Solar radiation pressure perturbations of earth satellite orbits.

AIAA Journal ◽  
1968 ◽  
Vol 6 (1) ◽  
pp. 120-126 ◽  
Author(s):  
E. LEVIN
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
Earth Satellite ◽  
Satellite Orbits ◽  
Pressure Perturbations

Earth satellite orbits with resonant lunisolar perturbations I. Resonances dependent only on inclination

1980 ◽  
Vol 372 (1749) ◽  
pp. 243-264 ◽  
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
Earth Satellite ◽  
Disturbing Function ◽  
Direct Solar Radiation ◽  
Satellite Orbits ◽  
Orbital Inclination ◽  
Lunisolar Perturbations ◽  
Pressure Perturbations

Earth satellite orbits resonant with respect to lunisolar gravity and direct solar radiation pressure perturbations are discussed with particular reference to those resonances the occurrence of which is dependent only on the satellite’s orbital inclination. All types of lunisolar resonance orbits are first classified in terms of the general commensurability condition, which is then expressed as a function of the non-angular elements of the satellite’s orbit and certain parameters of the perturbing forces. Rules and constraints for ascertaining the predominant resonance terms in the disturbing function expansion for a given commensurability are also derived. Finally, the resonances dependent only on inclination are discussed. Criteria for determining their existence are found and the predominant resonant terms for every commensurability of this type are given. A num­ber of important examples of resonance orbits in this category are also discussed.

Earth satellite orbits with resonant lunisolar perturbations - II. Some resonances dependent on the semi-major axis, eccentricity and inclination

1981 ◽  
Vol 375 (1762) ◽  
pp. 379-396 ◽  
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
Major Axis ◽  
Earth Satellite ◽  
Direct Solar Radiation ◽  
Satellite Orbits ◽  
Semi Major Axis ◽  
Lunisolar Perturbations ◽  
Pressure Perturbations

Earth satellite orbits resonant with respect to lunisolar gravity and direct solar radiation pressure perturbations are discussed with particular reference to those resonances satisfying commensurability conditions of the following form: ψ 4 = α ώ + γ (ώ p + Ṁ p ) ≈ 0 and ψ 5 = β Ω . + γ (ώ p + Ṁ p ) ≈ 0, where ω is the argument of perigee of the satellite’s orbit, Ω is the longitude of its ascending node, ω p is the argument of perigee of the lunar or solar orbits, and M p is the mean anomaly of the lunar or solar orbits; α, β and γ are integers. Certain simple relations are derived connecting the satellite’s semi-major axis, eccentricity and inclination; they must be satisfied, if the satellite is to exist in the commensurabilities ψ 4 ≈ 0 and ψ 5 ≈ 0. Tables are also given which contain the predominant resonant terms in the lunisolar gravity and direct solar radiation pressure disturbing function expansions for every commensurability of the type ψ 4 ≈ 0 and ψ 5 ≈ 0. Finally some important examples of these resonances are discussed.

Effects of Solar Radiation Pressure on Earth Satellite Orbits

Science ◽  
1960 ◽  
Vol 131 (3404) ◽  
pp. 920-921 ◽  
Author(s):  
R. W. Parkinson ◽  
H. M. Jones ◽  
I. I. Shapiro
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Solar Radiation Pressure ◽  
Earth Satellite ◽  
Satellite Orbits

scholarly journals Study the Effect of Solar Radiation Pressure at Several Satellite Orbits

2013 ◽  
Vol 10 (4) ◽  
pp. 1253-1261 ◽  
Author(s):  
Baghdad Science Journal
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Jacobian Matrix ◽  
Solar Radiation Pressure ◽  
Equation Of Motion ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Satellite Orbits ◽  
Orbit Satellite ◽  
Low Earth Orbit Satellite

The effects of solar radiation pressure at several satellite (near Earth orbit satellite, low Earth orbit satellite, medium Earth orbit satellite and high Earth orbit satellite ) have been investigated. Computer simulation of the equation of motion with perturbations using step-by-step integration (Cowell's method) designed by matlab a 7.4 where using Jacobian matrix method to increase the accuracy of result.

scholarly journals Phase space description of the dynamics due to the coupled effect of the planetary oblateness and the solar radiation pressure perturbations

2019 ◽  
Vol 131 (9) ◽  
Author(s):  
Elisa Maria Alessi ◽  
Camilla Colombo ◽  
Alessandro Rossi
Keyword(s):  
Phase Space ◽  
Solar Radiation ◽  
Radiation Pressure ◽  
Equilibrium Points ◽  
Hamiltonian Formulation ◽  
Solar Radiation Pressure ◽  
Major Axis ◽  
Integral Of Motion ◽  
Semi Major Axis ◽  
Pressure Perturbations

Abstract The aim of this work is to provide an analytical model to characterize the equilibrium points and the phase space associated with the singly averaged dynamics caused by the planetary oblateness coupled with the solar radiation pressure perturbations. A two-dimensional differential system is derived by considering the classical theory, supported by the existence of an integral of motion comprising semi-major axis, eccentricity and inclination. Under the single resonance hypothesis, the analytical expressions for the equilibrium points in the eccentricity-resonant angle space are provided, together with the corresponding linear stability. The Hamiltonian formulation is also given. The model is applied considering, as example, the Earth as major oblate body, and a simple tool to visualize the structure of the phase space is presented. Finally, some considerations on the possible use and development of the proposed model are drawn.

A discussion on orbital analysis - Properties of the upper atmosphere determined from satellite orbits

1967 ◽  
Vol 262 (1124) ◽  
pp. 157-171 ◽  
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Orbital Period ◽  
Solar Radiation Pressure ◽  
Major Axis ◽  
Artificial Satellites ◽  
Satellite Orbits ◽  
Atmospheric Drag ◽  
Sunspot Maximum ◽  
The Earth

Irregularities in the Earth’s gravitational potential perturb the orbits of artificial satellites in a great many ways. They cannot, however, change the mean value of the major axis of an orbit, which determines the period of revolution. To change the orbital period a dissipative force is required, such as the drag exerted on the satellite by the Earth’s atmosphere. Solar radiation pressure does not affect the period of a satellite provided the satellite does not cross the shadow cone of the Earth. If the orbit is all in daylight, the effect of the force cancels out after one revolution. If, however, the satellite goes in and out of the Earth’s shadow, and the orbit is not circular, the effect does not cancel out and radiation pressure will cause a change in the period. Atmospheric drag and solar radiation pressure are the only major forces that are known to affect the period of a satellite. Other forces, such as the interaction of an electrically charged satellite with atmospheric ions or with the magnetic field of the Earth, are undoubtedly present, but they are generally quite small. For low-orbiting satellites, with perigees below 300 km, the effect of atmospheric drag on the orbital period is so much larger than that of solar radiation pressure, that the latter can be neglected for all practical purposes. Above 400 km, however, radiation pressure makes itself felt, and above 700 km it may become more important than atmospheric drag. Actually, these figures vary a great deal with the phase of the solar cycle, since the atmosphere expands or contracts with solar activity. At sunspot minimum the effect of radiation pressure becomes comparable with that of atmospheric drag at about 600 km, while at sunspot maximum it does not become so below 1100 km.

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