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1.
技术规程是开展海空重力测量作业的重要依据。针对我国现行海空重力测量规范或标准缺乏现势性的问题,开展了海空重力测量测线布设密度、测量精度、空间分辨率、海空重力仪零点漂移与动态重复性等关键性指标分析和论证,提出了由测点重力中误差、系统差和平均误差3个指标组成的测量精度评估体系,以及由格值标定相对精度、零点月漂移量、月漂移非线性变化中误差和月漂移非线性变化限差4个指标组成的海空重力仪稳定性评估体系,给出了相关技术指标的验证和评估方法,同时对涉及船载重力测量测点归算、航空重力测量厄特沃什改正、测量平台倾斜改正及海空重力测量精度评估等关键性数学模型进行了分析和改进,旨在为下一步启动军民融合海空重力测量作业规程编制工作提供技术支撑。 相似文献
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飞机运动加速度的测量精度是制约航空重力测量技术发展的主要障碍之一。相较于传统动态差分GPS（differential GPS,DGPS）技术,所提方法采用单站测量模式,无需布设地面基准站。首先通过相位历元间差分解得高精度历元间位移序列,然后结合泰勒一阶中心差分获得载体加速度,重点分析了卫星轨道和卫星钟差对加速度估计的影响,结果表明,不同卫星轨道产品对加速度估计影响较小,而卫星钟差采样率对加速度估计的影响很大。结合中国陕西省境内的GT-2A航空重力测量系统飞行实测数据,利用单站法解算的加速度联合重力和姿态数据解算重力扰动结果与DGPS解算的重力扰动符合较好,当滤波长度为100 s时,两者互差优于1.0 mGal。重力扰动交叉点不符值网平差后,均方根（root mean square,RMS）为1.13 mGal。与地面重力实测值比较的结果表明,所提方法与DGPS方法在精度上基本一致,说明单站法标量航空重力测量是可行的。 相似文献
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This paper presents a unified approach to the least squares spherical harmonic analysis of the acceleration vector and Eötvös tensor (gravitational gradients) in an arbitrary orientation. The Jacobian matrices are based on Hotine’s equations that hold in the Earth-fixed Cartesian frame and do not need any derivatives of the associated Legendre functions. The implementation was confirmed through closed-loop tests in which the simulated input is inverted in the least square sense using the rotated Hotine’s equations. The precision achieved is at the level of rounding error with RMS about $10^{-12}{-}10^{-14}$ m in terms of the height anomaly. The second validation of the linear model is done with help from the standard ellipsoidal correction for the gravity disturbance that can be computed with an analytic expression as well as with the rotated equations. Although the analytic expression for this correction is only of a limited accuracy at the submillimeter level, it was used for an independent validation. Finally, the equivalent of the ellipsoidal correction, called the effect of the normal, has been numerically obtained also for other gravitational functionals and some of their combinations. Most of the numerical investigations are provided up to spherical harmonic degree 70, with degree 80 for the computation time comparison using real GRACE data. The relevant Matlab source codes for the design matrices are provided. 相似文献
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基于最小二乘配置法向下延拓航空重力的过程中,由于协方差矩阵严重病态,影响延拓结果的稳定性和精度。针对这一问题,提出了航空重力向下延拓的最小二乘配置Tikhonov正则化法。基于全球协方差函数模型建立航空重力数据与地面重力数据的协方差关系,引入基于广义交叉验证法,选择正则化参数的Tikhonov正则化法改善协方差矩阵的病态性,抑制观测噪声对延拓结果的放大影响。基于EGM2008重力场模型,设计了山区、丘陵和海域3种不同地形区域的航空重力数据向下延拓的仿真实验,实验结果验证了该方法的有效性。 相似文献
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Christopher Jekeli 《Journal of Geodesy》1992,66(1):54-61
The Global Positioning System (GPS) is considered in conjunction with a strapdown Inertial Measurement Unit (IMU) for measuring the gravity vector. A comparison of this system in space and on an airborne platform shows the relative importance of each system element in these two different acceleration environments. With currently available instrumentation, the acceleration measurement accuracy is the deciding factor in space, while on an Earth-bound (including airborne) platform, the attitude error of the IMU is most critical. A simulation shows that GPS-derived accelerations in space can be accurate to better than 0.1mgal for a 30s integration time, leading to estimates of 1° mean gravity anomalies on the Earth's surface with an accuracy of 4–5 mgal. On an airborne platform, the horizontal gravity estimation error is tightly coupled to the attitude error of the platform, which can only be bounded by external attitude updates. Horizontal gravity errors of 5mgal are achievable if the attitude is maintained to an accuracy of 1arcsec. 相似文献
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In the numerical evaluation of geodetic convolution integrals, whether by quadrature or discrete/fast Fourier transform (D/FFT) techniques, the integration kernel is sometimes computed at the centre of the discretised grid cells. For singular kernels—a common case in physical geodesy—this approximation produces significant errors near the computation point, where the kernel changes rapidly across the cell. Rigorously, mean kernels across each whole cell are required. We present one numerical and one analytical method capable of providing estimates of mean kernels for convolution integrals. The numerical method is based on Gauss-Legendre quadrature (GLQ) as efficient integration technique. The