摘要
小口径多管转管火炮是近程防御系统的基本组成部分之一,其射击精度直接影响到近程防御系统的反导效能。小口径多管转管火炮发射过程中膛口产生的高温高压复杂激波系是影响其射击精度的重要因素之一。本论文主要通过数值模拟的方法,计算和分析膛口流场的形成发展过程及其对弹丸飞行的影响。具体内容如下：
a)根据小口径火炮发射的实际物理过程,膛口流场的形成和发展与内弹道的瞬态变化过程是息息相关的。对内弹道过程的分析是准确模拟膛口流场变化过程的基础,对内弹道过程的数值分析首先采用集总参数数学模型,采用四阶Runge-Kutta法进行数值模拟,得到弹丸在膛内的运动规律。另外,通过建立火炮内弹道过程一维两相流模型,采用二阶精度的MacCormack差分格式对其数值模拟,分析了发射过程中膛内各状态参量的分布规律以及主要内弹道参量的变化规律,得到弹丸离开膛口时,膛内的气体参数在轴向上的分布情况。
b)模拟弹丸挤进膛内后膛口流场形成、发展及变化过程,耦合内弹道过程分析弹丸出炮口前后膛口附近区域的流场变化。耦合内弹道过程,建立二维轴对称气体动力学模型计算弹前气体及膛口流场,通过弹前阻力将二者同步耦合计算。数值模拟的结果与试验结果相符合,说明建立的模型和采用的计算方法是正确有效的。同时,通过数值模拟的结果详细地反映了膛口附近区域流场的瞬态变化过程。
c)针对火炮发射过程中膛口流场高温、高压、高速以及存在正激波、斜激波、相交激波等特点,构建基于BWIP(Blast Wave Identification Paramete)方法的动态网格自适应方法对某小口径非定常膛口流场进行数值模拟和仿真。对某小口径火炮的发射过程采用BWIP的动态自适应方法进行数值模拟,对于同样的膛口流场捕捉能力,采用BWIP的动态自适应方法可以较大的节省计算量。
d)研究线膛发射旋转稳定弹丸在膛口流场复杂激波系影响下的气动特性。通过划分局部加密的网格,采用双方程湍流模型求解可压缩的三维Navier-Stokes方程,数值模拟和分析旋转SOCBT (Secant Ogive Cylinder Boat Tail model)弹丸在复杂激波影响下的气动特性变化规律。数值模拟的结果与BRL (Ballistic Research Laboratory)实验室风洞实验数据相吻合。通过数值模拟进一步分析旋转速度、攻角、来流马赫数等对弹丸气动特性的影响,得到影响武器射击精度的弹丸表面压力不对称性分布规律以及弹丸阻力升力特性,分析不同旋转速度对内弹道后效期内弹丸速度增的影响规律。
e)根据小口径多管转管火炮发射的物理过程,建立三维气动力计算模型,采用AUSM+格式模拟分析多管转管火炮的膛口流场的发展变化过程。数值模拟的结果揭示了多管转管火炮膛口流场的特性,转管发射弹丸在膛口流场的影响下其表面的压力呈现明显的不对称性,进而导致在零攻角发射的情况下也会产生弹丸的侧向偏移,第一发弹丸的侧向偏移达到1.6m/s,而第二发弹丸出炮口后受到第一发弹丸发射导致的不对称膛口流场的影响,其侧向偏移明显大于第一发弹丸,达到3.8m/s。
The revolving barrel gun is the principal component of the Close-In Weapons System (CIWS). The defense against anti-ship cruise missile was derectly influenced by the gun's shot accruracy. There will be unsteady high-temperature high-pressure muzzle complex shock waves during the revolving barrel gun firing and the shot ejection process has an important effect on the shot accuracy. Numerical methods were used to simulate and analysis the muzzle flow formation and development process and its affect on the projetile movement. The main parts of this research are concluded as follows:
a) According to the actual physical process of the small caliber gun firing, the muzzle flow formation and development process is relational to the interior ballistic process. The interior ballistic lumped parameter model was solved using4th order Runge-Kutta scheme in the numerical simulation. The projectile movement law was got. The one-dimensional two-phase flow interior ballistic mathematical model was established and solved using MacCormack scheme in the numerical simulation. The change laws of interior ballistic parameters were analyzed. Base on the modeling results, the effect of different factors of the interior ballistic performance were discussed. The pressure distributions in the bore at shot exit ware obtained.
b) Muzzle flow fields are simulated from the projectile engraving. Based on the mathematical assumptions, the muzzle flow simulation model coupled the interior ballistic process was established. Coupled with interior ballistics process, the2D axial symmetrical aerodynamic model was established to simulate muzzle flow field. The two models are coupled by the resistance of pressure in front of projectile. The agreement of the numerical results with experimental results shows that the model and method provided in the paper is reasonable and effective. The chang process of the muzzle flow was shown by simulation.
c) During the gun firing, the muzzle flow field is high-temperature, high-pressure, high-velocity and includes normal shock, oblique shock, and intersection shock wave. According to the characteristics of muzzle flow, the BWIP (Blast Wave Identification Paramete) dynamic adaptive grid method with the numerical controller was established. The unsteady muzzle flow of the small caliber gun was simulated by solving two dimensional axisymmetric governing equations applying AUSM up scheme with the BWIP dynamic adaptive grid method. For the same shock capturing ability, the computer resource could be cut down.
d) In order to enhance the shot accuracy of gun system, aerodynamic characteristics the rifled structure launching projectile was investigated while the projectile flying over the complex muzzle flow field. The projectile aerodynamic characteristics change laws were simulated by solving three dimensional N-S equations applying k-epsilon turbulence model with local refinement of unstructured grids. Numerical results of SOCBT (Secant Ogive Cylinder Boat Tail model) projectile are in good agreement with experimental results, so the used computational model and CFD method is effective and relative. Aerodynamic characteristic variation laws are simulated and analyzed due to different parameters, including attack angle, projectile rotating speed and incoming Mach number. The projectile body pressure asymmetry distribution and the characteristics of lift/drag were obtained and analyzed. Coupled with the interior ballistic process, the projectile velocity variations in different rotating speed were simulated and analyzed.
e)The3D computational model was formulateated to illustrate the details of the flow field produced by the revolving barrel gun firing. The algorithm of a second order MUSCL approach with the AUSM+solver was used to simulate the high pressure muzzle flow field. The interior ballistic process was coupled with the simulation. The muzzle flow characteristics of the revolving barrel gun were illustrated by simulations. The muzzle flow field structure of a revolving barrel gun fire with no angle of attack was asymmetric while the projectile is flying through the flow.The maximum lateral velocity of the first and second projectile fired was about1.6m/s and3.8m/s.
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