侯晓 , 张旭 , 刘向阳 , 等 . 固体火箭发动机药柱结构完整性研究进展 [J ] . 宇航学报 , 2023 , 44 ( 4 ): 566 - 579 .

HOU X , ZHANG X , LIU X Y , et al. Research progress on structural integrity of solid rocket motor grain [J ] . Journal of Astronautics , 2023 , 44 ( 4 ): 566 - 579 . (in Chinese)

ZHANG Y M , WANG N F , MA W H , et al. Investigations of the mechanical response of dummy HTPB propellant grain under ultrahigh acceleration overload conditions using onboard flight-test measurements [J ] . Defence Technology , 2024 ,32: 473 - 484 .

CHYUAN S . Dynamic analysis of solid propellant grains subjected to ignition pressurization loading [J ] . Journal of Sound and Vibration , 2003 , 268 ( 3 ): 465 - 483 .

LI Q , LIU P J , HE G Q . Fluid-solid coupled simulation of the ignition transient of solid rocket motor [J ] . Acta Astronautica , 2015 ,110: 180 - 190 .

PEI S D , QIANG H F , WANG X R , et al. Mesoscopic failure behavior of HTPB propellant bonding interface under multi-angle pull-and-shear loading [J ] . Polymer Testing , 2024 ,132:108365.

LEI M , REN S L , CHEN E H , et al. Correlation between solid propellant failure and interface debonding in solid rocket motors [J ] . Polymer Testing , 2022 ,115:107755.

高峰 , 张泽 . 含装药缺陷的固体火箭发动机性能评估综述 [J ] . 兵工学报 , 2021 , 42 ( 8 ): 1789 - 1802 .

GAO F , ZHANG Z . Review on performance evaluation of solid rocket motors with charge defects [J ] . Acta Armamentarii , 2021 , 42 ( 8 ): 1789 - 1802 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2021.08.024 http://doi.org/10.3969/j.issn.1000-1093.2021.08.024 The charge defect is an important factor affecting the safe work of solid rocket motors (SRM). In order to ensure safe launch, the deviation of the SRM performance caused by the charge defects needs to be analyzed to evaluate the working performance of SRM. In view of the complexity of the behavior of charge defects, a complete evaluation system has not been established. For the behavior of SRM charge defects, the theoretical and experimental research methods of crack and debonding propagation are reviewed, including the research on the crack initiation criterion, the factors affecting the growth and the fracture performance of propellant material. The research status of the interaction mechanism between grain crack and gas is reviewed from two aspects: the boundary conditions of gas entering the crack and the influence of gas propagation on the crack propagation. In order to achieve the purpose of numerical simulation of complete working process of SRM with charge defects, the research on its numerical calculation methods is summarized and analyzed from combustion surface regression calculation method, fluid-heat-solid coupling calculation method and defect propagation calculation method. The numerical index of the working performance of SRM with charge defects is expected to be obtained, which will be used as a reference for performance evaluation of SRM with charge defects. Finally, the development in the research on the behavior of charge defects and numerical calculation methods is prospected.

刘瀚文 , 吕玺 , 付小龙 , 等 . 固体推进剂断裂与裂纹扩展研究进展 [J ] . 火炸药学报 , 2024 , 47 ( 10 ): 857 - 869 .

LIU H W , LÜ X , FU X L , et al. Progress of study on the fracture and crack propagation of solid propellant [J ] . Chinese Journal of Explosives & Propellants , 2024 , 47 ( 10 ): 857 - 869 . (in Chinese)

YANG L , XIE K , PEI J F , et al. Compressive mechanical properties of HTPB propellant at low,intermediate,and high strain rates [J ] . Journal of Applied Polymer Science , 2016 , 133 ( 23 ): 43512 .

刘畅 , 王哲君 , 强洪夫 , 等 . 低温动态准双轴拉伸加载下HTPB推进剂的热老化性能 [J ] . 宇航学报 , 2020 , 41 ( 3 ): 353 - 361 .

