Fault tolerant control with torque limitation based on fault mode for ten-phase permanent magnet synchronous motor

This paper proposes a novel fault tolerant control with torque limitation based on the fault mode for the ten-phase permanent magnet synchronous motor(PMSM) under various open-circuit and short-circuit fault conditions, which includes the optimal torque control and the torque limitation control based on the fault mode. The optimal torque control is adopted to guarantee the ripple-free electromagnetic torque operation for the ten-phase motor system under the post-fault condition. Furthermore, we systematically analyze the load capacity of the ten-phase motor system under different fault modes. And a torque limitation control approach based on the fault mode is proposed, which was not available earlier. This approach is able to ensure the safety operation of the faulted motor system in long operating time without causing the overheat fault. The simulation result confirms that the proposed fault tolerant control for the ten-phase motor system is able to guarantee the ripple-free electromagnetic torque and the safety operation in long operating time under the normal and fault conditions.     

首都机场终端区多进港队列排序优化策略与仿真

在现行可用空域中，通过流量管理策略与进港航班队列优化相结合可提高机场运行容量。以终端区航路航线间隔和扇区容量为约束，通过合理分配机场终端区边界的进港口流量．以总进场排队等待时间最短为目标，提出了协同调配流量和机动分流两种新策略，达到提高机场运行效率的目的。以首都机场为例，利用计算机仿真验证，结果表明：与现状运行相比较采用的优化策略排队进场可使进场延误和等待时间减少，并使离场正常率提高8％左右。     

对流天气下空域通行能力短缺预警及响应综述

对流天气是空域通行能力短缺的主要原因之一。为了解决这一问题,需要通过理论和实践创新,建立对流天气条件下空域通行能力短缺的预警和应急响应机制,提高空域资源配置效率。从对流天气影响信息解释转换、容量评估与预警及空域响应预案三个方面梳理了国内外研究现状,总体趋势是:对流天气逐渐通过各种解释转换模型被量化为对空域和航路的影响;对流天气下空域通行能力主要受管制员工作负荷的限制,只有准确评估对流天气下的工作负荷,才能做出正确的通行能力短缺预警;对流天气响应方案,逐渐由地面等待、增加同航迹间隔、返航、备降等高耗能的流量控制措施,转向以灵活使用空域预案确保改航方案的实施方向发展。课题的应用前景是可以化解对流天气下交通需求与空域通行能力不平衡的矛盾,提高预警准确度,减少响应前置时间,提高流量管理与容量管理协同运行的效率,减轻对流天气造成的航班延误,减少航空器运行成本,实现节能减排的要求。     

闭式布雷顿循环发电系统热力过程建模及其参数影响研究

针对闭式布雷顿循环发电系统热力循环过程及其参数影响,开展系统的热力过程参数建模研究,建立系统发电功率、比功率和效率的计算模型;在此基础上,研究闭式布雷顿循环发电系统比功率和效率随涡轮入口总温及效率、压气机入口总温、压气机压比及效率、累积总压恢复系数等的变化规律,考虑参数灵敏度及其优化潜力,提出可用灵敏度并对系统的比功率和效率进行灵敏度分析。研究表明,闭式布雷顿循环发电系统的比功率和效率随涡轮入口总温及效率、压气机压比及效率、系统累积总压恢复系数等参数的增大而增高,随压气机入口总温的增大而减小。在压气机入口总温、压比与效率、涡轮入口总温及效率、累积总压恢复系数等主要热力参数中,系统比功率灵敏度最高的参数为涡轮效率,系统效率灵敏度最高的参数为压气机压比。考虑参数的实际优化潜力,在循环工质一定的条件下,系统比功率可用灵敏度最高的参数为涡轮入口总温,系统效率可用灵敏度最高的参数为压气机压比。     

Spectroscopic diagnostics for CDS and SUMER

The CDS and SUMER instruments will make extensive use of spectroscopic diagnostics to determine the physical parameters of the solar transition region and corona. A great deal of effort is going into the development of these techniques to ensure that they are accurate. This requires interfacing solar analysis programs with the best available atomic data calculations. Recent developments in this work will be presented, with specific examples of useful spectral line ratios.     

