防护板尺寸对Whipple防护结构撞击损伤影响的实验研究

通过高速撞击实验,探讨了采用小尺寸防护板的可行性。实验中采用的Whipple结构由尺寸变化的1 mm厚防护板（前板）和尺寸固定的3 mm厚舱壁板（后板）组成,防护板与舱壁板间隔10 cm。防护板为边长分别为8、12、16和20 cm的方形2A12铝合金板,舱壁板为边长为20 cm的方形5A06铝合金板。实验过程中均采用直径为4 mm的铝合金球形弹丸,撞击速度为1.45~1.71 km/s。实验结果表明:Whipple防护结构在舱壁板被击穿的概率大于0.8的条件下和击穿概率为0的条件下的极限速度以及舱壁板临界击穿条件下的速度都与防护板尺寸无关;并且,防护板前后表面击穿孔的直径及击穿孔侧壁的倾斜角也与防护板尺寸无关;但是,在速度相同的条件下随着板尺寸的增大,防护板板面的最大挠度增大,而且,防护板挠曲面的凸凹方向也由单一的凹向变成凸凹方向交替出现;随着速度的增加和板尺寸的增大,防护板最大挠度的增量减小。     

过冷水滴撞击螺旋桨桨叶表面的数值模拟

本文介绍了某型螺旋桨在不同飞行状态下.求解桨叶水滴撞击特性的数值方法.该方法对桨叶运动模型进行简化,并在对绕桨叶运动的气流场计算的基础上,采用拉格朗日方法求解气流场中水滴运动方程,得到水滴运动轨迹.进而,确定了水滴对桨叶的撞击特性参数,为桨叶防冰系统设计提供条件.主要结论如下:(1)在巡航状态下,桨叶沿展向方向上总收集系数Em和局部收集系数β不断增大;(2)在爬升状态下,随着爬升高度H不断增大,飞行速度V0不断增大,水滴撞击在桨叶表面的范围有所增加,而且β随之增大;(3)随着水滴平均有效直径(MVD)的增大,水滴撞击在桨叶表面的范围明显增加同时,β在桨叶表面同一位置的值也随之增大.     

Low-velocity pneumatic conveying in horizontal pipe for coarse particles and fine powders

First, the characteristics of low-velocity conveying of particles having different hardness are experimentally investigated in a horizontal pipeline in terms of flow pattern and pressure drop to show that the slug flow can be classified into two types depending on the settling of particles along the pipeline, and the period is small for slug flow without the settled layer, which is called solitary slug flow. The pressure drop for soft particles is shown to be larger than that for hard particles. Then, experimental results are presented on horizontal fluidized-bed conveying of fine powders to show that air release from the top surface of the conveying channel is an imnortant factor for high mass flow rate of particles.     

Landing gear noise control using perforated fairings

Landing gears of commercial aircraft make an important contribution to total aircraft noise in the approach configuration. Using fairings to shield components from high speed impingement reduces noise. Furthermore, perforating these fairings has been confirmed by flight tests to further enable noise reduction. Following an earlier fundamental study of the application of perforated fairings, a study has been performed to investigate and optimize the benefits of bleeding air through landing gear fairings. By means of wind tunnel tests, an aerodynamic and acoustic survey has been performed on a simplified generic main landing gear to explore the influence of （perforated） fairings on the lower part of the gear. The results show that for this specific case, the application of impermeable fairings reduces noise in the mid- and high frequency range by shielding sharp edged components from high velocity impingement. However, below 1 kHz the noise is shown to increase significantly. Application of the perforations is shown to diminish this low frequency increase whilst maintaining the reduction in the mid- and high frequency range. The aerodynamic and acoustic measurements point in the direction of the separated flow of the fairings interacting with the downstream gear components responsible for the low frequency noise increase. Bleeding of the air through the fairings reduces the large scale turbulence in the proximity of these components and hence diminishes the low frequency noise increase.     

Mass Spectrometry of 2a, 4-Disubstituted 5-Benzoyl-2a, 3,4,5-tetrahydro-2-phenoxy-azeto [ 1,2-a ] [1,5 ] benzodiazepin - 1 （2H）-ones Under Electron Impact Ionization Conditions

The mass spectrometric fragmentation of 2a, 4-disubstituted 5-benzoyl-2a, 3,4, 5-tetrahydro-2-phenoxy-azeto[1,2-α] [ 1,5 ] benzodiazepin-I (2H)-ones has been investigated by means of mass-analyzed ion kinetic energy spectrometry under electron impact ionization conditions. All compounds tend to lose different moieties, such as phenoxy, phenoxy and H, and phenoxyketene. Both [ M^ - PhO ] and [ M^ - PhOH ] ions could further lose CO, and the [ M^ - PhOCH = C = O] ions could lose propene or styrene, PhCON, PhCOHN, and other fragments.     