LIU C , WANG Z J , QIANG H F , et al. Thermal aged properties of HTPB propellant at low temperature under dynamic quasi-biaxial tensile loading [J ] . Journal of Astronautics , 2020 , 41 ( 3 ): 353 - 361 . (in Chinese)

RANJAN R , MURTHY H , BHOWMIK D , et al. Behaviour of composite solid propellant under biaxial tensile loading [J ] . Polymer Testing , 2023 ,124:108054.

李辉 . 考虑围压效应的复合推进剂本构模型及其数值应用研究 [D ] . 南京 : 南京理工大学 , 2023 .

LI H . Research on constitutive model considering the confining pressure effect for composite solid propellant and its numerical application [D ] . Nanjing : Nanjing University of Science and Technology , 2023 . (in Chinese)

ZHOU D M , WANG H , HUI B Q , et al. Effect of confining pressure on the structural integrity of NEPE solid propellant grain [J ] . International Journal of Pressure Vessels and Piping , 2022 ,200:104819.

WANG Z J , QIANG H F . Mechanical properties of thermal aged HTPB composite solid propellant under confining pressure [J ] . Defence Technology , 2022 , 18 ( 4 ): 618 - 625 . DOI: 10.1016/j.dt.2021.06.014 http://doi.org/10.1016/j.dt.2021.06.014 With the purpose of investigating the effects of confining pressure and aging on the mechanical properties of Hydroxyl-terminated polybutadiene (HTPB) based composite solid propellant, tensile tests of thermal accelerated aged propellant samples under room temperature and different confining pressure conditions were performed through the use of a self-made confining pressure device and conventional testing machine. Afterwards, the maximum tensile stress σm and the corresponding strain εm for the propellant under different test conditions were obtained and analyzed. The results indicate that confining pressure and aging can significantly affect the mechanical properties of HTPB propellant, and the coupled effects are very complex. On the one hand, the stress σm increases as a whole when confining pressure becomes higher or thermal aging time rises. Besides, this stress is more sensitive to aging with increasing confining pressure. There are almost three regions in the stress increments σmP−σm0/σm0 and thermal aging time curves for HTPB propellant. The maximum value of the stress increment σmP−σm0/σm0 for the propellant is about 98% at 7.0 MPa and 170 d. On the other hand, the strain εm decreases with increasing thermal aging time under the whole confining pressure conditions. However, the variation of this strain with confining pressure is more complex at various thermal aging time, which is different from that of unaged solid propellant in previous researches. In addition, this strain is slightly less sensitive to aging as the confining pressure increases. Furthermore, there is also a critical confining pressure in this investigation, whose value is between 0.15 MPa and 4.0 MPa. Beyond this critical pressure, the trends of the stress σm and the corresponding strain εm all change. Moreover, there are some critical thermal aging time for the stress increment (σmP−σm0)/σm0 and strain increment (εmP−εm0)/εm0 of HTPB propellant in this investigation, which are about at 35, 50 and 170 d. Finally, based on the twin-shear strength theory, a new modified nonlinear strength criterion of thermal aged HTPB propellant under confining pressure was proposed. And the whole errors of fitted results are lower than 6%. Therefore, the proposed strength criterion can be selected as a failure criterion for the analysis the failure properties of aged HTPB propellant under different confining pressures, the structural integrity of solid propellant grain and the safety of solid rocket motor during ignition operation after long periods of storage. © 2021 China Ordnance Society

王龙 , 刘岳勋 , 吴圣川 , 等 . 基于原位X射线成像的推进剂损伤演化表征 [J ] . 航空学报 , 2023 , 44 ( 7 ): 427022 . DOI: 10.7527/S1000-6893.2022.27022 http://doi.org/10.7527/S1000-6893.2022.27022 为实现对硝酸酯增塑聚醚（NEPE）固体推进剂的细观损伤及其演化行为的可视化表征，基于自主研制的原位力学试验系统与第3代高分辨同步辐射X射线三维成像技术，对拉伸速率为0.1 mm/s下的NEPE固体推进剂单调拉伸过程进行三维成像原位观测和表征，获取初始状态固体推进剂的细微观形貌及其随拉伸载荷的演化特征，提取并分析其内部典型损伤的体积与球度随载荷的演化规律。结果表明：同步辐射原位成像技术能够准确获取NEPE固体推进剂的细观结构特征，可以基于灰度差异对固体推进剂的AP颗粒、Al颗粒、基体以及缺陷等实现特征的准确识别。研究发现，NEPE固体推进剂内部缺陷主要有2种，一种为颗粒内的孔洞，一种为AP颗粒/基体界面的初始脱湿。推进剂细观损伤首先表现为初始的界面脱湿形成的孔隙：在拉伸载荷较小时，推进剂的损伤形式主要表现为较大的AP颗粒脱湿形成的孔隙；在拉伸载荷较大时，除AP颗粒脱湿外可以观察到Al颗粒的脱湿，大量的AP颗粒脱湿后形成的孔隙相互融合，最终导致固体推进剂宏观断裂。对固体推进剂内部孔隙定量化表征的结果表明，孔隙体积随着拉伸载荷增大而增加，而球度变化与初始缺陷相关，有初始缺陷时，球度呈现单调减少的趋势，相反则呈现先增加后减少的变化趋势。

