Filter techniques in planet satellite orbit parameter estimation.

D. HARDER; J. E. CONNOR

doi:10.2514/3.4160

STUDY OF FILTER TECHNIQUE IN DISTANT PLANET SATELLITE ORBIT PARAMETER ESTIMATION

10.2514/6.1966-1848 ◽

1966 ◽

Author(s):

D. HARDER ◽

J. CONNOR

Keyword(s):

Parameter Estimation ◽

Satellite Orbit ◽

Filter Technique ◽

Orbit Parameter ◽

Planet Satellite

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A More Reliable Orbit Initialization Method for LEO Precise Orbit Determination Using GNSS

Remote Sensing ◽

10.3390/rs12213646 ◽

2020 ◽

Vol 12 (21) ◽

pp. 3646

Author(s):

Xuewen Gong ◽

Jizhang Sang ◽

Fuhong Wang ◽

Xingxing Li

Keyword(s):

Parameter Estimation ◽

Orbit Determination ◽

High Reliability ◽

Precise Orbit Determination ◽

Direct Approach ◽

Design Matrix ◽

Reference Orbit ◽

Stability Analyses ◽

Precise Orbit ◽

Orbit Parameter

Precise orbit determination (POD) using GNSS has been rapidly developed and is the mainstream technology for the navigation of low Earth orbit (LEO) satellites. The initialization of orbit parameters is a key prerequisite for LEO POD processing. For a LEO satellite equipped with a GNSS receiver, sufficient discrete kinematic positions can be obtained easily by processing space-borne GNSS data, and its orbit parameters can thus be estimated directly in iterative manner. This method of direct iterative estimation is called as the direct approach, which is generally considered highly reliable, but in practical applications it has risk of failure. Stability analyses demonstrate that the direct approach is sensitive to oversized errors in the starting velocity vector at the reference time, which may lead to large errors in design matrix because the reference orbit may be significantly distorted, and eventually cause the divergence of the orbit parameter estimation. In view of this, a more reliable method, termed the progressive approach, is presented in this paper. Instead of estimating the orbit parameters directly, it first fits the discrete kinematic positions to a reference ephemeris in the form of the GNSS broadcast ephemeris, which construct a reference orbit that is smooth and close to the true orbit. Based on the reference orbit, the starting orbit parameters are computed in sufficient accuracy, and then the final orbit parameters are estimated with a high accuracy by using discrete kinematic positions as measurements. The stability analyses show that the design matrix errors are reduced in the progressive approach, which would assure more robust orbit parameter estimation than the direct estimation approach. Various orbit initialization experiments are performed on the KOMPSAT-5 and FY3C satellites. The results have fully verified the high reliability of the proposed progressive approach.

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Artificial satellite orbit computations

Symposium - International Astronomical Union ◽

10.1017/s0074180900105662 ◽

1966 ◽

Vol 25 ◽

pp. 363-371

Author(s):

P. Sconzo

Keyword(s):

Artificial Satellite ◽

Satellite Orbit ◽

Artificial Satellites ◽

Orbital Elements ◽

Differential Correction ◽

Gravitational Effects ◽

Short Intervals ◽

The Subject ◽

Introductory Discussion ◽

Orbit Computation

In this paper an orbit computation program for artificial satellites is presented. This program is operational and it has already been used to compute the orbits of several satellites.After an introductory discussion on the subject of artificial satellite orbit computations, the features of this program are thoroughly explained. In order to achieve the representation of the orbital elements over short intervals of time a drag-free perturbation theory coupled with a differential correction procedure is used, while the long range behavior is obtained empirically. The empirical treatment of the non-gravitational effects upon the satellite motion seems to be very satisfactory. Numerical analysis procedures supporting this treatment and experience gained in using our program are also objects of discussion.

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