bluuebunny/crossref_metadata_2025_split huggingface dataset:
Thermal stability of 80 wt.% hydroxylamine nitrate/water
Authors: Kang L M , Xu S , Zhu C G , Xu F Y , Zhang J X , Wu X L , Luo Y M , Yang N 
Published: December 2024

Abstract
Liquid propellant systems are seeking alternatives to highly toxic hydrazine, with efforts focused on finding safer replacements. Hydroxylamine nitrate (HAN) as a high-energy ionic liquid is one of them. The purpose of the study is to investigate thermal characteristics of 80 wt.% hydroxylamine nitrate/water by DSC, thermal explosion and ARC tests and to evaluate its thermal hazard. The two decomposition stages for HAN were researched and the apparent activation energies were obtained by Ozawa-Doyle and Kissinger methods. Furthermore, thermal explosion temperature values acquired by DSC and thermal explosion at a constant heating rate were compared. The ARC test revealed the maximum self-heating rate and the time to maximum rate, which were used to classify the thermal hazard risk. Meanwhile, the gas generation of 80 wt.% HAN/water and HAN-based liquid propellant was compared, relating to the explosive hazard. The study is expected to provide valuable insights into the development, preservation, and transportation safety of HAN.
Boron-based combustion modifiers on combustion performance of boron-based fuel-rich propellants
Authors: He Na , Gao Xifei , Xin Yanping , Zhu Xueliang , Zhang Weihai , Zhang Yongli , Wei Jiao , Zhang Yuxuan 
Published: December 2024

Abstract
This paper investigates the effects of different boron-based combustion modifiers on the rheological, combustion and energy release characteristics of boron-based fuel-rich propellants. The results show that boron-based high-energy ionic salts (B1, B2, B3) and boron-based metallic fuels (Mg-Al-B), when combined with (AB+TAB)/HTPB mixed systems, exhibit superior rheological characteristics. The B2 and Mg-Al-B agglomerated particles demonstrate low apparent activation energy and high reaction rate constants, facilitating the rapid combustion of boron-based fuel-rich propellants. Furthermore, the synergistic catalytic effect of B2 and Mg-Al-B increases the static burning rate pressure index from 0.38 to 0.54 at 0.5∼5 MPa, with a dynamic pressure index of 0.52. These modifications improve the energy release efficiency η
c1 of the propellant, the energy release efficiency η
c2 of the primary combustion, and the combustion efficiency η
B of boron powder by 12.93%, 24.61%, and 34.06%, respectively. The primary injection efficiency exceeds 98%, significantly enhancing the combustion performance and energy release efficiency of boron-rich fuels.
Effect of SnO2 Nanoparticles Content on Ignition and Combustion Performance of Boron Particles
Authors: Deng Xueyuan , Yang Suyuan , Du Miao , Li Shuai , Mi Jing , Hao Lei , Wu Chenkai 
Published: December 2024

Abstract
Boron is a potential metallic fuel substitute for solid propellant, however, its application has been limited by the surface oxide layer. Metal oxide are proposed to improve its oxidation performance. In the paper, boron particles were coated with SnO2 nanoparticles (n-SnO2) by a hydrothermal method. The B@SnO2 particles were characterized by SEM, TEM, and XRD. The results show that the boron particles were uniformly coated with n-SnO2 with range from 5 nm to 20 nm. The thermal oxidation, ignition and combustion performances were characterized by using TG-DSC, oxygen bomb calorimeter and laser ignition testing system. The relationship between the content of SnO2 and the performance of ignition and combustion were established. Significant reduction of oxidation temperature of boron particles was observed after coating with n-SnO2. The effect was more obvious with increasing SnO2 content. Furthermore, with the increase of SnO2 content, the ignition delay time of B@SnO2 particles decrease, its heat of combustion and combustion efficiency first increase then decreases gradually. Compared with boron particles, the maximum combustion efficiency of B@SnO2 particles reaches to 86.03%, increased by 57.19%, and the minimum ignition delay time reaches to 8 ms, decreased by 46.7%. Therefore, the coating significantly reduced ignition temperature and increased heat, and the particles has profound application potential as the solid fuel.
Calculation of closed combustion performance based on evolution of gun propellant burning surface
Authors: Yuan Maobo , Liu Jihua , Zhao Yuhua , Jin Jianwei , Zhao Hongli , Guo Zhigang 
Published: December 2024