WANG L , LIU Y X , WU S C , et al. In-situ X-ray tomography based characterization of propellant damage evolution [J ] . Acta Aeronautica et Astronautica Sinica , 2023 , 44 ( 7 ): 427022 . (in Chinese)

WUBULIAISAN M , WU Y Q , HOU X . A unified viscoelastic model of progressive damage and failure for solid propellants [J ] . International Journal of Plasticity , 2023 ,170:103765.

乌布力艾散·麦麦提图尔荪 , 吴艳青 , 侯晓 , 等 . 固体推进剂黏弹性参数的确定及细观损伤演化 [J ] . 兵工学报 , 2024 , 45 ( 4 ): 1038 - 1046 . DOI: 10.12382/bgxb.2022.1256 http://doi.org/10.12382/bgxb.2022.1256 固体推进剂力学模型参数的准确性对其宏观力学响应预测具有重要的意义,为解耦标定固体推进剂非线性黏弹性模型参数,提出一种基于台阶应力松弛试验的模型参数确定方法。通过台阶应力松弛平衡响应确定固体推进剂弹性部分参数,通过小变形下的应力松弛确定无量纲松弛模量,分析一种固体推进剂力学响应。研究结果表明:固体推进剂在台阶应力松弛及单轴拉伸条件下的力学性能预测结果与试验结果吻合,验证了所提方法的有效性;由于平衡响应包含损伤,采用该方法标定的参数可用于预测含损伤固体推进剂力学响应。在此基础上,提出一种基于推进剂模型参数标定等效黏合剂力学参数的方法,并通过引入基于黏弹性脱湿准则的相界面模型建立代表性体积单元计算模型,实现在宽应变(~100%)范围内推进剂脱湿损伤分析,为推进剂宏观力学性能预测及细观损伤演化分析提供了支撑。

WUBULIAISAN M , WU Y Q , HOU X , et al. On the determination of viscoelastic model parameters and microstructural damage evolution of solid propellants [J ] . Acta Armamentarii , 2024 , 45 ( 4 ): 1038 - 1046 . (in Chinese) DOI: 10.12382/bgxb.2022.1256 http://doi.org/10.12382/bgxb.2022.1256 Accurately determining the model parameters of solid propellant is of great importance for the prediction of its macroscopic mechanical response. A parameter determination method based on multi-step stress relaxation experiments is proposed to calibrate the nonlinear viscoelastic model parameters of solid propellants uncoupled. The proposed method determines the parameters for the elastic part by multi-step stress relaxation equilibrium response and the dimensionless relaxation modulus by stress relaxation in the case of small deformation. The proposed method is then used to analyze the mechanical response of solid propellants. The results show that the predicted results of multi-step stress relaxation and uniaxial tension under different strain rates of the material agree with the experimental results, which verifies the validity of the proposed method. Moreover, since the equilibrium response includes damage, the parameters calibrated by the proposed method can be used to predict the mechanical response of solid propellant with damage. Consequently, the parameters of the composite matrix are derived from the determined parameters of solid propellant, and a viscoelastic debonding criterion-based interface model is introduced to establish a representative volume element (RVE) model, thus achieving the interface debonding analysis in a wide range of strain (~100%), which provides an effective method supporting the prediction of mechanical response and microstructural damage evolution of solid propellants.

