A ballistic compressor-based experiment for the visualization of liquid propellant jet combustion above 100 MPa

 This paper describes the components and operation of an experimental setup for the visualization of liquid propellant (LP) jet combustion at pressures above 100 MPa. The apparatus consists of an in-line ballistic compressor and LP injector. The ballistic compressor, based on a modified 76 mm gun, provides high-pressure (ca. 55 MPa) clear hot gas for the jet ignition. A piston (projectile) is fired toward a test chamber beyond the barrel’s end, and its rebound is arrested in a transition section that seals the test chamber to the barrel. The LP jet is injected once the piston is restrained, and combustion of the jet further elevates the pressure. At a preset pressure, a disc in the piston ruptures and the combustion gas vents sonically into the barrel. If a monopropellant is used, the jet injection-combustion process then resembles liquid rocket combustion but at very high pressures (ca. 140 MPa). This paper discusses the ballistics of the compression and compares experimental results to those predicted by a numerical model of the apparatus. Experimentally, a pressure of 70 MPa was achieved upon a 12.5 volumetric compression factor by firing a 10 kg piston into 1.04 MPa argon using a charge of 75 g of small-grain M1 propellant. Received: 16 December 1996/Accepted: 15 July 1997     

考虑活塞回复的侧向后喷武器两相流数值模拟

为研究活塞回复运动对火药燃气流动的影响,基于两相流理论对活塞控制侧向后喷武器的发射过程进行了数值模拟研究。考虑控制侧向后喷通道开闭的活塞-弹簧系统的往复运动,建立了结合膛内气固两相流、活塞腔内流固耦合和侧向排气管内气体瞬态流动的武器发射过程数学模型,并将数值模拟结果与相关文献进行了比较验证。得到了该武器发射过程中膛内流场分布与稀疏波传播特性,并与普通武器的膛内流场进行了对比分析。进一步研究了活塞回复运动对火药燃气流动和减后坐效率的影响。结果表明:相对于不考虑活塞的回复运动,在弹丸初速都降低1.52%的情况下,因为活塞回复关闭后喷通道,其减后坐效率由38.86%下降到32.88%,说明在此类武器研究中,不可忽视活塞回复运动。     

Some strain-gage applications to ballistic problems

This paper deals with three ballistic problems in which variable-resistance strain and temperature gages were used. High pressures beyond the range of available piezoelectric pressure transducers were determined from strain-gage measurements on a conventional-propellant gun. During firing, the chamber (a thick-walled tube, OD=2.5 in., wall ratio,w=OD/ID=2) was overstrained and autofrettaged so that elastic behavior was attained at elevated pressures up to about 120 kpsi. Strain gages were used on a light-gas gun to determine chamber pressures, piston velocities and pressures in the central breech (OD=7 in.,w=4.3). The central breech deformed plastically in most rounds, and pressures as high as 800 kpsi were estimated on the basis of the elastic strain recovered during unloading. Transient strains and temperatures were measured on a rifle gas tube (OD=3/16 in.,w=1.5). It was found that surface strains were not a reliable measure of the internal pressure because significant thermal strains were produced by the hot gases flowing through the tube.     

Suppression of oscillations of piston-aided wind tunnels

The method chosen to compensate for the forces acting on the barrel in the course of compression and confinement of the test gas in the settling chamber of a hypersonic wind tunnel with a free locking piston is justified. A method is proposed to compensate for the effect of adverse factors by optimizing the mass of an auxiliary piston introduced into the system. The effectiveness of the method is validated experimentally. As a result, for the case of gas compression to 200 MPa, the displacement of the center of mass of the barrel is reduced from 50 to 0.25 mm, which is smaller than the amplitude of elastic axial extension corresponding to the maximum pressure of the gas. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 49, No. 5, pp. 212–220, September–October, 2008.     

