GPS定时校频应用技术的基础研究

针对利用GPS进行定时校频技术开展了一系列的应用基础研究,包括GPS定时校频的方法及其不确定度、定时校频数据的处理等。在给出实验结果的同时,对影响GPS定时精度的各种因素(包括SA影响)进行了讨论;同时对提高GPS定时精度的途径作了初步探讨。     

支持MEMS的CAD/CAE系统结构研究

CAD/CAE技术在MEMS(Micro Electro Mechanical Systems)研究过程中具有非常重要的作用.本文首先介绍了用于MEMS的CAD/CAE技术特点,然后研究了MEMS CAD/CAE系统结构,给出了软件支持工具结构框图,指明了解决其中关键技术的途径.CAD/CAE技术的应用,将提高微型机电系统的设计质量,缩短研制周期,使之及早走向工业化.     

高空高速无人飞行器热控制系统设计

针对飞行时间短、速度和高度变化快、表面温度波动大的无人飞行器UAV(Unmanned Aerial Vehicles)热控制系统设计难题,提出了一种可解决实际工程问题的热分析计算方法.即把热天工况、冷天工况和标准天工况作为设计/试验工况;采用参考温度法、高超音速工程预测法或计算流体动力学CFD(Computational Fluid Dynamics)数值模拟法,确定了飞行器表面温度分布,并把其作为后续热分析数学模型的外边界条件;分析结构热容量对瞬态热载荷的影响,建立与之相应的边值问题方程,并采用有限差分法求解;根据高空高速飞行特点及瞬态热载荷值,确定仪器设备舱调温系统方案.     

多传感器信息融合技术

多传感器信息融合是Ｃ＾３Ｉ系统和电子综合战系统中的关键技术，本文从信息融合分类出发，讨论了单传感器的信息融合决策理论和技术以及多传感器信息融合原理，提出了多传感器信息融合专家系统，着重讨论贝叶斯法用于二元检测的分布式多传感器信息融合的检测方式。     

Coronal mass ejection detection using wavelets,curvelets and ridgelets: Applications for space weather monitoring

Coronal mass ejections (CMEs) are large-scale eruptions of plasma and magnetic field that can produce adverse space weather at Earth and other locations in the Heliosphere. Due to the intrinsic multiscale nature of features in coronagraph images, wavelet and multiscale image processing techniques are well suited to enhancing the visibility of CMEs and suppressing noise. However, wavelets are better suited to identifying point-like features, such as noise or background stars, than to enhancing the visibility of the curved form of a typical CME front. Higher order multiscale techniques, such as ridgelets and curvelets, were therefore explored to characterise the morphology (width, curvature) and kinematics (position, velocity, acceleration) of CMEs. Curvelets in particular were found to be well suited to characterising CME properties in a self-consistent manner. Curvelets are thus likely to be of benefit to autonomous monitoring of CME properties for space weather applications.     

Exploration and implementation of commonality valuation method in commercial aircraft family design

Commercial aircraft family design can reduce development costs, shorten development cycles, and expand the market coverage of aircraft. Commercial aircraft family development has become one of the most important features of modern aircraft design. This paper explores the effects of commonality on different aircraft models in a commercial aircraft family. The existing product commonality indexes are summarized and their limitations in the application to aircraft design are discussed. Then a new component commonality index is proposed based on the component decomposition structure. A model for calculating the aircraft program value is established,which considers development costs, manufacturing costs, sale price, operation costs and residual costs. The effects of aircraft commonality on time and economic costs of both development and manufacturing, and on sale price, are analyzed and quantified. The commonality evaluation strategy is obtained, which features comprehensive consideration of the aircraft program value and time costs. The break-even analysis of aircraft is proceeded on the basis of costs and price data. By using a real option method, the strategy considers the uncertainty of the aircraft program and the flexibility of the manufacturer. This strategy proves to be rational and applicable to aircraft design based on the calculation of three examples and the analysis of parameter sensitivity.     

绳索断裂对二维二次太阳翼展开过程影响分析

为识别二维二次太阳翼关键环节和预示其在轨展开故障模式，开展不同位置绳索断裂失效对太阳翼展开的影响程度分析。采用考虑绳索断裂的绳索联动轮力学模型，建立了适应于不同联动轮半径的联动轮受力模型，提出角度触发约束消除方法，解决了太阳翼第2次展开过程连续仿真问题，建立了太阳翼第2次展开动力学方程，分析了不同位置绳索断裂失效对太阳翼各板展开角度、展开构型和其他绳索张力的影响。分析表明，越靠近星体的绳索联动机构失效对太阳翼展开过程的影响越大，其中连接架上绳索联动机构失效可直接导致二维二次太阳翼在轨展开失败。     

HTPB官能度数学模型建立

为了研究自由基型液体端羟基聚丁二烯预聚物(HTPB)体系官能度分布情况,对其化学合成中自由电子转移情况进行了分析,并通过数学统计的方法对其官能度分布进行理论数值模拟,建立了适用于自由基型HTPB官能度分布的函数关系式,并与GPC所测结果进行对比。结果显示,计算所得函数关系式与测试数据吻合结果较好,数值模拟结果准确性较高;自由基聚合生产的不同批次的HTPB官能度分布存在较大差异,单官能度分子含量可从5%~24%,二官能度分子的含量可从50%~81%;利用数学统计得到的函数关系,可将复杂的HTPB官能度测试转变为简单的分子量分布测试。     

Contamination of short GRBs by giant magnetar flares: Significance of downward revision in distance to SGR 1806–20

We highlight how the downward revision in the distance to the star cluster associated with SGR 1806–20 by Bibby et al. (2008) reconciles the apparent low contamination of BATSE short GRBs by intense flares from extragalactic magnetars without recourse to modifying the frequency of one such flare per 30 years per Milky Way galaxy. We also discuss the variety in progenitor initial masses of magnetars based upon cluster ages, ranging from ∼50 M_⊙ for SGR 1806–20 and AXP CXOU J164710.2–455216 in Westerlund 1 to ∼17 M_⊙ for SGR 1900+14 according to Davies et al. (2009) and presumably also 1E 1841–045 if it originated from one of the massive RSG clusters #2 or #3.     

A fast pulse phase estimation method for X-ray pulsar signals based on epoch folding

X-ray pulsar-based navigation (XPNAV) is an attractive method for autonomous deep-space navigation in the future. The pulse phase estimation is a key task in XPNAV and its accuracy directly determines the navigation accuracy. State-of-the-art pulse phase estimation techniques either suffer from poor estimation accuracy, or involve the maximization of generally non-convex object function, thus resulting in a large computational cost. In this paper, a fast pulse phase estimation method based on epoch folding is presented. The statistical properties of the observed profile obtained through epoch folding are developed. Based on this, we recognize the joint prob-ability distribution of the observed profile as the likelihood function and utilize a fast Fourier transform-based procedure to estimate the pulse phase. Computational complexity of the proposed estimator is analyzed as well. Experimental results show that the proposed estimator significantly outperforms the currently used cross-correlation (CC) and nonlinear least squares (NLS) estima-tors, while significantly reduces the computational complexity compared with NLS and maximum likelihood (ML) estimators.