LEI M , CHEN E H , ZHAO Z A , et al. A temperature/strain-rate-dependent finite deformation constitutive and failure model for solid propellants [J ] . Science China Physics,Mechanics & Astronomy , 2023 , 66 ( 9 ): 294611 .

LI L L , REN J , WANG P , et al. A pixel-level weak supervision segmentation method for typical defect images in X-ray inspection of solid rocket motors combustion chamber [J ] . Measurement , 2023 ,211:112497.

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 http://doi.org/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。

WANG G J , WU Y Q , HOU X , 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 . (in Chinese) DOI: 10.12382/bgxb.2022.0747 http://doi.org/10.12382/bgxb.2022.0747 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.

伍鹏 , 李高春 , 王鑫 . HTPB推进剂三点弯曲过程试验与数值模拟 [J ] . 含能材料 , 2020 , 28 ( 6 ): 514 - 521 .

WU P , LI G C , WANG X . Experimental and numerical simulation on the damage process of HTPB propellant at the crack tip [J ] . Chinese Journal of Energetic Materials , 2020 , 28 ( 6 ): 514 - 521 . (in Chinese)

GAO B , LI Z , JI Y C . Experimental and XFEM simulation research on HTPB propellant precracks based on microscopic observation and DIC [J ] . Propellants,Explosives,Pyrotechnics , 2022 , 47 ( 6 ): e202200037 .

WANG T Y , XU J S , LI H , et al. Crack propagation velocity and fracture toughness of hydroxyl-terminated polybutadiene propellants:experiments and simulations [J ] . Engineering Fracture Mechanics , 2021 ,257:108034.

LONG B , WANG H L , GAO S S . Study on the fracture properties of HTPB propellant at low temperature [J ] . Propellants,Explosives,Pyrotechnics , 2020 , 45 ( 1 ): 136 - 140 .

汪文强 , 陈雄 , 郑健 , 等 . 冲击载荷下CMDB推进剂断裂性能实验研究 [J ] . 固体火箭技术 , 2015 , 38 ( 3 ): 372 - 377 ,395.

WANG W Q , CHEN X , ZHENG J , et al. Experimental research on CMDB propellant fracture under impact load [J ] . Journal of Solid Rocket Technology , 2015 , 38 ( 3 ): 372 - 377 ,395. (in Chinese)

WU Y , FAN Y N , CHEN X X , et al. Low/intermediate speed impact-induced ignition and damage of a novel high-energy solid propellant [J ] . Propellants,Explosives,Pyrotechnics , 2023 , 48 ( 8 ): e202300056 .

LI M , LI Z H , HE H , et al. Mechanical behaviors and constitutive relations under wide strain rate range for CMDB propellant [J ] . Polymer Testing , 2022 ,116:107806.

BASSETT W P , JOHNSON B P , SALVATI L , et al. Hot-spot generation and growth in shocked plastic-bonded explosives studied by optical pyrometry [J ] . Journal of Applied Physics , 2019 ,125:215904.

WANG R , WANG N F , ZHANG Y M , et al. Dynamic mechanical response and failure behavior of solid propellant under shock wave impact [J ] . Engineering Failure Analysis , 2024 ,164:108700.

DUAN Q Y , XUE H W , YANG Y H , et al. Study on fracture behavior of nickel-based single crystal superalloy subjected to high temperature fatigue using digital image correlation [J ] . International Journal of Fatigue , 2022 ,155:106598.

HE Z B , ZHANG K , LIN Y L , et al. An accurate determination method for constitutive model of anisotropic tubular materials with DIC-based controlled biaxial tensile test [J ] . International Journal of Mechanical Sciences , 2020 ,181:105715.

SHANG Y L , SHI J C , NING H B , et al. Ignition delay time measurements and kinetic modeling of CH4 initiated by CH3NO2 [J ] . Fuel , 2019 ,243: 288 - 297 .

SHI J C , SHANG Y L , YE W , et al. Shock-tube experiments and kinetic modeling of CH3NHCH3 ignition at elevated pressures [J ] . International Journal of Chemical Kinetics , 2018 , 50 ( 2 ): 90 - 97 .