Identification of vortices in a transonic compressor flow and the stall process

IntroductionVortex is often the essential element re-sponsible for triggering stall and surge in com-pressors.So the identification and the analysisof the vortices in compressor are usually quitehelpful for the understanding of the compressorbehavior.Howe…     

高超声速下表面凸起干扰气动热实验研究

 对高超声速飞行器表面凸起附近的气流流动和气动加热开展了实验研究和分析。实验在高超声速炮风洞中进行,来流马赫数为8.2、单位雷诺数为9.35×10⁶ m^-1。利用薄膜传热测量方法进行了凸起几何形状和边界层状态对干扰流动加热的影响评估。利用流油图谱和纹影摄像法得到了凸起周围的流动特征:若凸起上游边界层未分离,最大峰值热流发生在凸起侧方附近处;若凸起上游边界层完全分离,最大峰值热流通常发生在凸起的上游表面。实验发现最大峰值热流和来流边界层状态关系不大,原因是流动干扰区表现出较强的三维扰动特性,使得来流层流边界层在干扰区内会转变成过渡甚至完全湍流状态。     

用心设计一碗大米

漏佳旎,生活美学家、跨界设计师、"漏一手"主理人。很多人初识她都不相信会有人姓这样的姓,是不是自己听错了或看错了,每次都要解释一番。熟识后,朋友们更愿意亲切地叫她漏漏。     

Potential of laser-induced ablation for future space applications

This paper surveys recent and current advancements of laser-induced ablation technology for space-based applications and discusses ways of bringing such applications to fruition. Laser ablation is achieved by illuminating a given material with a laser light source. The high surface power densities provided by the laser enable the illuminated material to sublimate and ablate. Possible applications include the deflection of Near Earth Objects – asteroids and comets – from an Earth-impacting event, the vaporisation of space structures and debris, the mineral and material extraction of asteroids and/or as an energy source for future propulsion systems. This paper will discuss each application and the technological advancements that are required to make laser-induced ablation a practical process for use within the space arena. Particular improvements include the efficiency of high power lasers, the collimation of the laser beam (including beam quality) and the power conversion process. These key technological improvements are seen as strategic and merit greater political and commercial support.     

Hazard Prevention in Mission Plans for Aerial Vehicles Based on Soft Institutions

Hazard prevention in mission plans requires careful analysis and appropriate tools to support the design of preventive and/or corrective measures. It is most challenging in systems with large sets of states and complex state relations. In the case of sociotechnical systems, hazard prevention becomes even more dicult given that the behaviour of human centric components can at best be partially predictable. In the present article we focus on a specic class of sociotechnical systems namely air spaces containing pilot controlled as well as autonomous aircrafts and introduce the notion of relevant hazards. We also introduce soft institutions as an appropriate basis for analysis, with the aim of addressing relevant hazards. The concept of soft institutions is drawn from specication languages for interaction between agents in multi agent systems but, in our case, is adapted for use in systems that combine human and automated actors.     

Examining the use of the NeQuick bottomside and topside parameterizations at high latitudes

An examination of the high latitude performance of the bottomside and topside F-layer parameterizations of the NeQuick electron density model is presented using measurements from high latitude ionosonde and Incoherent Scatter Radar (ISR) facilities.For the bottomside, we present a comparison between modeled and measured B2Bot thickness parameter. In this comparison, it is seen that the use of the NeQuick parameterization at high latitudes results in significantly underestimated bottomside thicknesses, regularly exceeding 50%. We show that these errors can be attributed to two main issues in the NeQuick parameterization:(1) through the relationship relating foF2 and M3000F2 to the maximum derivative of F2 electron density, which is used to derive the bottomside thickness, and (2) through a fundamental inability of a constant thickness parameter, semi-Epstein shape function to fit the curvature of the high latitude F-region electron density profile.For the topside, a comparison is undertaken between the NeQuick topside thickness parameterization, using measured and CCIR-modeled ionospheric parameters, and that derived from fitting the NeQuick topside function to Incoherent Scatter Radar-measured topside electron density profiles. Through this comparison, we show that using CCIR-derived foF2 and M3000F2, used in both the NeQuick and IRI, results in significantly underestimated topside thickness during summer periods, overestimated thickness during winter periods, and an overall tendency to underestimate diurnal, seasonal, and solar cycle variability. These issues see no improvement through the use of measured foF2 and M(3000)F2 values. Such measured parameters result in a tendency for the parametrization to produce a declining trend in topside thickness with increasing solar activity, to produce damped seasonal variations, and to produce significantly overestimated topside thickness during winter periods.     

客舱内饰改装现状

众所周知,在波音737MAX飞机停飞后,全球各航空公司以租用或购买的形式获得替代型飞机,填补了由于波音737MAX飞机停飞导致的载客量缺口。因此,这在一定程度上推动了客舱升级业务。再加上最近一些航空公司倒闭导致市场上流出大量“空闲”飞机,因此飞机租赁市场也就十分活跃。例如,航空公司倒闭和飞机转租为位于法国蒙彼利埃的维修供应商Vallair带来了大量的飞机内饰升级和改装业务.     

The Scientific Measurement System of the Gravity Recovery and Interior Laboratory (GRAIL) Mission

The Gravity Recovery and Interior Laboratory (GRAIL) mission to the Moon utilized an integrated scientific measurement system comprised of flight, ground, mission, and data system elements in order to meet the end-to-end performance required to achieve its scientific objectives. Modeling and simulation efforts were carried out early in the mission that influenced and optimized the design, implementation, and testing of these elements. Because the two prime scientific observables, range between the two spacecraft and range rates between each spacecraft and ground stations, can be affected by the performance of any element of the mission, we treated every element as part of an extended science instrument, a science system. All simulations and modeling took into account the design and configuration of each element to compute the expected performance and error budgets. In the process, scientific requirements were converted to engineering specifications that became the primary drivers for development and testing. Extensive simulations demonstrated that the scientific objectives could in most cases be met with significant margin. Errors are grouped into dynamic or kinematic sources and the largest source of non-gravitational error comes from spacecraft thermal radiation. With all error models included, the baseline solution shows that estimation of the lunar gravity field is robust against both dynamic and kinematic errors and a nominal field of degree 300 or better could be achieved according to the scaled Kaula rule for the Moon. The core signature is more sensitive to modeling errors and can be recovered with a small margin.