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1.
Tidal Models in a New Era of Satellite Gravimetry 总被引:3,自引:0,他引:3
The high precision gravity measurements to be made by recently launched (and recently approved) satellites place new demands
on models of Earth, atmospheric, and oceanic tides. The latter is the most problematic. The ocean tides induce variations
in the Earth's geoid by amounts that far exceed the new satellite sensitivities, and tidal models must be used to correct
for this. Two methods are used here to determine the standard errors in current ocean tide models. At long wavelengths these
errors exceed the sensitivity of the GRACE mission. Tidal errors will not prevent the new satellite missions from improving
our knowledge of the geopotential by orders of magnitude, but the errors may well contaminate GRACE estimates of temporal
variations in gravity. Solar tides are especially problematic because of their long alias periods. The satellite data may
be used to improve tidal models once a sufficiently long time series is obtained. Improvements in the long-wavelength components
of lunar tides are especially promising.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
2.
The NASA/DLR satellite gravity mission GRACE, launched in March, 2002, will map the Earth's gravity field at scales of a few
hundred km and greater, every 30 days for five years. These data can be used to solve for time-variations in the gravity field
with unprecedented accuracy and resolution. One of the many scientific problems that can be addressed with these time-variable
gravity estimates, is post glacial rebound (PGR): the viscous adjustment of the solid Earth in response to the deglaciation
of the Earth's surface following the last ice age.
In this paper we examine the expected sensitivity of the GRACE measurements to the PGR signal, and explore the accuracy with
which the PGR signal can be separated from other secular gravity signals. We do this by constructing synthetic GRACE data
that include contributions from a PGR model as well as from a number of other geophysical processes, and then looking to see
how well the PGR model can be recovered from those synthetic data. We conclude that the availability of GRACE data should
result in improved estimates of the Earth's viscosity profile.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
3.
Spaceborne GPS receiver antenna phase center offset and variation estimation for the Shiyan 3 satellite 总被引:3,自引:2,他引:1
《中国航空学报》2016,(5):1335-1344
In determining the orbits of low Earth orbit (LEO) satellites using spaceborne GPS, the errors caused by receiver antenna phase center offset (PCO) and phase center variations (PCVs) are gradually becoming a major limiting factor for continued improvements to accuracy. Shiyan 3, a small satellite mission for space technology experimentation and climate exploration, was developed by China and launched on November 5, 2008. The dual-frequency GPS receiver payload delivers 1 Hz data and provides the basis for precise orbit determination within the range of a few centime-ters. The antenna PCO and PCV error characteristics and the principles influencing orbit determi-nation are analyzed. The feasibility of PCO and PCV estimation and compensation in different directions is demonstrated through simulation and in-flight tests. The values of receiver antenna PCO and PCVs for Gravity Recovery and Climate Experiment (GRACE) and Shiyan 3 satellites are estimated from one month of data. A large and stable antenna PCO error, reaching up to 10.34 cm in the z-direction, is found with the Shiyan 3 satellite. The PCVs on the Shiyan 3 satellite are estimated and reach up to 3.0 cm, which is slightly larger than that of GRACE satellites. Orbit validation clearly improved with independent k-band ranging (KBR) and satellite laser ranging (SLR) measurements. For GRACE satellites, the average root mean square (RMS) of KBR resid-uals improved from 1.01 cm to 0.88 cm. For the Shiyan 3 satellite, the average RMS of SLR resid-uals improved from 4.95 cm to 4.06 cm. 相似文献
4.
Space-Wise,Time-Wise,Torus and Rosborough Representations in Gravity Field Modelling 总被引:1,自引:0,他引:1
The decade of the geopotentials started July 2000 with the launch of the German high-low SST mission CHAMP. Together with the joint NASA-DLR low-low SST
mission GRACE and the ESA gradiometry mission GOCE an unprecedented wealth of geopotential data becomes available over the
next few years.
Due to the sheer number of unknown gravity field parameters (up to 100 000) and of observations (millions), especially the
latter two missions are highly demanding in terms of computational requirements. In this paper several modelling strategies
are presented that are based on a semi-analytical approach. In this approach the set of normal equations becomes block-diagonal
with maximum block-sizes smaller than the spherical harmonic degree of resolution. The block-diagonality leads to a rapid
and powerful gravity field analysis tool.
Beyond the more-or-less conventional space-wise and time-wise formulations, the torus approach and Rosborough's representation
are discussed. A trade-off between pros and cons of each of the modelling strategies will be given.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
5.