大型购物中心疏散时间预测方法的对比研究

以建筑性能化防火设计为依据，以保证人员在火灾中安全疏散为目标，以环境可提供的（或者说人员可利用的）疏散时间ASET大于人员安全疏散所必需的时间RSET为原则，以某大型购物中心为例，通过日本手算法与常用的人员疏散软件SIMULEX模拟结果进行对比，分析两者在应用上的可行性。     

一种低温低漏率高可靠的飞轮钎焊工艺方法研究

飞轮壳体密封焊接是飞轮装配的关键工序,针对飞轮在真空环境下长期保持低漏率的真空度稳定性、焊接温度不能超过80℃以及焊缝承压能力超过0.5MPa的高要求,通过低温钎料的选择及润湿性分析、钎焊接头剪切强度分析及飞轮钎焊工艺研究,摸索出了一种低温低漏率高可靠的飞轮钎焊工艺方法。本文以某型飞轮壳体组件焊接为例,通过高低温、振动、冲击等试验后保证飞轮真空度保持不变来验证该焊接方法可行性和可靠性。     

Optimum Design of Single Channel per Carrier Satellite Systems

Optimization of available satellite power and transponder bandwidth is utilized to minimize the Earth station G/T in satellite channel per carrier (SCPC) systems. The corresponding optimum transponder output backoff is obtained. Applications in system design are given. In a previous paper [1] the channel capacity of a satellite transponder handling single channel per carrier (SCPC) transmission was derived. The link carrier-to-noise (C/N) ratio was maximized over the output backoff and the maximum bandwidth available was determined. Given the bandwidth per channel for each carrier, the channel capacity was obtained. The objective of the present investigation is to derive the minimum G/T of the Earth station in SCPC systems by optimum utilization of available satellite power and transponder bandwidth. Applications in system design are discussed.     

采用框架角受限控制力矩陀螺的航天器姿态机动控制

以框架角受限的金字塔构型控制力矩陀螺(CMG)为执行机构,研究了航天器欧拉姿态机动控制问题.考虑控制力矩及航天器角速度约束等因素,对已有的姿态机动控制律进行了改进,使其能实现绕欧拉轴的大角度姿态机动.同时考虑力矩陀螺框架角受限情况,通过适当加入空转指令对框架角进行重构,设计了复合控制形式的控制力矩陀螺操纵律,并通过过渡...     

利用做过高载试验的飞机结构进行疲劳寿命研究

某型飞机的某框下半框腹板发生严重的腐蚀损伤.为保证飞机安全,对该部位采取了补强修复.根据规范要求,需要进行全尺寸疲劳试验.但受条件限制,疲劳试验只能在做过高载试验的飞机结构上进行,为此,进行了高载对疲劳寿命的影响研究和全尺寸疲劳寿命试验等研究工作.研究结果表明,使用做过高载静力试验的飞机结构进行疲劳寿命试验是可行的.     

柔性转子动力学特性及支承结构安全性设计

叶片飞失极限状态下,航空发动机转子系统承受冲击载荷和大不平衡载荷,载荷通过转子结构传递到支承结构,对支承结构造成严重损伤。从安全性的角度看,需要对航空发动机轴承-支承结构在极限载荷下的承载能力进行有效的定量评估。提出一种新型缓冲阻尼支承结构,通过对支点刚度突降和高阻尼设计,实现在止推轴承支点处大幅降低横向冲击载荷的影响。建立考虑支承结构刚度突变和阻尼特性的转子系统动力学方程,并计算突加不平衡激励下,转子系统支点动载荷分布的变化规律。结果表明:通过优化设计支点刚度和阻尼参数,缓冲阻尼支承结构,能够有效降低突加不平衡激励下止推滚珠轴承的支点动载荷,提高支承结构的安全性。     

飞机结构密封与失效修理

为提高飞机增压舱的密封能力,给出了飞机结构密封失效的修理程序、方法、试验验证、典型结构密封的措施等,以求达到增压舱正常加压和减缓机体腐蚀发生,保证飞机在寿命期内安全飞行。     

Remaining useful life prediction of aircraft lithium-ion batteries based on F-distribution particle filter and kernel smoothing algorithm

As an emergency and auxiliary power source for aircraft, lithium (Li)-ion batteries are important components of aerospace power systems. The Remaining Useful Life (RUL) prediction of Li-ion batteries is a key technology to ensure the reliable operation of aviation power systems. Particle Filter (PF) is an effective method to predict the RUL of Li-ion batteries because of its uncertainty representation and management ability. However, there are problems that particle weights cannot be updated in the prediction stage and particles degradation. To settle these issues, an innovative technique of F-distribution PF and Kernel Smoothing (FPFKS) algorithm is proposed. In the prediction stage, the weights of the particles are dynamically updated by the F kernel instead of being fixed all the time. Meanwhile, a first-order independent Markov capacity degradation model is established. Moreover, the kernel smoothing algorithm is integrated into PF, so that the variance of the parameters of capacity degradation model keeps invariant. Experiments based on NASA battery data sets show that FPFKS can be excellently applied to RUL prediction of Li-ion batteries.     