Abstract
In order to enhance the combustion performance evaluation ability of irregularly shaped gun propellants and accelerate the development of propellant energy-release control technology, the present work provides the calculation method of closed combustion performance based on the evolution of gun propellant burning surface. The 3-D structure of the gun propellant should be built, and then a steady-state heat conduction equation with a source term is set, which can be considered as the Poisson equation with a diffusion term. The variable in the equation is the burned web thickness of the propellant grain. Afterwards, finite element meshing was performed on the 3-D structure to obtain a dynamic database of equivalent surfaces with burned web size. The pressure during the closed combustion process can be obtained from the mass conservation equation as a function of the burned web thickness. Furthermore, the combustion time field can be derived based on the functional relationship between burning-rate and pressure. Ultimately, the variation of gas pressure versus time in the closed bomb could be obtained. The results showed that the burnout time of the tubular propellant was 1.6 ms shorter than that of the inner pore offset 0.5 mm under the design conditions. This research can provide researchers with a new method for calculating the closed combustion performance of irregular gun propellants, which can be applied to the design of propellant shapes and the study of launch safety of propellant charges.
Experimental study of propellant/liner interface fracture characteristics
Authors: Wang Guijun , Wu Yanqing , Wang Yuxiang , Huang Fenglei , Wang Tao 
Published: December 2024

Abstract
The propellant/liner interface debonding is one of the main failure modes affecting the structural integrity of solid rocket motors. In order to study the mechanical properties of the propellant/liner interface, the Double-Cantilever Beam (DCB) specimen of the propellant/liner interface was improved. Based on the propellant/liner interface DCB specimens, tensile tests at different temperatures and loading rates were carried out. Based on the digital image correlation(DIC) method, the strain field of the whole DCB specimen and the propellant part was analyzed respectively. Meanwhile, the fracture morphology of DCB specimen was analysed. The results show that the improved specimen can effectively characterize the properties of the propellant/liner interface. The propellant/liner interface shows obvious temperature and strain rate dependence, and the effect of temperature on the propellant/liner interface performance is more significant than that of loading rate. The deformation at the propellant/liner interface of the DCB specimen can reach about 50%, and the interface fracture mode of propellant/liner is cohesive fracture.
Numerical study of thermal safety of passive semiconductor bridges based on multiphysics field coupling
Authors: Zhang X , Liu P , Duan JN , Feng F 
Published: December 2024

Abstract
In order to study the thermal safety of high passivation semiconductor bridges, a NTC (negative temperature coefficient) thermistor is integrated into the SCB (Semiconductor Bridge), and the SCB-NTC shunt and the temperature change in the bridge area and the temperature change in the bridge area of the SCB are investigated based on the COMSOL under the excitation of different constant current sources. The results show that NTC has an obvious inhibiting effect on the temperature increase of SCB bridge area. The thermal equilibrium temperature of the bridge area is about 172 °C under 1.5 A excitation condition; under 2 A excitation condition, the thermal equilibrium temperature of the bridge area is about 206 °C. The current flowing through the NTC under 1.5 A excitation condition rises from 0.45 A to 0.78 A and stays unchanged; under 2 A excitation condition, the current flowing through the NTC rises from 0.6 A to 1.35 A and stays unchanged. By integrating the NTC on the SCB, the NTC thermistor shunt can reach 52%∼67.5%, which can reduce the temperature of the bridge area by 55%∼70%. The above simulation results are compared with the experimental results, and the simulation results are in high agreement with the experimental results.
Energy Release Characteristics of Laser Ignited Al/PTFE Reactive Materials
Authors: Wang Tianyi , Zhang Zhenwei , Ji Cheng , Cai Yuepei , He Yuan , He Yong 
Published: December 2024