Satellite-Satellite Laser Links for Future Gravity Missions 总被引:3,自引:0,他引:3
A strong candidate for use in future missions to map time variations in the Earth's gravity field is laser heterodyne measurements
between separate spacecraft. At the shortest wavelengths that can be measured in space, the main accuracy limitation for variations
in the potential with latitude is expected to be the frequency stability of the laser. Thus the development of simple and
reliable space-qualified lasers with high frequency stability appears to be an important goal for the near future.
In the last few years, quite high stability has been achieved by locking the second harmonic of a Nd:YAG laser to a resonant
absorption line of iodine molecules in an absorption cell. Such a laser system can be made quite robust, and temperature related
frequency shifts can be controlled at a low value. Recent results from laboratory systems are described. The Allan standard
deviation for the beat between two such lasers was 2 × 10−14 at 10 s, and reached 7 × 10−15 at 600 s.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
6.
The GRACE mission will map the Earth's gravity fields and its variations with unprecedented accuracy during its 5-year lifetime.
Unless ocean tide signals and their load upon the solid earth are removed from the GRACE data, their long period aliases obscure
more subtle climate signals which GRACE aims at. In this analysis the results of Knudsen and Andersen (2002) have been verified
using actual post-launch orbit parameter of the GRACE mission. The current ocean tide models are not accurate enough to correct
GRACE data at harmonic degrees lower than 47. The accumulated tidal errors may affect the GRACE data up to harmonic degree
60. A study of the revised alias frequencies confirm that the ocean tide errors will not cancel in the GRACE monthly averaged
temporal gravity fields. The S2 and the K2 terms have alias frequencies much longer than 30 days, so they remain almost unreduced in the monthly averages. Those results
have been verified using a simulated 30 days GRACE orbit. The results show that the magnitudes of the monthly averaged values
are slightly higher than the previous values. This may be caused by insufficient sampling to fully resolve and reduce the
tidal signals at short wavelengths and close to the poles.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
7.
Noriyuki Namiki Takahiro Iwata Nobuyuki Kawano Fumio Fuke Naoki Tateno Kazuyoshi Asari Hirotomo Noda Yusuke Kono Hideo Hanada Yukihiro Yahagi Zen’ichi Yamamoto Koji Tanaka Mitsuo Yamada Koji Matsumoto Sander Goossens 《Space Science Reviews》2010,154(1-4):103-121
The Japanese lunar mission Selenological and Engineering Explorer (SELENE) was launched in September 2007 and continued its mission until June 2009, when the main orbiter impacted with the surface of the Moon. SELENE consisted of three satellites: Main, Rstar, and Vstar. Rstar’s tasks were to forward up-link signals from the Usuada Deep Space Center (UDSC) to Main, and to down-link returning signals from Main to UDSC. We refer to this tracking sub-system as a four-way Doppler measurement. In contrast, conventional tracking systems between Rstar and UDSC as well as between Main and ground stations are referred to as two-way Doppler and range measurements. Using Main and Rstar, we successfully observed the gravity field over the farside of the Moon. Because four-way Doppler measurements via a relay sub-satellite were a fundamental experiment in space for Japanese space agencies, compatibility of radiometric instruments onboard Main and Rstar to UDSC were carefully examined at the UDSC using components manufactured for flight models. These tests not only proved the feasibility of the four-way Doppler measurements but also provided biases and variations of the four-way Doppler and two-way Doppler and range measurements that were later taken into account during the processing of tracking data and the analysis of the lunar global gravity field. 相似文献
8.
The Lunar Gravity Ranging System for the Gravity Recovery and Interior Laboratory (GRAIL) Mission 总被引:1,自引:0,他引:1
William M. Klipstein Bradford W. Arnold Daphna G. Enzer Alberto A. Ruiz Jeffrey Y. Tien Rabi T. Wang Charles E. Dunn 《Space Science Reviews》2013,178(1):57-76
The Lunar Gravity Ranging System (LGRS) flying on NASA’s Gravity Recovery and Interior Laboratory (GRAIL) mission measures fluctuations in the separation between the two GRAIL orbiters with sensitivity below 0.6 microns/Hz1/2. GRAIL adapts the mission design and instrumentation from the Gravity Recovery and Climate Experiment (GRACE) to a make a precise gravitational map of Earth’s Moon. Phase measurements of Ka-band carrier signals transmitted between spacecraft with line-of-sight separations between 50 km to 225 km provide the primary observable. Measurements of time offsets between the orbiters, frequency calibrations, and precise orbit determination provided by the Global Positioning System on GRACE are replaced by an S-band time-transfer cross link and Deep Space Network Doppler tracking of an X-band radioscience beacon and the spacecraft telecommunications link. Lack of an atmosphere at the Moon allows use of a single-frequency link and elimination of the accelerometer compared to the GRACE instrumentation. This paper describes the implementation, testing and performance of the instrument complement flown on the two GRAIL orbiters. 相似文献
9.
