A method for quickly predicting the concentration distribution of desensitizer in 5/7 modified single base gun propellant was proposed. A simple neural network model based on artificial neural network algorithm was established, and the experimental data of desensitizer concentration profile of 5/7 modified single-base propellant was used to train the model. The results show that after data training, the complex correlation coefficient R between the desensitizer concentration distribution curve output by the model and the experiment reaches to 0.93. This result shows that the constructed model can accurately and quickly predict the concentration profile curve of desensitizer in 5/7 modified single-base gun propellant under the given process parameters. Compared with the traditional testing method, it has the advantages of saving time, labor and convenience, which proves that the method has certain practicability. The model can also be used to predict the required manufacturing and storage process conditions of desensitizer propellant according to the desired concentration profile of desensitizer.

Due to the limitation of traditional manufacturing technologies for manuscript complex gun propellants, 3D vat photopolymerization technology was used to print gun propellant composed of hexogen(RDX)and photosensitive resin binder. Rotational viscometer, infrared thermal imager and universal material testing machine were used to test the viscosity, light curing exothermic reaction, mechanical properties of printed propellant. The rotational viscometer test results show that the 3D light curing polymerization printing technology is feasible. The photosensitive resin viscosity can be reduced from 42 to 1.5Pa·s by adding the diluent. Meanwhile, the viscosity can be reduced to a minimum at a very small shear rate. Infrared thermal imager results show that the curing process of photopolymerization is exothermic, and the highest curing temperature is 51.1℃, which satisfied the safety requirements of energy materials such as RDX. The mechanical properties results show that the tensile strength, compressive strength and bending strength of the 3D printed propellant are 6.46, 36.1 and 10.2MPa, respectively. The mechanical strength at room temperature is comparable to that of conventional gun propellant. The results indicate that the 3D printing method based on vat photopolymerization is feasible.

In order to fabricating gun propellants with complex structure, the photocurable gun propellants consisting of ultraviolet curable resin as binder and CL-20 as energetic solid additive are prepared by the material extrusion 3D printing technology. The mechanical properties and combustion performances of printed gun propellants are studied. The results show that the gun propellants with 70% solid content presents good adhesion between the extrusion layers after optimization of the printing conditions. The tensile strength and compressive strength of the printed gun propellant are 10.21MPa and 50.94MPa, respectively. Compared with triple-based gun propellants, the mechanical strength of printed gun propellant is higher, while the maximum deformation rate is smaller. The burn rate of the printed gun propellant was 17.88cm/s at 100MPa and the pressure exponent is 1.47, showing that the application of the material extrusion 3D printing technology for photocurable gun propellants is feasible.

To increase the burning progressivity and internal ballistic performance of small arms gun propellants, multi-hole gun propellants with 4-perforations are deployed, and the static & dynamic combustion performance are investigated. A closed-bomb is used to test the static combustion performance, and 5.8mm testing guns are used to test the dynamic combustion performance. The results show that, without deterring, the progressivity of 4-perforated gun propellant is better than that of oblate ball and 1-perforated gun propellants. The muzzle velocity of oblate ball and 1-perforated gun propellants are 17m/s and 40m/s lower than that of 4-perforated gun propellant, respectively. The light transmittance of oblate ball and 1-perforated gun propellants are 18% and 15% lower than that of 4-perforated gun propellant, respectively. The static and dynamic results show that 4-perforated gun propellants have better progressivity and internal ballistic performance than those of oblate ball and 1-perforated gun propellants.

In order to solve the problem of high chamber pressure of oblate spherical propellant containing high-energy solids at low-temperature, and to avoid the reduction of propellant energy, spherical double-base propellants with nitrate glycerol ether cellulose(NGEC)were prepared. The effects of NGEC on the shape, combustion performance, interior ballistic performance and sensitivity of oblate spherical propellant were investigated. The results showed that the uniformity of shape and size of spherical propellant granules were good after adding NGEC. The combustion of propellants presented progressive burning, and the impact sensitivity decreased by 30%. The interior ballistic performance was improved. At +15, +50 and -40℃, the average maximum bore pressure decreased by 10%, 8% and 15%. The low-temperature(-40℃)mechanical properties were improved, when the fragmentation rate was kept at 50%, and the high impact and impact resistance strength increased by 10.52% and 17.32%. NGEC is expected to be applied to spherical double-base spherical propellants.