Torsional impact response of a penny-shaped crack in a functional graded strip

The torsional impact response of a penny-shaped crack in a nonhomogeneous strip is considered. The shear modulus is assumed to be functionally graded such that the mathematics is tractable. Laplace and Hankel transforms were used to reduce the problem to solving a Fredholm integral equation. The crack tip stress field is obtained by considering the asymptotic behavior of Bessel function. Explicit expressions of both the dynamic stress intensity factor and the energy density factor were derived. And it is shown that, as crack driving force, they are equivalent for the present crack problem. Investigated are the effects of material nonhomogeneity and strip‘s highness on the dynamic fracture behavior.Numerical results reveal that the peak of the dynamic stress intensity factor can be suppressed by increasing the nonhomogeneity parameter of the shear modulus, and that the dynamic behavior varies little with the adjusting of the strip‘ s highness.     

基于人体损伤的中低速正面碰撞气囊点火状态分析方法研究

为降低驾驶员在中低速碰撞下受到的损伤, 利用2010年版丰田Yaris整车模型建立100%正面刚性壁碰撞有限元模型, 并根据驾驶员舱布置及相关法规要求建立Madymo约束系统仿真模型, 以验证有限元模型的准确性. 利用建立的碰撞模型, 在中低速碰撞中对不同气囊点火状态下的驾驶员所受损伤进行仿真. 结果表明, 该车型在35 km●h^-1及以上车速时, 点爆气囊能有效减少驾驶员损伤; 30 km●h^-1及以下车速时, 气囊点火会对驾驶员造成额外伤害; 中低速碰撞下, 驾驶员的胸部损伤程度较头部更容易受气囊点火时间影响.     

钨合金柱形弹超高速撞击水泥砂浆靶的侵彻深度研究

为探索钨合金柱形弹超高速撞击水泥砂浆靶的侵彻深度随撞击速度变化规律,利用二级轻气炮开展了?3.45 mm×10.5 mm的克级93 W钨合金柱形弹以1.82~3.66 km/s的速度撞击水泥砂浆靶的实验,利用CT图像诊断技术获得了侵彻深度和残余弹长随撞击速度的变化规律,对超高速撞击过程进行了数值模拟,结合数值模拟结果进一步分析了超高速撞击物理过程。结果表明:(1)超高速撞击条件下成坑是弹坑+弹洞型;(2)侵深-速度曲线呈现先增大后减小的现象,在弹速2.6 km/s附近存在侵彻深度极大值,约为8.5倍弹长,相对于中低速侵彻的深度并没有显著优势。(3)通过基于数值模拟得到的弹靶界面压力时程曲线将侵彻过程分为4个阶段,其中准定常侵彻阶段和第三侵彻阶段是决定总侵深的主要阶段。(4)随撞击速度增加,弹体侵蚀逐渐剧烈,此时准定常侵彻阶段的侵深变化不大,而第三侵彻阶段中的刚体侵彻部分大幅降低,导致总侵深大幅降低,使总侵深曲线呈现先增大后减小的现象。     

关于两粒子弹性散射中动能转移的再讨论

本文从靶粒子在弹性散射中所获得的速度入手，直接计算靶粒子所获得的动能，从而较《大学物理》１９９０年第４期上“关于两粒子弹性散射中功能的转移”一文更直观地求得了功能的转移关系。     

粒子音响效应

 宏观物体的相互撞击会发出响声.从陨星撞击地球时的轰鸣,到雪花落地时的沙沙作响;从子弹掠空时的呼啸,到石子击水时的叮咚有声,……这是人们都熟悉的现象.微观粒子撞击固体、液体和气体时能否发出响声呢?粒子音响效应的研究正是要探索这一问题。所谓粒子音响效应,就是具有动能的粒子与物质发生作用而产生音响的现象.这里所说的粒子,包括光子、电子、质子、μ子和离子、分子以及粒子团等等.这里所说的音响,包括正常人的耳朵能够听得至的声音和一般人的耳朵听不到的超声与次声.无论通常的声音还是超声与次声,其实质都是物质发生的一定频率的振动.