Attitude Measurement Low Frequency Error Identification and Compensation for Star Tracker with Gyros

The low-frequency error (LFE) of star tracker is the most critical problems in the high accuracy attitude determination for the satellite. In this paper a novel approach is proposed to identify and compensate the attitude measurement LFE of the star trackers. The main difficulty in the attitude LFE identification is to distinguish the attitude LFE from the attitude motion. To overcome this difficulty, the gyro data, which is sensitive to the attitude motion, was used to fit the measurement attitude data to obtain the reference attitude. It is shown that, the LFE can be identified by comparing the measurement attitude and the reference attitude. The attitude LFE repeated feature is characterized well by the proposed method. By utilizing the orbital repeated feature, the LFE of the star trackers can be estimated. Finally, a LFE compensation strategy is presented base on the LFE estimation results. The validity and efficiency of the proposed approach are demonstrated by the relative Euler angle results from two test star trackers on-board the STECE satellite.

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Low-frequency Periodic Error Identification and Compensation for Star Tracker Attitude Measurement

Chinese Journal of Aeronautics ◽

10.1016/s1000-9361(11)60426-3 ◽

2012 ◽

Vol 25 (4) ◽

pp. 615-621 ◽

Cited By ~ 11

Author(s):

Jiongqi WANG ◽

Kai XIONG ◽

Haiyin ZHOU

Keyword(s):

Low Frequency ◽

Star Tracker ◽

Attitude Measurement ◽

Error Identification ◽

Periodic Error

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HIGH-PRECISION ATTITUDE ESTIMATION METHOD OF STAR SENSORS AND GYRO BASED ON COMPLEMENTARY FILTER AND UNSCENTED KALMAN FILTER

ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences ◽

10.5194/isprs-archives-xlii-3-w1-49-2017 ◽

2017 ◽

Vol XLII-3/W1 ◽

pp. 49-53 ◽

Cited By ~ 4

Author(s):

C. Guo ◽

X. Tong ◽

S. Liu ◽

X. Lu ◽

...

Keyword(s):

Kalman Filter ◽

High Frequency ◽

Attitude Determination ◽

Unscented Kalman Filter ◽

Estimation Method ◽

Attitude Estimation ◽

Star Tracker ◽

Attitude Motion ◽

Complementary Filter ◽

Gyro Drift

Determining the attitude of satellite at the time of imaging then establishing the mathematical relationship between image points and ground points is essential in high-resolution remote sensing image mapping. Star tracker is insensitive to the high frequency attitude variation due to the measure noise and satellite jitter, but the low frequency attitude motion can be determined with high accuracy. Gyro, as a short-term reference to the satellite’s attitude, is sensitive to high frequency attitude change, but due to the existence of gyro drift and integral error, the attitude determination error increases with time. Based on the opposite noise frequency characteristics of two kinds of attitude sensors, this paper proposes an on-orbit attitude estimation method of star sensors and gyro based on Complementary Filter (CF) and Unscented Kalman Filter (UKF). In this study, the principle and implementation of the proposed method are described. First, gyro attitude quaternions are acquired based on the attitude kinematics equation. An attitude information fusion method is then introduced, which applies high-pass filtering and low-pass filtering to the gyro and star tracker, respectively. Second, the attitude fusion data based on CF are introduced as the observed values of UKF system in the process of measurement updating. The accuracy and effectiveness of the method are validated based on the simulated sensors attitude data. The obtained results indicate that the proposed method can suppress the gyro drift and measure noise of attitude sensors, improving the accuracy of the attitude determination significantly, comparing with the simulated on-orbit attitude and the attitude estimation results of the UKF defined by the same simulation parameters.

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RESEARCH ON INTEGRATED STATIC AND DYNAMIC GEOMETRIC CALIBRATION TECHNOLOGY FOR OPTICAL SURVEYING AND MAPPING SATELLITES

ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences ◽

10.5194/isprs-archives-xliii-b1-2020-141-2020 ◽

2020 ◽

Vol XLIII-B1-2020 ◽

pp. 141-148

Author(s):

Y. Wang ◽

X. Hu ◽

G. Xie

Keyword(s):

Low Frequency ◽

Calibration Method ◽

Frequency Error ◽

Attitude Measurement ◽

Correction Model ◽

Geometric Calibration ◽

Temperature Changes ◽

Sensor Platform ◽

System Errors ◽

Surveying And Mapping

Abstract. As the satellite latitude and camera temperature changes, temperature distortion in orbit makes the optical axis of the star sensor drifts slowly in the satellite body coordinate system, and the attitude measurement system contains low frequency errors that cannot be ignored. Low frequency errors are systematic in short periods, and occasional in long periods, which cause an error of a few minutes, so as to greatly reduce the positioning accuracy without control points of satellite photography. Traditional geometric calibration can only eliminate system errors caused by changes in optics in sensor platform and mechanical structures and etc., and cannot reduce the effect of low-frequency errors. An integrated static and dynamic geometric calibration method based on optical surveying and mapping satellites is proposed in this paper. The attitude system error and low frequency error are effectively detected by establishing a correction model of low frequency errors and analyzing the effective calibration process of traditional on-orbit calibration and dynamic calibration. Finally, relevant experiments are performed with image from satellite TIANHUI-1 in seven test fields, which verifies that this low-frequency error compensation method is correct and effective.

