Mussel-inspired PTW@PDA composites for developing high-energy gun propellants with reduced erosion and enhanced mechanical strength

The severe erosion and inadequate mechanical strength are prominent challenges for high-energy gun propellants.To address it,novel PTW@PDA composites was prepared by polydopamine(PDA)-modifying onto potassium titanate whisker(PTW,K_(2)Ti_(6)O_(13)),and after was incorporated into gun propellant as erosion-reducing and mechanical-reinforcing fillers.The interfacial characterizations results indicated that as-prepared PTW@PDA composites exhibits an enhanced surface compatible with propellant matrix,thereby facilitating their dispersion into propellants more effectively than raw PTW materials.Compared to original propellants,PTW@PDA-modified propellants exhibited significant less erosion,with a Ti-Kbased protective coating being detected on the eroded steel.And 0.5 wt%and 1.0 wt%addition of PTW@PDA significantly improved impact,compressive and tensile strength of propellants.Despite the inevitably reduction in relative force,PTW@PDA slightly increase propellant burning rate while exerting little adverse impact on propellant dynamic activity.This strategy can provide a promising alternative to develop high-energy gun propellant with less erosion and more mechanical strength.

Construction of smart propellant with multi-morphologies

Smart materials,which exhibit shape memory behavior in response to external stimuli,have shown great potential for use in biomedical applications.In this study,an energetic composite was fabricated using a UV-assisted DIW 3D printing technique and a shape memory material(SMP)as the binder.This composite has the ability to reduce the impact of external factors and adjust gun propellant combustion behavior.The composition and 3D printing process were delineated,while the internal structure and shape memory performance of the composite material were studied.The energetic SMP composite exhibits an angle of reversal of 18 s at 70°,with a maximum elongation typically reaching up to 280% of the original length and a recovery length of approximately 105%during ten cycles.Additionally,thermal decomposition and combustion behavior were also demonstrated for the energetic SMP composite.

One-step green method to prepare progressive burning gun propellant through gradient denitration strategy

Gradiently denitrated gun propellant(GDGP)prepared by a“gradient denitration”strategy is obviously superior in progressive burning performance to the traditional deterred gun propellant.Currently,the preparation of GDGP employed a tedious two-step method involving organic solvents,which hinders the large-scale preparation of GDGP.In this paper,GDGP was successfully prepared via a novelty and environmentally friendly one-step method.The obtained samples were characterized by FT-IR,Raman,SEM and XPS.The results showed that the content of nitrate groups gradiently increased from the surface to the core in the surface layer of GDGP and the surface layer of GDGP exhibited a higher compaction than that of raw gun propellant,with a well-preserved nitrocellulose structure.The denitration process enabled the propellant surface with regressive energy density and good progressive burning performance,as confirmed by oxygen bomb and closed bomb test.At the same time,the effects of different solvents on the component loss of propellant were compared.The result showed that water caused the least component loss.Finally,the stability of GDGP was confirmed by methyl-violet test.This work not only provided environmentally friendly,simple and economic preparation of GDGP,but also confirmed the stability of GDGP prepared by this method.

Experimental Simulation for Fracture of Gun Propellant Charge Bed

The simulation of compression and fracture of charge bed in chamber is one of the key problems in the study of launch safety of gun propellant charge. A new kind of experimental device that can be used for simulation is given. Its structure and operational principle are introduced. Using a semi-closed vessel as a source of compression force, the device can simulate any kind of dynamic environment in a gun propellant charge. Using the low temperature inert gas （N2） as the compression medium, the device can not only ensure that the simulation is real, but also protect the fragmentized propellant from combustion after experiment. Using the device, many simulation experiments have been accomplished, and dynamic environment of propellant fracture is acquired. With the experiments, fragmentized propellant for the compression and fracture of charge bed is obtained. Results of experiments show that the new device can be used to study the principle of the compression and fracture of charge bed.

Thermal Behavior,Nonisothermal Decomposition Reaction Kinetics of Mixed Ester Double-base Gun Propellants

