A new remaining useful life estimation method for equipment subjected to intervention of imperfect maintenance activities

As the key part of Prognostics and Health Management (PHM), Remaining Useful Life (RUL) estimation has been extensively investigated in recent years. Current RUL estimation studies considering the intervention of imperfect maintenance activities usually assumed that maintenance activities have a single influence on the degradation level or degradation rate, but not on both. Aimed at this problem, this paper proposes a new degradation modeling and RUL estimation method taking the influence of imperfect maintenance activities on both the degradation level and the degradation rate into account. Toward this end, a stochastic degradation model considering imperfect maintenance activities is firstly constructed based on the diffusion process. Then, the Probability Density Function (PDF) of the RUL is derived by the convolution operator under the concept of First Hitting Time (FHT). To implement the proposed RUL estimation method, the Maximum Likelihood Estimation (MLE) is utilized to estimate the degradation related parameters based on the Condition Monitoring (CM) data, while the Bayesian method is utilized to estimate the maintenance related parameters based on the maintenance data. Finally, a numerical example and a practical case study are provided to demonstrate the superiority of the proposed method. The experimental results show that the proposed method could greatly improve the RUL estimation accuracy for the degrading equipment subjected to imperfect maintenance activities.     

基于鲁棒伺服LQR的结冰飞机纵向控制律重构方法

由于防/除冰系统总会出现故障或者除冰不彻底,因此仅依靠防/除冰系统实现结冰条件下的安全飞行并非完全可靠,研究结冰后飞机控制律重构对飞机操纵安全和飞行安全极其重要。针对飞机的纵向运动建立了结冰影响模型和纵向动力学模型,采用鲁棒伺服线性二次型调节器(LQR)最优控制设计了飞机结冰后空中飞行纵向控制律,模拟了飞机在俯仰姿态保持模式下遭遇不同严重程度结冰后的动态响应特性,并与常规PID控制进行对比。结果表明,所设计的控制律能够有效改善结冰飞机的飞行性能和飞行品质,准确跟踪给定的俯仰角指令,且抗干扰能力、动态性能以及鲁棒性均优于常规PID控制。为飞机结冰后的重构控制问题和自动飞行控制,提供了新的思路。     

基于压缩感知的MIMO-SAR运动误差补偿与成像

多发多收合成孔径雷达（MIMO-SAR）利用多通道空间并行采样的优势可实现高分辨成像,但不可避免地存在运动误差与海量数据不便于存储与传输的问题。针对该问题提出一种基于压缩感知的MIMO-SAR运动误差补偿与成像方法。首先通过详细分析MIMO-SAR运动误差回波信号模型,在全采样条件下利用两步运动补偿技术实现对回波数据的运动误差补偿处理,其次针对降采样回波数据的运动误差补偿,通过构造变换算子与压缩感知（CS）重构模型的方法实现第1步运动误差补偿、距离脉压以及距离徙动校正处理,然后再进行第2步误差补偿与方位向脉压处理获得成像结果。最后通过仿真实验验证了所提方法能够在大幅压缩回波数据的情况下,实现MIMO-SAR运动误差补偿与成像处理。     

基于ALE流固耦合方法的刷式密封泄漏特性理论与实验研究

现有刷式密封流固耦合求解模型因刷丝变形接触导致网格畸变而难以计算。本文提出了基于ALE (Arbitrary Lagrange-Euler)流固耦合方法考虑刷丝变形接触的三维瞬态双向流固耦合求解模型,设计搭建了刷式密封泄漏特性和可观测刷丝运动轨迹的实验装置。实验研究了刷式密封刷丝运动状态对泄漏特性的影响,不同压比条件下的泄漏特性变化规律,在验证刷式密封流固耦合求解模型准确性基础上,数值分析了不同时刻刷式密封速度分布与刷丝运动状态,并研究了不同结构参数对泄漏特性的影响规律。研究结果表明:基于ALE流固耦合方法解决了传统刷式密封求解模型因刷丝变形接触导致网格畸变而难以计算的问题,可准确计算刷式密封流场特性和力学特性;刷式密封刷丝吹下效应会降低泄漏量,刷丝颤振现象主要发生在气流入口处的前排刷丝域,会引起泄漏量增大,在气流力作用下,刷丝束轴向厚度变小,有利于减小泄漏量;在本文研究条件下,刷丝固定端与自由端的中间部位最先发生变形,随着时间的变化,气流速度逐渐趋于稳定,最大速度出现在末排刷丝与后挡板接触位置,刷丝自由端变形最大;刷式密封泄漏量随径向密封间隙的增大而增大,与径向密封间隙0mm时相比,径向密封间隙0.2mm时泄漏量增加了51.6%～62.8%。随着刷丝排数的增大,泄漏量逐渐减小,当刷丝排数大于25排时,其对泄漏量影响较小。随着刷丝间隙、刷丝与后挡板之间的轴向间隙、后挡板保护高度的增大,泄漏量先逐渐增大后趋于平缓。     