To study the frictional static electricity characteristics of high energy nitramine gun propellant, the flume method was adopted to simulate the electrostatic electrification by friction of high-energy nitramine gun propellant in the process of manufacture and application, and a Faraday cylinder was used to measure the frictional electrostatic charge. The influence of the flume length, contact medium, humidity, morphology and propellant formulation on the electrostatic accumulation characteristics of the propellants were systematically studied. The results show that the high energy nitramine propellant granular is negatively charged after passing through the stainless steel flume. The electrostatic accumulation of propellant particles decreases by nearly 50% when the environmental humidity increases from 28% to 68%. According to the contact medium, the effect degree on electrostatic accumulation of the gun propellant is stainless steel > conductive rubber > aluminum alloy. The triboelectrification performance of homogeneous azide gun propellant is basically the same as that of high energy nitramine gun propellant. The larger the contact area between the particle and the chute, the higher the electrostatic accumulation. Due to the stripping of RDX particles, the electrostatic accumulation of nitramine gun propellant with 40%(mass fraction)RDX is 35% higher than that of homogeneous nitramine propellant. Luster treatment with 0.1%(mass fraction)of graphite can reduce the electrostatic accumulation of high energy nitramine gun propellant close to zero, while the electrostatic accumulation of the granular is reduced by 34% adding 0.75%(mass fraction)CNT.

A method for calculating and designing the shape of special-shaped propellants was proposed to calculate the burning surface area of propellants in the simulation of interior ballistic performance. The triangular, trapezoidal and quadrangular cylindrical propellants were designed. The change of surface area and volume with the burn depth was calculated using the principle of splitting-calculation-integration. The functional relationship between the generation intensity of gas and the combustion percentage of the propellant was deduced based on the geometric combustion law. Meanwhile, the effect of the inner-hole diameter on the incremental combustion performance of propellants was analyzed. The 12-hole trapezoidal cylindrical propellant was prepared to verify the accuracy of theoretical calculation. The results show that on the basis that the inner and outer web thickness remains the same and the length-to-diameter ratio unchanged, all the special shaped propellant possesses a progressive combustion characteristics. The splitting point moves backwards as the pore size decreases. However, the inner-hole diameter has a limited impact on the combustion process. The theoretical and experimental results of 12-hole trapezoidal cylindrical propellant deviate with each other resulted from size deviation and the ignition inconsistency. But, the 12-hole propellant still presents a combustion progressivity.

In order to evaluate the sensitivity of the gun propellant charge, the controllable pressure relief method was used to simulate the shell constraint of gun propellant charge. The pressure relief component was designed and installed at one end of the cook-off bomb to stimulate the extracting bullet force. The semi-closed bomb was used to verify the relief pressure. Slow cook-off tests were conducted to estimate the single-based gun propellant and low sensitive gun propellant by pressure relief cook-off bomb and standard cook-off bomb respectively. The results show that under the designed gas pressure of 10MPa and 5MPa, the pressure relief component responds quickly and the pressure relief response deviation is less than 10% in the semi-closed bomb test. For single-based gun propellant, the response degree in the standard and the pressure relief cook-off bomb is similar, presenting the reaction level of violent combustion. For low sensitivity gun propellant, there is a clear difference response level between the standard and pressure relief cook-off bomb. The low sensitivity gun propellant presents a mild combustion in the pressure relief cook-off bomb, and a violent combustion in the standard cook-off bomb.

The total volatile(alcohol and ketone)content of triple-based gun propellant during drying process was quickly determined by near-infrared spectroscopy. By comparing the spectral characteristics of triple-based gun propellant sample and the total volatile, the optimal modeling spectrum of the total volatile was determined. The optimum spectral pretreatment method was finally confirmed, depending on the effect of spectra pretreating methods of triple-based gun propellant. The calibration model of triple-based gun propellant was established by partial least squares method(PLS), and the optimal principal factor of the total volatile model was chosen as 8, and the prediction ability of the model was demonstrated. The results show that the optimal spectral range is 5700-6100cm^-1, and the best spectral pretreating method is the combination of first order derivative and SNV.The determination coefficient of the calibration(R²_C)is 0.9703, the root mean square error of calibration(RMSEC)is 0.1497; the determination coefficient of prediction(R²_P)is 0.9628, and the root mean square error of prediction(RMSEP)is 0.1879. The ratio of the standard deviation of the validation set to standard error of prediction(RPD)of the total volatile model is 6.7. The model is applied to the detection of the total volatile content in the drying process of triple-based gun propellant, the average deviation of the predicted value is 0.025%. This method exhibited good predictive performance and repeatability, which can realize the accurate detection of the total volatile content during the drying process of triple-based gun propellant in 60s.

