萤火一号火星轨道器开环追踪技术

中国首个火星探测器萤火一号计划于2009年10月和俄罗斯的火卫一采样探测器一道发射升空。萤火一号将探测火星的空间环境,并验证深空导航测控与通信技术。与常规的火星探测任务不同,该探测器的轨道与位置测量主要利用天文甚长基线干涉测量技术、开环跟踪测量技术、差分单程测距测速技术、同波束干涉测量技术以及单程Doppler测速技术承担。     

A study of GPS ionospheric scintillations observed at Shenzhen

Ionospheric scintillation variations are studied using GPS measurements at the low latitude station of Shenzhen (22.59°N, 113.97°E), situated under the northern crest of the equatorial anomaly region, from the Chinese Meridian Project. The results are presented for data collected during the current phase of rising solar activity (low to high solar activity) from December 2010 to April 2014. The results show that GPS scintillation events were largely a nighttime phenomenon during the whole observation period. Scintillation events mainly occurred along the inner edge of the northern crest of the equatorial anomaly in China. The occurrence of scintillations in different sectors of the sky was also investigated, and the results revealed that it is more likely for the scintillations to be observed in the west sector of the sky above Shenzhen. During the present period of study, a total number of 512 total electron content (TEC) depletions and 460 lock loss events were observed. In addition, both of these events are likely to increase during periods of high solar activity, especially because the strong scintillations are often simultaneously accompanied by TEC depletions and lock losses by GPS receivers.     

VLBI observations to the APOD satellite

The APOD (Atmospheric density detection and Precise Orbit Determination) is the first LEO (Low Earth Orbit) satellite in orbit co-located with a dual-frequency GNSS (GPS/BD) receiver, an SLR reflector, and a VLBI X/S dual band beacon. From the overlap statistics between consecutive solution arcs and the independent validation by SLR measurements, the orbit position deviation was below 10?cm before the on-board GNSS receiver got partially operational. In this paper, the focus is on the VLBI observations to the LEO satellite from multiple geodetic VLBI radio telescopes, since this is the first implementation of a dedicated VLBI transmitter in low Earth orbit. The practical problems of tracking a fast moving spacecraft with current VLBI ground infrastructure were solved and strong interferometric fringes were obtained by cross-correlation of APOD carrier and DOR (Differential One-way Ranging) signals. The precision in X-band time delay derived from 0.1?s integration time of the correlator output is on the level of 0.1?ns. The APOD observations demonstrate encouraging prospects of co-location of multiple space geodetic techniques in space, as a first prototype.     

Space object material identification method of hyperspectral imaging based on Tucker decomposition

Space object material identification method based on Tucker decomposition is proposed and demonstrated experimentally. Space target generally has a low spatial resolution because of the limitation in detection distance. Hyperspectral imaging (HSI) technology can capture the image from visible light to shortwave infrared continuously while providing the spatial and spectral information of the target, thereby introducing a new space target detection and identification approach. However, the data obtained by the HSI system often contain mixed pixels, thereby causing difficulties in target material identification. In this work, a material identification method of hyperspectral data based on Tucker decomposition is proposed by combining mixed spectral theory with tensor decomposition. The feasibility of the method is verified by using satellite model hyperspectral data with different spatial resolutions compared with the endmember obtained from the non-negative matrix decomposition (NMF), independent component analysis (ICA), tensor singular value decomposition (t-SVD). The average CORR of NMF, ICA, t-SVD and the proposed method is 0.2694, 0.5818, 0.6397 and 0.937, correspondingly. Therefore, the proposed method has demonstrated a more remarkable performance in terms of material identification, the analysis results of the material abundance distribution that used the proposed method.     

Remaining useful life prediction for engineering systems under dynamic operational conditions: A semi-Markov decision process-based approach

For critical engineering systems such as aircraft and aerospace vehicles, accurate Remaining Useful Life(RUL) prediction not only means cost saving, but more importantly, is of great significance in ensuring system reliability and preventing disaster. RUL is affected not only by a system's intrinsic deterioration, but also by the operational conditions under which the system is operating. This paper proposes an RUL prediction approach to estimate the mean RUL of a continuously degrading system under dynamic operational conditions and subjected to condition monitoring at short equi-distant intervals. The dynamic nature of the operational conditions is described by a discrete-time Markov chain, and their influences on the degradation signal are quantified by degradation rates and signal jumps in the degradation model. The uniqueness of our proposed approach is formulating the RUL prediction problem in a semi-Markov decision process framework, by which the system mean RUL can be obtained through the solution to a limited number of equations. To extend the use of our proposed approach in real applications, different failure standards according to different operational conditions are also considered. The application and effectiveness of this approach are illustrated by a turbofan engine dataset and a comparison with existing results for the same dataset.     

