空间重粒子击中卤虫卵的定位技术及其生物效应

为了能够估价空间重粒子对单个生物细胞的放射生物学效应,我们设计、制成了卤虫卵-核乳胶夹层式生物包.经搭载我国“8885”卫星飞行数天后回收.用图象分析仪研究了空间重离子在核乳胶上留下的径迹及其分布;并实验观察了卤虫卵的前期发育情况.看到:随星飞行过的卤虫卵与地面对照组相比,其发育能力明显降低,表现为孵化率低且发育时间推迟.实验表明:生物样品板-核乳胶影象定位技术能清楚而比较准确地给出卤虫卵(或其他生物细胞)受重离子作用的信息,是重离子生物效应及其作用机理研究的可行实验手段及分析方法之一.     

地效飞行器发展回顾及前景展望

介绍了国内外地效飞行器发展情况和研制的最新进展,对其特点和应用前景进行了叙述.分析了地效飞行器发展中存在的技术障碍.探讨了地效飞行器的发展方向.     

The accuracy of data from ionosondes for the estimation of hmF2 and the identification of global change in the ionosphere

A long temporal series of simulated ionograms was generated with a superimposed secular variation of −14 km/century on the h_mF2 parameter. These ionograms were interpreted by the automatic scaling program Autoscala. By applying four different empirical formulas, four artificial series of h_mF2 were generated and then processed with the same methods used by other authors for real data sets. Data analysis of the simulated ionograms revealed the artificially imposed long-term trend. These results lead to the conclusion, that regardless of the empirical formula used, the accuracy of h_mF2 from ionosonde measurements would be adequate to observe a long-term trend of −14 km/century.     

偏转弹头导弹控制系统设计与仿真

根据弹头的可偏转特性,利用无根多刚体系统动力学方法建立了偏转弹头导弹的动力学模型,并对通道间的耦合特性及弹头偏转对弹体运动的影响进行了分析。在此基础上,将通道间的耦合及弹头偏转对弹体运动的影响作为干扰项处理,将气动参数的非线性变化等效为标称参数的摄动,利用变结构控制理论设计了偏转弹头导弹的控制器。仿真结果表明,所设计的变结构控制器能够有效地减小和消除俯仰、偏航通道对滚转通道的耦合作用以及弹头偏转对弹体运动的影响,较好地抑制了导弹气动参数的摄动,具有较高的稳态精度和良好的动态性能。     

A simulation study on the mode conversion process from slow Z-mode to LO mode by the tunneling effect and variations of beaming angle

For a particular angle of incidence wave, it is possible for a slow Z-mode wave incident on an inhomogeneous plasma slab to be converted into an LO mode wave. But for another wave normal angle of the incident wave, it has been considered impossible, since an evanescence region exists between two mode branches. In this case we expect that the mode conversion takes place through the tunneling effect. We investigate the effect of the spatial scale of the density gradient on the mode conversion efficiency in an inhomogeneous plasma where the mode conversion can occur only by the tunneling effect. We use the computer simulation solving Maxwell’s equations and the motion of a cold electron fluid. By considering the steepness of the density gradient, the simulation results show the efficient mode conversion could be expected even in the case that the mismatch of the refractive indexes prevents the close coupling of plasma waves. Also, we show for these cases the beaming angle does not correspond to Jones’ formula. This effect leads to the angles larger and smaller than the angle estimated by the formula. This type of mode conversion process becomes important in a case where the different plasmas form a discontinuity at their contact boundary.     

Mach reflection in steady supersonic flow considering wedge boundary-layer correction

Mach reflection in steady supersonic flow is an important phenomenon having received extensive studies, among which simplified theoretical models to predict the size of Mach stem and other flow structure are of particular interest. Past efforts for such models were based on inviscid assumption while in real cases the flow is viscous. Here in this paper we consider the influence of wedge boundary layer on the Mach stem height. This is done by including a simplified boundary layer model into a recently published inviscid model. In this viscous model, the wedge angle and the trailing edge height, which control the Mach stem height, are replaced by their equivalent ones accounting for the displacement effect of the wedge boundary layer, with the boundary layer assumed to be laminar or fully turbulent. This viscous model is shown to compare well with numerical results by computational fluid dynamics and gives a Mach stem height as function of the Reynolds number and Mach number. It is shown that due to the viscous effect, the Mach stem height is increased, through increasing the effective wedge angle.     

