Parameter optimization of a single-FOV-double-region celestial 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.

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Multiple model adaptive estimation for the celestial navigation system

2015 34th Chinese Control Conference (CCC) ◽

10.1109/chicc.2015.7260467 ◽

2015 ◽

Cited By ~ 1

Author(s):

Hui Peng ◽

Fangfang Zhao ◽

Shuangfei Fan ◽

Zhongliang Tang ◽

Wei He

Keyword(s):

Navigation System ◽

Adaptive Estimation ◽

Multiple Model ◽

Celestial Navigation ◽

Multiple Model Adaptive Estimation

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

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410016636153 ◽

2016 ◽

Vol 231 (2) ◽

pp. 218-228 ◽

Cited By ~ 5

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.

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

Journal of Navigation ◽

10.1017/s0373463318000346 ◽

2018 ◽

Vol 71 (6) ◽

pp. 1567-1588 ◽

Cited By ~ 1

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.

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Error Correction of Infrared Earth Radiance for Autonomous Navigation

Journal of Navigation ◽

10.1017/s0373463316000424 ◽

2016 ◽

Vol 69 (6) ◽

pp. 1427-1437 ◽

Cited By ~ 2

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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Based on Grid Reference Frame for SINS/CNS Integrated Navigation System in the Polar Regions

Complexity ◽

10.1155/2019/2164053 ◽

2019 ◽

Vol 2019 ◽

pp. 1-8 ◽

Cited By ~ 1

Author(s):

Song Lijun ◽

Zhao Wanliang ◽

Cheng Yuxiang ◽

Chen Xiaozhen

Keyword(s):

Reference Frame ◽

Navigation System ◽

Inertial Navigation System ◽

Inertial Navigation ◽

Polar Regions ◽

Integrated Navigation ◽

Integrated Navigation System ◽

Celestial Navigation ◽

Low Latitudes ◽

And Performance

As the inertial navigation system cannot meet the precision requirements of global navigation in the special geographical environment of the Polar Regions, this paper presents Strapdown Inertial Navigation System (SINS)/Celestial Navigation System (CNS) integrated navigation system of airborne based on Grid Reference Frame (GRF) and the simulation is carried out. The result of simulation shows that the SINS/CNS integrated navigation system is superior to the single subsystem in precision and performance, which not only effectively inhibits the error caused by gyro drift but also corrects the navigation parameters of system without delay. Comparing the simulation in the middle and low latitudes and in the Polar Regions, the precision of SINS/CNS integrated navigation system is the same in the middle and low latitudes and in the Polar Regions.

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Altitude estimation for a celestial navigation system based on infrared Earth measurement

Acta Astronautica ◽

10.1016/j.actaastro.2019.03.054 ◽

2019 ◽

Vol 159 ◽

pp. 105-111

Author(s):

Bin Gou ◽

Yong-mei Cheng ◽

Anton H.J. de Ruiter

Keyword(s):

Navigation System ◽

Celestial Navigation ◽

Altitude Estimation

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SINS/Landmark Integrated Navigation Based on Landmark Attitude Determination

Sensors ◽

10.3390/s19132917 ◽

2019 ◽

Vol 19 (13) ◽

pp. 2917

Author(s):

Shuqing Xu ◽

Haiyin Zhou ◽

Jiongqi Wang ◽

Zhangming He ◽

Dayi Wang

Keyword(s):

Navigation System ◽

Inertial Navigation System ◽

Attitude Determination ◽

Feature Matching ◽

Integrated Navigation ◽

Basic Scheme ◽

Integrated Navigation System ◽

Celestial Navigation ◽

Landmark Navigation ◽

Navigation Method

Based on the situation that the traditional SINS (strapdown inertial navigation system)/CNS (celestial navigation system) integrated navigation system fails to realize all-day and all-weather navigation, this paper proposes a SINS/Landmark integrated navigation method based on landmark attitude determination to solve this problem. This integrated navigation system takes SINS as the basic scheme and uses landmark navigation to correct the error of SINS. The way of the attitude determination is to use the landmark information photographed by the landmark camera to complete feature matching. The principle of the landmark navigation and the process of attitude determination are discussed, and the feasibility of landmark attitude determination is analyzed, including the orthogonality of the attitude transform matrix, as well as the influences of the factors such as quantity and geometric position of landmarks. On this basis, the paper constructs the equations of the SINS/Landmark integrated navigation system, testifies the effectiveness of landmark attitude determination on the integrated navigation by Kalman filter, and improves the navigation precision of the system.

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