共查询到17条相似文献,搜索用时 187 毫秒
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重力梯度仪安装在惯性稳定平台上,忽略载体姿态角改变等条件下的影响,在空间上保持方向不变,因此载体相对于重力梯度仪的旋转会改变其周围空间的质量分布,从而引起自身梯度的变化.这种自身梯度变化影响了重力梯度仪的测量精度,是动基座重力梯度测量误差的重要来源.由于周围环境物体到重力梯度仪的距离很近,采用基于中心引力梯度的方法计算自身梯度具有较大误差.推导了基于加速度计输出的重力梯度仪自身梯度补偿方法.仿真结果表明通过基于中心引力梯度的方法和基于加速度计输出的方法分别计算单位质量的质量点产生的自身梯度时,0.3m位置处自身梯度补偿的偏差超过5E,采用基于加速度计输出的方法进行自身梯度补偿更加精确. 相似文献
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重力梯度是重力位的二阶微分,对地球密度扰动具有更高的分辨率,能够更加精细、全面地反映重力位在空间上的变化。高精度重力梯度测量在地质调查、地球重力场测绘、惯性导航以及基础科学研究等方面发挥着重要作用。量子重力梯度仪是近年来快速发展的一种基于激光操控原子技术的新型高精度重力梯度测量设备,具有测量精度高、长期稳定性好等特点,尤其是对振动噪声具有良好的抑制效果。目前,量子重力梯度仪的最佳灵敏度可达4E/√Hz,与最先进的旋转加速度计式重力梯度仪灵敏度3E/√Hz的水平相当。本文介绍了量子重力梯度仪的基本原理和应用,并分析了其国内外研究现状,最后讨论了目前限制量子重力梯度仪灵敏度的主要因素以及未来发展方向。 相似文献
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准确的发动机特性曲线是其性能计算的基础。文章讨论了多种情况的特性曲线插值方法:在工作点位置区间内,对小数据情况引入了新的插值方法;多数据时,采用三次样条插值方法进行插值;在工作点位置区间外,数据较多时,基于最小二乘法进行不同工作点的拟合;当工作点位置数据较少,利用新的插值方法在区间内引入虚拟工作点增加数据点,后按照数据较多的情况处理。所得结果与实际数值比较,精度较高,具有一定的参考价值。 相似文献
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重力数据处理对获取高精度重力异常值有着重要作用,是重力测量的核心技术。重力仪在搭载运动载体进行重力测量时,载体的高频振动对重力测量数据和GPS数据均会产生不可避免的干扰,导致提取的重力异常粗值含有大量高频噪声。围绕重力数据的处理方法这一核心技术,介绍了FIR低通滤波、零相移滤波、标准Kalman滤波、正反Kalman滤波4种滤波方法的基本原理,运用这4种方法处理了SAG捷联式重力仪的某次实际飞行测量数据,比对了基于SINS/GPS组合导航和SINS/DGPS组合导航的重力测量数据处理结果。通过对本次试验重复测线内符合精度进行比对,验证了4种方法的可行性和优劣性,同时验证了SAG重力仪的测量精度。 相似文献
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针对重力梯度辅助定位中,存在重力梯度的强非线性分布及系统模型偏差等问题,将STUPF引入匹配定位过程。该方法根据残差信息实时调节系统状态跟踪能力,有效应对模型偏差对定位的影响。基于真实INS数据的仿真实验结果表明,STUPF可达到较好的定位效果,且与标准PF、GPF算法相比,其在定位的精度、稳定性及运算量上具有一定优势。 相似文献
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The Juno Gravity Science Instrument 总被引:1,自引:0,他引:1
Sami W. Asmar Scott J. Bolton Dustin R. Buccino Timothy P. Cornish William M. Folkner Roberto Formaro Luciano Iess Andre P. Jongeling Dorothy K. Lewis Anthony P. Mittskus Ryan Mukai Lorenzo Simone 《Space Science Reviews》2017,213(1-4):205-218
The Juno mission’s primary science objectives include the investigation of Jupiter interior structure via the determination of its gravitational field. Juno will provide more accurate determination of Jupiter’s gravity harmonics that will provide new constraints on interior structure models. Juno will also measure the gravitational response from tides raised on Jupiter by Galilean satellites. This is accomplished by utilizing Gravity Science instrumentation to support measurements of the Doppler shift of the Juno radio signal by NASA’s Deep Space Network at two radio frequencies. The Doppler data measure the changes in the spacecraft velocity in the direction to Earth caused by the Jupiter gravity field. Doppler measurements at X-band (\(\sim 8\) GHz) are supported by the spacecraft telecommunications subsystem for command and telemetry and are used for spacecraft navigation as well as Gravity Science. The spacecraft also includes a Ka-band (\(\sim 32\) GHz) translator and amplifier specifically for the Gravity Science investigation contributed by the Italian Space Agency. The use of two radio frequencies allows for improved accuracy by removal of noise due to charged particles along the radio signal path. 相似文献
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Global Gravity Field Recovery Using Solely GPS Tracking and Accelerometer Data from Champ 总被引:2,自引:0,他引:2
Reigber C. Balmino G. Schwintzer P. Biancale R. Bode A. Lemoine J.-M. König R. Loyer S. Neumayer H. Marty J.-C. Barthelmes F. Perosanz F. Zhu S. Y. 《Space Science Reviews》2003,108(1-2):55-66
A new long-wavelength global gravity field model, called EIGEN-1, has been derived in a joint German-French effort from orbit
perturbations of the CHAMP satellite, exploiting CHAMP-GPS satellite-to-satellite tracking and on-board accelerometer data
over a three months time span. For the first time it becomes possible to recover the gravity field from one satellite only.
