Effects Of Direct And Indirect Solar Radiation Pressure In Orbital Parameters Of GPS Satelittes

AbstractIn this paper we determined the variation of the Keplerian orbital elements of a GPS satellite due to the direct and indirect action of solar radiation pressure. For this study, we created a soft program to determine the Keplerian elements. This soft uses the initial conditions of position and speed of a GPS satellite and solves the Laplace integration problem using Runge - Kutta algorithm of 4th order.

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A discussion on orbital analysis - Some problems of orbital prediction

Philosophical Transactions of the Royal Society of London. Series A, Mathematical and Physical Sciences ◽

10.1098/rsta.1967.0035 ◽

1967 ◽

Vol 262 (1124) ◽

pp. 100-105

Keyword(s):

Solar Radiation ◽

Radiation Pressure ◽

Solar Radiation Pressure ◽

Atmospheric Model ◽

Orbital Elements ◽

Air Drag ◽

Gravitational Perturbations ◽

Pass Through ◽

Orbital Analysis ◽

Made In

Attention is paid to the problem of predicting accurately (a) the orbital elements of a balloon satellite over long periods of time, and (b) the time the satellite will pass through a given point in the orbit, a few days or weeks in advance of the event. It is shown that by computing the solar radiation pressure and gravitational perturbations of the orbit of the balloon satellite Echo 2, the orbital elements can be predicted reasonably accurately several months in advance. For the balloon satellite Explorer 19, allowing for air drag at perigee, computed from a simple atmospheric model in addition to the effect of solar radiation pressure, results in significant improvement in predicting the period of revolution a few months in advance. Finally, by numerically integrating the air-drag effect round the orbit, it is shown that a considerable improvement can be made in the accuracy of predicting the time at which a satellite will pass through a given point on the orbit.

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Design of Artificial Sun-Synchronous Orbits with Main Zonal Harmonics and Solar Radiation Pressure Using Continuous Low-Thrust Control Strategies

Open Astronomy ◽

10.1515/astro-2019-0012 ◽

2019 ◽

Vol 28 (1) ◽

pp. 124-130

Author(s):

Akram Masoud ◽

Walid Ali Rahoma ◽

Elamira Hend Khattab ◽

Fawzy Ahmed Abd El-Salam

Keyword(s):

Solar Radiation ◽

Radiation Pressure ◽

Control Strategies ◽

Solar Radiation Pressure ◽

Continuous Variable ◽

Low Thrust ◽

Surface Mapping ◽

Orbital Parameters ◽

Zonal Harmonics ◽

Thrust Control

AbstractArtificial sun-synchronous orbits are suitable for remote sensing satellites and useful in giving accurate surface mapping. To design such orbits accurately with arbitrary orbital elements, three control strategies are provided with the consideration of main zonal harmonics up to J4 and solar radiation pressure (SRP). In this paper, the continuous variable low-thrust control is used as a way to achieve these artificial orbits and given by electric propulsions rather than chemical engines to enlarge lifespan of the spacecraft. The normal continuous low-thrust control is used to illustrate the control strategies. Furthermore, formulas for refinement of normal control thrusts are applied to overcome errors due to approximations. The results of the simulation show that the control strategies explained in this paper can realize sun-synchronous orbits with arbitrary orbital parameters without side effects and the effect of solar radiation pressure is very small relative to main zonal harmonics. A new technique is suggested, ASSOT-3, to minimize fuel consumption within one orbital period more than others. This technique is based on computing the root mean square of the rate of ascending node longitude instead of the average.

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Controlling the Perturbations of Solar Radiation Pressure on the Lorentz Spacecraft

Symmetry ◽

10.3390/sym12091423 ◽

2020 ◽

Vol 12 (9) ◽

pp. 1423

Author(s):

A. Mostafa ◽

M. I. El-Saftawy ◽

Elbaz I. Abouelmagd ◽

Miguel A. López

Keyword(s):

Solar Radiation ◽

Lorentz Force ◽

Radiation Pressure ◽

Solar Radiation Pressure ◽

True Anomaly ◽

Orbital Parameters ◽

Numerical Investigations ◽

Geosynchronous Orbits

The aim of the present paper is to analyze the viability of using Lorentz Force (LF) acting on a charged spacecraft to neutralize the effects of Solar Radiation Pressure (SRP) on the longitude of the ascending node and the argument of perigee of the spacecraft’s orbit. In this setting, the Gauss planetary equations for LF and SRP are presented and averaged over the true anomaly. The averaged variations for the longitude of the ascending node (h) and the argument of perigee (g) are invariant under the symmetry (i,g)⟶(−i,−g) due to Lorentz Force. The sum of change rates due to both perturbing forces of LF and SRP is assigned by zero to estimate the charge amount to balance the variation for the argument of perigee and longitude of ascending. Numerical investigations have been developed to show the evolution of the charge quantity for different orbital parameters at both Low Earth and Geosynchronous Orbits.

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