Abstract
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.
Highlights
The importance of taking into account the influence of radiation pressure on artificial satellite motion does not admit discussion when noting the discrepancies between theories computations and practical observations of balloon-type satellites
The required values of the charge per mass unit (q), to balance the variations on the longitude of ascending node (h) and the argument of perigee (g) due to the solar radiation pressure and Lorentz Force will be investigated numerically through Figures 1–16, which is measured by the Coulomb/Kg unit
These investigations are given for showing the evaluation of the charge (q) versus different orbital parameters, both for Low Earth Orbit (LEO) and a Geosynchronous Orbit (GSO)
Summary
The importance of taking into account the influence of radiation pressure on artificial satellite motion does not admit discussion when noting the discrepancies between theories computations and practical observations of balloon-type satellites. The influence that is related to solar radiation pressure exceeds that of drag atmospheric at a height of 800 km and the force equals 10−5 dyn/cm for an atmospherical model with an exospheric temperature of 1400 k [1]. Pressure (SRP) on the Lorentz Spacecraft (LS) from different views. In [2], the authors used the variation of vector elements approach to obtain first order relations for the change rates in the osculating elements, which are generated by SRP. While [4] studied canonically the effect of SRP on space craft with complex shape. In [5], the authors studied the resonance effect, which is introduced by the commensurability between the different mean motions
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