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Intel MKL在Bernese GNSS数据处理中的应用

为提高Bernese GNSS software数据处理效率，将英特尔数学核心函数库(math kernel library，MKL)应用于Bernese 精密定轨数据处理，对比分析多个MKL矩阵求逆函数与Bernese 原有程序的计算效率。使用2019-03全球200个测站北斗/GNSS数据进行实验分析，结果表明，采用参数预消除策略时，参数预消除步骤消耗时间明显大于矩阵求逆，使用MKL处理数据效率提升不明显；而未采用参数预消除策略时，使用MKL矩阵求逆函数可显著提高矩阵求逆效率，其中dpotri函数矩阵求逆计算效率最高，消耗时间平均值为133 s，相比Bernese 原有程序计算速度可提高13倍。     

对流层模型评估及其在GNSS精密单点定位中的应用

以水汽辐射计（WVR）精确测定的天顶方向延迟值作为参考,评估Saastamoinen、GPT2、EGNOS、UNB3M四种常用对流层模型在上海地区的改正精度;并将WVR观测值及以上4种对流层模型计算的对流层延迟值作为真值应用到GNSS精密单点定位（PPP）中,评估其对定位精度的影响。比较发现,GPT2模型的对流层改正精度比其余3种要好,其天顶干延迟（ZHD）的偏差均值与中误差分别为-0.11 cm、±0.75 cm,天顶湿延迟（ZWD）的平均偏差与中误差分别为-2.34 cm、±7.67 cm;和传统的PPP结果相比,采用WVR对流层观测值的定位精度提高了16%。     

荧光分光光度法测定海洋生物中的谷胱甘肽

对应用荧光分光光度法测定海洋生物中还原型谷胱甘肽(GSH)含量的方法进行了研究,并测定了分属于鱼、虾、贝、藻的10种海洋生物中谷胱甘肽的含量。利用邻苯二甲醛与GSH反应构成的荧光体系,在激发波长为365nm,发射波长为425nm的条件下,方法的回收率为99.22%~99.69%,变异系数为2.16%。应用此方法测得10种海洋生物中谷胱甘肽的含量为:红笛鲷(Lutjanussanguineus)0.399mg/g,银鲳(Pampusargenteus)0.352mg/g,大海鲢(Megalopscyrinoides)0.561mg/g,尖紫蛤(Sanguinolariaacuta)0.289mg/g,菲律宾蛤仔(Ruditapesphilippinarun)0.287mg/g,墨吉对虾(Penaeusmerguiensis)0.892mg/g,凡纳滨对虾(Litopenaeusvannamei)1.434mg/g,囊藻(Colpomeniasinu-ose)0.221mg/g,石莼(Ulvalactucal)0.727mg/g,马尾藻(Sargassummuticum)0.137mg/g。     

Orbital linkages of Comet 6P/d'Arrest based on its asymmetric light curve

We present an investigation of different models of the nongravitational acceleration on Comet 6P/d'Arrest, as used in orbital linkages spanning 150 years from the discovery of the comet in 1851 until the recent observations made in 2001. Some of our models use the time-shifted g-like function to represent the variation of outgassing rate, but the main thrust is on models using instead a production curve that is fitted to recent light curve observations—mainly those in 1976. We pay special attention to the proper scaling of such a production curve, when applied to other apparitions with a different perihelion distance q, and we find a best fit with a q^−1.6 power-law. Generally, the best fit is found with models, in which the acceleration components are expressed in terms of the angular parameters of the rotating nucleus. We thus find the orientation of the spin axis, and using the orbital evolution we are able to predict a variable time shift of the outgassing curve. The very best results are found when applying this time shift to the light-curve based, angular models. The totality of the 1851-2001 observations can then be linked with a mean residual of less than 4″. This may be brought down to ∼^2″ by solving for individual ‘activity parameters’ of all apparitions, which are multiplicative factors applied to the acceleration amplitudes. These turn out to be within 10% of unity for the best fit. We have also performed a linkage to the observations of Comet 1678 (La Hire) using our models. We find an indication of a secular increase of the amount of asymmetry of the outgassing with respect to perihelion, part of which is due to the variable time shift caused by the orbital evolution.     

