A Novel Differential Doppler Measurement-Aided Autonomous Celestial Navigation Method for Spacecraft During Approach Phase

2017 ◽  
Vol 53 (2) ◽  
pp. 587-597 ◽  
Author(s):  
Xiaolin Ning ◽  
Mingzhen Gui ◽  
Jiancheng Fang ◽  
Yu Dai ◽  
Gang Liu
Keyword(s):  
Doppler Measurement ◽  
Differential Doppler ◽  
Celestial Navigation ◽  
Navigation Method ◽  
Approach Phase

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.

X-ray Pulsar/Starlight Doppler Deeply-integrated Navigation Method

2017 ◽  
Vol 70 (4) ◽  
pp. 829-846 ◽  
Author(s):  
Yidi Wang ◽  
Wei Zheng ◽  
Dapeng Zhang
Keyword(s):  
Estimation Method ◽  
Propagation Model ◽  
Phase Estimation ◽  
Integrated Navigation ◽  
Computationally Efficient ◽  
Doppler Measurement ◽  
X Ray ◽  
Pulse Phase ◽  
The Cost ◽  
Navigation Method

An X-ray pulsar/starlight Doppler deeply-integrated navigation method is proposed in this paper. A starlight Doppler measurement-aided phase propagation model, which can remove the orbital effect within the recorded photon Time Of Arrivals (TOAs), is derived, and guarantees that the pulse phase can be extracted from the converted photon TOAs using computationally efficient methods. Some simulations are performed by a hardware-in-loop system to verify the performance of the integrated pulse phase estimation method as well as of the integrated navigation method. The integrated pulse phase estimation method could achieve an estimation performance similar to the existing method for orbiting vehicles at the cost of much less computational complexity, is capable of handling the signals of millisecond pulsars, and is applicable to various vehicles. In addition, the proposed integrated navigation method could provide reliable positioning results for various vehicles.

Solar oscillation time delay measurement assisted celestial navigation method

2017 ◽  
Vol 134 ◽  
pp. 152-158 ◽  
Author(s):  
Xiaolin Ning ◽  
Mingzhen Gui ◽  
Jie Zhang ◽  
Jiancheng Fang ◽  
Gang Liu
Keyword(s):  
Time Delay ◽  
Solar Oscillation ◽  
Celestial Navigation ◽  
Delay Measurement ◽  
Navigation Method ◽  
Time Delay Measurement

scholarly journals SINS/Landmark Integrated Navigation Based on Landmark Attitude Determination

Sensors ◽  
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.

Recursive adaptive filter using current innovation for celestial navigation during the Mars approach phase

2017 ◽  
Vol 60 (3) ◽  
Author(s):  
Xiaolin Ning ◽  
Zhuo Li ◽  
Weiren Wu ◽  
Yuqing Yang ◽  
Jiancheng Fang ◽  
...  
Keyword(s):  
Adaptive Filter ◽  
Celestial Navigation ◽  
Approach Phase

XNAV/CNS Integrated Navigation Based on Improved Kinematic and Static Filter

2013 ◽  
Vol 66 (6) ◽  
pp. 899-918 ◽  
Author(s):  
Yidi Wang ◽  
Wei Zheng ◽  
Xueyin An ◽  
Shouming Sun ◽  
Li Li
Keyword(s):  
Navigation System ◽  
Optimal Estimation ◽  
Systematic Errors ◽  
Integrated Navigation ◽  
Unscented Transformation ◽  
X Ray ◽  
Celestial Navigation ◽  
Improved Performance ◽  
High Orbit ◽  
Navigation Method

In order to enhance the independent viability of high-orbit satellites, an X-ray pulsar-based navigation (XNAV)/celestial navigation system (CNS) integrated navigation method is proposed. An improved kinematic and static filter is derived to fulfil data fusion that can obtain an optimal estimation for global use. In the filter, unscented transformation is used to reduce linearization error, and the technique of separate-bias is used to reduce the impacts of systematic errors in XNAV measurements. The results of simulations have shown that the proposed navigation system can reach a positioning accuracy of less than 100 m, an improved performance over separate XNAV and CNS.

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