The effect of oil pressure and temperature on barrel film thickness and barrel dynamics of an axial piston pump

Efficiency improvement in piston pumps and motors is a major task in pump development. Just a small improvement in efficiency can have a significant financial impact, particularly on large manufacturing plants employing many large-power pumps. According to the bibliography, effort has been concentrated in studding slipper swash plate leakage, forces, torques and slipper dynamics, but less attention has been given to the understanding the barrel dynamics and the inherent clearance between the barrel and the port plate. This paper clarifies the understanding of the complex barrel dynamics, pointing out how barrel-port plate film thickness depends on oil pressure and temperature. The paper demonstrates that mixed lubrication exist between the barrel face and the port plate under some of the conditions studied, proving that elastic metal to metal forces play an important role when studding barrel dynamics. According to the authors, more effort should be considered into properly designing the barrel sliding surface since both volumetric and mechanical efficiencies are very much dependent on this design. Fluid used hydraulic oil ISO 32.     

Implementation of ADER scheme for a bore on an unsaturated permeable slope

The paper details the implementation of the Godunov‐type finite volume Arbitrary high order schemes using Derivatives (ADER) scheme for the case of a large source term in the continuity equation of the nonlinear shallow water equations. The particular application is the movement of a bore on a highly permeable slope. The large source term is caused by the infiltration into the initially unsaturated slope material. Infiltration is modelled as vertical downwards piston‐like flow with Forchheimer quadratic parameterisation of the resistance law. The corresponding ODE is solved using the fourth‐order Runge–Kutta method. The surface and subsurface flow models have been tested by comparison with analytical solutions. Example predictions of surface bore propagation and wetting front propagation are presented for a range of slope permeabilities. The effects of permeability on bore run‐up, water depths and velocities are illustrated. The ADER scheme is capable of handling the source term, including the extreme case when this term dominates the volume balance. Copyright © 2011 John Wiley & Sons, Ltd.     

Heat transfer during transient compression: Measurements and simulations

Experiments have been performed to assess the utility of unsteady one-dimensional heat conduction modelling for the calculation of heat losses during a free piston compression process. Heat transfer measurements have been obtained within a gun tunnel barrel using surface junction thermocouple instrumentation. The gun tunnel was operated with a relatively heavy piston such that the shock waves induced by the piston motion were weak. Peak heat transfer values are estimated reasonably well by the unsteady one-dimensional model. However, overall quantitative agreement between the measurements and calculations has not been achieved at this stage, principally because the development of turbulent heat transport was not properly modelled. Received 21 September 2001 / Accepted 11 March 2002 – Published online 11 June 2002     

Two-phase flows in gun barrel: Theoretical and experimental studies

In the paper theoretical and numerical model of two-phase flow of solid granular propellant and its products of combustion in the gun barrel during interior ballistic cycle is given. Two cases are considered: base ignition of propellant charge and ignition by igniter. The theoretical model includes the balance equations of mass, momentum and energy for both phases, as well as necessary constitutive laws. The igniter efflux in the propellant chamber is obtained by incorporation in the model the two-phase flow model of igniter function. The convergent, unconditionally stable, numerical procedure is formed to solve the system of equations of the theoretical model. An original procedure of numerical grid adaptation to the flow field increase, caused by the projectile motion down the gun bore, is developed. The TWOPIB code for the computation of whole interior ballistic cycle of ammunition is developed. Four kinds of experimental investigations were carried out:igniter function in open air, flamespreading through propellant charge in the fibreglass tube during base ignition or during ignition by igniter, and firing of 100 mm APFSDS projectile. Verification of the theoretical–numerical approach by the comparison with experimental data is carried out. The great number of computational results is presented for the parameters that can not be measured, but which are necessary for more complete understanding of examined processes. The presented theoretical–numerical access enables, not only the complete optimisation of propellant charges, but more successful solutions of many interior ballistic problems.     