空气流速和自热效应对湿度传感器测量准确度的影响

通过对多种典型型号湿度传感器在不同空气流速条件下对同一相对湿度测量结果的变化的实验研究,得出了0～1.5 m/s流速范围内湿度传感器的示值随流速的变化趋势,即示值随流速增大而增大,总变化量最大达2%RH以上,且变化主要发生0.5 m/s以下的低流速情况下,同时传感器表面温度随流速增大而降低,两者变化趋势相互吻合。进一步分析表明,上述现象是湿度传感器的自热效应和空气与传感器之间的对流换热效应共同作用的结果,它给湿度传感器的测量结果带来新增不确定度。     

新一代运载火箭氢氧模块动力系统试验风险分析

针对新一代运载火箭氢氧模块动力系统试车试验台进行了风险分析.分析方法采用基于元件的系统级FMECA和基于工艺流程的过程FMECA相结合的方法,引入“发生可能性”和“严酷度”两个指标,建立FMECA工作表,实现了风险因素量化分析与控制,并引入“风险指数”对风险事项排序.通过分析共识别Ⅰ、Ⅱ类单点故障模式45项,提出了试验台在设计、生产、使用和操作中应采取的控制措施,使系统可靠性得到了增长.该方法有效拓展了大型地面试验风险管理的思路.     

强迫扰动下的射流撞击雾化特性

为全面把握撞击式喷嘴的工作特性，进一步认识雾化在燃烧不稳定中所起的作用，采用试验结合数值模拟的方法开展了强迫扰动条件下撞击式喷嘴的非稳态雾化特性研究。试验方面，采用水力扰动装置产生喷前压力扰动，由脉动压力传感器记录喷前的脉动压力，由高速摄影对动态的喷雾场进行背光拍摄。数值模拟则是基于开源程序Gerris开展，通过给定周期性变化的速度入口来模拟前端压力扰动下的撞击雾化过程。首先验证了建立的数值模拟方案处理非稳态雾化的有效性，其次将自然雾化与强迫扰动雾化进行对比，分析了强迫扰动条件下的撞击雾化特性，最后研究了扰动频率与扰动幅值对于撞击雾化的影响。结果表明：强迫扰动下的射流撞击喷雾场出现了弓形液滴群局部聚集的现象，并且在时间上表现出周期性特征，雾化频率与强迫扰动的频率一致。在研究的频率范围（1 257~3 563 Hz）内，撞击式喷嘴的雾化对扰动都有响应。扰动频率主要影响相邻弓形液滴群之间的间距以及雾场与扰动压力之间的相位关系，扰动幅值则主要影响雾化Klystron效应的强度。随着扰动幅值的增大，液膜的破碎长度减小，撞击点下游的流量特性由线性向非线性转变，由正弦波形转变为陡峭前缘波形。     

矢量喷流下平尾偏转对飞机气动性能的影响

通过系列参数试验,研究有、无矢量喷流作用下飞机平尾偏转对飞机气动特性、操纵特性以及飞机绕流/矢量喷流之间干扰特性的影响.实验结果表明:在亚音速中小迎角下,有、无矢量喷流时平尾偏转并不影响飞机的纵向静稳定性,只是改变飞机的零升力矩系数m_z0和零升力迎角α₀,但平尾偏转可以较大幅度地改善前体机翼的绕流形态,减缓机翼涡及边条涡的破裂.此外当飞机处于失速状态时,矢量喷流对于涡破裂失速流动表现出强烈的干扰作用,对飞机的气动特性产生了较大的影响,其干扰区域不仅局限于飞机后体,而且还延伸至前机体,该有利气动干扰量可以达到飞机气动力的10%以上.