scholarly journals Effect of the Earth’s oblateness, the Shadow of the Earth due to the Solar Radiation Pressure and Magnetic Force on the Motion and Stability of two satellites connected by an extensible cable in circular orbit of the Centre of Mass

2013 ◽  
Vol 8 (3) ◽  
pp. 63-69
Author(s):  
Vijay Kumar ◽  
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Circular Orbit ◽  
Magnetic Force ◽  
Solar Radiation Pressure ◽  
Centre Of Mass ◽  
The Earth ◽  
Earth’S Oblateness

scholarly journals The motion of a geosynchronous satellite

1986 ◽  
Vol 114 ◽  
pp. 293-295
Author(s):  
K. B. Bhatnagar
Keyword(s):  
Angular Velocity ◽  
Solar Radiation ◽  
Radiation Pressure ◽  
Angular Position ◽  
Orbital Plane ◽  
Solar Radiation Pressure ◽  
Orbital Inclination ◽  
Geosynchronous Satellite ◽  
The Earth ◽  
Earth’S Equatorial Ellipticity

The motion of a geosynchronous satellite has been studied under the combined gravitational effects of the oblate Earth (including its equatorial ellipticity), the Sun, the Moon and the solar-radiation pressure. It is observed that the orbital plane rotates with an angular velocity the maximum value of which is 0.058°/yr. and regresses with a period which increases both as the orbital inclination and the altitude increase. The effect of earth's equatorial ellipticity on the regression period is oscillatory whereas that of Solar-radiation pressure is to decrease it.The synchronism is achieved when the angular velocity of the satellite is equal to the difference between the spin-rate of the Earth and the regression rate of the orbital plane. With this angular velocity of the satellite, the ground trace is in the shape of figure eight, though its size and position relative to the Earth change as the time elapses. The major effect of earth's equatorial ellipticity is to produce a change in the relative angular position of the satellite as seen from the Earth. If the satellite is allowed to execute large angle oscillations the mid-point of oscillation would be at the position of the minor axis of the earth's equatorial section. The oscillatory period T has been determined in terms of the amplitude Γ and the tesseral harmonic J2(2). From this result we can determine the value of J2(2) as T and Γ can be observed accurately.

scholarly journals On the use of a continuous thrust to find bounded planar trajectories at given altitudes in Low Earth Orbits

2020 ◽  
Vol 10 (1) ◽  
Author(s):  
Allan Kardec de Almeida ◽  
Jhonathan Orlando Murcia Piñeros ◽  
Antonio Fernando Bertachini de Alme Prado
Keyword(s):  
Nonlinear Dynamics ◽  
Solar Radiation ◽  
Drag Force ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
The Moon ◽  
The Earth ◽  
Low Earth Orbits ◽  
Earth Orbits ◽  
Different Altitudes

Abstract In this work, it is shown how a spacecraft equipped with a thrust and subjected to a drag force can be bounded at specific altitudes as function of the parameters of the thrust. It is used nonlinear dynamics tools to find attractors, which bound the motion of the spacecraft. For a specific set of parameters of the thrust, the spacecraft is bounded to a given altitude. Several forms for the thrusts are proposed in order to bound the altitude of the spacecraft. The influence of several forms of perturbations in the altitude of the spacecraft is also investigated in this work, like the solar radiation pressure, gravity of the Moon and oblateness of the Earth. Finally, nonlinear dynamics tools are also used to investigate transfers among the bounded orbits in different altitudes.

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