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为了确定射弹击穿飞机油箱后附近干舱的引燃和燃烧,需要对燃油通过穿孔泄露过程中燃油的泄露质量及雾化液滴的数目和尺寸进行定量计算分析。该文建立了用于模拟高速射弹击穿油箱后燃油泄露过程的解析模型,给出了燃油初始泄露速度的定量计算方法,利用最大熵原理和质量守恒定律,推出了弹丸撞击条件下泄露燃油液滴尺寸数目分布函数和索特尔平均直径SMD的计算公式,并采用Harmon液滴索特尔平均直径经验计算公式定量计算泄露燃油的平均直径。研究结果表明燃油的初始泄露速度随射弹速度的增加而呈线性增加,液滴索特尔平均直径随穿孔直径的增加而增加,随射弹速度的增加而呈线性减小。研究结果为下一步进行油箱附近于舱引燃和燃烧提供理论基础。
In order to determine the ignition and combustion of the dry cargo near the tank after the projectile has broken down, it is necessary to quantitatively analyze the quality of the leaked fuel and the number and size of atomized droplets during the leakage of the fuel through the perforations. In this paper, an analytical model for simulating the process of fuel leakage after high-speed projectile penetrating a fuel tank is established. The quantitative calculation method for the initial leakage rate of fuel is given. By using the principle of maximum entropy and the law of mass conservation, The size distribution function of droplets, and the calculation formula of SMD of SMD, and the average diameter of leaked fuel is quantitatively calculated by Harmon droplet SOTm empirical formula. The results show that the initial leakage rate of fuel increases linearly with the increase of projectile velocity. The mean Soxhlet diameter increases with the increase of perforation diameter and decreases linearly with the increase of projectile velocity. The results provide the theoretical basis for the next step of piloting and burning the cabin in the vicinity of the fuel tank.