Proton irradiation damage mechanism of the InAlAs／InGaAs／InAlAs quantum well

InP-based high electron mobility transistors (HEMT) have shown a great potential for national defense and satellite radar in space radiation environment applications. This paper studies the proton radiation damage mechanism of its critical structure InAlAs／InGaAs／InAlAs quantum well. The proton projection range and vacancy defect information are obtained at different incident proton energies of 50keV, 75keV and 200keV by SRIM software. With the increase of proton energy, the proton injection depth is increasing and eventually protons pass through the material layers. Besides, the proton radiation induced vacancy defects numbers around hetero-junction increase first and decrease subsequently, and As vacancies are the main proton radiation induced defects. In addition, non-ionizing energy loss (NIEL) of In_0.52Al_0.48As and In_0.53Ga_0.47As material is computed under different incident proton energies by the analytical model. The change trend of NIEL is identical to the induced vacancy numbers, namely, NIEL first increases and then decreases as the incident proton energy increases. Finally the degrading effect of the radiation-induced As defect is detected in the two-dimensional electron gas in the quantum well, which confirms that the major proton radiation damage mechanism of the quantum well is the induced vacancy defects by NIEL.     

Ultralow frequency wave characteristics extracted from particle data: Application of IGSO observations

Interaction between ultralow frequency (ULF) waves and charged particles plays an important role in the acceleration of particles in the Van Allen radiation belts. The strong wave-particle interaction predicts an energy-dependent observational signature of particle flux variations during different stages of the ULF wave evolution. In this paper, we find that the energetic particle data newly available from an IGSO spacecraft are quite consistent with theoretical predictions, which enables the application of a best-fit procedure to quantitatively extract key parameters of the ULF waves from the particle data. The general agreement between observations and the best-fit results validates the scenario of wave-particle drift resonance within the entire ULF life span, and provides a new technique to understand the ULF wave characteristics in the absence of electromagnetic field data. We also examine the minor differences between observations and the best-fit results, and propose that the differences may result from a longitudinal dependence of the ULF wave power to be considered in a future study.     

偏馈式构架反射器展开冲击特性分析

As the off-fed truss reflector is connected to the platform by a single edge and deployed rapidly through being driven by the spring, the impact influence acts obviously on both the reflector and the platform. Due to limitations of the ground test, the in-orbit deployment impact characteristics of truss reflector are difficult to obtain. Then, by taking a certain reflector as the research object, a dynamic model is established with multibody dynamic software. Based on the modified model with ground deployable tests, in-orbit deployment impact characteristics are obtained by simulation analysis. Therefore, the method for multibody dynamic modeling is suitable for truss reflector dynamic research, and the result is useful for the deployable reliability optimization.     

基于相关向量机的高光谱图像解混方法

针对传统的高光谱数据解混方法中存在的解混精度不高、丰度图模糊的缺陷,提出一种基于相关向量机的高光谱图像解混方法(unmixing algorithm based on relevance vector machine,UARVM)。其核心思想是采用改进的一对余型的相关向量机将多分类问题转化为多个二分类的问题,且求取出每个样本所对应的归属类别的概率值,即丰度值来完成图像的解混。理论研究和仿真结果表明:相对于传统解混方法,UARVM解混精度高,丰度分布图效果好。     

镜面微振动时点扩散函数的仿真分析

提出了一种高精度求解光学系统中镜面振动在曝光时间内形成的点扩散函数(PSF)的数值计算方法。传统方法计算镜面振动造成像点位移情况,并仅由该值评估镜面振动时系统调制传递函数(MTF)下降情况。该方法忽略了光学系统镜面位置发生改变时其光学系统自身MTF也会同时变化的特性,将导致误差产生。该误差在光学元件振幅较小时并不显著,但随着振幅的加大,该误差会变得不可忽略。该方法通过细分成像过程来计算每一个时刻的点扩散函数,并将这些点扩散函数进行积分来消除该误差。该方法适用于计算任意角度入射的空间光线在经过一个不稳定的光学系统后形成的点扩散函数。     

基于灰色关联分析的卫星初始轨道优选方法

卫星初始轨道优选是一项复杂而且具有多目标性的问题,所以必须利用一系列的评价指标才能全面系统地评价各种初始轨道.针对各种数据源确定的多组初始轨道如何选优问题,提出了一种应用于卫星初始轨道优选的灰色关联分析方法,建立了初始轨道选优的评价指标体系,成功地利用标称轨道作为属性基向量,解决了比较数列的生成问题并给出了具体的应用实例.实例计算结果表明,该方法计算简单,结果可靠,可为决策者的选择提供依据.     

Influence of starting powder choice on structure property relations in gadolinia stabilized zirconia 3Gd-TZP manufactured from co-milled starting powders

Two 3Gd-TZP materials were manufactured from powders produced by intense mixing and milling of unstabilized zirconia starting powders and gadolinia as stabilizer oxide by hot pressing at 1250 °C – 1400 °C. The materials show a combination of high toughness and moderate strength. In detail depending on starting powder the two TZP showed distinct differences concerning transformation characteristics, sintering temperature dependence of mechanical properties and the tendency to develop R-curve related deformation features such as non-linear stress strain curves and formation of transformation bands prior to fracture.     

面向卫星数据系统的SpaceWire应用模型仿真研究

针对我国未来航天应用的需要,建立了SpaceWire总线在卫星在轨数据系统应用的半物理仿真平台,对SpaceWire总线的仿真应用模型进行了设计与实现.仿真系统采用了冗余容错结构,在节点故障时,能够通过Dijkstra算法重新计算最优通信路径,对路由表进行动态重构,实现对节点故障的动态容错.另外,通过对SpaceWire总线的通信性能测试结果的分析研究指出,SpaceWire总线在卫星在轨数据系统中可以用于提高总线数据传输的带宽和实时性,然而总线系统的基础可靠性还应当由1553B总线来提供.     

中断驱动系统模型检验

针对一类中断驱动系统提出了一种建模和模型检验的方法.该系统通常由中断处理程序和操作系统调度的任务组成,前者由中断源触发后处理中断事件,后者则负责处理系统的日常任务以及某些中断处理事件的后续处理.因为这类系统是实时控制系统,对中断事件的处理需要在规定时间内响应并完成,否则可能造成严重的系统失效.为了帮助系统设计人员在系统设计过程中应用模型检验技术来提高系统的正确性,首先确定了此类系统中与时序性质相关的系统要素(包括系统调度任务、中断源、中断处理程序)和相关参数,并要求设计人员在设计阶段明确指出这些要素的参数.然后,提出了将这些要素和参数自动转化为形式化模型的方法:使用时间自动机对中断事件进行建模,使用中断向量表和CPU处理栈对中断处理过程进行建模.对于得到的形式化模型,给出了针对中断处理超时错误的检测方法,并在此基础上给出了针对共享资源的完整性、子程序原子性的检验方法.     

A novel three‐dimensional guidance law implementation using only line‐of‐sight azimuths

A novel three‐dimensional guidance law using only line‐of‐sight azimuths based on input‐to‐state stability and robust nonlinear observer is proposed for interception of maneuvering targets. The proposed guidance law does not need any prior information of unknown bounded target maneuvers and uncertainties. Since in practice the line‐of‐sight rate is difficult for a pursuer to measure accurately, a nonlinear robust observer is introduced to estimate it. A three‐dimensional guidance law with bearing only measurement is obtained for interception of maneuvering targets. The presented algorithm is tested using computer simulations against a maneuvering target. Copyright © 2014 John Wiley & Sons, Ltd.