少烟HTPB/AP/RDX/Al推进剂比冲效率分析

对少烟HTPB／AP／RDX／A1推进剂能量性能进行了理论计算，通过BSFφ165和φ315试验发动机试验，考察了试验发动机类型，工作压力对经冲效率的影响，而且与高铅含量HTPB／AP／RDX／A1推进剂的比冲效率进行了比较，结果表明，铅含量对推进剂的比冲效率有显著的影响，低铝配方的比冲效率比高铝配方的比冲效率相对要高些；对于推进剂组分确定的配方，合适选择发动机的工作压力，可以不同程度地提高比冲效率，对于同一类型推进剂配方，通过计算理论比冲，结合比冲效率水平，可以对实际比冲进行有效的预估。     

AP/HTPB复合推进剂用纳米Co粉的制备

以CoCl_2·H_2O和水合联氨(N_2H_4·H_2O)为主要原料,采用化学还原法制备了纳米Co粉.在不同工艺条件下制备了树枝状纳米Co粉和球形纳米Co粉,用TEM和XRD对产物进行了表征,同时用DTA测试了加入球形纳米Co粉后AP的热分解性能.结果表明,反应介质的黏度和分散剂性质对纳米Co粉粒度及形貌影响较大,在最佳工艺条件下制备了颗粒尺寸均匀、粒度为50~60 nm的球形纳米Co粉;球形纳米Co粉能使AP热分解反应的高温分解峰温度显著下降;添加质量分数2%的球形纳米Co粉,复合推进剂的燃速明显提高,压力指数大幅降低.     

超声空化-表面活性剂水溶法提取RDX/Al/AP/HTPB炸药中的AP

为了对RDX/Al/AP/HTPB炸药的有效成分进行分离回收,研究了以超声空化-表面活性剂水溶法提取RDX/Al/AP/HTPB炸药中高氯酸铵(AP)的分离工艺,探讨了各工艺参数对AP提取率的影响。结果表明,表面活性剂浓度、提取时间和超声频率是影响AP提取率的主要因素,表面活性剂种类为次要因素,料液质量比和提取次数对AP提取率的影响很小。最佳工艺条件为:室温,提取时间40min,料液质量比1∶3,提取次数1次,超声功率3.0kW,表面活性剂为吐温80(质量分数2.0%)。     

丁羟推进剂溶胀处理的实验研究

采用单一溶剂和混合溶剂分别对丁羟(HTPB)推进剂进行溶胀处理,得到了溶胀比随时间的变化曲线以及溶胀后的质量损失,并对溶胀后的推进剂进行扫描电子显微镜(SEM)/能谱表征。结果表明:HTPB推进剂在溶剂的作用下只能发生溶胀,不能溶解;在单一溶剂的实验中,丙酮的溶胀效果最好;使用合适的混合溶剂可提高溶胀效果;推进剂的质量损失与推进剂的溶胀程度及其组分在溶剂中的溶解度有关;经四氢呋喃溶胀后的HTPB推进剂质量损失率最大,高氯酸铵(AP)组分明显减少,可以用来进行AP的回收。     

超细AP/HTPB悬浮液的流变特性

在改进NDJ-4型旋转粘度仪的基础上。对切应力τ、切变速率γ及剪切速度指数n等流变学参数进行了估算。从填充分数、工艺助剂等方面对含硼富燃固体推进剂用超细AP／HTPB悬浮液流变特性进行了实验研究。结果表明．AP颗粒间通过粘合剂体系形成相互作用是悬浮液呈假塑性流动的主要原因．表面活性助剂(SH)可明显改善超细粒AP的表面性能。     

含微米级AP的HTPB推进剂工艺性能和力学性能

制备了含微米级AP(质量分数大于50%)的HTPB推进剂药浆和标准试件,利用流变仪测试了+20℃和-40℃时药浆的表现黏度,用材料试验机测试了标准试件的力学性能,讨论了增塑比、AP粒度级配、键合剂等对HTPB推进剂工艺性能和力学性能的影响。结果表明,当增塑比为0.42、AP粒度级配采用25%的120μm AP、30%的6~8μm AP和20%的1μm AP时,推进剂样品6h的表观黏度为1 267Pa·s,低温延伸率达到38%。     