Thanks to CHAMP'S tailored orbit characteristics and dedicated instrumentation, providing continuous tracking and on-orbit
measurements of non-gravitational satellite accelerations, the three months CHAMP-only solution provides the geoid and gravity
with an accuracy of 20 cm and 1 mgal, respectively, at a half wavelength resolution of 550 km, which is already an improvement
by a factor of two compared to any pre-CHAMP satellite-only gravity field model.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
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Possible Future Use of Laser Gravity Gradiometers 总被引:1,自引:0,他引:1
With the GRACE mission under way and the GOCE mission well along in the design process, detailed questions concerning the
type of future mission that may follow them have arisen. It is generally agreed that determining the time variations in the
Earth's gravity field with as high spatial and temporal resolution as is feasible will be the main driver for such a mission.
The possible use of laser heterodyne measurements between separate satellites in such a mission has been discussed by a number
of people. The first suggestion of emphasizing time variation measurements in a laser mission was the TIDES concept presented
in 1992 by Colombo and Chao. Then, in 2000, a GRACE Follow-On mission using laser measurements between two drag-free satellites
was discussed by Watkins el al. (2000).
More recently, the possibility of utilizing laser measurements between more than two satellites in order to determine two
or more components of the gravity gradient tensor simultaneously has been proposed by Balmino. This approach may be desirable
in order to reduce the aliasing of time variations between geopotential terms of different degree and order, as well as to
improve the resolution in longitude, despite the cost of the additional satellites. In this paper, we discuss specific possible
mission geometries for measuring the two diagonal in-plane components of the gravity gradient tensor simultaneously. This
could be done, for example, by laser heterodyne measurements between two pairs of satellites in coplanar and nearly polar
orbits.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
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主动段扰动引力是引起弹道导弹制导方法误差的主要因素。因此,要提高导弹的制导精度,就必须能够在弹上实时计算扰动引力。但现有方法在计算快速性和存储量之间无法得到有效协调。为此,把广义延拓逼近思想引入有限元逼近方法中,将插值单元周围节点的信息也包含到单元内一点扰动引力的计算当中,建立了一种新的数学模型。对所选发射空域,在发射坐标系中进行了直角坐标划分。计算结果表明,这种方法能够更加精确地逼近弹道导弹主动段的扰动引力,在600 km×250 km×6 km的主动段飞行区域内,只需要保存60个节点数据,就能使由逼近误差导致的落点偏差小于10 m,是一般有限元逼近方法精度的4倍以上。 相似文献
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The science of inertial navigation has evolved to the point that the traditional gravity model is a principal error source in advanced, precise systems. Specifically, the unmodeled vertical deflections of the earth's gravitational field are a major contributor to CEP (circular error probable) divergence in precise terrestrial inertial navigation systems (INS). Over the years, several studies have been undertaken to the development of advanced techniques for accurate, real-time compensation of gravity disturbance vectors. More complex on-board gravity models which compute vertical deflection components will reduce the CEP divergence rate, but imperfect modeling due to on-board processing limitations will still cause residual vertical deflection errors. In order to eliminate or reduce gravity-induced errors in the INS requires measurement of gravity disturbance values and in-flight compensation to the inertial navigator. It is assumed in this paper that gravity disturbance values have been measured prior to the airborne mission and various techniques for compensation are to be considered. As part of a screening process in this study, several gravity compensation techniques (both deterministic and stochastic models) were investigated. The screening process involved identification of gravity models and algorithms, and developments of selection criteria for subsequent screening of the candidates. 相似文献