analytical approach is based on kernel weighting factors, computed in planar approximation close to the computation point, and used to convert non-planar kernels from point to mean representation. A numerical study exemplifies the benefits of using mean kernels in Stokes’s integral. The method is validated using closed-loop tests based on the EGM2008 global gravity model, revealing that using mean kernels instead of point kernels reduces numerical integration errors by a factor of ~5 (at a grid-resolution of 10 arc min). Analytical mean kernel solutions are then derived for 14 other commonly used geodetic convolution integrals: Hotine, Eötvös, Green-Molodensky, tidal displacement, ocean tide loading, deflection-geoid, Vening-Meinesz, inverse Vening-Meinesz, inverse Stokes, inverse Hotine, terrain correction, primary indirect effect, Molodensky’s G1 term and the Poisson integral. We recommend that mean kernels be used to accurately evaluate geodetic convolution integrals, and the two methods presented here are effective and easy to implement. 相似文献
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利用最新研制的一套弱力测试平台,对FG5X-246绝对重力仪观测值准确度指标进行了测试试验。通过弱力测试平台升降装置改变扰动质量体与测量点之间的距离,从而改变测量点处叠加的扰动引力场大小。通过比较FG5X-246绝对重力观测值变化量与理论扰动引力场变化量之间的差异,从而确定FG5X-246绝对重力观测值的准确度。测试结果显示当扰动质量体从1.810 4 m高度降到1.409 9m高度时,外部扰动引力场变化了48.81 μGal(1Gal=1cm/s~2),FG5X-246绝对重力仪感应到48.0 μGal的重力变化,FG5X-246绝对重力仪测量值与理论值之差为0.81 μGal。当扰动质量体从1.810 4m降到1.010 1m高度时,外部扰动引力场变化了-15.44 μGal,FG5X-246绝对重力仪感应到-16.20 μGal的重力变化,测量值与理论值之差为0.76 μGal。当扰动质量体从1.409 9 m降到1.010 1m高度时,外部扰动引力场变化了-64.20 μGal,FG5X-246绝对重力仪感应到-64.25 μGal的重力变化,测量值与理论值之差为0.05 μGal。上述测量结果表明,此次FG5X-246绝对重力仪感应到外部引力变化的误差均不超过1 μGal,即其测量值准确度优于1 μGal。 相似文献
10.
Bernd Eissfeller 《Journal of Geodesy》1996,70(9):539-545
Linear gravity field state space models are still a useful tool to model the anomalous gravity field in vector gravimetry, airborne gravimetry, inertial geodesy and navigation. This paper deals with an idea ofJordan and Heller (1978) to solve analytically the upward continuation problem of Markov gravity models.In contrary to the standard Markov shaping filter approach the height dependency of the covariance function, i.e. variance factor and correlation length as function of height, is strictly introduced in state space and not neglected. Using some basic integral transforms, a general upward continuation integral is derived for the n-th order Markov process. The upward continuation integral is solved for the special and practically important case of 2nd order Markov process in very detail. This leads to the introduction of the special sine and cosine integral functions into the the mathematical covariance model. The features of the covariance model are analyzed analytically and the height dependency is discussed numerically. 相似文献
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A comparison of stable platform and strapdown airborne gravity 总被引：3，自引：1，他引：2
C. L. Glennie K. P. Schwarz A. M. Bruton R. Forsberg A. V. Olesen K. Keller 《Journal of Geodesy》2000,74(5):383-389
To date, operational airborne gravity results have been obtained using either a damped two-axis stable platform gravimeter
system such as the LaCoste and Romberg (LCR) S-model marine gravimeter or a strapdown inertial navigation system (INS), showing
comparable accuracies. In June 1998 three flight tests were undertaken which tested an LCR gravimeter and a strapdown INS
gravity system side by side. To the authors' knowledge, this was the first time such a comparison flight was undertaken. The
flights occurred in Disko Bay, off the west coast of Greenland. Several of the flight lines were partly flown along existing
shipborne gravity profiles to allow for an independent source of comparison of the results. The results and analysis of these
flight tests are presented. The measurement method and error models for both the stable platform and strapdown INS gravity
systems are presented and contrasted. An intercomparison of gravity estimates from both systems is given, along with a comparison
of the individual estimates with existing shipborne gravity profiles. The results of the flight tests show that the gravity
estimates from the two systems agree at the 2–3 mGal level, after the removal of a linear bias. This is near the combined
noise level of the two systems. It appears that a combination of both systems would provide an ideal airborne gravity survey
system, combining the excellent bias stability of the LCR gravimeter with the higher dynamic range and increased spatial resolution
of the strapdown INS.