The thermal decomposition behavior and nonisothermal reaction kinetics of the double-base gun propellants containing the mixed ester of triethyleneglycol dinitrate（TEGDN） and nitroglycerin（NG） were investigated by thermogravimetry（TG） and differential thermogravimetry（DTG）, and differential scanning calorimetry（DSC） under the high-pressure dynamic ambience. The results show that the thermal decomposition processes of the mixed nitric ester gun propellants have two mass-loss stages. Nitric ester evaporates and decomposes in the first stage, and nitrocellulose and centralite II（C2） decompose in the second stage. The mass loss, the DTG peak points, and the terminated temperatures of the two stages are changeable with the difference of the mass ratio of TEGDN to NG. There is only one obvious exothermic peak in the DSC curves under the different pressures. With the increase in the furnace pressure, the peak temperature decreases, and the decomposition heat increases. With the increase in the content of TEGDN, the decomposition heat decreases at 0.1 MPa and rises at high pressure. The variety of mass ratio of TEGDN to NG makes few effect on the exothermic peak temperatures in the DSC curves at different pressures. The kinetic equation of the main exothermal decomposition reaction of the gun propellant TG0601 was determined as： dα/dt=1021.59（1-α）3e-2.60×104/T. The reaction mechanism of the process can be classified as chemical reaction. The critical temperatures of the thermal explosion（Tbe and Tbp） obtained from the onset temperature（Te） and the peak temperature（Tp） are 456.46 and 473.40 K, respectively. ΔS≠, ΔH≠, and ΔG≠ of the decomposition reaction are 163.57 J·mol^-1·K^-1, 209.54 kJ·mol^-1, and 133.55 kJ·mol^-1, respectively.

Formulation development and characterization of cellulose acetate nitrate based propellants for improved insensitive munitions properties

Cellulose acetate nitrate(CAN) was used as an insensitive energetic binder to improve the insensitive munitions(IM) properties of gun propellants to replace the M1 propellant used in 105 mm artillery charges.CAN contains the energetic nitro groups found in nitrocellulose(NC),but also acetyl functionalities,which lowered the polymer's sensitivity to heat and shock,and therefore improved its IM properties relative to NC.The formulation,development and small-scale characterization testing of several CAN-based propellants were done.The formulations,using insensitive energetic solid fillers and high-nitrogen modifiers in place of nitramine were completed.The small scale characterization testing,such as closed bomb testing,small scale sensitivity,thermal stability,and chemical compatibility were done.The mechanical response of the propellants under high-rate uni-axial compression at,hot,cold,and ambient temperatures were also completed.Critical diameter testing,hot fragment conductive ignition(HFCI) tests were done to evaluate the propellants' responses to thermal and shock stimuli.Utilizing the propellant chemical composition,theoretical predictions of erosivity were completed.All the small scale test results were utilized to down-select the promising CAN based formulations for large scale demonstration testing such as the ballistic performance and fragment impact testing in the105 mm M67 artillery charge configurations.The test results completed in the small and large scale testing are discussed.

Innovative boron nitride-doped propellants

The U.S. military has a need for more powerful propellants with balanced/stoichiometric amounts of fuel and oxidants. However, balanced and more powerful propellants lead to accelerated gun barrel erosion and markedly shortened useful barrel life. Boron nitride(BN) is an interesting potential additive for propellants that could reduce gun wear effects in advanced propellants(US patent pending 2015-026P). Hexagonal boron nitride is a good lubricant that can provide wear resistance and lower flame temperatures for gun barrels. Further, boron can dope steel, which drastically improves its strength and wear resistance, and can block the formation of softer carbides. A scalable synthesis method for producing boron nitride nano-particles that can be readily dispersed into propellants has been developed. Even dispersion of the nano-particles in a double-base propellant has been demonstrated using a solvent-based processing approach. Stability of a composite propellant with the BN additive was verified. In this paper, results from propellant testing of boron nitride nano-composite propellants are presented, including closed bomb and wear and erosion testing. Detailed characterization of the erosion tester substrates before and after firing was obtained by electron microscopy,inductively coupled plasma and x-ray photoelectron spectroscopy. This promising boron nitride additive shows the ability to improve gun wear and erosion resistance without any destabilizing effects to the propellant. Potential applications could include less erosive propellants in propellant ammunition for large, medium and small diameter fire arms.

An Operational Modal Analysis Experimental Technique for Self-propelled Gun

The experimental modal analysis of the selected self-propelled gun was completed to obtain its modal frequency distribution and modes by using an operational modal analysis experimental technique.The result obtained by the method was compared with that obtained by the traditional method.It indicates that the two results are in good agreement.

Discussion on Mechanism of Breech-Blow Caused by Propellant Charge

From the view point of launch safety caused by fracture of propellant charge,this paper points out that the safety criterion of pressure wave is inadequate to evaluate the launch safety of propellant charge based on the initial negative differential pressure and sensitivity tests.Generally,the maximum barrel pressure does not depend upon the intensity of pressure wave correspondingly.The pressure wave intensity can not describe the fracture degree of propellant charge in chamber and reflect the mechanical environment of propellant charge fracturing exactly and wholly.The evaluation criterion for launch safety of propellant charge should be built on the basis of depicting the fracture degree of propellant bed.