Abstract
In this study, the energy release mechanism in aluminum/polytetrafluoroethylene (Al/PTFE) reactive materials was investigated through combustion experiments employing laser ignition. Al/PTFE specimens with different Al particle sizes and different ratio were prepared by molding and sintering. The combustion processes and temperature fluctuations were documented using high-speed cameras and temperature sensors. It was found that specimens with micron Al failed to sustain combustion following the cessation of laser energy, whereas specimens with nano Al displayed a lower ignition threshold and sustained self-propagating reactions. The high surface reactivity and extensive specific surface area increased the susceptibility of specimens with nano Al to oxidation, which, following initial reactions, resulted in diminished reactivity and reduced energy release compared to specimens with micron Al. As the Al content increases in the specimens, the time required to reach the highest reaction temperature is reduced, concurrently with an augmentation in energy liberated. This correlation substantiates that within specified boundaries, an elevation in Al content precipitates an enhancement in both the efficacy and magnitude of the energy release.
Analysis and comparative study on the detonation performance of different heavy metal azides through theoretical calculations
Authors: Peng Yue , Zhang Lei , Xie Mingwei , Meng Qingying 
Published: December 2024

Abstract
In this paper, the detonation performance of different types of heavy metal azides is analyzed and compared using the detonation thermodynamic calculation method. Using the Virial-Peng-Long (VPL) equation of state (EOS) which based on the theoretical values of the 2-5th order virial coefficients of the Exponential-6 (Exp-6) potential to describe the high temperature and high pressure thermodynamic state of the gaseous detonation product N2, and the trinomial EOS Wu-Chen-Peng (WCP) which based on the universal Debye temperature specific volume function was used to describe the thermodynamic relations of the corresponding condensed metal product. Based on the VPL EOS and WCP EOS, the detonation velocity, detonation C-J (Chapmann-Jouguet) pressure and isentropic expansion P-V relations of detonation products for four kinds of metal azides: lead azide, silver azide, cuprous azide, and cupric azide, were obtained at different densities through detonation thermodynamic calculations. The detonation performance of different metal azides was compared and evaluated by combining detonation heat and gaseous product content. The reaults show that cupric azide has relatively better detonation velocity and work capacity, especially suitable for initiation by driving flyer. Lead azide and silver azide have higher detonation C-J pressure which are suitable to direct initiation.
The detonation pressure measurement of lead azide based on PDV technology
Authors: Yuan Xiaoxia , Yang Kun , Qin Guosheng , Wang Kexuan 
Published: December 2024

Abstract
In order to measure the detonation pressure of lead azide, a test method and device for the detonation pressure of lead azide was designed in this paper. Based on the PDV technology, the interface particle velocity tests of lead azide were carried out, and the heights of the charge were 1.5 mm, 2.0 mm and 4.0 mm respectively. Then, the interface particle velocity curves of lead azide with different heights were obtained by mediating the original data. Owing to the interface particle velocity variation process corresponding to the pressure distribution in its ZND detonation model, we can obtain the VM peak and CJ point of lead azide from interface particle velocity curve of 4.0 mm charge height. The VM peak and CJ point of lead azide is 1553±30 m/s and 1031 m/s, respectively. Finally, based on impedance matching formula, it can be obtained that the VN pressure is 25.097 GPa and the detonation pressure (CJ pressure) is 15.705 GPa, and the duration of the detonation reaction zone is about 49 ns.
Life Assessment Method And Current Situation Analysis of Initiating Explosive Device
Authors: Li Fang , Wang Hong gang , Wang Meng , Wang Yanyan , Zhang Dong dong 
Published: December 2024

