Simulation of two-dimensional interior ballistics model of solid propellant electrothermal-chem ical launch with discharge rod plasma generator

Instead of the capillary plasma generator(CPG),a discharge rod plasma generator(DRPG)is used in the30 mm electrothermal-chemical(ETC)gun to improve the ignition uniformity of the solid propellant.An axisymmetric two-dimensional interior ballistics model of the solid propellant ETC gun(2D-IB-SPETCG)is presented to describe the process of the ETC launch.Both calculated pressure and projectile muzzle velocity accord well with the experimental results.The feasibility of the 2D-IB-SPETCG model is proved.Depending on the experimental data and initial parameters,detailed distribution of the ballistics parameters can be simulated.With the distribution of pressure and temperature of the gas phase and the propellant,the influence of plasma during the ignition process can be analyzed.Because of the radial flowing plasma,the propellant in the area of the DRPG is ignited within 0.01 ms,while all propellant in the chamber is ignited within 0.09 ms.The radial ignition delay time is much less than the axial delay time.During the ignition process,the radial pressure difference is less than 5 MPa at the place 0.025 m away from the breech.The radial ignition uniformity is proved.The temperature of the gas increases from several thousand K(conventional ignition)to several ten thousand K(plasma ignition).Compare the distribution of the density and temperature of the gas,we know that low density and high temperature gas appears near the exits of the DRPG,while high density and low temperature gas appears at the wall near the breech.The simulation of the 2D-IB-SPETCG model is an effective way to investigate the interior ballistics process of the ETC launch.The 2D-IB-SPETC model can be used for prediction and improvement of experiments.

Cluster Warhead Dispersing Technique and Its Interior Ballistic Calculation

Cluster warhead dispersing technique is analyzed with gas dynamic theory. It is seen that the front cover opening and two stage dispersing system is suitable for guided sub missiles whose number is not so large. The interior ballistic performances of this system are calculated with numerical calculation method. The performances such as the pressure in the pressure chambers and the velocity of the sub missiles are obtained in curve form.

Effects of interior ballistic factors on dispersion of central blast tube cluster munitions

This article uses nonlinear dynamics analysis software AUTODYN-2D to establish an interior ballistic model of cen- tral blast tube cluster munitions dispersion. The interior ballistic process of the central blast tube duster munitions dispersion was simulated. The state of submunitions dispersion was obtained as interior ballistic conditions changed. The effect of shell stress groove on shell opening was discussed. The shell with stree groove is helpful for submunitions dispensing effectively and uniformly. The effect of liner material on submunitions dispersing was discussed. It can be found that foam liner can reduce the interior ballistic pressure, increase the pressure action time, reduce the acceleration of the submunitions and increase the sub- munitions dispersing velocity. These results provide some reference for the theory and experiment research of the central blast tube cluster munitions dispersion.

Numerical simulation and optimized design of cased telescoped ammunition interior ballistic

In order to achieve the optimized design of a cased telescoped ammunition(CTA) interior ballistic design,a genetic algorithm was introduced into the optimal design of CTA interior ballistics with coupling the CTA interior ballistic model. Aiming at the interior ballistic characteristics of a CTA gun, the goal of CTA interior ballistic design is to obtain a projectile velocity as large as possible. The optimal design of CTA interior ballistic is carried out using a genetic algorithm by setting peak pressure, changing the chamber volume and gun powder charge density. A numerical simulation of interior ballistics based on a 35 mm CTA firing experimental scheme was conducted and then the genetic algorithm was used for numerical optimization. The projectile muzzle velocity of the optimized scheme is increased from 1168 m/s for the initial experimental scheme to 1182 m/s. Then four optimization schemes were obtained with several independent optimization processes. The schemes were compared with each other and the difference between these schemes is small. The peak pressure and muzzle velocity of these schemes are almost the same. The result shows that the genetic algorithm is effective in the optimal design of the CTA interior ballistics. This work will be lay the foundation for further CTA interior ballistic design.

Application of Two-dimensional Viscous CE/SE Method in Calculation of Two-phase Detonation

The method of two-dimensional viscous space-time conservation element and solution element (CE/SE) can be used to calculate the gas-liquid two-phase interior flow field in pulse detonation engine (PDE). In this paper, the evolution of the detonation wave and the distribution of its physical parameters were analyzed. The numerical results show that the change of axial velocity of gas is the same as that of detonation pressure. The larger the liquid droplet radius is, the longer the time to get stable detonation wave is. The calculated results coincide with the experimented results better.

