共查询到19条相似文献，搜索用时 296 毫秒
1.
2.
《武汉大学学报(信息科学版)》2020,(4)
运动误差可由位姿变化反映,基于此提出了一种利用同名像点位姿变化建立某型器物量测系统误差补偿新方法。该方法首先在位置1处观测,通过控制器主动做定量位姿变化到位置2,结合位置1处外方位元素与坐标转换原理得到位置2处外方位元素初始值,进而利用条件共线方程解得位置2处标定板角点拟合像素坐标;然后在位置2处观测,并将标定板中同名像点像素坐标作为观测值,与拟合值作差可列出误差方程式,迭代求解误差改正数;最后利用获得的多组误差数据,通过非线性最小二乘拟合获得运动误差补偿模型。实验表明,利用该方法检测运动误差无需测量仪器参与,操作便捷,代价成本低;此外,补偿模型所需参数较少,补偿后误差减小至亚毫米级。 相似文献
3.
4.
FAST对馈源舱精调机构的位姿测量提出了极高的精度要求。本文介绍了由全站仪组成的精调机构测量系统,计算了全站仪跟踪观测棱镜时的主要观测条件,包括棱镜入射角、观测距离和观测高度角,并进行了棱镜初始指向的优化配置。结果表明,棱镜入射角的最大值约为35°,平均值约为13°~18°,由此产生的测量误差可以忽略;观测距离约为140~350 m,估算全站仪动态测距精度约为2.1~2.4 mm;观测高度角约为0~40°,分布合理,且有利于全站仪的防护。仿真测量结果表明,9个测站的定位精度优于2.5 mm,定姿精度优于360";6个测站的定位精度优于3 mm,定姿精度优于430",均达到精调机构的位姿测量精度要求。 相似文献
5.
针对如何快速实时地获取运动目标位姿参数的问题,该文提出了一种单目运动目标位姿实时测量的方法,设计了标志点像物方匹配检测状态机和快速跟踪匹配状态机。匹配检测状态机在无标志点差异的条件下,采用反投影法得到最佳物像匹配对应关系,为快速高效跟踪匹配提供位姿初始解;提出了一种基于精度评定的状态切换机制,既发挥了跟踪匹配的高效性,又避免跟踪失败造成的位姿测量永久失败。实验结果表明,反投影法能够有效地筛选出最佳的像物方匹配对应关系,快速跟踪匹配状态机能够通过跟踪标志点高效地计算匹配关系和位姿参数,状态切换机制及时地判断跟踪错误,并迅速切换至匹配检测状态,实时测量全过程能高稳健运行。 相似文献
6.
7.
快速、精准的建筑物变化检测对城市规划建设等业务管理具有重要意义。随着卫星遥感技术的快速发展,基于高分辨率遥感影像的建筑物变化检测得到了广泛关注。针对像元级建筑物变化检测方法往往精度不足而目标级建筑物变化检测方法过程烦琐等问题,本文提出结合像元级和目标级的高分辨率遥感影像建筑物变化检测方法。首先综合高分辨率遥感影像的多维特征,利用随机森林分类器进行影像集分类,以获取像元级建筑物变化检测结果;然后对后时相遥感影像进行图像分割,获得影像对象;最后融合像元级建筑物变化检测结果和影像对象,识别变化的建筑物目标。利用双时相QuickBird高分辨率遥感影像进行建筑物变化检测试验,结果表明：本文提出的方法能够削弱光照、观测角度等环境差异对建筑物变化检测的影响,显著改善建筑物变化的检测精度。 相似文献
8.
多台激光跟踪仪组网联合动态测量具有测量范围大、测量精度高、采样频率高的优点,在工业大尺寸动态位姿测量领域具有广泛的应用前景。目前激光跟踪仪动态测量精度评定主要针对单台激光跟踪仪,无法满足多台激光跟踪仪动态位姿测量精度评定的要求。文中提出基于物方先验约束条件的动态位姿测量精度评定方法,通过空间圆轨迹发生器和铟钢四面体,提供刚性约束条件和动态测量基准,实现对不同运动速度、不同采样频率的位姿测量精度进行评定。测试数据分析表明,基于物方先验约束条件的动态位姿测量精度评定方法能够有效的实现对测量精度的评定。 相似文献
9.
多尺度分割的高分辨率遥感影像变化检测 总被引：4，自引：1，他引：3
针对高空间分辨率的遥感影像,提出了一种基于多尺度分割的变化检测算法。采用Mean-Shift分割算法对影像进行多尺度分割,构建了不同尺度上的地理对象,以不同尺度上的地理对象灰度均值构建了变化检测的多尺度特征向量,采用变化矢量分析法获得最后的变化检测结果。以城镇区和农田区的Quick Bird影像对本文算法进行了检验,从精度评价的效果来看,无论城镇区还是农田区,采用面向对象的变化检测方法精度都高于基于单像素的检测方法,且当尺度层数固定时,多尺度组合的变化检测结果优于单一尺度的变化检测结果,对城镇、农田区域的变化检测的精度分别达到87.57%和81.55%。本文算法既可以顾及大面积同质区域变化,又可以反映小的地物目标及边缘部分的变化,能够很好地满足城镇、农田等不同环境背景下的变化检测需求,在国土资源监测中具有一定的应用价值。 相似文献
10.