Abstract
This paper analyzes and studies the methods and current status of life assessment for initiating explosive devices in China. The main focus is on the analysis of methods and standards for evaluating the storage life of initiating explosive devices, the impact of acceleration models and coefficients on the results of life assessment, and the impact of experimental program design on the results of life assessment. The reasons for the deviation between the results of life assessment for initiating explosive devices using accelerated life testing methods and the storage life of initiating explosive devices in natural environments are discussed, and suggestions for the use of life assessment methods for initiating explosive devices are proposed.
Laser Response Mechanism of Typical Ammonium-Nitrate and Furazan based Energetic Graphene Oxide Composites
Authors: Chen Jianhua , Lu Feipeng , Yu Xiaogang , Zheng Wei , Peng Qiqi , He Aifeng , Jing Bo 
Published: December 2024

Abstract
Graphene oxide (GO) had been used for the energetic performance regulation of high energy density energetic materials (HEDMs), such as balancing the contradiction between high energy and high sensitivity of ammonium nitrate and furazan based energetic materials. However, GO based energetic composites shown photosensitization characteristics, which could bring risks to their safe application in novel battle environments. In this paper, cyclotrimethylnitrosamine (RDX), hexanitrohexazazane (CL-20), and 3,4-dinitrofurazanyl Furoxane oxide (DNTF) were taken as typical research objects to prepare their GO based energetic composites, and an evaluation method of laser response characteristics of energetic materials was established, the laser response characteristics and hot spot ignition mechanism of GO@RDX, GO@CL-20, and GO@DNTF were obtained. This work not only provided ideas for the safety design of energetic materials, but also provided support for applications such as reliable ignition output.
On experiments of the Al/PTFE cylindrical shell under inner explosive loading
Authors: Du J Y , Guo L , Zhang Z , He Y 
Published: December 2024

Abstract
To investigate the reactive incandescence of the Al/PTFE energetic material under explosive loading, this study utilized explosive-driven experiments with two inert control groups, Al2O3/PTFE and W/PTFE. According to explosion experiments, it is found that the firelight of the Al/PTFE cylindrical shell are brighter, cover a wider range, and last longer than the inert shell. Furthermore, it is considered that the subsequent aerobic reactions have a relatively minor impact on the shock wave parameters, especially the peak overpressure.
Prediction of fragment impact energy release overpressure based on machine learning
Authors: Zhang Z , Zhang Z Y , Du J Y , Cheng J , Chen P , Ma Y , Wang C T 
Published: December 2024

Abstract
The overpressure within a quasi-sealed chamber serves as a crucial metric for assessing the energy release behavior and impact potential of energetic fragments. Combining one-dimensional shock wave theory and material microparameters, different machine learning models were trained to predict the overpressure generated by different energetic fragments. The final results demonstrate that the RF model achieved the highest prediction accuracy, with an RMSE error of 0.0251 MPa. Notably, the mathematical expression generated by symbolic regression only incorporated four features. After iterative training of symbolic regression using four features, the prediction accuracy was notably higher. This accuracy surpassed that of the DT model and KNN model, which were trained with eight features. However, it still fell slightly below the accuracy of the GBDT model, which was also trained with eight features.
Effect of particle gradation on the rheological properties of three-component HTPB propellants
Authors: Zhang Xu-long , Deng Zi-tong , Xu Wen-long , Jiang Li-ping , Xu Hui-Xiang , Qu Bei , Huang Hai-tao , Li Ji-zhen 
Published: December 2024

Abstract
To compare the applicability of particle gradation models commonly used in solid propellants, a variety of particle gradation models including constant-ratio gradation, maximum loading fraction gradation, and rolling gradation model, were used in the study of three-component HTPB propellants. The initial conditions were set to configure the slurries of the propellants, and the viscosity of the slurries was measured by using a rotational rheometer, and the power model was utilized to determine the rheological superiority of the slurries. The reason for the better rheological properties of the slurries is explained in conjunction with fractal theory. The results show that the Rolling gradation model is the best suited for AP single particle gradation of the three-component HTPB propellants and that its higher applicability may be related to having a higher fractal dimension number, which is positively correlated with the rheological properties. These findings help to optimize the formulation design of a three-component HTPB composite solid propellant and improve its performance.
An image processing method for visualizing the Mach reflection process.
Authors: Haoyu Zhang , Yuxin Xu , Xiaolong Jiao , Xudong Li , Peng Xu 
Published: December 2024