In order to research and develop a new type of gun propellant with high energy and high burning rate characteristics, an appropriate amount of high burning rate functional material ethylenediamine triethylenediamine perchlorate(SY)was added in the high energy gun propellant formulation containing CL-20. Thermogravimetric analysis(TG), differential scanning calorimetry(DSC)and accelerating rate calorimeter(ARC)were used to study the effect of SY on the thermal decomposition reaction of the high energy propellant. Meanwhile, the relevant kinetic parameters of the thermal decomposition process were also calculated and discussed. The results show that the SY significantly accelerated the mass loss rate of the gun propellant. The maximum mass loss rate was increased by 43%, resulting from the promoted thermal decomposition of NC component. The adiabatic decomposition termination temperature of gun propellant with 3% SY increased from 790.4 to 1305.7℃, with an increase of 515.3℃. The final exotherm was increased from 1492.72 to 2335.22J/g, with an increase of 1040.50J/g. The addition of SY promoted the thermal decomposition reaction more completely. The results of calculated activation energy by Kissinger and Ozawa method were reduced by 40.5 and 38.5kJ/mol respectively.

To address the problems such as inconvenient operation and difficulty in the accurate control of nitrogen pressure in the current process of nitrogen filling and replacement for launch canisters, and to meet the requirements of nitrogen filling and replacement for launch canisters in remote and harsh environments, an automatic nitrogen filling system based on sparrow search algorithm (SSA)-PID and Kalman filter control is designed. The system takes PLC as the core and adopts the Kalman filter to filter the temperature, humidity and pressure parameters. SSA is used to optimize the parameters of the improved PID algorithm, and then the optimized improved PID control algorithm is employed to complete the control of the nitrogen filling process and the replacement process. Finally, the host computer is utilized to monitor and control the components in the system through MODBUS RTU bus communication, thus realizing the automatic and accurate operation of the nitrogen filling system. The MATLAB simulation and application results show that the nitrogen filling system of launch canisters based on SSA-PID and Kalman filter can improve the working efficiency and quality of launch canister maintenance, realize the functions of manual and automatic working modes, fault alarm and data recording, and meet the requirements of nitrogen filling and replacement for launch canisters in harsh environment.

Using the acoustic emission (AE) technique, a series of Brazilian disk tests with a central notch (BDCN) under mixed loading are conducted to investigate the fracture mechanism of steel fiber reinforced concrete (SFRC). The evolution of the AE parameters during the fracture process is analyzed. The results indicate that the damage process consists of three stages based on the characteristics of the cumulative signal strength and load versus time relationships. The damage in the first stage is caused by the microcrack initiation, and then the coalescence and extension of microcracks. AE signals captured during the third stage are caused by the debonding and extension of steel fibers. By employing the machine learning algorithm and analyzing the AE parameters, the damage mechanism of SFRC is revealed. Using Gaussian mixture models, it is possible to classify damage sources as tensile cracks or shear cracks. Tensile cracks dominate the damage process, while shear cracks contribute to it. From the support vector machine, it is evident that the boundaries between tensile and shear cracks are not always straight lines passing through the origin.

To improve the generalityof launchers, this paper proposes a new type of ejection device, wihch is a controllable thrust vertical launcher similar to the concentric canister. Through the numerical calculation of zero-dimensional interior ballistics and simulation of three-dimensional interior ballistics, the influence of the gas outlet area of the low-pressure chamber on the internal ballistic performance of the launcher is analyzed. By means of polynomial fitting, the relationship between the gas outlet area of the low-pressure chamber and the maximum ejection acceleration, the ejection velocity, and the ejection time are obtained, and the fitted formulas are verified. The findings are as follows. It is feasible to change the gas outlet area of the low-pressure chamber to control the thrust of the launcher; the maximum ejection acceleration, ejection velocity, and ejection time change approximately linearly with the gas outlet area, so as the area of the gas outlet of the low-pressure chamber decreases, the maximum ejection acceleration increases, the ejection velocity increases, and the ejection time decreases; the error of maximum ejection acceleration obtained by the relational expression is within 8%, and the errors of the ejection velocity and the ejection time are both within 4%.