随着在轨失效航天器数量不断增加,针对这类空间非合作目标的在轨服务需求日益迫切。由于在轨的非合作目标飞行器上无法布置合作标志器,通过提取非合作目标上的关键轮廓角点对其进行跟踪。本文针对空间非合作目标所具有的特性,传统Harris算子对运动非合作目标角点的检测中存在大量的伪角点,提出一种基于Canny边缘检测的Shi-Tomasi角点检测方法,即对影像先进行滤波、二值化及形态学处理,其次利用Canny边缘检测获得其轮廓后再进行Shi-Tomasi角点检测。实验结果表明,该算法能有效地解决深空中光照条件等因素造成的角点难以检测问题以及减少伪角点,对空间非合作目标的关键角点提取有较好地检测精度和准确性。 相似文献
11.
两种SAR数据目标定位的比较 总被引：2，自引：2，他引：0
和以前的定位方法相比,距离-多普勒(R—D)定位法因不需要选地面参考点进行定位,在许多遥感应用方面具有独特的优势和重要意义。本文论述了利用卫星星历数据和雷达回波数据的距离-多普勒信息对SAR图像目标定位的原理,并对相对位置定位算法的计算公式进行了推导。通过该定位方法对Radarsat和ERS图像目标进行了定位,详细说明了轨道参数、斜距参数、多普勒参数等获取方法,比较了这两种数据目标定位具体算法和精度的差异。 相似文献
12.
针对传统影像拼接方法需要控制点的问题,该文提出一种基于位姿信息的小型无人机影像拼接方法。首先从机载GPS和惯性导航单元获取无人机拍摄的位置姿态参数,利用Harris算法提取特征点,采用SIFT描述方法计算特征向量,通过近似最近邻算法和PROSAC算法对匹配的同名点对精化。然后根据同名点对像平面坐标和航拍时的位置姿态信息,计算影像之间的变换矩阵,通过最小二乘原理平差计算以提高变换矩阵精度。最后利用变换矩阵实现无人机多幅影像的拼接,得到兴趣区域全景图。实验结果验证了该方法在拼接效果方面具有优势。 相似文献
13.
为满足深空探测器的精确定姿需求,提出了一种惯性测量单元(IMU)辅助的X射线脉冲星定姿方法。该方法用IMU的速率陀螺来估计航天器短时姿态,观测两颗或多颗脉冲星的X射线辐射信号,将拟合得到的观测矢量作为滤波器信息输入,利用这两种测姿手段在时间和空间上的互补特性,提供一种全天候、抗干扰性强的定姿方法。仿真结果表明,相比于EKF,基于UKF的俯仰、横滚和偏航三姿态角的测量精度可提高21.9%、21.1%和31.7%;与仅使用脉冲星或IMU的定姿方法相比,组合定姿方法的俯仰角估计精度分别提高了32.5%和77.6%。 相似文献
14.
无地面控制点的星载SAR影像直接对地定位研究 总被引：2，自引：0，他引：2
针对星栽合成孔径雷达（SAR）对地面目标的定位问题，分析了在无地面控制点的情况下，利用距离-多普勒（R-D）模型和地球模型进行对地定位的理论与方法，给出了在无地面控制点（GCP）而有数字高程模型的情况下利用R-D模型进行对地定位的求解方法。用天津地区ERS-1数据进行实验，其结果与当地地形图进行比较，精度在50m以内，表明该文提出的方法是正确、可行的。 相似文献
15.
GF-4 PMI影像着火点自适应阈值分割 总被引：1，自引：0，他引：1
为探究具有单中波红外通道的高分四号卫星(GF-4)PMI数据在林火监测中的应用方法,通过对覆盖近年发生森林火灾的多景GF-4 PMI影像分析,采用"劈窗法"构建GF-4 PMI数据的着火点自适应阈值检测算法;在云南省玉龙纳西族自治县、俄罗斯阿穆尔州和俄罗斯外贝加尔边疆区等3个实验区进行了着火点检测应用,并以目视解译的着火点结果为参照资料,对该算法的着火点检测精度进行了评价。结果表明,该算法在这3个实验区的着火点检测准确率均高于80.0%,基于着火点检测精度验证设定的综合评价指标高于0.780,可应用于GF-4PMI影像着火点的检测。 相似文献
16.
