinson pressure bar (SHPB). The experimental results show that the mechanical properties of NEPE propellant are both rate dependent and temperature dependent. With decreasing temperature or increasing strain rate, the modulus and rigidity obviously increase. Based on the previous models proposed by Yang and Pouriayevali, we propose a modified viscohyperelastic constitutive model which can describe the mechanical response over a large range of strain rates. Then we add a rate-dependent temperature item into the modified model to make a thermovisco-hyperelastic constitutive model. By comparing the experimental results with the model, we find that the thermovisco-hyperelastic constitutive model can correctly describe the uniaxial compressive mechanical properties of NEPE propellant at different temperatures and over a large range of strain rates from the static state to 4500 s−1.
YANG L M , SHIM V P W , LIM C T . A visco-hyperelastic approach to modelling the constitutive behaviour of rubber [J ] . International Journal of Impact Engineering , 2000 , 24 ( 6/7 ): 545 - 560 . DOI: 10.1016/S0734-743X(99)00044-5 http://doi.org/10.1016/S0734-743X(99)00044-5 https://linkinghub.elsevier.com/retrieve/pii/S0734743X99000445 https://linkinghub.elsevier.com/retrieve/pii/S0734743X99000445
韩龙 . 复合固体推进剂细观损伤机理及本构模型研究 [D ] . 南京 : 南京理工大学 , 2017 .
HAN L . Research on themesoscopic damage mechanism and nonlinear viscoelastic constitutive model of composite propellant [D ] . Nanjing : Nanjing University of Science and Technology , 2017 . (in Chinese)
LI T P , XU J S , HAN J L , et al . Effect of microstructure on micro-mechanical properties of composite solid propellant [J ] . Micromachines , 2021 , 12 ( 11 ): 1378 . DOI: 10.3390/mi12111378 http://doi.org/10.3390/mi12111378 https://www.mdpi.com/2072-666X/12/11/1378 https://www.mdpi.com/2072-666X/12/11/1378 This study was aimed at determining the effect of microstructure on the macro-mechanical behavior of a composite solid propellant. The microstructure model of a composite solid propellant was generated using molecular dynamics algorithm. The correlation of how microstructural mechanical properties and the effect of initial interface defects in propellant act on the macro-mechanics were studied. Results of this study showed that the mechanical properties of propellant rely heavily on its mesoscopic structure. The grain filling volume fraction mainly influences the propellant initial modulus, the higher the volume fraction, the higher initial modulus. Additionally, it was found that the ratio of particles influences the tensile strength and breaking elongation rate of the propellant. The big particles could also improve the initial modulus of a propellant, but decrease its tensile strength and breaking elongation rate. Furthermore, the initial defects lowered the uniaxial tensile modulus, tensile strength, and the relaxation modulus of propellant, but did not affect the relaxation behavior of the propellant.
乌布力艾散·麦麦提图尔荪 , 吴艳青,侯晓,王宁.细观结构参量对推进剂力学性能影响的数值研究 [J ] . 复合材料学报 , 2022 , 39 ( 6 ): 2949 - 2961 .
MAIMAITITUERSUN W B L A S , WU Y Q , HOU X , et al . Numerical investigations on mesoscopic structure parameters affecting mechanical responses of propellant [J ] . Acta Materiae Compositae Sinica , 2022 , 39 ( 6 ): 2949 - 2961 . (in Chinese)
VAN RAMSHORST M C J , et al .DI BENEDETTO G L, DUVALOIS W, Investigation of the Failure Mechanism of HTPB/AP/Al propellant by In-situ Uniaxial Tensile Experimentation in SEM [J ] . Propellants, Explosives, Pyrotechnics , 2016 , 41 ( 4 ): 700 - 708 . DOI: 10.1002/prep.v41.4 http://doi.org/10.1002/prep.v41.4 https://onlinelibrary.wiley.com/toc/15214087/41/4 https://onlinelibrary.wiley.com/toc/15214087/41/4
HOU Y F , XU J S , ZHOU C S , et al . Microstructural simulations of debonding, nucleation, and crack propagation in an HMX-MDB propellant [J ] . Materials & Design , 2021 , 207 : 109854 .