缸内激波对锥顶型燃烧室的活塞破坏机理

以二维数值模拟为基础,研究了锥顶型燃烧室内的冲击波发展的震荡过程,得到作用于活塞不同位置处的超压分布。模拟结果表明:由于燃烧室结构的独特性,导致冲击波能在特定区域进行汇聚,致使该区域超压明显高于其他区域。将该模拟结果与实际破坏失效的活塞进行对比,发现冲击波汇聚区域往往就是活塞被破坏的地方。数值模拟结果与实际破坏结果吻合很好。这为设计燃烧室形状以避免冲击波对活塞造成破坏提供了理论基础。     

固体差动随行装药高初速火炮内弹道理论分析

提出了一种基于差动原理的固体差动随行装药的高初速火炮发射方案,该方案能有效克服传统随行装药技术提高初速必将伴随射弹底部最大压力增加的缺点。它的主要特点是运用差动原理,实现不同组合件之间的速度不同,自动压缩储能室使随行工质向弹后连续喷射,有效抑制和消除了弹丸运动引发的稀疏波影响,提高了火炮工作容积利用率。推导了差动随行组合弹丸不同组合件动力学模型,给出了弹载工质物理量分布关系式。计算结果表明,在最大膛压、飞行弹丸底部最大压力、弹重及弹丸行程等不变条件下,随行药量取10.2 kg,某大口径火炮的弹丸初速可提高26%,火炮工作容积利用率提高约44%。该方案可为火炮提高初速和实现超远程发射提供新的途径。     

自紧身管临界裂纹尺寸的概率断裂力学研究

基于概率断裂力学理论和Mome Caflo模拟方法，本文进行了自紧身管临界裂纹尺寸的可靠性研究。自紧身管内表面的疲劳裂纹考虑为半椭圆形式。裂纹尖端处的应力强度因子由内压和自紧残余应力共同产生。自紧残余应力采用了符合身管材料具有强化和包辛格效应性能推导的公式计算，它产生的应力强度因子通过权函数方法得到。根据断裂准则，可计算出自紧身管的临界裂纹尺寸。实例分析表明，对数正态分布为临界裂纹尺寸的最佳分布，同时给出了在各种置信度和可靠度下自紧身管的临界裂纹尺寸。     

Problem of Increasing the Survivability of Two–Stage Ballistic Guns

The paper proposes methods for increasing the survivability of light–gas guns, including new designs and nonconventional modes of shot. It is established theoretically and experimentally that a decrease in the cone angle of the conical adapter to 2.5 — 3° leads to a severalfold increase in the survivability of the high–pressure chamber. A compound piston with a liquid or gel–like filler is designed. The mode of shot from a light–gas gun with superlight pistons and without a diaphragm is justified and tested experimentally. Conical and measuring adapters with liners made of thermally– and wear–resistant alloys are designed to prevent ablation of the light–gas gun barrel.     

二级轻气炮内弹道的数值模拟与性能分析

为了优化二级轻气炮的设计参数和工作参数,必须进行数值模拟。本文介绍了准一维不定常流的Lagrangian算法,讨论了数值模拟中的若干问题,分析了气动过程。根据我们的数值模拟,归纳了影响气炮性能的一些基本规律,可供选择工作参数时综合分析。     

基于流固耦合的燃气冲刷烧蚀内膛特性分析

火炮发射时,火药燃气与身管间发生剧烈的传热传质作用是导致身管烧蚀的重要因素。为了研究某155 mm火炮中高温高压高速的燃气流对身管的烧蚀特性,采用CFD流固耦合方法,建立了发射过程中的身管非稳态流动传热模型,并根据炮钢在不同温度下的烧蚀特点,将烧蚀过程分为热化学烧蚀和熔化烧蚀,建立了分段烧蚀模型。计算结果表明,身管内壁温度随时间的增加先迅速增大,随后逐渐降低。整体上,内壁温度随身管轴向距离的增大而逐渐降低。身管膛线起始区域的壁面温度最高,其烧蚀是熔化和热化学烧蚀共同导致的,而线膛部的大部分区域仅发生了热化学烧蚀。总烧蚀量随着身管轴向距离的增大而逐渐降低,膛线起始部的烧蚀最为严重,单发总烧蚀量（常温）为5.06μm。同时分析了不同工况对身管烧蚀特性的影响,发现最大烧蚀量与初始壁面温度呈现很强的正相关性,温度的升高会加剧身管的烧蚀。     