空－空机炮模态的综合火力／飞行控制系统设计

针对国产某型号高速歼击机的数学模型及其数字式三轴电传操纵控制增稳系统，采用经典控制理论的方法，在数字式三轴电传操纵控制增稳系统的基础上，分析、设计了一种复杂的非线性控制系统──空－空机炮模态的综合火力／飞行控制系统．文中给出了该控制系统的构成，讨论了火力／飞行耦合器的结构．数学仿真表明，所设计的综合火力／飞行控制系统具有良好的性能，由于采用的飞机数学模型及其数字式三轴电传操纵控制增稳系统的真实性，使得所设计的综合火力／飞行控制系统具有较强的实际意义和工程使用价值．     

飞行器相对姿态运动的静力学、运动学和动力学方法

文章系统地研究了飞行器相对姿态运动描述问题 ,提出了求解相对姿态运动的静力学方法、运动学方法和动力学方法 ,特别是在动力学方法中 ,提出了飞行器相对姿态运动的角加速度合成定理。所得结果可作为飞行器相对姿态运动的分析和数值仿真的理论基础 ,并为今后进一步研究飞行器相对运动制导和控制问题打下基础     

Impact of loading effects on determination of the International Terrestrial Reference Frame

The International Terrestrial Reference Frame (ITRF), as a realization of the International Terrestrial Reference System (ITRS), is represented by a set of station positions and linear velocities. They are intended to be used as regularized coordinates to which some corrections should be added to access instantaneous coordinates. The latest ITRS realization is the ITRF2005, which has integrated time series of station positions to form long-term solutions for the four space geodetic techniques. Currently, a purely linear model is used to parameterize station displacements in the estimation process, plus occasional discontinuities in case of earthquakes or equipment changes. However the input data have been derived without applying surface loading models and so surface loading effects are supposed to be embedded in the coordinates as measured quantities. We evaluate the effect of applying a posteriori loading corrections, which include the effect of atmospheric, non-tidal ocean, and continental water loading, to time series of positions estimated from Satellite Laser Ranging (SLR), Very Long Baseline Interferometry (VLBI), and Global Positioning System (GPS) data. We notice that they reduce about 50% or more of the annual signals in the translation and scale parameter time series of the SLR and VLBI techniques, except in SLR Z translation. In general, the estimated secular frame definition is negligibly affected and estimated positions and velocities are not significantly modified for stations that have accumulated a large number of observations. A multi-technique combination of such derived frames allows concluding that, for some cases, loading model corrections might degrade co-located station coordinates almost as much as they benefit them. However, most significant improvement of the estimated secular coordinates is observed for stations with less than 100 estimated positions as demonstrated with a multi-technique combination.     

空间四面体翻滚机器人运动学分析及仿真实验

对四面体及多面体机器人的研究现状进行了分析.介绍了空间四面体翻滚机器人的结构,由6根伸缩臂和4个顶部节点平台组成,通过伸缩臂的运动可以使四面体的重心失稳,实现翻滚运动.结合四面体翻滚机器人的运动形式,给出了翻滚的临界条件,根据不同的运动阶段对四面体翻滚机器人进行了运动学分析.利用Adams虚拟样机技术对四面体翻滚机器人进行了运动学仿真,并进行了样机的实验,验证了方法的正确性.该分析结果可进一步用于空间四面体翻滚机器人的动力学分析和优化设计.     

火星探测器轨道运动建模的时空基准转换研究

火星探测的理论研究和工程实践需要一套便于描述火星探测器轨道运动的时空基准转换体系,环火星轨道的探测任务期间需要给出探测器以火星为基准的运动信息,而地面测控只能获得探测器以地球为基准的运动信息。为此,文章定义了一套新的以火星为基准的坐标系以及过渡到以地球为基准的坐标系,并给出了各坐标系转换的求解方法。最后,对以文中所提出的时空转换基准为基础建立的火星探测器轨道运动模型进行数值仿真,并将计算结果同STK进行了比较,验证了该时空转换体系的正确性。     

严格回归轨道的管道导航方法研究

分析了作为参考轨道的严格回归轨道与卫星在轨运行状态的相对运动关系,提出近地遥感卫星的管道导航方法。由于参考轨道的设计只考虑高精度的地球非球形摄动,与在轨卫星的动力学环境存在差别,这导致两者之间存在切航向漂移。基于高精度的轨道动力学模型和位置确定方法,设计了卫星与参考轨道采样点的沿航向对齐算法,从而获取了卫星相对参考轨道采样点的相位时间偏差和卫星在参考轨道编队坐标系切航向平面内的相对运动轨迹,进而引入椭圆的“最小二乘适配法”获取相对运动轨迹的特征量。所研究的管道导航方法可应用于基于GNSS测量数据的卫星自主轨迹保持。