Initial orbit determination of BDS-3 satellites based on new code signals

AbstractWe consider initial determination of asteroid orbits in the case of small numbers of observations and short observational arcs. For asteroids having long arcs, we can assess the orbital uncertainties with the help of the covariance matrix that, in the phase space of the orbital elements, defines a set of probability ellipsoids. In initial orbit determination, because of the nonlinear characteristics and multiple solutions of the inversion problem, we cannot readily use the covariance matrix to estimate the orbital uncertainties. However, by computing the eigenvalues and eigenvectors of the formal correlation matrix (that is, by deriving the eigenorbits), we can discern the most indeterminate orbital elements. Here we solve the eigenproblem for 17 single-apparition asteroids.

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Estimation of Distribution Algorithm for Initial Orbit Determination of Too-short-arc Based on Kernel Density Estimation

Chinese Astronomy and Astrophysics ◽

10.1016/j.chinastron.2018.01.009 ◽

2018 ◽

Vol 42 (1) ◽

pp. 141-154

Author(s):

Wang Xin ◽

Li Xin-ran

Keyword(s):

Density Estimation ◽

Kernel Density Estimation ◽

Orbit Determination ◽

Kernel Density ◽

Estimation Of Distribution Algorithm ◽

Initial Orbit Determination ◽

Estimation Of Distribution ◽

Short Arc ◽

Initial Orbit

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Machine Learning Approach to Initial Orbit Determination of Unknown LEO Satellites

15th International Conference on Space Operations ◽

10.2514/6.2018-2566 ◽

2018 ◽

Cited By ~ 2

Author(s):

Byoung-sun Lee ◽

Won-Gil Kim ◽

Junho Lee ◽

Yoola Hwang

Keyword(s):

Machine Learning ◽

Orbit Determination ◽

Learning Approach ◽

Initial Orbit Determination ◽

Machine Learning Approach ◽

Leo Satellites ◽

Initial Orbit

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Initial Orbit Determination Using Single Frequency GPS Measurements of Launch Vehicle

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.599-601.964 ◽

2014 ◽

Vol 599-601 ◽

pp. 964-969

Author(s):

Guo Hu Xue ◽

Jun Shan Mu ◽

Hui Fen Li ◽

Li Wei Zhu ◽

Yang Liu

Keyword(s):

Orbit Determination ◽

Launch Vehicle ◽

Single Frequency ◽

Gps Measurements ◽

Precise Ephemeris ◽

Initial Orbit Determination ◽

Orbit Segment ◽

Radar Measurements ◽

Initial Orbit

Orbit determination by using GPS measurements of a launch vehicle is an important option for the initial orbit determination of the vehicle's payload, and its accuracy is higher than the results generated by radar measurements. However, only broadcast GPS ephemeris and clock products are used in the current GPS measurements processing method, and Klobuchar model is directly used. The paper proposes to use precise ephemeris and clock products, and adopts an improved ionospheric model based on altitude factor for GPS measurements processing. The dynamic smoothing method is further used. The numerical results show that the proposed method can improve the early orbit satellites orbit segment to determine accuracy.

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