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沈业炜 , 仉玉成 , 童丽伦 . 中性键合剂在叠氮高能推进剂中应用工艺研究 [J ] . 上海航天 , 2017 , 34 ( 6 ): 90 - 95 .

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宋琴 , 王艳萍 , 廖菊平 , 等 . 叠氮微烟推进剂宽温域力学性能研究 [J ] . 火炸药学报 , 2021 , 44 ( 4 ): 521 - 525 . DOI: 10.14077/j.issn.1007-7812.202102006 http://doi.org/10.14077/j.issn.1007-7812.202102006 为研究战斗部壳体破片平均质量与平均穿孔面积的关系,针对3种战斗部装药JH-2、JOXL-1、RBOE-1设计了战斗部静爆试验和水井回收试验。应用图像处理技术,利用侵彻孔洞图像轮廓信息和自然破片平均质量的关系,标定了3种炸药的破片平均质量比例系数。结果表明,当壳体破片质量大于0.1g的破片计入有效破片时,3种炸药的破片平均质量比例系数分别为0.2249、0.3010、0.3907; 当壳体破片质量大于1g的破片计入有效破片时,3种炸药的破片平均质量比例系数分别为0.5521、0.5772、1.0646; 通过战斗部静爆后自然破片的穿靶试验可获得战斗部壳体形成自然破片的平均质量,较大程度地减少了以往试验的复杂性,方便在实际工程中应用,可为常规战斗部乃至不敏感战斗部的毁伤效能评估研究提供一种新的技术途径。

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谢五喜 , 赵昱 , 刘运飞 , 等 . 3,3-二叠氮甲基氧丁环-四氢呋喃共聚醚推进剂的力学性能影响因素 [J ] . 化工新型材料 , 2020 , 48 ( 2 ): 163 - 165 , 172. 采用力学性能测试和扫描电镜等手段研究了不同网络调节剂、固化剂和键合剂对3,3-二叠氮甲基氧丁环-四氢呋喃共聚醚 (BAMO-THF)推进剂力学性能的影响。结果表明:网络调节剂三羟甲基丙烷使推进剂高温50℃和常温25℃强度提高到0.318MPa和0.358MPa;固化剂的异氰酸酯使推进剂高温和常温强度提高到0.656MPa和0.734MPa;组合键合剂N和T使BAMO-THF推进剂的高温、低温和常温强度分别达到0.653MPa、2.228MPa和0.693MPa,延伸率分别为47.0%、62.1%和42.3%。

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ZHANG H N , CHANG H , LI X J , et al . The effect of strain rate on compressive behavior and failure mechanism of CMDB propellant [J ] . Defence Technology , 2022 , 18 ( 3 ): 467 - 475 . DOI: 10.1016/j.dt.2021.02.007 http://doi.org/10.1016/j.dt.2021.02.007 The compressive mechanical behavior of composite modified double base (CMDB) propellant was investigated across a wide scope of strain rates ranging from 10−3 s−1 to 4210 s−1 at room temperature, by applying a conventional universal testing machine and a split Hopkinson tension bar (SHPB), respectively. The derived stress-strain curves at different strain rates show a strong rate dependence, indicated that yield stress, ultimate stress and strain energy density of CMDB propellant all increase with strain rate by following a power law function, while the amplification of increase are different. The deformation and damage modes of CMDB propellant has changed from a typical ductile manner (cracking along the axial direction) to a brittle manner (maximum shear failure) with increasing of strain rate. Scanning electron microscopy (SEM) was employed to explore the microscopic failure characteristics of CMDB propellant. Under quasi-static loading, the nearly parallel micro-cracks propagating along the axial direction and the debonding of RDX particle without particle crushing can be observed. While under dynamic loading, the micro-crack is 45° angle to the axial direction, and multiple cracking modes of RDX particles appeared. Finally, the correlation between strain energy density and failure mechanisms of CMDB propellant was revealed by developing four characteristic failure modes. The findings of this study is very important to evaluate the structural integrity of CMDB propellant. © 2021 China Ordnance Society

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