The ACE Science Center

The Advanced Composition Explorer (ACE) mission is supported by the ACE Science Center for the purposes of processing and distributing ACE data, and facilitating collaborative work on the data by instrument investigators and by the space physics community at large. The Science Center will strive to ensure that the data are properly archived and easily available. In particular, it is intended that use of a centralized science facility will guarantee appropriate use of data formatting standards, thus easing access to the data, will improve communications within and to the ACE science working team, and will reduce redundant effort in data processing. Secondary functions performed by the Science Center include acting as an interface between the scientists and the mission operations team. This revised version was published online in June 2006 with corrections to the Cover Date.     

Distributed target detection in compound-Gaussian noise with Rao and Wald tests

The problem of detecting distributed targets in compound-Gaussian noise with unknown statistics is considered. At the design stage, in order to cope with the a priori uncertainty, we model noise returns as Gaussian vectors with the same structure of the covariance matrix, but possibly different power levels. We also assume that a set of secondary data, free of signal components, is available to estimate the covariance matrix of the disturbance. Since no uniformly most powerful test exists for the problem at hand we devise and assess two detection strategies based on the Rao test, and the Wald test respectively. Remarkably these detectors ensure the constant false alarm rate property with respect to both the structure of the covariance matrix as well as the power levels. Moreover, the performance assessment, conducted also in comparison with the generalized likelihood ratio test based receiver, shows that the Wald test outperforms the others and is very effective in scenarios of practical interest for radar systems.     

Neural controllers for systems with unknown dynamics

This study presents a methodology for specifying a neural controller for a system about which no a priori model information is available. The neural design presumes that a finite duration input/output (I/O) histogram on the system is available. The design procedure extracts from the histogram sufficient information to specify the neural feedback controller. The resultant controller will drive the system along a general output reference profile (unknown during the design). The resultant controller also exhibits the capability of disturbance rejection and the capacity to stabilize unstable plants     

压力载荷下的结构拓扑-形状协同优化

 压力载荷作用下的结构轻量化设计是工程中的常见问题,由于压力加载面的可设计性,现有以固定载荷为基础的拓扑优化技术不能很好地处理这类问题。直接采用CAD参数化样条或B样条曲线描述压力加载面,通过拓扑和形状变量的联合优化满足了工程实际对结构轻量化与边界的功能性与光滑性设计要求。同时,为了避免结构边界形状变化时有限元网格刷新引起的定义拓扑伪密度变量的困难,用所提出的背景网格和密度点技术实现了每一步单元密度设计迭代结果的自动传递,并采用网格变形技术实现了形状设计变量灵敏度分析。采用4个数值算例验证了方法的有效性,其中发动机承力框架的设计结果充分说明该方法在航空结构设计中的重要应用价值。     

模态综合的多级子结构分析——两种改进装配法

当今国内外流行的模态综合法都属于“单级综合法”。它对大型复杂结构动力分析的应用仍将受到计算机容量的较大限制。本文在子结构装配方面提出的“多级综合法”与“逐步综合法”可以克服这一障碍,并能提高计算效率。另外,本文采用的“刚性子结构技术”能使模态综合法保持其功能与特点,具有重要的实用价值。文中算例表明,只要采用本文频率判据,两种改进装配法的精度是可靠的。     

弹射式导弹发射时载机动力学响应研究

建立了载机自然飞行时的动力学模型,并验证了该模型的有效性。同时为其设计了一套弹射式发射架,分析了在不同弹射力、不同弹射架位置参数条件下载机的动力学响应。研究结果表明,弹射力是保证载机与导弹安全分离的重要因素,对导弹的出舱速度影响较大,且弹射架沿载机纵向位置的改变对载机纵向运动影响明显,沿载机展向位置的改变对载机横航向运动影响显著。     

复合材料主起落架整流罩结构设计要求及方法

民用飞机主起落架整流罩多采用复合材料结构进行设计,提出了适用于民机的主起落架整流罩结构设计的要求及方法,介绍了通常采用的技术方案,包括结构形式、结构组成、连接方式等。要保证设计方法具有一定的先进性,技术方案成熟可行,就要考虑其功能、承载、耐久性等结构设计要求,同时因其内部结构经常处于恶劣的环境中,所以要兼顾其结构保护以及维修性设计,即具有很好的抗冲击性和防潮湿性能。