超高压环境下再生式喷雾燃烧过程的多维多相流数值模拟

液体药火炮内再生式喷雾燃烧过程的主要特点，一是处于超高压下，二是燃烧过程与决定液体喷射过程的移动边界高度耦合。建立了充分反映上述特点的多维多相流数学模型，对液滴相还考虑了液滴之间的碰撞与聚合以及液滴与湍流之间的相互作用。运用任意拉格朗日－欧拉数值方法进行了数值求解，得出了与实验基本一致的结果。给出并分析了过程各主要物理参量的时空分布，揭示了再生式喷雾燃烧过程的基本特征。     

液体发射药电热化学发射内弹道一维两相流模型及数值模拟

在理论分析的基础上 ,结合实验条件建立了液体发射药电热化学发射内弹道一维两相流数学模型 ,该模型包含电弧等离子体生成和运动、等离子体卷吸液体发射药生成小液滴以及膛内多相流体的相互作用。利用该模型对电热化学发射内弹道过程进行了数值模拟 ,并将模拟结果与实验数据进行了分析比较 ,结果表明模拟结果与实验数据基本吻合。     

再生式喷雾燃烧过程中着火延迟期的影响特性

对液体药火炮中的再生式喷雾燃烧过程进行了大量的实验研究，发现了着火延迟期对再生式喷雾燃烧过程的重要影响。建立了反映着火后燃烧室内压力状态与着火延迟期间各参量之间关系的分析模型；结果表明，随着着火延迟期的延长，延迟期间液体药堆积量不断增加，进而导致着火后压力升高率急剧增大。运用零维数学模型对整个再生喷雾燃烧过程进行了模拟，模拟结果进一步证实了分析模型结论，较好地再现了正常燃烧过程和非正常燃烧过程的基本特征，阐明了着火延迟期对再生喷雾燃烧过程影响的物理本质。     

一种整装式液体发射药燃烧控制技术

介绍了整装式条件下液体发射药（ＢＬＰ）的一种燃烧控制技术。采用多孔介质及其附着剂，改善并控制填充于其中的液体发射药燃烧性能。在不采用喷射雾化装置条件下，实现液体发射药稳定燃烧，控制燃烧速度，强化化学反应过程。     

含能液滴在高压下爆裂性燃烧现象的研究

利用挂滴装置研究了含能液滴ＬＰ１８４６在高温４４０～６２０℃、高压１．５２～３．５５ＭＰａ环境下爆裂性燃烧的规律。给出液滴从受热到爆裂性燃烧的时间序列照片，并定量测试液滴直径随时间的变化关系以及着火延迟期。初步分析了液滴爆裂性燃烧的机理，即液相化学反应。最后建立了液滴着火延迟期的工程计算模型，其计算值和实验数据吻合。     

含能气体射流与液体相互作用的实验研究

为了研究整装式液体发射药的燃烧稳定性的控制方法,设计了点火喷射模拟装置及4种多级渐扩型观察室,利用数字高速摄像系统,观察含能气体射流在液体模拟工质中的扩展过程,并对实验中出现的喷孔壅塞现象进行了分析.结果表明:射流在渐扩型结构中扩展稳定,喷射压力、喷孔直径和渐扩结构对射流扩展形态和气液掺混过程有显著影响,通过合理调整这些参数,可以实现对射流扩展过程的有效控制;喷孔壅塞时射流扩展形态非对称,影响气液掺混,不利于控制射流的稳定性.     

点火能量对单基发射药燃烧爆炸特性的影响

为了探究点火能量对单基发射药燃烧爆炸特性的影响，自主设计了发射药燃烧爆炸试验装置。使用黑火药对单基发射药点火，开展燃烧爆炸实验。通过对铝制鉴定板及约束钢筒内壁烧蚀痕迹的分析，获得不同点火能量对单基发射药燃烧爆炸特性的影响。结果表明，点火初期约束钢筒内发射药燃烧反应不完全，反应剧烈程度较弱；随着距点火端距离增大，发射药燃烧反应剧烈程度变强，但此时反应仍不完全；在约束钢筒末端发射药反应完全。在4.0、5.0和8.0 kJ点火能量下，发射药点火初期到反应剧烈程度迅速增强的成长距离分别为54.66、 53.95和19.38 cm。20.0 kJ能量点火初期发射药反应剧烈程度较强，传播至末端时发射药发生爆燃反应，鉴定板产生明显凹痕；发射药在约束钢筒内不同位置分别发生了缓慢燃烧、快速燃烧和爆燃。     

