Ephemeris Error Correction in Celestial Navigation System Considering Earth’s Precession-Nutation

Optik ◽  
2020 ◽  
pp. 166152
Author(s):  
Bin Gou ◽  
Ke-yu Qi ◽  
Yong-mei Cheng ◽  
Yuan-yuan Xu ◽  
Zhen Sun
Keyword(s):  
Error Correction ◽  
Navigation System ◽  
Celestial Navigation

Structured condition number and its application in celestial navigation system with variable observability degree

2018 ◽  
Vol 12 (2) ◽  
pp. 182-192 ◽  
Author(s):  
Jin Liu ◽  
Xiao-Lin Ning ◽  
Xin Ma ◽  
Ming-Zhen Gui ◽  
Jian-Cheng Fang ◽  
...  
Keyword(s):  
Condition Number ◽  
Navigation System ◽  
Celestial Navigation

scholarly journals Analysis of Ephemeris Errors in Autonomous Celestial Navigation during Mars Approach Phase

2016 ◽  
Vol 70 (3) ◽  
pp. 505-526 ◽  
Author(s):  
Xiaolin Ning ◽  
Zhuo Li ◽  
Yuqing Yang ◽  
Jiancheng Fang ◽  
Gang Liu
Keyword(s):  
Navigation System ◽  
Autonomous Navigation ◽  
Great Influence ◽  
Position Error ◽  
The Sun ◽  
Deep Space ◽  
Velocity Error ◽  
Celestial Navigation ◽  
Approach Phase ◽  
Autonomous Navigation System

A Celestial Navigation System (CNS) is a feasible and economical autonomous navigation system for deep-space probes. Ephemeris errors have a great influence on the performance of CNSs during the Mars approach phase, but there are few research studies on this problem. In this paper, the analysis shows that the ephemeris error of Mars is slowly-varying, while the ephemeris error of Phobos and Deimos is periodical. The influence of the ephemeris errors of Mars and its satellites is analysed in relation to both the Sun-centred frame and the Mars-centred frame. The simulations show that the position error of a probe relative to the Sun caused by the Mars ephemeris error is almost equal to the ephemeris error itself, that the velocity error is affected slightly, and that the position and velocity relative to Mars are hardly affected. The navigation result of a Mars probe is also greatly affected by the quantities and periodicities of the ephemeris errors of Phobos and Deimos, especially that of Deimos.

scholarly journals Parameter optimization of a single-FOV-double-region celestial navigation system

2020 ◽  
Vol 28 (17) ◽  
pp. 25149
Author(s):  
Jie Jiang ◽  
Yan Ma ◽  
Guangjun Zhang
Keyword(s):  
Parameter Optimization ◽  
Navigation System ◽  
Celestial Navigation

Research on angles-only/SINS/CNS relative position and attitude determination algorithm for a tumbling spacecraft

2016 ◽  
Vol 231 (2) ◽  
pp. 218-228 ◽  
Author(s):  
Lijun Zhang ◽  
Shan Qian ◽  
Shifeng Zhang ◽  
Hong Cai
Keyword(s):  
Relative Position ◽  
Navigation System ◽  
Attitude Determination ◽  
A Priori ◽  
Celestial Navigation ◽  
Inertia Parameter ◽  
Rate Information ◽  
Final Approach ◽  
Tumbling Target ◽  
Target Spacecraft

In this paper, the relative navigation technique of final approach phase for a tumbling target spacecraft is studied and exploited. It is assumed that the tumbling target is in failure or out of control and there is no good a priori rotation rate information. The Euler’s rotational dynamics is used to propagate the target angular velocity, and the unknown inertia parameter circumstance is also considered. The chaser spacecraft is equipped with three strapdown gyros and accelerometers and a star sensor that determine the absolute motion parameters, and an optical camera that measures relative azimuth and elevation angles to the target spacecraft. On the basis of the rotational and translational motions of both spacecrafts, an angles-only/ strapdown inertial navigation system/celestial navigation system navigation filter is designed. Simulation results indicate that the proposed algorithm can accurately estimate the relative position, velocity, and attitude between two spacecrafts and compensate the biases of the gyros and accelerometers.