月球探测器LP精密定轨及月球重力场模型解算

对美国1998年发射的月球探测器LP任务阶段共19个月的双程测距测速轨道跟踪数据进行了精密定轨,对定轨结果通过轨道残差及重复弧段差异进行了精度评价。利用LP正常任务阶段三个月的轨道跟踪数据进行了月球重力场模型解算,通过重力场功率谱、轨道残差和月球自由空气重力异常对解算模型进行了精度评价。结果表明精密定轨及月球重力场模型解算合理。对进一步融合嫦娥一号轨道跟踪数据和LP数据解算自主的高精度月球重力场模型具有参考意义。
　
     

真空热试验中闭环温度控制参数分析

为了满足航天器真空热试验温度控制的新要求,文章通过对控制参数与温度控制设定目标值之间数值关系的分析与研究,得出通过电阻性加热器加热、以辐射换热为主要加热途径的温控系统对象,最优比例参数Kc值与目标设定温度成近似正比关系,积分参数Ti值可取固定值,微分参数Td对控制动态品质影响可忽略。具有上述特性的系统可使用参数寻找方法:即在真空热试验之前通过热响应曲线套用公式确定该对象的数学模型,然后使用数值分析的方法,寻找最优的PID参数。通过这种预先估计PID控制参数方法,可以改善电阻特性类控温系统的控制品质。     

A Novel PF-LSSVR-based Framework for Failure Prognosis of Nonlinear Systems with Time-varying Parameters

Particle filtering (PF) is being applied successfully in nonlinear and/or non-Gaussian system failure prognosis. However, for failure prediction of many complex systems whose dynamic state evolution models involve time-varying parameters, the traditional PF-based prognosis framework will probably generate serious deviations in results since it implements prediction through iterative calculation using the state models. To address the problem, this paper develops a novel integrated PF-LSSVR framework based on PF and least squares support vector regression (LSSVR) for nonlinear system failure prognosis. This approach employs LSSVR for long-term observation series prediction and applies PF-based dual estimation to collaboratively estimate the values of system states and parameters of the corresponding future time instances. Meantime, the propagation of prediction uncertainty is emphatically taken into account. Therefore, PF-LSSVR avoids over-dependency on system state models in prediction phase. With a two-sided failure definition, the probability distribution of system remaining useful life (RUL) is accessed and the corresponding methods of calculating performance evaluation metrics are put forward. The PF-LSSVR framework is applied to a three-vessel water tank system failure prognosis and it has much higher prediction accuracy and confidence level than traditional PF-based framework.     

图模型与学习算法结合的贝叶斯网络自动建模

针对纯数据驱动的贝叶斯网络结构学习算法的准确度和效率较低的问题,提出了一种融合多信号流图模型与K2学习算法的贝叶斯网络自动建模方法。该方法利用多信号流图模型能够描述信号之间传递与依赖关系的能力,结合K2学习算法在结构学习中的优势,实现了专家知识与数据驱动方法有效融合的贝叶斯网络结构自动学习算法。通过与常用网络结构学习算法的对比实验证明,该融合算法显著降低了结构学习对学习范围和训练数据规模的要求,具有更高的学习准确度和运算效率。采用真实系统实例阐述了该融合算法的应用过程,验证了算法的实用性。      

智能材料和结构在变体飞行器上的应用现状与前景展望

变体飞行器可以根据不同的飞行条件改变自身形状以获得最优的气动性能,大大提高飞行器的综合性能,是未来飞行器发展的重要方向之一。新型智能材料和结构具有驱动、变形、承载、传感等特点,为变体飞行器的设计提供了新的技术途径。本文根据不同可变形机翼结构分类,详细阐述了智能材料和结构在自适应结构、智能驱动器和变形蒙皮等方面的研究现状。变体飞行器的实现亟需解决变形/承载一体化蒙皮技术、轻质大输出力驱动器技术和自适应结构技术等关键技术,本文还对智能材料和结构未来在变体飞行器上的应用前景进行了展望。