Received: 3 June 1999 / Accepted: 30 November 1999 相似文献
12.
GPS phase accelerations for moving-base vector gravimetry 总被引：6，自引：1，他引：6
For airborne gravimetry using INS and GPS, the accelerations from both systems are differenced to yield the gravity acceleration.
Usually, the GPS acceleration is determined by first solving for the position of the vehicle relative to a base station and
subsequently taking two time derivatives of the vertical component. An alternative method is to time-differentiate the observed
phases directly, thus avoiding the cycle ambiguity problem that must be solved for positioning and that is fraught with (certainly
not insurmountable) difficulties in the event of a cycle slip. Due to the largely unpredictable receiver-clock errors and
the imposition of the Selective Availability degradation, doubly differenced (in space) phase accelerations are used to obtain
the relative vehicle accelerations. Test results for stationary receivers show that the acceleration vector can be determined
from phase accelerations to an accuracy of 1 mgal for 40-s averages. The mathematical formulation of the acceleration determination
also highlights certain other advantages over traditional methods, such as the avoidance of the E?tv?s correction, although
a similar kind of velocity effect must be determined.
Received: 9 September 1996 / Accepted: 14 April 1997 相似文献
13.
Adaptive filtering of GOCE-derived gravity gradients of the disturbing potential in the context of the space-wise approach 总被引：1，自引：0，他引：1
Filtering and signal processing techniques have been widely used in the processing of satellite gravity observations to reduce measurement noise and correlation errors. The parameters and types of filters used depend on the statistical and spectral properties of the signal under investigation. Filtering is usually applied in a non-real-time environment. The present work focuses on the implementation of an adaptive filtering technique to process satellite gravity gradiometry data for gravity field modeling. Adaptive filtering algorithms are commonly used in communication systems, noise and echo cancellation, and biomedical applications. Two independent studies have been performed to introduce adaptive signal processing techniques and test the performance of the least mean-squared (LMS) adaptive algorithm for filtering satellite measurements obtained by the gravity field and steady-state ocean circulation explorer (GOCE) mission. In the first study, a Monte Carlo simulation is performed in order to gain insights about the implementation of the LMS algorithm on data with spectral behavior close to that of real GOCE data. In the second study, the LMS algorithm is implemented on real GOCE data. Experiments are also performed to determine suitable filtering parameters. Only the four accurate components of the full GOCE gravity gradient tensor of the disturbing potential are used. The characteristics of the filtered gravity gradients are examined in the time and spectral domain. The obtained filtered GOCE gravity gradients show an agreement of 63–84 mEötvös (depending on the gravity gradient component), in terms of RMS error, when compared to the gravity gradients derived from the EGM2008 geopotential model. Spectral-domain analysis of the filtered gradients shows that the adaptive filters slightly suppress frequencies in the bandwidth of approximately 10–30 mHz. The limitations of the adaptive LMS algorithm are also discussed. The tested filtering algorithm can be connected to and employed in the first computational steps of the space-wise approach, where a time-wise Wiener filter is applied at the first stage of GOCE gravity gradient filtering. The results of this work can be extended to using other adaptive filtering algorithms, such as the recursive least-squares and recursive least-squares lattice filters. 相似文献
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航空重力测量中低通滤波器参数的优选 总被引：4，自引：0，他引：4
从含有大量噪声的航空重力仪测量值中提取重力场信息，最常用的方法是使用低通滤波器，欲获得性能优良的滤波器，必须合理地选择滤波器的设计参数。文中利用一组实测GPS数据，讨论了滤波器长度，截止频率，权函数等参数对滤波效果的影响，给出了航空重力测量应用中滤波器参数的若干选择原则。 相似文献
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Measurements of gravity were made on boardU.S.S. Becuna (SS 319) with a Vening Meinesz pendulum apparatus and a Graf sea gravimeter at approximately the same time.
Comparison of data uncorrected for depth of submergence, E?tvos correction and second order effects of horizontal acceleration
showed that there was a change related to time of observation. These corrections were not made as they would be the same for
both sets of observations, and no provision had yet been made to take care of the horizontal accelerations for the Graf sea
gravimeter. The variation with otime could be caused by instrumental drift or scale calibration. After removal of this effect
by visually fitting the data trend with a straight line, there were three observations with large discrepancies, seventeen
with discrepancies of 3–9 mgal and thirty-nine with discrepancies of 0–3 mgal, showing close approach to a statistical distribution.