A High-accuracy SINS/CNS Integrated Navigation Scheme Based on Overall Optimal Correction

2018 ◽  
Vol 71 (6) ◽  
pp. 1567-1588 ◽  
Author(s):  
Jiafang Zhu ◽  
Xinlong Wang ◽  
Hengnian Li ◽  
Huan Che ◽  
Qunsheng Li
Keyword(s):  
Long Range ◽  
Navigation System ◽  
Integration Scheme ◽  
Integrated Navigation ◽  
Position Information ◽  
Optimal Correction ◽  
Integrated Navigation System ◽  
Celestial Navigation ◽  
Geometric Relationship ◽  
Navigation Scheme

In order to utilise the position and attitude information of a Celestial Navigation System (CNS) to aid a Strapdown Inertial Navigation System (SINS) and make it possible to achieve long-range and high-precision navigation, a new SINS/CNS integrated navigation scheme based on overall optimal correction is proposed. Firstly, the optimal installation angle of the star sensor is acquired according to the geometric relationship between the refraction stars area and the star sensor's visual field. Secondly, an analytical method to determine position and horizontal reference is introduced. Thirdly, the mathematical model of the SINS/CNS integrated navigation system is established. Finally, some simulations are carried out to compare the navigation performance of the proposed SINS/CNS integrated scheme with that of the traditional gyro-drift-corrected integration scheme. Simulation results indicate that in the proposed scheme, without the aid of SINS, CNS can provide attitude and position information and the errors of the SINS are able to be estimated and corrected efficiently. Therefore, the navigation performance of the proposed SINS/CNS scheme is superior to that of a more traditional scheme in long-range flight.

Picking Robot Camera Calibration System Based on OpenCV

2012 ◽  
Vol 430-432 ◽  
pp. 1963-1966 ◽  
Author(s):  
Hong Xing Peng ◽  
Xiang Jun Zou ◽  
Jun Tao Xiong ◽  
Ding Zhong Wu ◽  
Jia Hui Shen ◽  
...  
Keyword(s):  
Error Correction ◽  
Camera Calibration ◽  
High Precision ◽  
Navigation System ◽  
Geometric Model ◽  
Robot Vision ◽  
Calibration System ◽  
Vision Navigation ◽  
Equation Solution ◽  
Radial Distortion

Aim at the effect of the radial distortion and tangential distortion, the camera calibration principle, geometric model and complex equation solution were studied, in order to reduce the artificial participation in proofreading and error correction, then the camera’s software precise calibration module based on OpenCV was developed. The results showed that the system was quickly speed, high precision and could satisfy the requirements of robot vision navigation system and built the foundation for the next step research.

Error Correction of Infrared Earth Radiance for Autonomous Navigation

2016 ◽  
Vol 69 (6) ◽  
pp. 1427-1437 ◽  
Author(s):  
Jianqing Li ◽  
Changsheng Gao ◽  
Tianming Feng ◽  
Wuxing Jing
Keyword(s):  
Adverse Effect ◽  
Navigation System ◽  
Autonomous Navigation ◽  
Least Square ◽  
Infrared Radiance ◽  
The Earth ◽  
Celestial Navigation ◽  
Correction Scheme ◽  
The Relationship ◽  
Navigation Information

A strapdown inertial navigation system and celestial navigation system integrated autonomous navigation scheme is proposed in this paper, using the navigation information obtained from Earth sensors and star sensors. To eliminate the adverse effect caused by the asymmetry of Earth infrared radiance, the relationship between Earth infrared radiance brightness and effective horizon height is found. According to the relationship as well as the measuring principle of the Earth sensor, this paper derives a function to correct the measurement of the Earth sensor. Then, the angle-distance of stars can be calculated, and using this information, we can estimate the navigation information of a ballistic missile by least square estimation. The simulation results show that the error of Earth infrared radiance has a great effect on the navigation precision, and by using the correction scheme, this adverse effect can be greatly mitigated. This correction scheme is available and effective.

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