Study on the analysis method on ballistic performance of deterred propellant with large web size in large caliber artillery

As for the characteristics of combustibility of deterrent propellant with large web size which is used in large-caliber gun and interior ballistic performance, the combustion characteristics of deterrent propellant are obtained by using closed-bomb experiments. The combustion law of deterrent propellant and the classic interior ballistic model of composite charge are given. By simulation and analysis the results of the artillery firing test, the burning rate variation law and the interior ballistics simulation parameters of propellant A are determined, and the burning rate relationship between propellant A and propellant B obtained from closed-bomb, then the ballistic performance of propellant B is predicted. The results show that the predicted results are in good agreement with the experimental results. The study shows that the burning rate law of deterrent propellant with large web size can be obtained by closed-bomb experiment. Using the method provided in this paper can accurately predict the interior ballistic performance and provide an important basis for improving the accuracy of interior ballistic calculation.

Dynamic inverse control of feedback linearization in ballistic correction based on nose cone swinging

It is a complicated nonlinear controlling problem to conduct a two-dimensional trajectory correction of rockets.By establishing the aerodynamic correction force mathematical model of rockets on nose cone swinging,the linear control is realized by the dynamic inverse nonlinear controlling theory and the three-time-scale separation method.The control ability and the simulation results are also tested and verified.The results show that the output responses of system track the expected curve well and the error is controlled in a given margin.The maximum correction is about±314 m in the lengthwise direction and±1 212 m in the crosswise direction from the moment of 5 s to the drop-point time when the angle of fire is 55°.Thus,based on the dynamic inverse control of feedback linearization,the trajectory correction capability of nose cone swinging can satisfy the requirements of two-dimensional ballistic correction,and the validity and effectiveness of the method are proved.

一种双级弹射作动筒对抛分离输出特性研究

为满足武器系统低过载对抛分离功能要求,设计了一种对抛式双级弹射作动筒,基于零维内弹道理论建立了对抛式双级弹射作动筒内弹道模型,对其分离输出特性进行了仿真,并对内弹道模型的准确性进行了试验验证。结果表明,对抛式双级弹射作动筒内弹道模型准确可靠,压强仿真曲线与实测曲线基本吻合,分离输出参数仿真值与实测值基本一致,误差不超过5%。本研究能够为同类型对抛式双级弹射作动筒的设计提供理论指导。

壁面开孔方式对可渗透喷管推力性能影响数值研究

为降低传统大扩张比喷管在低空飞行时喷管内燃气过膨胀带来的推力损失,提出一种具有自适应高度补偿功能的可渗透壁喷管。对采用不同壁面开孔方式的可渗透喷管进行数值模拟,对比并分析喷管的全弹道推力性能。计算结果显示,可渗透喷管在低空下的推力补偿效果明显,比冲增益最高达10%,在高空下的推力损失低至1%,高度平均比冲增益最高达1.5%。在孔隙率、壁面开孔形状相同的情况下,壁面开孔尺度越小可渗透喷管的推力性能越好,但总体上不同壁面开孔尺度的可渗透喷管的全弹道性能差异为0.6%。产生性能差异的主要原因是相同孔隙率的情况下,低空通过小尺度孔进入喷管的气流更均匀,对可渗透段内壁面压强的提升以及分离激波的削弱效果更好,因此带来的低空推力补偿效果更好。在孔隙率、壁面开孔尺度相同的情况下,采用圆柱孔的可渗透喷管的推力性能要优于圆锥孔的可渗透喷管。综合性能最好的圆柱孔可渗透喷管与综合性能较差的渐缩型圆锥孔可渗透喷管的全弹道性能相差约3.3%。

一种高速低过载导弹弹射分离燃气做功装置设计研究

为满足某型号导弹弹射分离燃气做功系统低过载及高出筒速度的要求,基于两级燃气发生器分时序点火方式,设计了一种新型两级组合式弹射分离燃气做功装置,建立了弹射内弹道仿真模型,对其作用过程中高、低压室内部压强、负载速度及冲击过载进行仿真和试验研究,并与基于单燃气发生器的导弹弹射分离过程进行了对比。结果表明:所设计的两级组合式弹射分离燃气做功装置的负载出筒速度为19.4 m·s^(-1),最大过载为31.4 g,能够满足高出筒速度和低过载的指标要求;低压室最大压强、负载最大出筒速度和最大过载的仿真和试验误差分别为4.4%、-3.1%和2.5%,表明所建立的两级组合式燃气做功装置内弹道模型具有较高可靠性,能够有效指导同类型弹射内弹道设计和性能预测。

