月面环境下的载人月球车半主动悬架控制策略

月球地形复杂加之低重力与低附着环境,传统车辆悬架的舒适性和稳定性较差。车辆行驶过程中会出现胎跳,导致轮胎与地面接触不良,甚至出现轮胎腾空情况。为了提高载人探月车辆的被动悬架的性能,以及车辆越障的平顺性。提出一种应用于半主动悬架的比例-积分-微分(PID)控制策略,采用Adams与Simulink联合仿真分析方法进行动力学性能的仿真与对比分析。在Adams中基于1/6重力的月面仿真环境下搭建1/4悬架模型,并在Simulink中建立月面路面激励位移与PID控制器,以车辆垂直加速度与悬架可变阻尼力作为PID控制器的输入量与输出量,得出载人月球车悬架性能指标。联合仿真分析结果显示:车身垂直加速度、悬架动行程、轮胎动载荷、轮胎离地间距都有大幅度的提升,表明采用PID控制器的半主动悬架可以有效提高乘坐舒适性与稳定性,同时操作性与安全性得到进一步保证。     

小流量高速离心叶轮参数设计和三维造型

对小流量高速离心叶轮一维气动优化设计及快速三维造型方法进行了研究,并发展了相应的计算程序.采用所述的方法,以Krain叶轮为基准对象,在保证原设计点性能的情况下进行了叶轮的全新参数设计和快速三维造型.造型中对叶片中心线进行了曲率优化控制,使得叶片符合气动性能优良的“S”型叶片.最后采用经校验的CFD软件对新设计的叶轮进行了全三维数值验证.数值验证结果显示:在设计流量时等熵效率为93.9%,增压比为4.794,与Krain叶轮设计点CFD验证的结果偏差分别为0.24%和2.14%,验证了该设计方法及程序的可行性.      

滑阀分组件真空钎焊工艺性研究

文中着重介绍某型飞机发动机加力控制系统附件压比调节器真空钎焊用钎料BVAg-1的研制、工艺试验过程和工艺参数匹配。成功地解决了焊接与材料热处理加工温度之间的制约矛盾,提高了产品的焊接可靠性。     

Expectations for Crater Size and Photometric Evolution from the Deep Impact Collision

The NASA Discovery Deep Impact mission involves a unique experiment designed to excavate pristine materials from below the surface of comet. In July 2005, the Deep Impact (DI) spacecraft, will release a 360 kg probe that will collide with comet 9P/Tempel 1. This collision will excavate pristine materials from depth and produce a crater whose size and appearance will provide fundamental insights into the nature and physical properties of the upper 20 to 40 m. Laboratory impact experiments performed at the NASA Ames Vertical Gun Range at NASA Ames Research Center were designed to assess the range of possible outcomes for a wide range of target types and impact angles. Although all experiments were performed under terrestrial gravity, key scaling relations and processes allow first-order extrapolations to Tempel 1. If gravity-scaling relations apply (weakly bonded particulate near-surface), the DI impact could create a crater 70 m to 140 m in diameter, depending on the scaling relation applied. Smaller than expected craters can be attributed either to the effect of strength limiting crater growth or to collapse of an unstable (deep) transient crater as a result of very high porosity and compressibility. Larger then expected craters could indicate unusually low density (< 0.3 g cm⁻³) or backpressures from expanding vapor. Consequently, final crater size or depth may not uniquely establish the physical nature of the upper 20 m of the comet. But the observed ejecta curtain angles and crater morphology will help resolve this ambiguity. Moreover, the intensity and decay of the impact “flash” as observed from Earth, space probes, or the accompanying DI flyby instruments should provide critical data that will further resolve ambiguities.     

某微型涡喷发动机数控系统研制

介绍了某微型发动机数控系统的研制技术,以及在供油装置设计中所体现的微发数控系统的特点。对该数控系统的总体设计、供油装置设计、控制器设计技术进行了分析,并给出了该系统与发动机的匹配试验结果。该研究结果对设计数控系统具有较好的借鉴和参考作用。     

基于L1趋势滤波的飞控传感器降噪方法

针对飞行控制传感器中普遍存在的噪声信号,提出了一种基于L1趋势滤波技术的在线降噪方法。首先简要介绍了L1趋势滤波技术,引入了滑动窗口对算法进行改进以满足实时在线应用需求。以气压计所采集的信号为例,采用原始飞参数据,利用该方法进行降噪处理,并与文献中常用的小波降噪方法进行初步比较,基于Matlab的仿真结果验证了该方法的可行性。     

遥感小卫星简介——以"北京一号"小卫星为例

高性能对地观测小卫星DMC 4--“北京一号”2005年10月27日在俄罗斯普列谢茨克发射场由宇宙3M火箭成功发射。文章针对小卫星的结构特点和数据特点,指出DMC小卫星图像数据具有获取灵活、重返周期短和大区域覆盖等优势,在地质灾害的调查、监测和预警工作中具有巨大的应用潜力。     

Upwards migration phenomenon on molten lunar regolith: New challenges and prospects for ISRU

As part of our research on the feasibility of producing commodities from lunar regolith by thermal-driven processes with minimal terrestrial precursors we need to characterize, reproduce, and understand thermophysical properties of the molten regolith still unforeseen under the lunar vacuum conditions at a scalable sample size. Two unanticipated phenomena, apparently caused by lunar melt’s surface tension under vacuum, have been revealed in our research work, vacuum void formation and upwards migration. In this paper we present our findings and thinkable explanation on the upwards migration phenomenon experimentally observed and consistently replicated as JSC-1A lunar regolith simulant melted at high vacuum. Upwards migration of molten lunar regolith will make future lunar ISRU’s melting processes both challenging as molten bulk material would migrate upwards along the container’s walls, and also promising on new opportunities for alternative ISRU’s sustainable processes as regolith’s upwards migration takes place in uniformed thin-film pattern. Among the potential ISRU’s processes that might use controlled thermal thin-film-based migration without the necessity of terrestrial precursors are production of feedstock for 3D printing, fractional separation of regolith’s component’s (O₂, metals, and alloys) via pyrolysis, film coating, purification of valuables solid crystals including silicon, and fabrication of key elements for microfluidic, and MEMS devices. Thermal upwards migration phenomenon on JSC-1A’s melt is formulated and explained by the authors as due to thermal Marangoni effect (also known as thermo-capillarity) in which temperature gradients within the melt’s bulk and along the crucible’s wall yield the surface tension large enough to supersede the gravitational force and yield the experimentally observed upwards thin-film migration. As far as the authors know, upwards thermal migration of molten JSC-1A (or other lunar simulant regolith) under vacuum has not been reported in the literature. A thermal mathematical model accounting for thermal Marangoni effect on molten JSC-1A agrees with what experimentally was observed, the formation of the meniscus on the melt-wall surface interface along with an incipient upwards migration in thin-film pattern along the crucible wall that, according to the model, experiences large temperature gradient, an important factor to trigger the thermal Marangoni effect along with the fact that surface tension of the molten lunar regolith material is temperature dependent.