10.
How to Climb the Gravity Wall 总被引:2,自引:0,他引:2
Space Science Reviews - What type of gravity satellite mission is required for the time after GRACE and GOCE? Essentially, the variables at our disposal are experiment altitude, compensation of... 相似文献
11.
The Gravity Recovery and Climate Experiment (GRACE), which was successfully launched March 17, 2002, has the potential to
create a new paradigm in satellite oceanography with an impact perhaps as large as was observed with the arrival of precision
satellite altimetry via TOPEX/Poseidon (T/P) in 1992. The simulations presented here suggest that GRACE will be able to monitor
non-secular changes in ocean mass on a global basis with a spatial resolution of ≈500 km and an accuracy of ≈3 mm water equivalent.
It should be possible to recover global mean ocean mass variations to an accuracy of ≈1 mm, possibly much better if the atmospheric
pressure modeling errors can be reduced. We have not considered the possibly significant errors that may arise due to temporal
aliasing and secular gravity variations. Secular signals from glacial isostatic adjustment and the melting of polar ice mass
are expected to be quite large, and will complicate the recovery of secular ocean mass variations. Nevertheless, GRACE will
provide unprecedented insight into the mass components of sea level change, especially when combined with coincident satellite
altimeter measurements. Progress on these issues would provide new insight into the response of sea level to climate change.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
12.
高精度、高分辨率的重力及重力梯度基准图是决定潜艇水下辅助导航定位精度的关键因素。我国海洋重力测量目前的主要比例尺为1:1000000,在局部区域可达1:500000,测线间隔分布相对稀疏。传统的网格化插值技术在远离测点位置时容易产生虚假异常,或异常特征发生偏移。构建了全张量重力梯度数据的6个梯度分量的联合网格化方法,利用各个梯度分量与引力位在波数域中的关系重构了引力位,实现了重力和重力梯度数据的再计算,从而实现了网格处理。通过模型数据和实测数据,验证了该方法在插值异常分辨率和位置准确性上具有优势。 相似文献
13.
This paper presents a review of geoid error characteristics of three satellite gravity missions in view of the general problem
of separating scientifically interesting signals from various noise sources. The problem is reviewed from the point of view
of two proposed applications of gravity missions, one is the observation of the mean oceanic circulation whereby an improved
geoid model is used as a reference surface against the long term mean sea level observed by altimetry. In this case we consider
the presence of mesoscale variability during assimilation of derived surface currents in inverse models. The other experiment
deals with temporal changes in the gravity field observed by GRACE in which case a proposed experiment is to monitor changes
in the geoid in order to detect geophysical interesting signals such as variations in the continental hydrology and non-steric
ocean processes. For this experiment we will address the problem of geophysical signal contamination and the way it potentially
affects monthly geoid solutions of GRACE.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
14.
Geodetic Methods for Calibration of GRACE and GOCE 总被引:2,自引:0,他引:2
It is beyond doubt that calibration and validation are essential tools in the process of reaching the goals of gravity missions
like GRACE and GOCE and to obtain results of the highest possible quality. Both tools, although general and obvious instruments
for any mission, have specific features for gravity missions. Therefore, it is necessary to define exactly what is expected
(and what cannot be expected) from calibration and what from validation and how these tools should work in our case. The general
calibration and validation schemes for GRACE and GOCE are outlined. Calibration will be linked directly to the instrument
and the measurements whereas validation will be linked to data derived from the original measurements. Calibration includes
on-ground, internal, and external calibration as well as error assessment. The calibration phase results in corrected measurements
along with an a posteriori error model. Validation of e.g. calibrated measurements or geoid heights means checking against
independent data to assess whether there are no systematic errors left and/or whether the error model describes the true error
reasonably well. Geodetic methods for calibration typically refer to external calibration and error assessment, and will be
illustrated with an example.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
15.
Reconstructed attitude data for the Hipparcos mission as obtained in the final stages of the data analysis for the published
catalogue is used to derive detailed information on the dynamics of the satellite. Most elements of the inertia tensor of
the satellite could be calibrated from the observed acceleration data, which are also used to reconstruct torques due to solar
radiation and gravity gradient, and the magnetic moment of the satellite and it's interaction with the magnetic field surounding
the Earth. The effects of the oblateness of the Earth on the gravity gradient are evaluated and shown to be negligable. The
magnetic field model includes both the `main' and the `disturbance' fields. The remaining systematic effects in residual torques
are most likely attributed to variations in the magnetic field that are local and are beyond the models used to describe it.
The angular momentum vector for one of the gyros was reconstructed from the torque it asserted on the satellite while it was
running in redundant mode.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
16.