激波诱导气流与液幕,液柱相经作用的实验研究

利用激波管对激波诱导气流与液幕,液柱的相互作用进行了实验研究。通过比较发现,这种相互作用下的液体块变形破碎过程与以往对于液滴进行的研究结果很不相。     

发射药燃烧热辐射传播规律

采用构建物理数学模型和实验验证的方法,首次提出发射药燃烧热辐射柱体理论模型;利用自由场条件下的单基发射药燃烧热辐射实验,对比分析球体热辐射模型,验证了柱体理论模型能够客观反映发射药燃烧热辐射传播规律。实验表明,自由场条件下4种不同单基发射药药量的燃烧热辐射实验数据与柱体燃烧理论模型相吻合;同时由数据拟合分别得到单基发射药热通量与药量、距离以及热剂量与药量、距离的定量函数关系,可为准确评估单基发射药燃烧热辐射毁伤效应提供相关理论基础。     

高速液体受限射流扩展形态研究

采用一种火药燃烧驱动液体喷射的新装置及其测试系统，研究受限空间中高速惰性液体射流的扩展结构。观察了环境反压、液体粘性、喷嘴结构等参量对射流扩展形态的影响，分析了射流雾化机理。研究结果对改进燃烧室设计及控制燃烧稳定性有一定的指导意义。     

RLPG点火及冷态喷射过程研究

报道了再生式液体发射药火炮 (RLPG)点火及模拟工质冷态喷射过程的实验结果 ,定量测试了燃烧室、贮液室压力曲线。实验表明 ,采用液体阻尼可以有效减弱点火过程中的压力振荡。针对点火喷射过程建立了数学物理模型 ,并进行了相应数值模拟 ,计算值和实验数据吻合较好。研究结果对深入分析再生式液体发射药火炮内弹道循环有指导意义和参考价值。     

HAN基液体发射药电点火特性的实验研究

在两级电点火装置上，利用高压脉冲电源进行了ＨＡＮ基液体发射药的电点火实验。实验观测到:在液体发射药的可靠点火过程中，存在着无电弧与电弧两种放电方式。实验研究了实现无电弧点火、限制电弧放电所需的电源特性参数及点火结构参数。目前电能利用率保持在６０％以上，而电弧放电能量仅占负载所吸收总电能的３０％。这种电点火系统对于提高武器自动化程度、增加射速等均具有重要的实际意义。     

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     

液体药再生喷射燃烧特性的实验研究

利用逆向式再生环形喷射装置，研究了高速喷射条件下液体的点火燃烧性能。实验研究发现:喷射条件下液体药的点火燃烧性能较整装式液体装药容易实现一致性，且燃速大幅度增加。同时研究了伴随再生喷射燃烧过程所出现的高频压力振荡，分析了高频压力振荡产生的原因。提出了液体药喷射条件下点火延迟度的概念，它可作为评价ＲＬＰＧ点火器工作性能的指标之一。利用喷射点火延迟度的概念，比较了液体药喷射点火延迟性能对于喷口面积、活塞质量、液体药粘度及液体药能量等参量变化的敏感性。     

Projectile acceleration in a single-stage gun at breech pressures below 50 MPa

Experimental studies were carried out to investigate projectile acceleration in a single-stage gun at breech pressures below 50 MPa. The gun was driven by firing either liquid or solid propellant. In-bore projectile velocity was continuously recorded using the well-known, precise VISAR interferometer technique so that accurate projectile acceleration data could be deduced. Both the attained projectile acceleration and muzzle exit velocity depend upon the charge-to-mass ratio and the pressure at which the blow-out disk ruptures. The results obtained from these experiments render information on the interplay between propellant combustion and projectile acceleration for low in-bore pressure regimes, and they provide the input data required for adequate numerical simulation.     

Projectile dynamics at low barrel pressures

A mathematical model for a projectile shot at low pressures in the space behind the projectile space is developed. The pressure rise is limited because of the nonsimultaneity of propellant ignition and combustion and the discharge of the propellant combustion products through the gap between the projectile and the walls of the gun barrel. The kinetic characteristics of flame propagation over the propellant particles are determined. A comparison of calculation and experimental data is performed. The calculation results are used in designing 2A85 self-propelled launchers and upgrading 2A30 self-propelled launchers. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 48, No. 6, pp. 44–49, November–December, 2007.     

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.     

再生式液体发射药火炮贮液室流体响应特性的分析

在再生式液体发射药火炮中，贮液室流体系统可能发生由自激振动与强迫振动构成的耦合振荡，在喷射结束期很可能形成共振。文中利用线性化近似方法推导出流体系统压力与流速的传递方程，并分析了贮液室流体系统对于瞬变激励的响应模态，其结论得到了实验结果的验证。这种研究方法对于再生式液体发射药火泡机构设计有重要的指导意义。