To deal with the problems of ablation, erection and retraction when using the deflector for exhaust conduction during thermal launching process of vehicular missiles, a new exhaust conduction scheme where carbon dioxide is ejected to impact gas jet so as to lower the temperatures of the launch vehicle and the missile is proposed. Taking the computational fluid dynamics(CFD) as the main research method, a three-dimensional steady model is established, and the characteristics of the cross flow field of gas jet and carbon dioxide are analyzed. The conclusions are drawn as follows: the temperatures of the launch vehicle and the missile decrease and then increase with the increase of the length of lower pipes; their temperatures decrease as the angle between the upper pipes and the launch vehicle wall decreases; the temperatures decrease with the decreasing height between the upper pipe orifices and the lower pipes. As the scheme remains meaningful when the distance between the nozzle exit and the ground is changed, this study provides a feasible new idea to design the exhaust conduction system for the thermal launching of vehicular missiles.

For the problem that the propellant structure is difficult to meet the increasing demand of complex structure, a model of extrusion deposition 3D printing is established, and the process parameters in the extrusion deposition 3D printing are determined.The influences of 3D printing process parameters, such as needle inner diameter, printing speed and temperature, on propellant size and tensile strength were experimentally studied. The results show that, when the inner diameter of the needle is 0.7 mm, the printing speed is 3 mm/s, and the temperature is 35 ℃, the size of printed propellant sample is the best. When the inner diameter of the needle is 0.7 mm, the printing speed is 4 mm/s, and the floor temperature is 35 ℃, the tensile strength of printed propellant sample is the best.

The traditional aging invalidation evaluation of gun propellants is mainly for the chemical stability of propellants during storage without considering the migration of deterrent in the aspect of physical change. Based on the diffusion principle and the relationship between the deterrent distribution and the combustion performance, a migration invalidation evaluation method is established for testing the percentage increase in the maximum dynamic vivacity of deterred double-base gun propellants by closed vessel experiment. Through the closed vessel and ballistic experiment, the linear growth model of the increasing percentage of the maximum dynamic vivacity of deterred double-base gun propellants with the aging time was obtained, and the validity of the established method was verified. The variation of the stabilizer content with aging time is analyzed by gas chromatography. It is revealed that the invalidation time of deterred double-base gun propellants caused by the aging migration is earlier than that of the chemical stability. The aging invalidation evaluation of the deterred double-base gun propellants should follow the “double threshold principle” to ensure their storage safety and use safety.

The Realizable k-ε turbulence model，the mixture multiphase model and the dynamic layering mesh update method are used to investigate the interior ballistics of a new independent water-surface launching canister，and analyze its influencing factors by modeling the relative motion between the missile and the canister. The interior ballistics and the internal flow characteristics of canister launcher on water-surface and ground are analyzed and compared numerically，and the influence of the canister emerging velocity on the interior ballistics is investigated. Results show that the launchers on water-surface and ground have the similar flow characteristics in the gaps and in the pressures in the low pressure chambers. The exit velocity of the missile on water-surface is faster than that on ground，the maximum missile load on water-surface is 20% less than that on ground，and the launch time for the water-surface launching is 14% less than that on ground.The flow results show that the gas does not directly interact with the water surface，therefore the phase change energy dissipation does not happen.The emerging velocity changes the ejection velocity increment by affecting the force of water on the canister.The nonlinear effect of the emerging velocity on the increment of ejection velocity can be ignored because the buoyancy variation is far less than the gas force，so the exit velocity of missile is a linear superposition of the emerging velocity and the increment of ejection velocity.

A rapid prediction method of the bearing capacity of launching site is proposed to improve the quick response ability of the missile launching，which is based on linear multiple regression algorithm，back propagation(BP) algorithm and radial basis function (RBF) algorithm. An optimized Latin hypercube sampling method with parameter sensitivity is applied to construct the sample space. The approximate models evaluated by different algorithms under different loads are established and proved to be effective. Evaluation algorithm of the bearing capacity of unknown launching site is established to predict the probable maximum deflection under launch load using dynamical response of the launching site under erection load. The results show that the RBF algorithm has the best prediction performance and the regression coefficients under erection and launch loads are 0.941 and 0.983.The average error between predicted and simulated results is 10.46%. For the launching site with higher bearing capacity，the residual error of the evaluation algorithm ranges in ±2 mm.

