The Effect of Equatorial Spread F on Relative Orbit Determination of GRACE Using Differenced GPS Observations

AbstractThe problem of binary asteroids orbit determination is of particular interest, given knowledge of the orbit is the best way to derive the mass of the system. Orbit determination from observed points is a classic problem of celestial mechanics. However, in the case of binary asteroids, particularly with a small number of observations, the solution is not evident to derive. In the case of resolved binaries the problem consists in the determination of the relative orbit from observed relative positions of a secondary asteroid with respect to the primary. In this work, the problem is investigated as a statistical inverse problem. Within this context, we propose a method based on Bayesian modelling together with a global optimisation procedure that is based on the simulated annealing algorithm.

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Integrating BDS and GPS for precise relative orbit determination of LEO formation flying

Chinese Journal of Aeronautics ◽

10.1016/j.cja.2018.06.001 ◽

2018 ◽

Vol 31 (10) ◽

pp. 2013-2022 ◽

Cited By ~ 1

Author(s):

Bin YI ◽

Defeng GU ◽

Xiao CHANG ◽

Kai SHAO

Keyword(s):

Orbit Determination ◽

Formation Flying ◽

Relative Orbit

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Precise Orbit Determination of BDS MEO Satellites Based on Satellite TT&C Stations

International Journal of Aerospace Engineering ◽

10.1155/2016/7856353 ◽

2016 ◽

Vol 2016 ◽

pp. 1-13

Author(s):

Kezhao Li ◽

Zhiwei Li ◽

Lin Chai ◽

An-min Ding ◽

Jin-ben Wei ◽

...

Keyword(s):

Orbit Determination ◽

Precise Orbit Determination ◽

Satellite System ◽

Calculation Model ◽

Geostationary Orbit ◽

Precise Orbit ◽

Triple Frequency ◽

Relative Orbit ◽

Sufficient And Necessary Conditions

A novel method, which is based on the triple-frequency combination and Space-Based Telemetry, Tracking, and Command (STT&C) stations, is proposed in this paper. Considering BeiDou Navigation Satellite System (BDS) Geostationary Orbit (GEO) and Inclined Geostationary Orbit (IGSO) satellites as the STT&C facilities, firstly, we presented the BDS Medium Earth Orbit (MEO) satellites’ precise orbit determination scheme based on triple-frequency combination. Then, we gave the sufficient and necessary conditions about the visibility and the coverage rate calculation model of STT&C to BDS MEO satellite. And then we deduced the model of BDS MEO satellites precise orbit determination based on triple-frequency combination observations. At last, we designed the simulation calculation. The simulation results show that orbit determination of BDS MEO satellite based on STT&C station can be realized at all times. And most of the simulation period time, under the condition of the dm level orbit determination for GEO/IGSO satellites, the position accuracy of the relative orbit determination is better than 4 m, the horizontal accuracy of the relative orbit determination is within 2.5 m, and the vertical accuracy of the relative orbit determination is less than 3.5 m.

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Precise Orbit Determination of Cubesats Using Duty Cycled GPS Observations

10.33915/etd.6035 ◽

2018 ◽

Author(s):

Sean Lantto

Keyword(s):

Orbit Determination ◽

Precise Orbit Determination ◽

Precise Orbit ◽

Gps Observations

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GPS Based Reduced-Dynamic Orbit Determination for Low Earth Orbiters with Ambiguity Fixing

International Journal of Aerospace Engineering ◽

10.1155/2015/723414 ◽

2015 ◽

Vol 2015 ◽

pp. 1-11 ◽

Cited By ~ 3

Author(s):

Yang Yang ◽

Xiaokui Yue ◽

Jianping Yuan

Keyword(s):

Orbit Determination ◽

Precise Determination ◽

Low Earth Orbit ◽

Carrier Phase Ambiguity ◽

Performance Results ◽

Gravity Recovery ◽

Leo Satellite ◽

Gps Observations ◽

Reduced Dynamic

With the ever-increasing number of satellites in Low Earth Orbit (LEO) for scientific missions, the precise determination of the position and velocity of the satellite is a necessity. GPS (Global Positioning System) based reduced-dynamic orbit determination (RPOD) method is commonly used in the post processing with high precision. This paper presents a sequential RPOD strategy for LEO satellite in the framework of Extended Kalman Filter (EKF). Precise Point Positioning (PPP) technique is used to process the GPS observations, with carrier phase ambiguity resolution using Integer Phase Clocks (IPCs) products. A set of GRACE (Gravity Recovery And Climate Experiment) mission data is used to test and validate the RPOD performance. Results indicate that orbit determination accuracy could be improved by 15% in terms of 3D RMS error in comparison with traditional RPOD method with float ambiguity solutions.

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