HTPB推进剂湿热加速老化实验研究

对HTPB推进剂进行了不同湿热条件下的加速老化实验,并测量了不同老化时间推进剂的失重百分数、力学性能以及恢复吸湿后力学性能的恢复情况,描述了湿热老化实验过程中的实验现象,结合温度和湿度对推进剂作用机理,对实验现象、力学性能的变化和恢复情况进行了分析。结果表明：HTPB推进剂在湿热老化过程中发生了组分分解、降解和迁移,同时产生“晶析”现象;湿热老化过程可以分为三个阶段,其中第一阶段为吸湿占主导的阶段,第三阶段为氧化交联占主导的阶段,第二阶段与湿热老化的应力水平有关,温度≥60℃、湿度≥75%RH条件下为高聚物断链稍占优势的阶段,60℃/65%RH条件下为氧化交联稍占优势的阶段;不同湿热老化条件对HTPB推进剂失重的影响机理不同,85%RH湿度条件下以吸湿占主导作用,≤75%RH湿度条件下吸湿、组分的分解和迁移随老化时间分阶段起作用,温度对化学变化起加速作用;物理老化引起的力学性能几乎可以完全恢复,由化学老化引起的性能退化无法恢复。     

HTPB/Al/AP/RDX复合推进剂组元之间相互作用研究

为了探索HTPB/Al/AP/RDX复合推进剂组元之间的相互作用,用DSC和TG-DTG方法以及分解反应动力学计算研究了递增组元的4个混合体系(包括HTPB黏合剂体系、HTPB/Al、HTPB/Al/AP和HTPB/Al/AP/RDX推进剂体系)中各组元之间的相互作用。结果表明,DTG峰温以及反应速率常数k可以表征各组元之间的相互作用,其DSC和TG过程可以分为3个阶段;除Al外,各组元之间存在相互作用,各阶段的质量损失测定值与按组分含量计算的加合值吻合得相当好,表明各组元并没有明显的跨阶段分解;AP与HTPB黏合剂的分解温度区间接近或部分重叠,在HTPB/Al/AP和HTPB/Al/AP/RDX的混合体系中发生了强烈氧化还原作用:四组元体系中RDX在200℃及220℃的速率常数k分别为1.53和6.81s-1,均大于单质RDX在同一温度下的速率常数1.33×10-6和1.06×10-5s-1,说明AP可以加速RDX的分解,但RDX对AP或(AP+HTPB)分解的影响呈现复杂的情况,由于HTPB/Al/AP和HTPB/Al/AP/RDX两体系中AP与HTPB的共同分解过程中存在“等动力学点”(308.0℃),温度低于此点时(AP+HTPB)分解速率常数k因RDX存在而下降,而当温度高于此点时则该k值因RDX存在而增大。通过RDX分解机理解释了存在这种现象的原因。     

溶解法回收硬质聚氯乙烯的研究

本通过选择性溶解的方法对硬质PVC的回收进行了较为详细的研究，确立了四氢呋喃／正庚烷体系为该方法的最佳体系，其PVC树脂的回收率大于85％。同时实现了溶剂与沉淀剂的回收与循环使用。实验还发现采用先加溶剂后加PVC料的加料方式、提高溶解温度及降低PVC料的粒度有利于PVC料在溶剂中的溶解。     

丁羟复合推进剂的辐射点火

采用CO2激光点火装置,对丁羟复合推进剂的点火过程进行了实验研究,利用描述固体推进剂物化现象的一维传热模型对复合推进剂的辐射点火特性进行了理论分析。通过最小二乘法拟合实验数据得到了丁羟复合推进剂的点火准则。结果表明,丁羟复合推进剂的点火过程主要包括惰性加热及气相点火过程,惰性加热时间和点火延迟时间随热流密度的增大而减小,且随着热流密度的增大,热流密度的影响逐渐降低。固相传热数学模型能够比较准确地描述复合推进剂的辐射点火特性。     

Numerical Simulation of Quenched Combustion Model for AP/HTPB Propellant under Transient Depressurization

In order to study the out‐of‐phase blowing effect of ammonium perchlorate/hydroxyl terminated polybutadiene (AP/HTPB) under transient depressurization, a two‐dimensional periodic sandwich model of AP/HTPB sandwich unsteady combustion was established. The gas‐solid two‐step total reaction was used to couple the gas‐solid boundary layer, and the AP/HTPB step‐down temperature criterion was applied. The numerical simulation comparative analysis under the initial combustion pressure 3.5 MPa∼10 MPa and the initial depressurization rate of 1000 MPa/s∼2000 MPa/s was experimented. The results show that under the condition of initial combustion pressure of 3.5 MPa and pressure reduction rate of 1000 MPa/s, the formation of narrow diffusion chemical reaction zone appears in the initial stage of depressurization; when the combustion pressure drops to about 1.7 MPa, the flame appears dual characteristics: diffusion and premixed combustion; when the pressure dropped to 0.1 MPa, the flame is premixed combustion. AP(g) is the main factor causing the out‐of‐phase blowing effect. During the initial stage of combustion, AP(g) decomposes rapidly and its decomposition product is close to the combustion surface; with the rapid decrease of pressure, the gas‐phase heat feedback decreases, leading to the decrease of AP(g) decomposition rate and AP(g) diffusion to the gas phase, which is the initial phase of out‐of‐phase blowing effect; when the gas phase heat feedback reduced and the temperature is below 750 K, the decomposition of AP(g) is stopped and the undecomposed AP(g) is further diffused to the gas phase region, which exacerbates the out‐of‐phase blowing effect, leading to the extinguishment of AP/HTPB. The unsteady combustion flame extinction time increases with the initial combustion pressure, and decreases with the initial depressurization rate.     