XU F , ARAVAS N , SOFRONIS P . Constitutive modeling of solid propellant materials with evolving microstructural damage [J ] . Journal of the Mechanics and Physics of Solids , 2008 , 56 ( 5 ): 2050 - 2073 . DOI: 10.1016/j.jmps.2007.10.013 http://doi.org/10.1016/j.jmps.2007.10.013 https://linkinghub.elsevier.com/retrieve/pii/S0022509607002074 https://linkinghub.elsevier.com/retrieve/pii/S0022509607002074
HUR J , PARK J B , JUNG G D , et al . Enhancements on a micromechanical constitutive model of solid propellant [J ] . International Journal of Solids and Structures , 2016 , 87 : 110 - 119 . DOI: 10.1016/j.ijsolstr.2016.02.025 http://doi.org/10.1016/j.ijsolstr.2016.02.025 https://linkinghub.elsevier.com/retrieve/pii/S0020768316000871 https://linkinghub.elsevier.com/retrieve/pii/S0020768316000871
韩龙 , 许进升 , 周长省 . 基体特性对HTPB推进剂力学性能的影响 [J ] . 航空动力学报 , 2017 , 32 ( 10 ): 2553 - 2560 .
HAN L , XU J S , ZHOU C S . Effect of matrix material properties on the mechanical behavior of HTPB composite propellant [J ] . Journal of Aerospace Power , 2017 , 32 ( 10 ): 2553 - 2560 . (in Chinese)
CHU C C , NEEDLEMAN A . Void nucleation effects in biaxially stretched sheets [J ] . Jounal of Engineering Materials and Technology , 1980 , 102 ( 3 ): 249 - 256 .
李辉 , 许进升 , 周长省 , 等 . HTPB推进剂温度相关性失效准则 [J ] . 含能材料 , 2018 , 26 ( 9 ): 732 - 738 .
LI H , XU J S , ZHOU C S , et al . Failure criterion related to temperature for HTPB propellant [J ] . Chinese Journal of Energetic Materials , 2018 , 26 ( 9 ): 732 - 738 . (in Chinese)
王鸿丽 . 改性双基推进剂含损伤粘弹塑性本构模型及应用研究 [D ] . 南京 : 南京理工大学 , 2018 .
WANG H L . Research on visco-Elastic-plastic constitutive model with damage of modified double-base propellant and its application [D ] . Nanjing : Nanjing University of Science and Technology , 2018 . (in Chinese)
马赛尔 . 复合推进剂高应变率力学性能及本构模型研究 [D ] . 南京 : 南京理工大学 , 2017 .
MA S E . Research on the mechanical properties and constitutive model of composite propellant [D ] . Nanjing : Nanjing University of Science and Technology , 2017 . (in Chinese)
程吉明 . 预应变作用下复合固体推进剂损伤本构及应用研究 [D ] . 西安 : 西北工业大学 , 2019 .
CHENG J M . Damage constitutive model of composite solid propellant under prestrain and its application [D ] . Xi’an : Northwestern Polytechnical University , 2019 . (in Chinese)
刘梅 , 高波 , 董新刚 , 等 . 固体发动机药柱完整性失效的判据 [J ] . 固体火箭技术 , 2018 , 41 ( 4 ): 424 - 427 ,508.
LIU M , GAO B , DONG X G , et al . Failure criterion of solid motors at ignition pressurization loading [J ] . Journal of Solid Rocket Technology , 2018 , 41 ( 4 ): 424 - 427 ,508. (in Chinese)
SHEN Z B , ZHANG L , LI Y F . Structural integrity analysis and experimental investigation for solid rocket motor grain subjected to low temperature ignition [C ] //Proceedings of the 2019 7th Asia Conference on Mechanical and Materials Engineerin. Tokyo , Japan : EDP Sciences , 2019 , 293 : 04005 .
宋仕雄 . 低温点火状态下固体发动机药柱结构完整性分析 [D ] . 西安 : 航天动力技术研究院 , 2018 .
SONG S X . Structural integrity analysis of solid motor grain under low temperature ignition [D ] . Xi’an :The 41st Institute of the Fourth Academy of CASC, 2018. (in Chinese)
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