一种新型结构火炮身管膛线的计算分析

针对传统的火炮身管内弹道结构形式,提出了一种新型结构形式的火炮身管膛线——渐变截面结构膛线。以大口径火炮身管膛线作为研究对象,计算分析传统等截面结构膛线和渐变截面结构膛线的弹丸弹带挤进阻力、导转侧向力、膛线截面面积和膛线摩擦力的变化情况。计算结果表明,新型渐变截面结构膛线有利于增强弹丸弹带的挤入能力,减少膛线根部应力集中,减少弹丸弹带对膛线的冲击和磨损,有效提升弹丸弹带的闭气性能,同时渐变结构膛线可有效减小弹丸在膛内运动时受到的扰动,使得弹丸在膛内运行平稳,减少炮口章动,在保证射击精度的同时,有利于提高身管的使用寿命。     

有限元在身管与药筒高压接触变形计算中的应用

本文针对自动武器中药筒和身管变形的变间隙、变锥度的特点,构造了身管和药筒的截面环等参元分析模型,并据此建立了相应的增量形式的弹塑性有限元求解方程．针对贴膛不同时刻的特点,在身管和药筒上配置了配点对,应用变形协调条件,编制了药筒和身管高压间隙变形的有限元求解程序．并给出了数值计算实例．     

Determination of gun propellants erosivity: Experimental and theoretical studies

Requirements for higher and higher performances of contemporary guns intensify investigations concerning influence of various factors on barrel erosion. The most important parameter for the life of the gun is the type of the gun propellant. The device based on modification of 37 mm M39 gun for investigating influence of gun propellant on barrel erosion is used. The nozzle (main part of device) mass loss during firing was the measure of gun propellant erosivity. The theory of nozzle erosion includes basic thermal, chemical and metallurgical factors. The main thermal and chemical factors are maximum nozzle inside surface temperature and gun propellant composition. The maximum nozzle surface temperature was determined theoretically by developed interior ballistic model with heat transfer, and experimentally by micro thermocouples measurements and solution of inverse heat conduction problem. The coefficients of gun propellants erosivity are determined in experimental and theoretical way.     

驱动气体的密度梯度对弹丸发射速度的影响

为进一步提升轻气炮的发射能力,提出采用梯度气体替代单一氢气或氦气作为驱动气体的方法,通过对等直径发射器进行分析,建立了弹丸在梯度气体驱动下的加速运动模型,对比了氖-氦梯度气体驱动与单一氦气驱动的发射能力差异,分析了梯度气体参数对发射性能的影响。结果表明,与单一氦气驱动相比,氖-氦梯度气体驱动能够提升0.4～1.4 km/s的发射速度或降低0.2～0.9 GPa的发射过载;气体的密度和活塞的运动速度对发射速度和过载的影响最大,气体压力和多方气体指数的影响次之;梯度气体中,高密度气体应选择多方气体指数和密度较高的气体（如氖气、氩气等）;梯度气体界面位置（高密度气体占比）对发射速度的影响不大,但高密度气体占比少有利于降低弹底压力。     

非火药驱动的二级轻气炮的发射参数分

介绍了一台５７ｍｍ口径一级压缩气炮驱动的１０ｍｍ口径二级轻气炮，并分析了这种气炮的特点。对其发射参数和发射效果之间的关系进行了数值计算模拟，计算弹速与实测弹速的差异小于１０％。根据计算模拟结果，分析了活塞质量、活塞驱动气压、泵管初充气压和弹丸释放气压等发射参量同弹速和二级气室的气压气温峰值的关系，评估了１０／５７二级轻气炮的发射能力。     

Structural Stability of Unsteadily Accelerated Liquid Pistons

The possibility of the fragmentation of a liquid piston moving with variable acceleration, due to air jets forming on its free surface and penetrating inward, is established experimentally. The liquid piston acceleration regimes in which air jets capable of penetrating into the liquid are formed from initial perturbations on its free surface are theoretically analyzed.