The locations, types and orientations of cracks on concrete specimens with bilateral openings during the shear failure process under uniaxial compressive loading are inversed tostudy the temporal and spatial evolution law of cracks based on the improved acoustic emission localization method and the moment tensor theory. The results of moment tensor analysis show that the growth of tensile cracks is dominant in the tensile damage zone, and the growth of shear cracks is dominant in the shear damage zone, which are consistent with the conditions of actual stress and damage in the specimen. This indicates that the moment tensor theory is a useful method to further study the mechanism of damage evolution in concrete，as it can be used for describing the distribution and migration of tensile stress and shear stress effectively. The results of waveform analysis show that the duration ofacoustic emission (AE) signal corresponding to tensile crack is about 800 μs, and the frequency range is 7-500 kHz. The AE signals associated with mixed-mode crack and shear crack have frequency ranges from 7 kHz to 500 kHz and from 7 kHz to 250 kHz, respectively, and have higher duration of about 1 720 μs and 1 880 μs, respectively. The main reason is that the energy released by shear rupture is higher than that by tensile rupture, and the average frequency of shear wave released by shear rupture is lower than that of stress wave released by tensile rupture.

为探索发射装药挤压破碎对燃烧规律的影响，利用发射装药挤压破碎模拟试验装置，对发射药药床进行了系列挤压试验，对不同发射药样品进行了密闭爆发器试验，研究了其挤压破碎发射的密闭爆发器燃烧规律。结果表明，发射药破碎后初始燃烧加强，高压区燃烧减弱。药粒破碎不利于发射装药的发射安全性。

为从微观的角度研究NGu对含RDX的硝胺发射药燃速压力指数改变的影响，采用改进的小型点火燃烧模拟装置，在35 MPa左右对几种发射药进行低压中止燃烧实验。通过SEM电镜观察发射药在低压下燃烧的表面状况。结果表明，在硝胺发射药的燃烧过程中，NGu在燃烧表面形成较厚的熔融层，抑制了RDX的爆燃；RDX的爆燃与燃烧表面熔融层之间的“均衡状态”影响发射药燃速压力指数的变化，当RDX与NGu质量比小于1时，燃速压力指数明显降低；当RDX和NGu同时存在时，发射药的燃烧表面有针状晶体生成。

In order to analyze the low temperature c oefficient mechanism of singlebase propellant deterred by poly (ethylene glyco l dimethacrylate) (D1), the physicochemical properties, liner expansion coeffici ent and mechanical performance, of polymer D1 and singlebase propellant at dif ferent temperatures are studied by dynamic mechanical analyzer and material test er. Combustion performances of deterred multiperforation singlebase propell ants are studied by closed bomb test and interruptedburning test. Results show? that the linear expansion coefficients of D1 has large difference with that of? singlebase propellant. The exposedperforation ratio of deterred singlebase? propellants at low temperature is larger than that at normal temperature. The l ow temperature coefficient effect of singlebase propellant deterred by polyer? D1 is the comprehensive results of two factors:(1) the differences of coefficien t of? expansion between the propellants and polymer D1 lead to some spaces between pol ymer D1 and propellants surface and increase burning surface area at low tempera ture; (2) the increase of burst ratio of deterred multiperforation propellants? at low temperature also reduces the temperature coefficient.

用等离子体点火中止燃烧装置，研究了等离子体点火太根 药、双基药、硝胺药及单基药的燃烧中止现象，借助所得回收样品的显微照片和中止压力- 时间曲线分析了等离子体与发射药的相互作用规律。结果表明，由于等离子体的侵蚀和辐射 作用，发射药的燃烧表面不规则；不同配方发射药的点火延迟时间不同，太根发射药等离子 体点火的延迟时间最短，容易实现等离子体点火。发射药的理化性质，包括配方和添加剂成 分、表面状况、热传导系数和光学吸收系数等对等离子体点火有着显著影响。