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Influence on Inertia the Moment of Inertia Matrix of Three Degrees of Freedom Air-Bearing Testbed

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.706-708.1393 ◽

2013 ◽

Vol 706-708 ◽

pp. 1393-1396

Author(s):

Yan Bin Li ◽

Ren Song Zou ◽

Tong Jiang

Keyword(s):

Attitude Control ◽

Degrees Of Freedom ◽

Attitude Determination ◽

Euler Angle ◽

Element Model ◽

Moment Of Inertia ◽

Attitude Motion ◽

Air Bearing ◽

The Moment ◽

And Control

To improve the accuracy of attitude determination and control stabilization when simulating attitude motion of satellites in the space, the finite element model of the platform of 3-DOF spacecraft attitude control simulator was founded. Gravity field of air bearing testbed and formula for platform’s moment of inertia on the action of gravity was induced The result shows platform’s attitude accuracy error exist because of main principal axis of inertia change of direction.on the action of gravity, The more large value it is, the more error is .Error of inertia main axis changes as sine curve with the change of two horizontal Euler angle.

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Low-Frequency Error Extraction and Compensation for Attitude Measurements from STECE Star Tracker

Sensors ◽

10.3390/s16101669 ◽

2016 ◽

Vol 16 (10) ◽

pp. 1669 ◽

Cited By ~ 3

Author(s):

Yuwang Lai ◽

Defeng Gu ◽

Junhong Liu ◽

Wenping Li ◽

Dongyun Yi

Keyword(s):

Low Frequency ◽

Star Tracker ◽

Frequency Error ◽

Attitude Measurements

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An Improved Time Integration Method Based on Galerkin Weak Form with Controllable Numerical Dissipation

Applied Sciences ◽

10.3390/app11041932 ◽

2021 ◽

Vol 11 (4) ◽

pp. 1932

Author(s):

Weixuan Wang ◽

Qinyan Xing ◽

Qinghao Yang

Keyword(s):

High Frequency ◽

Integration Method ◽

Time Integration ◽

Low Frequency ◽

Weak Form ◽

High Accuracy ◽

Numerical Dissipation ◽

Frequency Range ◽

Time Integration Method ◽

Numerical Damping

Based on the newly proposed generalized Galerkin weak form (GGW) method, a two-step time integration method with controllable numerical dissipation is presented. In the first sub-step, the GGW method is used, and in the second sub-step, a new parameter is introduced by using the idea of a trapezoidal integral. According to the numerical analysis, it can be concluded that this method is unconditionally stable and its numerical damping is controllable with the change in introduced parameters. Compared with the GGW method, this two-step scheme avoids the fast numerical dissipation in a low-frequency range. To highlight the performance of the proposed method, some numerical problems are presented and illustrated which show that this method possesses superior accuracy, stability and efficiency compared with conventional trapezoidal rule, the Wilson method, and the Bathe method. High accuracy in a low-frequency range and controllable numerical dissipation in a high-frequency range are both the merits of the method.

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Fuzzified time-frequency method for identification and localization of power system faults

Journal of Intelligent & Fuzzy Systems ◽

10.3233/jifs-189769 ◽

2021 ◽

pp. 1-13

Author(s):

Pullabhatla Srikanth ◽

Chiranjib Koley

Keyword(s):

Power System ◽

High Accuracy ◽

Fuzzy Decision ◽

Frequency Method ◽

Time Frequency ◽

Novel Approach ◽

S Transform ◽

Different Types ◽

Power System Faults ◽

Frequency Magnitude

In this work, different types of power system faults at various distances have been identified using a novel approach based on Discrete S-Transform clubbed with a Fuzzy decision box. The area under the maximum values of the dilated Gaussian windows in the time-frequency domain has been used as the critical input values to the fuzzy machine. In this work, IEEE-9 and IEEE-14 bus systems have been considered as the test systems for validating the proposed methodology for identification and localization of Power System Faults. The proposed algorithm can identify different power system faults like Asymmetrical Phase Faults, Asymmetrical Ground Faults, and Symmetrical Phase faults, occurring at 20% to 80% of the transmission line. The study reveals that the variation in distance and type of fault creates a change in time-frequency magnitude in a unique pattern. The method can identify and locate the faulted bus with high accuracy in comparison to SVM.

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Wavelet Filter Approach for GPS Attitude Tracking System on Ship

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.450.552 ◽

2010 ◽

Vol 450 ◽

pp. 552-555

Author(s):

Ping Wang ◽

Kai Xue ◽

Qiu Hong Li

Keyword(s):

High Frequency ◽

Tracking System ◽

Tracking Error ◽

Low Frequency ◽

Attitude Measurement ◽

Visual Effects ◽

Error Sources ◽

Attitude Tracking ◽

Servo Mechanism ◽

Filter Approach

GPS attitude tracking system on the ship is a servo mechanism which could be used for counteracting the effects of the ship’s pitch and roll. But the attitude measurement precision of ship is more important to the tracking precision of the servo mechanism. As one of the major error sources, the noises of GPS attitude measurement bring out the steady tracking error of the tracking servo mechanism. To reduce the steady error due to the noise, the threshold noise removing method of wavelet is used to eliminate the noise. And the better result with the meaning of standard deviation and the better visual effects could be gotten by using the method. The signals of the processed high frequency and the retained low frequency could be reconstructed with the original signals. Therefore, the signals after noise removing could be obtained. The threshold noise removing method of wavelet used to remove the noise of GPS attitude information in the paper is of great value in practice.

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