模块装药短管炮实验及数值模拟研究

大口径加榴炮主要以模块装药结构为主,炮管内部流场复杂。基于模块装药结构,对短管炮内部燃烧场分区域建立二维轴对称两相流内弹道数理模型,采用MUSCL格式对该模型进行离散求解,编制程序对短管炮膛内流场进行了数值模拟,研究两模块装药结构在燃烧过程中的膛内流场特性以及不同破膜压力对两模块装药结构膛内燃烧的影响。仿真结果表明:与实验值相比,计算获得的膛内压力全局平均误差约为7.42%,峰值误差仅0.72%,说明所建立的内弹道数学模型与编制的程序能够较好地对两模块装药火炮发射过程进行数值模拟。模块药盒对火焰波的传递有阻碍作用,在模块药盒破裂之前,火焰波与压力波主要在模块内部流动,与外界物质交换较少。模块药盒破碎后,火药颗粒才随着压力波向膛内自由空间运动,火焰波和压力波开始在膛内传递。随着模块药盒破裂压力的增大,模块装药膛内发射药燃烧越充分,压力上升时间减少。点火药燃气从传火孔处向周围区域扩散,膛内温度也从传火孔处开始升高,逐渐向四周传导,从而点燃发射药。

基于鲸鱼算法的内弹道性能优化

针对某航炮对最大炮口初速越来越高的要求,以提高最大炮口初速为优化设计目标,对弧厚和发射药药量进行优化设计。选用具有操作简单、跳出局部最优的能力强等优点的鲸鱼算法,将鲸鱼算法与该炮内弹道数学模型相结合,对内弹道性能进行优化。结果表明:该方法优化效果较好,最大炮口初速得到了有效提升,所采用的鲸鱼算法与内弹道相结合是可行的,为后续其他类型火炮内弹道设计提供了一定参考。

一级气体炮发射开启特性分析及试验测试验证

为了研究一级气体炮内弹道发射开启特性,考虑内腔室各联通状态,建立了基于结构参数的内弹道和开启特性的描述方程,仿真分析了一级气体炮自励式开启特性,获得了高压气室、排气室、阻尼腔、缓冲腔和弹后腔的开启过程中位移时间瞬态特性,弹体发射加速规律,明确了弹体发射自励式开启阀的开启条件,并构建了口径为50 mm的一级气体炮发射平台,测试结果表明:试验结果相对于仿真计算最大偏差小于3%,验证了基于内腔室结构参数的描述方程的适应性和准确性,为基于发射参数设计气体炮内腔室各结构参数提供了可靠的数理描述方程。

尼龙-紫铜复合弹带结构设计及动态挤进特性分析

针对大口径火炮在弹带挤进阶段由于应力过大易对炮膛内壁造成损伤的问题,以大口径火炮发射过程的内弹道特性为背景,展开尼龙-紫铜复合弹带的结构设计及其动态挤进过程的数值仿真研究。基于现有紫铜材质弹带,通过注塑工艺制备一种尼龙-紫铜复合结构弹带,降低挤进过程中的弹带应力。利用经典内弹道方程组求解内弹道过程中弹丸弹底压力变化,并作为动力条件展开动力学分析,使用单一及复合材质弹带的弹丸挤进过程中的内弹道动力学参数,分析尼龙厚度对复合弹带性能的影响。研究发现,相比于紫铜弹带弹丸,相同条件下使用尼龙弹带的弹丸内弹道动力学参数更高,而挤进终点时刻弹带应力更低;对于使用复合结构弹带的弹丸而言,其内弹道性能和弹带尼龙含量相关。复合弹带尼龙厚度越厚,则挤进过程中弹丸内弹道动力学参数越高,而挤进终点时刻弹带应力越低。相关研究可为中大口径火炮弹带设计提供一定参考。

火箭弹尾射流对发射平台壁面冲击研究

火箭弹发射时,火箭弹尾部燃气射流会形成波系结构复杂的燃气冲击流场。为分析燃气对发射平台的冲击,基于有限体积法,采用了Realizable k-ω模型,耦合了火箭弹的内弹道过程,建立火箭弹尾部燃气射流三维的数值模拟模型。以安装在发射平台上的火箭发射器为例,分别在火箭弹高角为15°和28°工况下射击时,通过尾部喷出的火药气体流场进行计算,分析尾部火药燃气射流对平台壁面的冲击作用,得到在不同高角射击下不同时刻的气流速度场以及对发射平台壁面的冲击压力,绘制出对壁面的压力曲线图,并且对壁面压力的冲击变化过程做出了分析研究并将其结果与试验对照,验证了数值模拟结果的准确性,在高角为28°时,相较与高角为15°其火药燃气射流对平台壁面的冲击作用明显更大。