Aging of HTPB/Al/AP Rocket Propellant Formulations Investigated by DMA Measurements

Three HTPB‐based rocket propellant formulations containing ammonium perchlorate and aluminum particles, with different aluminum content and particle size, have been manufactured. The study has focused on the change of mechanical properties with aging time by using dynamic mechanical analysis (DMA). Therefore, propellant formulations underwent an accelerated aging program, in air (RH<10 %), between 60 °C and 90 °C with aging time adjusted to a thermal equivalent load of 15 to 20 years at 25 °C. DMA investigations revealed distinct changes in the shape of the loss factor curve. These curves were modeled with three exponentially modified Gaussian (EMG) functions in order to get the molecular interpretation of the involved aging phenomena by separating the binder fractions with different mobility. Aging of propellant formulations can be followed by considering only two parameters: the areas of the second and third loss factor transition peaks (A₂, A₃), and the corresponding maximum temperature values of the assigned Gauss peaks (Tc₂, Tc₃).     

不同温度条件下HTPB推进剂干燥恢复研究

以在30℃、RH为100%条件下湿老化5 d的丁羟(HTPB)推进剂试样为研究对象,分别进行了在10、30、50℃3种温度下的干燥恢复试验,测试了干燥恢复过程中推进剂试样的失水率和力学性能。综合分析了试验数据,得到了不同温度下干燥时初始阶段推进剂试样的失水率、抗拉强度恢复速率,以及各力学性能参量恢复度90%且伸长率比值1.2的恢复时间。对抗拉强度测试中得到的断面照片进行了对比和分析,将样品30℃干燥恢复1、4、9 d后的单向拉伸曲线绘制在一张图上进行比较寻找规律,在对试验数据和试验现象分析总结的基础上探讨了HTPB推进剂干燥恢复过程中氢键的作用规律。     

亚大气压下AP/HTPB微尺度稳态燃烧的数值模拟

为研究亚大气压下高氯酸铵/端羟基聚丁二烯(AP/HTPB)的燃烧特性,采用三步反应动力学机理,建立二维三明治模型,耦合气固两相;对20~80kPa下AP/HTPB的微尺度燃烧进行模拟,并与高压下(4MPa)AP/HTPB燃烧特性差异进行对比。结果表明,亚大气压下BDP模型中第一步反应靠近燃面,放热量较大,在AP/HTPB推进剂燃烧过程中占主导地位;燃烧环境压强不同,导致火焰的特性不同,亚大气压下火焰中扩散与混合过程共存,高压下为扩散火焰;相比于高压,亚大气压火焰离燃面远,面积大;由于高低压下放热区域及放热率差异导致气固相温度分布不同,从而影响燃面形状,亚大气压下AP与HTPB交界处相对于整个燃面突出,而高压下交界处相对于整个燃面凹陷。     

Effect of Coating of Ammonium Perchlorate with Fluorocarbon on Ballistic and Sensitivity Properties of AP/Al/HTPB Propellant

Fluorocarbon polymers are used to enhance thermal stability and electrostatic protection of composite propellant compositions. A precipitation technique has been developed to coat ammonium perchlorate (AP) using a copolymer of hexafluoropropylene and vinylidene fluoride (HFP‐VF) with the help of solvent‐counter solvent method. The coated AP has been used to prepare propellant compositions in different ratio based on hydroxyl terminated polybutadiene (HTPB), aluminium powder along with uncoated AP and studied for viscosity build‐up and visco‐elastic behaviour as well as mechanical, ballistic, thermal and sensitivity properties keeping 86% solid loading. The data on viscosity build‐up indicate that as the percentage of viton coated AP increases end of mix viscosity and viscosity build‐up increase accordingly. The mechanical properties data reveal that tensile strength and percentage elongation are found in increasing order. The burn rate of the composition also increases on higher percentage of HFP‐VF coated AP. The thermal stability of composition increases as the percentage of HFP‐VF coated AP increases. The data on sensitivity indicate that impact sensitivity decreases on increasing the percentage of HFP‐VF coated AP while no change is observed in friction sensitivity value.     

丁羟推进剂/衬层粘接界面材料力学性能研究

比较了目前测试推进剂/衬层粘接界面性能的方法。针对丁羟推进剂/衬层粘接界面,采用国内外关于推进剂与金属材料粘接界面性能的微型拉伸试验方法,设计并开展了微型拉伸试验,得出该推进剂材料在粘接界面处的受影响区域范围及相应的材料性能特征。