超临界二氧化碳在螺杆挤出过程中塑化混合酯发射药的研究:在线流变仪设计与实验测量

为了改善混合酯发射药的加工流动性,在其挤出过程中注入超临界二氧化碳(SC-CO_(2))作为增塑剂;为了更好地研究塑化过程,设计制造了一个在线狭缝流变仪用来测量混合酯发射药的剪切黏度和流变参数。流动曲线表明,混合酯发射药和SC-CO_(2)/发射药混合物都是非牛顿假塑性流体,幂律模型可以用来描述SC-CO_(2)/发射药混合物的流变行为。实验研究了剪切黏度随加工温度和增塑剂含量的变化规律,结果显示较高的加工温度有利于降低剪切黏度。在注入SC-CO_(2)后,黏流活化能降低了约20 kJ/mol。SC-CO_(2)被证明是一种有效的增塑剂,可以显著改善混合酯发射药的流动性。并且随着SC-CO_(2)含量的增加,挤出过程中的流动性会更好,但增塑剂含量的不断增加并不能无限制地提升塑化效果。

含CL-20的微孔发射药的设计及性能研究

为了研究六硝基六氮杂异伍兹烷(CL-20)含量及微孔结构对发射药性能的影响,采用超临界发泡工艺设计并制备了含CL-20的微孔发射药。利用扫描电子显微镜(SEM)观察了发射药的形貌结构,通过密闭爆发器实验、简支梁冲击仪和摩擦感度仪等研究了发射药的燃烧性能、力学性能和感度。结果表明:CL-20颗粒均匀地分散在样品表面及内部,样品内部形成了大量尺寸为0.08~2.00μm的泡孔;CL-20颗粒的加入降低了样品的力学性能,CL-20含量越高,样品的抗冲击强度与拉伸强度降低得越明显;随着CL-20含量的增加,样品的摩擦感度和静电感度会随之升高,燃速也会得到一定程度的提高;经发泡改性后的样品的力学性能弱于未经发泡改性的样品;发泡工艺能够抑制因CL-20含量上升而导致的感度上升;经过发泡后的样品,燃烧性能得到了显著提升,样品的L-B(相对动态活度-相对压力)曲线在B为0~0.10范围内即出现急速上升趋势,L在B为0.14~0.18范围内达到最大,CL-20质量分数为15%和20%时,L_(max)分别为14.39 MPa^(-1)·s^(-1)和9.70 MPa^(-1)·s^(-1)。

自行加榴炮系统反应时间优化研究

武器系统反应时间是反映武器装备自动化水平和火力反应能力的重要战技指标。针对某大口径自行加榴炮系统反应时间过长、作战效率较低、无法适应现代战场需求的问题,推导了操瞄解算模型,按照操瞄解算模型自动调炮,研究了操瞄调炮与弹药装填机构动作的特点和时长,设计分步并行的方法,优化了调炮动作与装填动作的联动过程,并进行试验对比分析。试验结果表明,相较于传统方法,优化后的方法使得该型自行加榴炮的平均系统反应时间减少了7.02 s,系统反应速度提高了32.3%,使之可以快速、高效地完成规定的战术动作,明显提升其战场生存能力和作战效率。

2/1樟单基发射药的真空与非真空环境安定性试验可替代性研究

基于深空探测用单基发射药在外太空中要经受长时间真空、温度交变等复杂的太空环境,而现有标准的安定性评估方法对其不适用的情况,设计了2/1樟单基发射药在75℃高温真空和非真空条件下的对比试验,测试双环境应力下药剂的安定剂含量、热分解性能及药剂成分等安定性敏感参量。结果表明:在试验周期10d内,药剂在75℃真空和非真空的试验环境下,其二苯胺含量、分解温度和氮含量等参数无显著性差异。本研究可为单基发射药在复杂多变环境下的安定性评估提供参考。

高动态条件下的自行高炮稳定跟踪力矩分析

研究了高动态条件下炮塔及身管质量偏心所产生动载荷对自行高炮稳定跟踪系统伺服电机等效输出力矩的影响,基于刚体转动的欧拉动力学方程,建立了质量偏心状态下的炮塔、自行高炮身管与车体之间的动力学模型。分别在车体摇摆、平动,以及摇摆与平动复合运动时,对自行高炮稳定指向和目标跟踪状态下的炮塔方位轴和俯仰轴动力学特性进行了仿真,系统分析了动载荷干扰力矩的特点。仿真结果表明:在自行高炮稳定指向的条件下,车体仅平动时,方位轴、俯仰轴的动载荷及输出力矩与车体加速度呈正比;车体复合运动时,方位轴、俯仰轴的动载荷及输出力矩随车体平动速度的增大而增大。行进间跟踪相比车体无平动下的跟踪,方位轴、俯仰轴的动载荷及输出力矩有了显著的增加,且双轴动载荷对输出力矩的作用更为突出。研究结果为行进间射击的自行高炮炮控系统设计提供了理论依据。