Abstract
In near-ground explosions, Mach reflection occurs, generating Mach waves with considerable destructive power. Consequently, the propagation of these waves is a critical focus in the study of such detonations. This study presents a visualization method for the Mach reflection process based on image processing. By employing image processing techniques, the trajectories of the triple points are obtained, allowing for the analysis of their movement under varying explosive charges and heights. Results indicate that the interaction between detonation products and air, coupled with multiple reflections of rarefaction waves within the detonation products, leads to the convergence of these rarefaction waves at the explosion center, forming new shock waves. These shock waves, upon interacting with the ground, reflect again, resulting in multiple peaks in the overpressure time curves at measurement points. Additionally, it was observed that a smaller scaled height of the explosive charge results in a more curved Mach stem. For a constant explosive height, increasing the explosive quantity only marginally increases the height of the Mach stem. This research provides valuable insights into the Mach reflection phenomena in near-ground explosions.
Advances in surface coating and performance enhancement of ammonium perchlorate
Authors: Liu Chao , Chang Shengquan , Su Linan , Wang Hao 
Published: December 2024

Abstract
Ammonium perchlorate (AP), which has the advantages of high oxygen content, good thermal and chemical stability, and no solid residue after thermal decomposition, is considered to be the most widely used oxidiser for solid propellant applications. However, the high mechanical sensitivity, moisture absorption, and thermal decomposition temperature of AP seriously affect the performance of the solid propellant. In this paper, we systematically review the research progress of the improvement of desensitization, anti-hygroscopicity, and thermal decomposition performance by surface coating of AP. At the same time, the surface coating methods are focusing on electrospray technology, reduced pressure distillation, ultrasonic synthesis, liquid phase deposition, supercritical fluid, intermittent spray coating, and electrostatic self-assembly coating method. Among above, intermittent spray coating and liquid phase deposition method are the preferred surface coating method due to their uniformity of coating, ease of adhesion and good performance enhancement. It is expected that the research on surface coating and performance enhancement of AP can greatly promote the innovation and development of AP in the field of high burning rate solid propellant.
Study on jet formation characteristics of PTFE/Al composite energetic liner
Authors: Tian Longnian , Li Ming , Peng Yucheng 
Published: December 2024

Abstract
This study aims to elucidate the characteristics of composite energetic jet formation. Employing the finite element software, a numerical simulation was performed to investigate the process of jet formation in a composite energetic liner, which integrates PTFE/Al reactive material with an Al metal liner. A comparative analysis was conducted between the jet formation process of the composite energetic liner and that of conventional energetic liners, the simulation revealed that material stratification occurs during the jet formation process of the composite energetic liner, with the high-temperature region being concentrated in the metal at the jet’s head. The study further examined the impact of the cone angle and relative thickness of the composite energetic liner on the jet’s morphology and temperature distribution during the collapse formation process. It was determined that the cone angle predominantly influences the jet velocity and the distribution of the metal jet, with less significant variance in temperature distribution. The relative thickness of the composite liner significantly affects the material stratification and modifies the temperature distribution within the jet. The outcomes of this research contribute to the practical application of composite energetic liners and offer a foundational basis for further investigation into the damage effects of composite energetic warheads against airfield runway targets.
Laser ignition of a GAP/ADN/AzBT mixture: ignition behavior
Authors: Li H , Zhan L W , Xu S Y , Pei Q , Xu Y , Lu H L , Zhang Z , Yao E G , Hao H X , Zhao F Q 
Published: December 2024

Abstract
The laser ignition experiments of a GAA (GAP/ADN/AzBT(1,1’-Azobis-1,2,3-triazole)) mixture were carried out to study the ignition behaviours and combustion patterns during burning process. The ignition images show that GAA mixture entered a flameless burning regime following a relatively gloomy ignition period while GA mixture generated a visible flame after ignition. The ignition behaviour analysis suggested that adding AzBT to GA mixture could increase the condensed-phase heat release in burning process.