A Correction Algorithm of Aberration of Light for Spacecraft Attitude Determination System

2012 ◽  
Vol 166-169 ◽  
pp. 3197-3201
Author(s):  
Bao Hua Li ◽  
Xi Jun Chen ◽  
Yang Pang ◽  
Bo Qi Xi
Keyword(s):  
Mathematical Models ◽  
Coordinate System ◽  
Attitude Determination ◽  
Spacecraft Attitude ◽  
Star Sensor ◽  
Correction Algorithm ◽  
Attitude Error ◽  
Determination System ◽  
Space Coordinate ◽  
Celestial Sphere

There is the long periodicity attitude error between true attitude and measurement attitude using star sensor for spacecraft attitude determination system because of aberration of light. Aberration of light occurs because the spacecraft’s velocity has a component that is perpendicular to the line traveled by the light incoming from the star. The type of aberration is analyzed and their constants of aberration are calculated in this paper. According to the constants the aberration, the correction mathematical models of parallax of aberration of light of these types of aberration are derived. The parallax of aberration of light of the recognized stars in the FOV of star sensor is calculated with the mathematical models. Then the true vectors of recognized stars at image space coordinate system of star sensor are calculated. The measurement attitude of star sensor is calculated with the true vectors of recognized stars and their vectors at celestial sphere coordinate system. The simulations show the long periodicity attitude error is corrected with the method in this paper. At last the correction of aberration of light was successfully demonstrated using two star sensors with real sky experiment in 2011.

ANALYSIS ON ATTITUDE POSITION OF EARTH CENTERED INERTIAL (ECI) BASED ON RAZAKSAT DATA

2015 ◽  
Vol 76 (12) ◽  
Author(s):  
Mohd Zamri Hasan ◽  
Sazali Yaacob ◽  
Amran Ahmed ◽  
Nor Hazadura Hamzah ◽  
Shamshul Bahar Yaakob ◽  
...  
Keyword(s):  
Coordinate System ◽  
Reference Frame ◽  
Earth Rotation ◽  
Attitude Determination ◽  
Three Dimensional ◽  
Measurement Data ◽  
Inertial Reference Frame ◽  
Determination System ◽  
Line Elements

Attitude determination system (ADS) is a process to control the orientation of satellite to make sure that the orientation of satellite is relative to inertial reference frame such as Earth. Earth Centered Inertial (ECI) is one of reference frame for satellite that determines the attitude in three dimensional spacecraft. Since RazakSAT orbits on earth, ECI coordinate system will be used for satellite relative to earth rotation. This paper is about the analysis on attitude position of ECI and velocity at X, Y and Z axis based on RazakSAT data. Satellite Tools Kit (STK) is used to estimate the attitude and velocity based on Two Line Elements (TLE) of RazakSAT. The result is compared with RazakSAT measurement data to observe the accuracy of estimation by using STK.

Gyroscope fault accommodation based on dedicated Kalman filters

2019 ◽  
Vol 234 (2) ◽  
pp. 254-266 ◽  
Author(s):  
Liliang Li ◽  
Chuan Liu ◽  
Yanzhao Zhang ◽  
Zhenhua Wang ◽  
Yi Shen
Keyword(s):  
Kalman Filter ◽  
Numerical Simulations ◽  
Kalman Filters ◽  
Attitude Determination ◽  
Selection Strategy ◽  
Star Sensor ◽  
Fault Accommodation ◽  
Determination System

To improve the reliability of the attitude determination system with redundant gyroscopes, this article proposes a gyroscope fault accommodation method using a bank of dedicated Kalman filters. The redundant gyroscopes are divided into several groups and then a dedicated Kalman filter is designed for each group of gyroscopes. The residuals generated by the dedicated Kalman filters indicate the consistency levels between the measurements of the star sensor and the gyroscopes. Based on the estimation results provided by the Kalman filters, a fault accommodation method using online selection strategy is proposed to attenuate the effect of the fault. Numerical simulations are used to demonstrate the effectiveness of the proposed method.

Multiple-model adaptive estimator for spacecraft attitude sensor calibration

2017 ◽  
Vol 89 (3) ◽  
pp. 457-467 ◽  
Author(s):  
Kai Xiong ◽  
Chunling Wei
Keyword(s):  
Kalman Filter ◽  
Convergence Rate ◽  
Attitude Determination ◽  
Spacecraft Attitude ◽  
Star Sensor ◽  
Multiple Model ◽  
Content Type ◽  
Adaptive Estimator ◽  
Calibration Algorithm ◽  
Novel Method

Purpose This paper aims to present a multiple-model adaptive estimator (MMAE) to calibrate the star sensor low frequency error (LFE). The star sensor LFE, which is caused primarily by the periodic thermal distortion, has a great impact on spacecraft attitude determination accuracy. Design/methodology/approach The unfavorable effect of the LFE can be partly eliminated by using the calibration algorithm based on the augmented Kalman filter (AKF). However, the AKF may be worse than the traditional Kalman filter (KF) in the absence of the LFE. To cope with this problem, the MMAE is applied first time for combining the AKF and the KF in the spacecraft attitude determination system, such that satisfactory performance can be achieved in different operating scenarios. Findings The convergence of the presented MMAE is demonstrated through a formal derivation. A novel method is proposed to tune the MMAE design parameter, such that the convergence rate of the estimator is increased. It is shown via numerical studies that the presented algorithm outperforms the AKF and the KF. Practical implications The calibration algorithm is applicable for spacecraft attitude determination. Originality/value An effective star sensor LFE calibration algorithm based on the MMAE is developed. In addition, a novel method is proposed to increase convergence rate of the estimator.

Robust H ∞ filtering for a spacecraft attitude determination system with affine LPV approach

2016 ◽  
Vol 55 ◽  
pp. 158-169 ◽  
Author(s):  
Shujie Yang ◽  
Gongliu Yang ◽  
Yuhuan Li ◽  
Jing Li ◽  
Jing Wang
Keyword(s):  
Attitude Determination ◽  
Spacecraft Attitude ◽  
Determination System
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