The very high accuracy of the Doppler and range measurements between the two low-flying and co-orbiting spacecraft of the
GRACE mission, which will be at the μm/sec and ≈10 μm levels respectively, requires that special procedures be applied in
the processing of these data. Parts of the existing orbit determination and gravity field parameters retrieval methods and
software must be modified in order to fully benefit from the capabilities of this mission. This is being done in the following
areas: (i) numerical integration of the equations of motion (summed form, accuracy of the predictor-corrector loop, Encke's
formulation): (ii) special inter-satellite dynamical parameterization for very short arcs; (iii) accurate solution of large
least-squares problems (normal equations vs. orthogonal decomposition of observation equations); (iv) handling the observation
equations with high accuracy. Theoretical concepts and first tests of some of the newly implemented algorithms are presented.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
17.
星间基线高精度确定是分布式干涉合成孔径雷达(InSAR)系统完成科学任务的重要保证,受星载全球定位系统(GPS)接收机连续跟踪弧段短、个别弧段共视GPS卫星个数少或模糊度固定成功率低、频繁轨道机动等因素影响,分布式InSAR高精度基线确定仍有不可靠的风险。通过多机构产品互比来识别基线精度较差的时间段,降低不可靠风险,并通过多机构产品融合进一步提高基线精度。选用重力反演与气候实验(GRACE)卫星数据进行实验,国防科技大学(NDT)和西安测绘研究所(CHS)采用不同的基线处理软件和简化动力学策略,保证了各自的基线产品具有一定的独立性。实验表明,多机构互比对可以有效识别基线精度较差的时间段,NDT和CHS的基线产品之间具有很好的一致性,互比对残差的均方根(RMS)在R、T、N方向分别为0.7、0.9、0.7 mm,二者之间没发现明显系统偏差,大约97.86%的基线三维互比对残差量级在2 mm以内。两个机构基线产品融合后发现可进一步降低基线产品中的随机波动误差,K/Ka波段测距(KBR)系统校核结果表明融合基线产品精度较NDT基线产品提高8.97%,较CHS基线产品提高29.21%。 相似文献
18.
J. D. Anderson J. W. Armstrong J. K. Campbell F. B. Estabrook T. P. Krisher E. L. Lau 《Space Science Reviews》1992,60(1-4):591-610
The gravitation and celestial mechanics investigations during the cruise phase and Orbiter phase of the Galileo mission depend on Doppler and ranging measurements generated by the Deep Space Network (DSN) at its three spacecraft tracking sites in California, Australia, and Spain. Other investigations which also rely on DSN data, and which like ours fall under the general discipline of spacecraft radio science, are described in a companion paper by Howard et al. (1992). We group our investigations into four broad categories as follows: (1) the determination of the gravity fields of Jupiter and its four major satellites during the orbital tour, (2) a search for gravitational radiation as evidenced by perturbations to the coherent Doppler link between the spacecraft and Earth, (3) the mathematical modeling, and by implication tests, of general relativistic effects on the Doppler and ranging data during both cruise and orbiter phases, and (4) an improvement in the ephemeris of Jupiter by means of spacecraft ranging during the Orbiter phase. The gravity fields are accessible because of their effects on the spacecraft motion, determined primarily from the Doppler data. For the Galilean satellites we will determine second degree and order gravity harmonics that will yield new information on the central condensation and likely composition of material within these giant satellites (Hubbard and Anderson, 1978). The search for gravitational radiation is being conducted in cruise for periods of 40 days centered around solar opposition. During these times the radio link is least affected by scintillations introduced by solar plasma. Our sensitivity to the amplitude of sinusoidal signals approaches 10-15 in a band of gravitational frequencies between 10-4 and 10-3 Hz, by far the best sensitivity obtained in this band to date. In addition to the primary objectives of our investigations, we discuss two secondary objectives: the determination of a range fix on Venus during the flyby on 10 February, 1990, and the determination of the Earth's mass (GM) from the two Earth gravity assists, EGA1 in December 1990 and EGA2 in December 1992. 相似文献
19.
20.
Drinkwater M. R. Floberghagen R. Haagmans R. Muzi D. Popescu A. 《Space Science Reviews》2003,108(1-2):419-432
This paper introduces the first ESA Core Earth Explorer mission, GOCE, in the context of ESA's Living Planet programme. GOCE
will measure highly accurate, high spatial resolution differential accelerations in three dimensions along a well characterised
orbit: the mission is planned for launch in early 2006. The mission objectives are to obtain gravity gradient data such that
new global and regional models of the static Earth's gravity field and of the geoid can be deduced at length scales down to
100 km. These products will have broad application in the fields of geodesy, oceanography, solid-earth physics and glaciology.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献