A CE-5T1 spacecraft completed a high-speed skip re-entry to the earth after a circumlunar flight on October 31, 2014. In addition to the strapdown inertial navigation system (SINS), a lightweight GPS receiver with rapid acquisition was developed as a navigation sensor in the re-entry capsule. The GPS receiver effectively solved the poor accuracy problem of long-term navigation using only the SINS. In contrast to ground users and low-earth-orbit spacecraft, numerous factors, including high altitude and kinetic characteristics in high-speed skip re-entry, are important for GPS positioning feasibility and were presented in accordance with the flight data. GPS solutions started at nearly 4900 km orbital altitude during the phases of re-entry process. These solutions were combined by an inertial measurement unit in a loosely coupled integrated navigation method and SINS navigation initialization. A simplified GPS/SINS navigation filter for limited resources was effectively developed and implemented on board for spacecraft application. Flight data estimation analyses, including trajectory, attitude, position distribution of GPS satellite, and navigation accuracy, were presented. The estimated accuracy of position was better than 42 m, and the accuracy of velocity was better than 0.1 m/s. 相似文献
17.
针对运动航天器收到的脉冲星信号受Doppler效应影响,难以准确测量脉冲到达时间的问题,提出了基于三阶小波互累积量的脉冲星累积脉冲轮廓时间延迟测量算法。结果表明,当信号受到Doppler效应影响时,该算法测量精度优于现有算法,适用于脉冲星导航系统中脉冲到达时间的测量。 相似文献
18.
This paper describes a low earth orbiter micro-satellite attitude determination algorithm using GPS phase and pseudorange
data as the only observables. It is designed to run in real-time, at a rate of 10 Hz, on-board the spacecraft, using minimal
chip and memory resources. The spacecraft design includes four GPS antennas deployed on boom arms to improve the antenna separations.
The boom arms feature smart sensors, from which time-varying deformation data are used to calculate changes in the body-fixed
system (BFS) co-ordinates of the attitude antennas. These data are used as input to the attitude algorithm to improve the
accuracy of the output.
The conventional double-difference phase observation equations have been re-arranged so that the only unknown parameters in
the functions (once the ambiguities have been determined) are the spacecraft Euler angles. This greatly increases the redundancy
in the mathematical model, and is exploited to enhance the algorithm's ability to trap observations contaminated by unmodelled
multipath. This approach has been shown to be successful in identifying phase outliers at the 5–10 mm level. Speed of execution
of the program is improved by utilising numerical differentiation of the model equations in the linearisation process. Furthermore,
as the number of solve-for parameters is reduced to three by the chosen mathematical model, matrix inversion requirements
are minimised. A novel approach to ambiguity resolution and determination of initial estimates of the attitude parameters
has been developed utilising a heuristic technique and the known, and time varying, BFS co-ordinates of the antenna array.
Algorithm testing is based on a simulation of the micro-satellite trajectory combined with variations in attitude derived
from spin-stabilisation and periodic roll and pitch parameters. The trajectory of the spacecraft centre of mass was calculated
by numerical integration of a force model using Earth gravity field parameters, third body effects due to the Sun and the
Moon, dynamic Earth tide effects (solar and lunar), and a solar radiation pressure model. Frame transformations between J2000
and ITRF97 used the IERS conventions. A similar approach was used to calculate the trajectories of all available GPS satellites
during the same period, using initial conditions of position and velocity from IGS precise orbits. RMS differences between
the published precise orbit and the integrated satellite positions were at the 5-mm level. Phase observables are derived from
these trajectories, biased by simulation of receiver and satellite clock errors, cycle slips, random or systematic noise and
initial integer ambiguities. In the actual simulation of the attitude determination process in orbit, GPS satellite positions
are calculated using broadcast ephemerides.
The results show that the aim of 0.05° (two sigma) attitude precision can be met provided that the phase noise can be reduced
to the level of 1–2 mm. Attitude precision was found to vary strongly with constellation geometry, which can change quite
rapidly depending on the variations in spacecraft attitude. The redundancy in the mathematical model was found to be very
effective in trapping and isolating cycle slips to the double difference observations that are contaminated. This allows for
the possibility of correcting for cycle slips without full recourse to the ambiguity resolution algorithm.
Electronic Publication 相似文献
19.
DEM matching is a technique to match two surfaces or two DEMs, at different reference frames. It was originally proposed to replace the need of ground control points for absolute orientation of perspective images. This paper examines DEM matching for precise mapping of pushbroom images without ground control points. We proved that DEM matching based on 3D similarity transformation can be used when model errors are only on the platform’s position and attitude biases. We also proposed how to estimate bias errors and how to update rigorous pushbroom sensor models from DEM matching results. We used a SPOT-5 stereo pair at ground sampling distance of 2.5 m and a reference DEM dataset at grid spacing of 30 m and showed that rigorous pushbroom models with accuracy better than twice of the ground sampling distance both in image and object space have been achieved through DEM matching. We showed further that DEM matching based on 3D similarity transformation may not work for pushbroom images with drift or drift rate errors. We discussed the effects of DEM outliers on DEM matching and automated removal of outliers. The major contribution of this paper is that we validate DEM matching, theoretically and experimentally, for estimating position and attitude biases and for establishing rigorous sensor models for pushbroom images. 相似文献