将单基发射药亚硝化后用单扫描方波极谱法测定溶液中的二苯胺（DPA）含量，用丙酮溶解单基发射药试样,使用组成与待测样品相同的单基标准样品作工作曲线。在5%丙酮/0.025 mol·L^-1 H₂SO₄/5.0×1^-3mol·L^-1NaNO₂底液中，测量DPA亚硝化产物在电位为-0.5V（vs.SCE）的峰电流。结果表明，峰电流与DPA浓度在3.5×10^-6～1.0×10^-4m ol·L^-1范围内具有良好的线性关系（γ=0.999）。测定了单基发射药8/1 -12样中的DPA含量，与溴化法测定结果一致。试验的加标回收率达98.2%～102.4%。

用密闭爆发器-红外光谱法静态测试和便携红外现场动态测试两种检测方法，对影响某口径炮射导弹发射药燃气成分CO浓度的因素进行测试和研究。结果表明,燃烧压强对发射药燃气中CO浓度没有明显影响，而不同发射药CO生成量有明显区别；降低导弹保温温度、使用内添加剂或同时使用一定用量的外添加剂均可降低坦克车内CO的峰值浓度；开启坦克发动机,将显著提高坦克车内CO浓度的下降速度，而不影响炮尾CO测试的峰值；改善发射药点传火性能，可有效减少炮尾火焰现象。这些试验现象可用水煤气反应机理、氧平衡及内弹道原理来解释。

为建立气体生成猛度Γ与已燃发射药质量分数Ψ的理论表达式，对双层管状变燃速发射药的燃气生成规律进行了理论分析。在服从几何燃烧定律的条件下，以双层管状药的初始药形尺寸及内外层药的燃速比、密度比为基本变量，推导出变燃速发射药的Γ-Ψ表达式，得出发挥双层变燃速管状药渐增性燃烧特点所需的临界长径比。通过Γ-Ψ计算曲线，说明这种发射药的内径、长径比及燃速比影响其燃气生成规律。结果表明，当双层管状发射药的初始药形尺寸及内外层药的燃速比取值适当时，会出现前期为渐增性燃烧、中后期有一个Γ值的阶跃情况。

利用气相色谱法对某新型发射药中钝感剂含量与分布进行了测定.借助一些假设和萃取时间及所萃取樟脑含量数据,建立了钝感剂在发射药中的含量分布模型.分析了结果误差,计算了含樟脑发射药的内弹道性能.讨论了钝感剂含量及其分布对内弹道性能主要指标pm,v0的影响.结果表明,所提出的基本假设是合理的,钝感剂含量及分布显著影响内弹道性能.

采用丙酮石油醚混合溶剂为浸取液浸泡发射药,用气相色谱测定不同时刻从发射药中浸取出来的樟脑,用浸取液中的樟脑浓度c与浸取时间t的关系曲线表征发射药中的樟脑浓度分布.重复实验结果表明,对同一发射药样品,在确定的浸取条件下,浸取曲线重复性一致,浸取曲线仅由发射药中樟脑的浓度分布来确定.实验结果表明,当樟脑的浓度分布变化时,浸取曲线也发生相应变化.因此,可以用浸取/气相色谱法来表征发射药中钝感剂樟脑的浓度分布.

运用差示扫描量热法和化学分析法,研究了RDX在高能太根发射药中的迁移行为.结果表明:含不同粒度RDX的太根发射药,在65 ℃条件下,经过4个月的加速迁移后,发射药中各部位RDX的质量分数与高温加速迁移前基本相同.存贮时间导致太根发射药中RDX含量发生不规律的微量变化,可以认为在测定误差范围内,RDX粒度对其迁移性能也没有明显影响.化学分析法和热分析法所测得的RDX含量一致,表明热分析法用于迁移研究是可行的,是研究含高能固体添加剂的发射药中组分迁移的有效方法之一.