Development of an observational error model

In calculating the orbit of a minor planet with a least-squares algorithm, current practice is to assume that all observations of a given era have the same uncertainty, and that the errors in these observations are uncorrelated. These assumptions are unrealistic; and they lead to sub-optimal orbits.Our objective is to develop and validate an observational error model that provides realistic estimates of the uncertainties and correlations in asteroid observations. When used to populate the covariance matrix of the least-squares algorithm, the resulting orbits are shown to more accurately and precisely represent asteroid trajectories.     

New Definition of Discovery for Solar System Objects

We propose a new formal definition of discovery for a Solar System object. It is based on an objective and mathematically rigorous algorithm to assess when a set of observations is enough to constitute a discovery. When this definition is satisfied, in almost all cases the orbit is defined well enough to establish the nature of the object discovered (Main Belt vs. Near Earth Asteroid, Trans-Neptunian vs. long period comet). The frequency of occurrence of exceptions is estimated by a set of numerical experiments. The availability of a non-subjective definition of discovery allows some rules to be adopted for the assignment of discovery credit with a minimum risk of dispute. Such rules should be fair, encourage good practice by the observers and acknowledge the contribution of the orbit computers providing the identifications and the orbits, as well as the one of all the contributing observers.     

Atmospheric densities derived from CHAMP/STAR accelerometer observations

The satellite CHAMP carries the accelerometer STAR in its payload and thanks to the GPS and SLR tracking systems accurate orbit positions can be computed. Total atmospheric density values can be retrieved from the STAR measurements, with an absolute uncertainty of 10-15%, under the condition that an accurate radiative force model, satellite macro-model, and STAR instrumental calibration parameters are applied, and that the upper-atmosphere winds are less than . The STAR calibration parameters (i.e. a bias and a scale factor) of the tangential acceleration were accurately determined using an iterative method, which required the estimation of the gravity field coefficients in several iterations, the first result of which was the EIGEN-1S (Geophys. Res. Lett. 29 (14) (2002) 10.1029) gravity field solution. The procedure to derive atmospheric density values is as follows: (1) a reduced-dynamic CHAMP orbit is computed, the positions of which are used as pseudo-observations, for reference purposes; (2) a dynamic CHAMP orbit is fitted to the pseudo-observations using calibrated STAR measurements, which are saved in a data file containing all necessary information to derive density values; (3) the data file is used to compute density values at each orbit integration step, for which accurate terrestrial coordinates are available. This procedure was applied to 415 days of data over a total period of 21 months, yielding 1.2 million useful observations. The model predictions of DTM-2000 (EGS XXV General Assembly, Nice, France), DTM-94 (J. Geod. 72 (1998) 161) and MSIS-86 (J. Geophys. Res. 92 (1987) 4649) were evaluated by analysing the density ratios (i.e. “observed” to “computed” ratio) globally, and as functions of solar activity, geographical position and season. The global mean of the density ratios showed that the models underestimate density by 10-20%, with an rms of 16-20%. The binning as a function of local time revealed that the diurnal and semi-diurnal components are too strong in the DTM models, while all three models model the latitudinal gradient inaccurately. Using DTM-2000 as a priori, certain model coefficients were re-estimated using the STAR-derived densities, yielding the DTM-STAR test model. The mean and rms of the global density ratios of this preliminary model are 1.00 and 15%, respectively, while the tidal and latitudinal modelling errors become small. This test model is only representative of high solar activity conditions, while the seasonal effect is probably not estimated accurately due to correlation with the solar activity effect. At least one more year of data is required to separate the seasonal effect from the solar activity effect, and data taken under low solar activity conditions must also be assimilated to construct a model representative under all circumstances.     

Assessment of the resonant perturbation errors in Galilean satellite ephemerides using precisely measured eclipse times

Astrometric satellite positions are derived from timings of their eclipses in the shadow of Jupiter. The 548 data points span 20 years and are accurate to about 0.006 arcsec for Io and Europa and about 0.015 arcsec or better for Ganymede and Callisto. The precision of the data set and its nearly continuous distribution in time allows measurement of regular oscillations with an accuracy of 0.001 arcsec. This level of sensitivity permits detailed evaluation of modern ephemerides and reveals anomalies at the 1.3 year period of the resonant perturbations between Io, Europa and Ganymede. The E5 ephemeris shows large errors at that period for all three satellites as well as other significant anomalies. The L1 ephemeris fits the observations much more closely than E5 but discrepancies for the resonant satellites are still apparent and the measured positions of Io are drifting away from the predictions. The JUP230 ephemeris fits the observations more accurately than L1 although there is still a measurable discordance between the predictions and observations for Europa at the resonance period.