Satellite orbit decay due to atmospheric drag

Satellite moving under the gravitational field of Earth deviates from its two-body elliptic orbit, due to the combined effects of the gravitational field of Earth, atmospheric drag, solar radiation pressure, third-body gravitational effects, etc. This paper utilizes the KS regular element equations to solve Newtonian equations of motion to obtain numerical solution with respect to perturbing forces, like, Earth's gravity (includes zonal, sectorial and tesseral harmonics terms), atmospheric drag and solar radiation pressure. Effectiveness of the theory is illustrated by comparing the results with some of the existing theories in literature.

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On Satellite Orbit Decay Compensation in Low Earth Orbits

2018 Space Flight Mechanics Meeting ◽

10.2514/6.2018-2226 ◽

2018 ◽

Cited By ~ 2

Author(s):

Ehsan Taheri ◽

Robert A. Zidek ◽

Ilya Kolmanovsky ◽

Anouck Girard

Keyword(s):

Satellite Orbit ◽

Orbit Decay ◽

Low Earth Orbits ◽

Earth Orbits

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Satellite orbit under influence of a drag - analytical approach

Serbian Astronomical Journal ◽

10.2298/saj1795053m ◽

2017 ◽

pp. 53-58 ◽

Cited By ~ 1

Author(s):

M.M. Martinovic ◽

S.D. Segan

Keyword(s):

Computer Algebra ◽

Computer Algebra System ◽

Analytical Approach ◽

Satellite Orbit ◽

Numerical Approach ◽

Artificial Satellites ◽

Atmospheric Drag ◽

Orbital Elements ◽

Air Density ◽

Good Agreement

The report studies some changes in orbital elements of the artificial satellites of Earth under influence of atmospheric drag. In order to develop possibilities of applying the results in many future cases, an analytical interpretation of the orbital element perturbations is given via useful, but very long expressions. The development is based on the TD88 air density model, recently upgraded with some additional terms. Some expressions and formulae were developed by the computer algebra system Mathematica and tested in some hypothetical cases. The results have good agreement with iterative (numerical) approach.

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Analytical Solution of a Super Low Satellite Orbit Disturbed by Atmospheric Drag Considering J2 Perturbation

2013 5th International Conference on Intelligent Human-Machine Systems and Cybernetics ◽

10.1109/ihmsc.2013.224 ◽

2013 ◽

Author(s):

Teng Yi ◽

Ye Yan ◽

Shenglin Wen ◽

Yang Zhou

Keyword(s):

Analytical Solution ◽

Satellite Orbit ◽

Atmospheric Drag ◽

J2 Perturbation

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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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