通过塑化成型试验，找出双螺杆机塑化成型的工艺规律，用正交试验确定工艺参数。用极差分析方法分析了溶剂比、模具形式、螺杆组合方式、模具水温、螺杆水温对产品密度、机头压力和扭矩的影响。结果表明，模具形式对 产品密度影响最大，溶剂比对机头压力影响最大，螺杆组合方式对主机扭矩影响最为显著 。分析了螺杆转速对机头压力和加料频率对扭矩的作用关系，为双螺杆技术在连续化、自动 化发射药生产线中的工程化应用提供了依据。

为探索混合硝酸酯增塑的聚醚聚氨酯黏合剂体系的新型发射药的燃烧性能,通过密闭爆发器常规实验和高压实验,研究分析了JMZ发射药在不同压力范围的燃烧特性.结果表明,JMZ发射药在低压下的燃速压力指数较大,具有高含量RDX硝胺发射药的共同特征,但在高压下的燃速压力指数逐渐变小,与制式发射药相当,在燃速压力指数的变化过程中不存在明显的转折现象.另外,JMZ发射药在起始阶段表现出了良好的燃烧渐增性,对身管武器的应用是十分有利的.

试验装置是由等离子体发生器、半密闭爆发器本体和一个专用螺栓以及其他附件组成.中止压力和燃烧室的容积可调,等离子体输出参量如输出能量、峰值电流、充电电压、脉冲宽度等可以根据试验要求在一定的范围内变动.该装置可以研究在等离子体点火条件下,发射药燃烧中止后的表面微观变化和燃烧反应机理,从而了解等离子体能量辐射与发射药吸收关系以及等离子体与发射药相互作用时的能量传递方式及其影响因素.

为满足高膛压火炮对高能发射药力学性能的应用要求,优化了RGD7高能硝胺发射药基础配方的黏结剂体系,分析了高能固体填料RDX和NQ与黏结剂体系的界面粘结性能.用配方体系中加入键合剂方法改善了高能硝胺发射药的力学性能.

为了科学评估库存发射药的安全贮存寿命,通过对库存弹药(发射药)长期贮存试验研究,得到了在库存环境下贮存30多年部分发射药的DPA含量试验数据,建立了相应的数据处理数学模型和安全贮存寿命预测方法.依据试验结果和该数据处理方法,计算出该发射药在置信水平为90%的条件下,安全贮存寿命不低于56年.经试验验证,该评估结果与实际情况基本相符,表明提出的估算库存发射药安全寿命的方法是可以接受的.

针对现有太根包覆发射药,研究了其内外包覆层在不同温度下的力学性能.通过拉伸、压缩和冲击试验,探讨了内外包覆层力学性能的差异,并通过中止燃烧试验,得出实际太根包覆药在不同温度下的破孔规律.研究发现,太根药内外包覆层的力学性能受温度影响较大,可利用这一特性来制造低温感包覆药.加入阻燃剂二氧化钛后,包覆层的力学性能降低,但在不同温度下的变化趋势不变,不会对包覆药的整体效果造成不利影响.

根据身管武器内弹道特点,提出了变燃速发射药的概念,论述了基本原理和实现该原理的技术方法.采用内层为高燃速发射药,外层为低燃速发射药,达到变燃速的目的.实验证明,两层结构的变燃速发射药具有所希望的能量释放规律,表现出很好的渐增性燃烧.变燃速发射同时还具有高能量、普遍适应性、高安全性等特点.

通过对发射药燃烧性能调节与控制技术途径的对比分析,提出了适用于高增塑剂含量的叠氮硝胺(DIANP)发射药燃烧性能调节与控制技术方案,确定了适合DIANP 发射药的钝感包覆剂配方.利用密闭爆发器研究了钝感包覆DIANP 发射药的燃烧性能及其影响因素,试验结果表明:采用钝感包覆处理技术可以降低DIANP 发射药的初始燃气生成猛度,获得了渐增性燃烧的效果.钝感包覆剂的用量是影响钝感包覆DIANP 发射药燃烧性能的主要因素.

首先对炮射导弹的发射特点进行了分析,认为炮射导弹发射药的特殊性在于燃烧压力介于固体推进剂和常规固体发射药之间;针对炮射导弹发射过程中小于100 MPa的压力范围,采用密闭爆发器在相应的压力条件下对其燃烧特性进行测试与评价,并与常规枪炮发射药的测试结果进行比较,认为两者之间具有不同的特征表现,对新型炮射导弹发射药的装药设计具有指导意义.

从发射药能源的本质特性出发,将发射药的科学技术剖析为能量生成与集约、能量释放与转化、能源制造与加工、能源表征与评价4个层面,并对其进行了描述,期望对发射药科学技术本质的认识、相关科学技术概念加以深化,同时为发射药研究者提供参考.