基于改进小波阈值的自行火炮信号降噪方法研究

为有效滤除自行火炮柴油发动机振动信号中的噪声,提出基于改进小波阈值的振动信号降噪方法。运用改进的自适应噪声完备集成经验模态分解处理原始振动信号得到各个本征模态函数分量,通过多尺度排列熵检测分量的随机性,筛选出需要降噪的分量,使用改进的小波阈值降噪方法对筛选出的分量降噪,重构降噪后的分量与无需降噪的分量,获得所需的振动信号。同时,针对人工选取多尺度排列熵中各参数对计算结果影响较大的问题,提出一种改进麻雀搜索算法对多尺度排列熵中各参数进行寻优。分别通过仿真信号和实验室实测数据验证所提方法的可行性和有效性,结果表明:与小波阈值降噪、多小波相邻系数降噪和ICEEMDAN-MPE-小波阈值降噪方法相比,所提方法应用于仿真信号时信噪比分别提升5.989 4 dB、6.078 7 dB和1.565 3 dB;应用于实验室实测数据时,降噪误差比分别降低22.143 3、6.834 9和0.722 7,为自行火炮振动信号降噪提供一种新的思路。

Comparative analysis of the effects of gunpowder and plasma ignition in closed vessel tests

This paper presents the results of a comparative investigation into the effects of the ignition method on the ballistic properties of a single-base gun propellant,as determined via closed vessel tests.Conventional gunpowder ignition and plasma jet ignition methods were used,and differences in the ignition time were analysed.The influence of the ignition method on the dynamic vivacity is discussed.It is shown that this influence is significant in the first phase of the combustion process,and with respect to the low values of the loading density.In the second phase of the combustion process,and for large values of the loading density,the dynamic vivacity plots for the two ignition methods converge.Regarding the burning law,close values of the exponent were obtained for the two ignition methods.The dynamic vivacity plots determined for plasma ignition reveal stronger dependence on the loading density than those determined for gunpowder ignition.The conclusion is that plasma ignition is not a solution to the problems inherent to the process of determining the ballistic properties of propellants,which results in deviation of the burning process from the geometric burning law.

硝基胍发射药制备工艺过程中的流变本构方程研究

以硝基胍发射药实际生产加工过程中不同时段的药料为研究对象,采用自主研发的固体推进剂专业双料筒毛细管流变仪测试药料的流变特性,并对流变特性曲线进行拟合,获得硝基胍发射药的流变本构方程。结果表明:硝基胍发射药具有典型的假塑性流体特征;延长捏合时间有利于高分子链充分溶胀;剪切应力-剪切速率曲线采用自构函数y=Aln^(2)x+Blnx+C时的拟合效果较好;剪切黏度-剪切速率曲线采用Williamson流变本构方程时的拟合效果好。

液体发射药迫击炮低压发射性能的数值及实验研究

针对精确制导炮弹低过载发射需求,研究液体发射药迫击炮低膛压发射性能,建立了液体药再生喷雾燃烧内弹道模型并进行数值计算,基于60 mm口径液体发射药迫击炮实验系统,测试了燃烧室和贮液室压力及弹丸初速,验证了内弹道模型的正确性。分析了液体发射药质量、弹丸质量对内弹道特性的影响规律。结果表明,当液体药装药量为40 g时,燃烧室达到最大压力40 MPa,随着装药量进一步增加,最大膛压保持不变,而膛压充满度逐渐升高,初速增加,最大膛压只决定于再生喷射机构,说明液体发射药迫击炮具有突出的低膛压、高初速发射性能。与传统固体发射药迫击炮相比,液体发射药迫击炮对弹丸质量具有较低的敏感性,在弹丸质量增加130%的情况下,膛压仅增加40%,而弹丸最大过载降低了39%,使其发射过载远低于常规火炮,对发射制导弹药具有明显优势。

聚多巴胺包覆四孔发射药的结构与性能

针对现有球扁发射药的减面性燃烧、钝感剂迁移等突出问题,基于多巴胺(DA)在四孔发射药表面的自聚合反应获得聚多巴胺(PDA)包覆四孔发射药,利用扫描电镜和拉曼光谱研究其微观结构组成,采用热重分析仪、密闭爆发器等分析其热力学、燃烧等性能。研究结果表明:PDA能够较好地包覆于四孔发射药表面,且在四孔发射药表面团聚形成的颗粒尺寸可达5μm;PDA对四孔发射药的表面包覆作用显著提升了四孔发射药燃烧的渐增性,相比于原药,PDA包覆四孔发射药的初始活度L i和最大活度L m分别降低了42.05%和60.25%,渐增性系数提高了53.90%;经加速老化后PDA包覆四孔发射药的燃烧性能变化较小,55℃老化30 d后其L_(i)和L_(m)仅分别升高了1.69%和0.59%,表明PDA包覆四孔发射药具有良好的长贮稳定性。