汽车安全气囊用混合式发生器点火过程内压影响因素研究

混合式气体发生器具有产气量大、气体温度低、残渣少、启动速度快、节能环保等显著优点,主要应用于汽车帘式气囊。点火建压过程是影响混合式气体发生器内弹道性能的关键因素之一,文章根据某帘式气囊用混合式气体发生器结构、工作原理和工作过程,建立点火建压内弹道模型,分析计算火药配方、火药形状和点火孔规格对点火建压内弹道性能的影响,并且计算结果可以为混合式气体发生器点火建压内弹道性能调节提供一定的理论依据。

低温破碎及装药结构对内弹道性能影响的数值分析

以大口径火炮密实装药发射安全性为背景,对火药颗粒低温破碎及装药结构对内弹道特性的影响进行了数学建模和仿真分析。针对中心点传火管结构的大口径火炮密实装药,建立传火管及装药床的双一维两相流数学模型,结合膛内火药颗粒应力及破碎度函数,采用数值差分方法对内弹道过程进行数值仿真,研究火药温度及混合装药方案对火药颗粒破碎度及火炮内弹道性能的影响。结果表明,在低温条件下,单一装药结构火药颗粒将发生破碎,且破碎度随温度降低而增大,在-20℃和-40℃条件下,最大破碎度分别达到1.896和2.487,膛内压力分别为690.32MPa和803.64MPa,增幅达到16.4%;在总装药质量6.25kg不变的条件下,小颗粒药装药质量从0增至0.4kg,最大破碎度从2.487减至1.803,膛内压力从803.64MPa减至740.81MPa,由此可见混合装药结构可以有效避免火药颗粒的破碎。

内弹道加速度信号误差优化方法研究

在使用弹载存储式加速度传感器系统进行火炮内弹道的运动参数获取时,由于其内部电源纹波与传感器自身所携带干扰等原因,采集到的加速度信号携带多种噪声,导致加速度解算误差变大。为了减小加速度的解算误差,提出了基于改进自适应噪声的完备集成经验模态分解(ICEEMDAN)的加速度信号处理方法,并根据Spearman相关系数与模糊熵值的综合评价方式对模态分量进行降噪处理,使用处理后的模态分量进行加速度信号重构。对重构前后的加速度信号进行时频域分析和多种算法滤波效果对比,结果表明,信号中的噪声被有效滤除,相对于数字滤波、平滑滤波、EMD等算法,ICEEMDAN算法处理后的加速度信号的信噪比有明显提高;处理后的加速度信号解算的平均相对误差率为2.67%,相比于直接对原始信号速度解算,平均相对误差率减小了9.43%。因此在对内弹道加速度信号进行解算时,使用ICEEMDAN算法进行信号处理可以有效降低积分解算误差。

装填参数对水下新型气幕式发射内弹道性能的影响

为降低水下全淹没发射过程中射弹的附加质量,提高射弹初速,基于水下气幕式发射原理,提出了一种气幕的新型形成方式,即通过在发射管内壁开设沟槽,引导射弹后的火药燃气在发射管内汇聚形成气幕;建立了气幕式发射流体动力学模型,对该气幕形成方式下的发射过程进行了数值模拟,分析了装填参数对发射内弹道性能的影响。结果表明,与全淹没式发射相比,气幕式发射可将最大膛压降低89.4%,射弹初速提高53.3%;推进用包覆火药的包覆层燃速指数从0.75增大到0.78时,气幕排水时间缩短,弹丸启动时管内燃气体积分数大幅降低,弹丸初速降低,但内弹道全过程大幅缩短,发射频率提高;包覆层厚度的微小变化对内弹道性能影响较小。

Experimental research on the launching system of auxiliary charge with filter cartridge structure

A launching system with a filter cartridge structure was proposed to improve the muzzle velocity of the projectile.The combustion chamber of the launching system is divided into two fixed chambers,one is located in the breech chamber,and the other is arranged in the barrel.The breech chamber charge was ignited first,and the charges in the auxiliary chambers were ignited by the high-temperature,highpressure combustible gas trailing the projectile.In this way,the combustible gas in the auxiliary chambers could compensate for the pressure drop caused by the movement of the projectile.The proposed device features the advantage of launching a projectile with high muzzle velocity without exceeding the maximum pressure in the chamber.In order to obtain some internal ballistic characteristics of the launch system,some critical structure,such as the length of the filter cartridge auxiliary charge,the combustion degree of the propellant in the chamber,and the length of the barrel,are discussed.The experimental results show that with the increased auxiliary charge length,a pressure plateau or even a secondary peak pressure can be formed,which is less than the peak pressure.The projectile velocity increased by 23.57%,14.64%,and 7.65%when the diaphragm thickness was 0 mm,1 mm,and2 mm,respectively.The muzzle velocity of the projectile can be increased by 13.42%by increasing the length of the barrel.Under the same charge condition,with the increase of barrel length,the energy utilization rate of propellant increases by 28.64%.