含能燃烧催化剂K2Pb[Cu(NO2)6]对RDX-CMDB推进剂性能的影响  

Effect of energetic combustion catalyst K2Pb[Cu(NO2)6]on performance of RDX-CMDB propellant

作　　者：夏亮 郭效德[1] 梁力 吴瑞强 魏晓琳 郭鑫娟 XIA Liang;GUO Xiaode;LIANG Li;WU Ruiqiang;WEI Xiaoling;GUO Xinjuan(National Special Superfine Powder Engineering Technology Research Center of China,NUST,Nanjing 210094,China;Shanxi Xingan Chemical Industry Group Co.,Ltd.,Taiyuan 030008,China)

机构地区：[1]南京理工大学国家特种超细粉体工程技术研究中心,南京210094 [2]山西兴安化学工业集团有限公司,太原030008

出　　处：《固体火箭技术》2020年第4期489-496,共8页Journal of Solid Rocket Technology

摘　　要：采用共沉淀法制备出一种含能配合物K 2Pb[Cu(NO 2)6],研究其作为含能燃烧催化剂对RDX-CMDB推进剂性能的影响。采用X射线衍射仪(XRD)、扫描电镜(SEM)、激光粒度仪、能谱仪(EDS)及高效液相色谱仪(HPLC)对K 2Pb[Cu(NO 2)6]的结构、形貌、粒度、元素分析及纯度进行表征。将K 2Pb[Cu(NO 2)6]采用内加法和外加法两种方式添加到RDX-CMDB推进剂中,探究其对推进剂性能的影响,进一步研究加少量不同铜盐与K 2Pb[Cu(NO 2)6]复配后对燃速和压强指数的影响。采用靶线法、单幅放大彩色摄影技术和甲基紫法测定其静态燃速、火焰结构及化学安定性能。结果表明,制备的K 2Pb[Cu(NO 2)6]样品形貌规整,呈立方体晶型,纯度非常高,达到100%;采用内加法将K 2Pb[Cu(NO 2)6]添加到RDX-CMDB推进剂中,可使原推进剂压强指数降低0.115;将少量不同铜盐与K 2Pb[Cu(NO 2)6]复配调节推进剂的燃烧性能,发现均有明显的降低压强指数和稳定燃速的效果,其中在8~12 MPa范围内,K 2Pb[Cu(NO 2)6]和水杨酸铜复配后可使推进剂的压强指数下降至0.277;火焰结构表明,添加K 2Pb[Cu(NO 2)6]的RDX-CMDB推进剂燃烧符合双基推进剂燃烧的一般规律;在常温常压下,含K 2Pb[Cu(NO 2)6]的RDX-CMDB推进剂可能具有抑制燃烧火焰面积作用;K 2Pb[Cu(NO 2)6]的高温分解产物主要是PbO和CuO,可以协同催化调节推进剂的燃烧性能;添加K 2Pb[Cu(NO 2)6]的RDX-CMDB推进剂的化学安定性能在标准许可范围内,对推进剂化学安定性影响不大。在该RDX-CMDB推进剂中,形貌规整的K 2Pb[Cu(NO 2)6]是一种效果较好的含能燃烧催化剂。An energetic complex K 2Pb[Cu(NO 2)6]was prepared by co-precipitation method,and its effect on the performance of RDX-CMDB propellant as an energetic combustion catalyst was studied.Using X-ray diffractometer(XRD),scanning electron microscope(SEM),laser particle size analyzer,energy spectrometer(EDS),and high performance liquid chromatography(HPLC)to structure,morphology,particle size of K 2Pb[Cu(NO 2)6],elemental analysis and purity.K 2Pb[Cu(NO 2)6]was added to the RDX-CMDB propellant in two ways,internal and external,to explore its effect on the propellant performance.Further study the effect of adding a small amount of different copper salts with K 2Pb[Cu(NO 2)6]on the burning rate and pressure index.The target line method,single-magnification color photography technology and methyl violet method were used to determine its static burning rate,flame structure and chemical stability.The results show that the prepared K 2Pb[Cu(NO 2)6]sample has a regular morphology and a cubic crystal form,and the purity is very high,up to 100%.Adding K 2Pb[Cu(NO 2)6]to RDX-CMDB propellant by internal addition can reduce the pressure index of the original propellant by 0.115.Mixing a small amount of different copper salts with K 2Pb[Cu(NO 2)6]to adjust the combustion performance of the propellant,it was found that both have a significant effect on reducing the pressure index and stabilizing the burning rate.Among them,within the range of 8~12 MPa,the compounding of K 2Pb[Cu(NO 2)6]and copper adipate can reduce the pressure index of the propellant to 0.277.The flame structure shows that the combustion of RDX-CMDB propellant with K 2Pb[Cu(NO 2)6]is in line with the general rule of dual-base propellant combustion.Under normal temperature and pressure,RDX-CMDB propellant containing K 2Pb[Cu(NO 2)6]may have the function of suppressing the flame area.The high-temperature decomposition products of K 2Pb[Cu(NO 2)6]are mainly PbO and CuO,which can synergistically catalyze the combustion performance of propellants.The chemical stability of

关 键 词：K2Pb[Cu(NO2)6] RDX-CMDB 含能燃烧催化剂 压强指数 火焰结构 化学安定性 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]