The three large discrepancies may be dismissed because of very bad depth control during the observations. The discrepancies
3–9 mgals are larger than expected and perhaps are attributable to depth control and inadequate observation time for the Graf
sea gravimeter.
It is concluded that the Graf sea gravimeter shows great promise for use on a submarine. An apparatus to take into account
the horizontal acceleration effects must be added, and suitable drift characteristic obtained. Despite its advantages of ruggedness,
ease of operation, ease of data reduction, reduced size and weight, many more comparisons of the Graf sea gravimeter with
the Vening Meinesz pendulum equipment should be made before the latter are displaced
Probably the Graf sea gravimeter will be usable on a stable platform on a surface vessel at least in calm sea states. 相似文献
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Although airborne gravimetry is now considered a fully operational technique, errors due to motion compensation using differential
GPS (DGPS) continue to influence both its accuracy and the range of applications in which it can be used. In typical medium-resolution
applications such as airborne geoid mapping, errors due to DGPS contribute considerably to the error budget of an airborne
gravity system. At the same time, efforts to increase the resolution of such systems for demanding applications such as resource
exploration remain impedded by errors in DGPS.
This article has three objectives. The first one is to compare eight industrially relevant DGPS software packages for the
determination of aircraft acceleration. The second objective is to analyze and quantify the effect that each relevant portion
of the DGPS error budget has on the determination of acceleration. Using data sets that represent a wide range of operational
conditions, this is done in the frequency domain over a range of frequencies corresponding to spatial resolution as high as
450 m. The third objective is to use that information to recommend and demonstrate approaches that optimize the estimation
of aircraft acceleration for determining the geoid and for resource exploration.
It is shown, for example, that the time of day in which the survey is carried out and the dynamic characteristics of the aircraft
being used are two of the most crucial parameters for very high-resolution gravity field estimation. It is demonstrated that
when following the above-mentioned recommendations, agreements with ground daa of better than 1.5 and 2.5 mGal can be achieved
for spatial resolutions (half-wavelengths) of 2.0 and 1.4 km, respectively. ? 2002 Wiley Periodicals, Inc. 相似文献
18.
K. H. Neumayer 《Journal of Geodesy》1998,72(12):698-704
An attempt is made to bridge the gap between closed-form harmonic upward continuation (HUC) of analytic covariance functions
of the disturbing potential of the anomalous local gravity field and the numerical shaping filter construction when the local
gravity vector is modelled in the framework of Kalman filtering. Some fundamental concepts of the local gravity field, interpreted
as a stochastic process that is stationary in the plane and harmonic in the upper half space, are reviewed. The shaping-filter
modelling technique for the local gravity vector is introduced. To determine the relation between the disturbing potential
covariance function and the gravity vector covariance matrix, the role of the so-called admissible pair is established. It
is shown that rescaling an admissible pair leads to an analogue rescaling of the shaping filter matrices derived hereof; no
cumbersome numerical recalculations are necessary. The class of covariance functions whose corresponding shaping filters possess
a closed-form HUC are identified as models whose HUC can be interpreted as a rescaling.
Received: 17 December 1997 / Accepted: 7 September 1998 相似文献
19.
Gravity gradient modeling using gravity and DEM 总被引：2，自引：0，他引：2
A model of the gravity gradient tensor at aircraft altitude is developed from the combination of ground gravity anomaly data
and a digital elevation model. The gravity data are processed according to various operational solutions to the boundary-value
problem (numerical integration of Stokes’ integral, radial-basis splines, and least-squares collocation). The terrain elevation
data are used to reduce free-air anomalies to the geoid and to compute a corresponding indirect effect on the gradients at
altitude. We compare the various modeled gradients to airborne gradiometric data and find differences of the order of 10–20 E
(SD) for all gradient tensor elements. Our analysis of these differences leads to a conclusion that their source may be primarily
measurement error in these particular gradient data. We have thus demonstrated the procedures and the utility of combining
ground gravity and elevation data to validate airborne gradiometer systems. 相似文献
20.
L&R海空重力仪测量误差综合补偿方法 总被引：2，自引：0，他引：2
为了削弱各类误差源的影响,提出了一种两阶段误差综合补偿方法:第一阶段采用相关分析法对仪器厂家标定的交叉耦合改正(CC改正)的不足进行修正;第二阶段采用测线网平差对各类剩余误差的综合影响进行补偿。实际观测数据处理结果验证了该方法的有效性和可靠性。 相似文献