scholarly journals Effectiveness of KS elements in satellite orbit prediction using earth's gravity, drag and solar radiation pressure

2020 ◽  
Vol 8 (1) ◽  
pp. 19
Author(s):  
T. R. Saritha Kumari ◽  
M. Xavier James Raj
Keyword(s):  
Gravitational Field ◽  
Solar Radiation ◽  
Radiation Pressure ◽  
Equations Of Motion ◽  
Solar Radiation Pressure ◽  
Satellite Orbit ◽  
Atmospheric Drag ◽  
Third Body ◽  
Gravitational Effects ◽  
Tesseral Harmonics

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. 

scholarly journals Dynamical taxonomy of the coupled solar radiation pressure and oblateness problem and analytical deorbiting configurations

2020 ◽  
Vol 132 (11-12) ◽  
Author(s):  
Ioannis Gkolias ◽  
Elisa Maria Alessi ◽  
Camilla Colombo
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Invariant Manifolds ◽  
Equations Of Motion ◽  
Solar Radiation Pressure ◽  
Orbital Evolution ◽  
Mission Design ◽  
Simple Analytical Expression ◽  
Practical Applications ◽  
Resonant Interactions

AbstractRecent works demonstrated that the dynamics caused by the planetary oblateness coupled with the solar radiation pressure can be described through a model based on singly averaged equations of motion. The coupled perturbations affect the evolution of the eccentricity, inclination and orientation of the orbit with respect to the Sun–Earth line. Resonant interactions lead to non-trivial orbital evolution that can be exploited in mission design. Moreover, the dynamics in the vicinity of each resonance can be analytically described by a resonant model that provides the location of the central and hyperbolic invariant manifolds which drive the phase space evolution. The classical tools of the dynamical systems theory can be applied to perform a preliminary mission analysis for practical applications. On this basis, in this work we provide a detailed derivation of the resonant dynamics, also in non-singular variables, and discuss its properties, by studying the main bifurcation phenomena associated with each resonance. Last, the analytical model will provide a simple analytical expression to obtain the area-to-mass ratio required for a satellite to deorbit from a given altitude in a feasible timescale.

scholarly journals Dynamics of Satellites Around Asteroids in Presence of Solar Radiation Pressure

2015 ◽  
Vol 10 (S318) ◽  
pp. 259-264
Author(s):  
Xiaosheng Xin ◽  
Daniel J. Scheeres ◽  
Xiyun Hou ◽  
Lin Liu
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Equilibrium Points ◽  
Equations Of Motion ◽  
Solar Radiation Pressure ◽  
Approximate Solutions ◽  
Triaxial Ellipsoid ◽  
Stability Maps ◽  
The Stability ◽  
Near Earth Asteroids

AbstractDue to the close distance to the Sun, solar radiation pressure (SRP) plays an important role in the dynamics of satellites around near-Earth asteroids (NEAs). In this paper, we focus on the equilibrium points of a satellite orbiting around an asteroid in presence of SRP in the asteroid rotating frame. The asteroid is modelled as a uniformly rotating triaxial ellipsoid. When SRP comes into play, the equilibrium points transformed into periodic orbits termed as``dynamical substitutes". We obtain the analytical approximate solutions of the dynamical substitutes from the linearised equations of motion. The analytical solutions are then used as initial guesses and are numerically corrected to compute the accurate orbits of the dynamical substitutes. The stability of the dynamical substitutes is analysed and the stability maps are obtained by varying parameters of the ellipsoid model as well as the magnitude of SRP.

scholarly journals Study of Some Strategies for Disposal of the GNSS Satellites

2015 ◽  
Vol 2015 ◽  
pp. 1-14 ◽  
Author(s):  
Diogo Merguizo Sanchez ◽  
Tadashi Yokoyama ◽  
Antonio Fernando Bertachini de Almeida Prado
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Equations Of Motion ◽  
Solar Radiation Pressure ◽  
Geopotential Model ◽  
The Sun ◽  
The Moon ◽  
Orbital Eccentricity ◽  
Atmospheric Reentry ◽  
Quantitative Influence

The complexity of the GNSS and the several types of satellites in the MEO region turns the creation of a definitive strategy to dispose the satellites of this system into a hard task. Each constellation of the system adopts its own disposal strategy; for example, in the American GPS, the disposal strategy consists in changing the altitude of the nonoperational satellites to 500 km above or below their nominal orbits. In this work, we propose simple but efficient techniques to discard satellites of the GNSS by exploiting Hohmann type maneuvers combined with the use of the2ω˙+Ω˙≈0resonance to increase its orbital eccentricity, thus promoting atmospheric reentry. The results are shown in terms of the increment of velocity required to transfer the satellites to the new orbits. Some comparisons with direct disposal maneuvers (Hohmann type) are also presented. We use the exact equations of motion, considering the perturbations of the Sun, the Moon, and the solar radiation pressure. The geopotential model was considered up to order and degree eight. We showed the quantitative influence of the sun and the moon on the orbit of these satellites by using the method of the integral of the forces over the time.

scholarly journals Dynamics in the circular restricted three body problem with perturbations

2017 ◽  
Vol 5 (1) ◽  
pp. 19 ◽  
Author(s):  
Abdullah Abduljabar Ansari ◽  
Mehtab Alam
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Body Problem ◽  
Equations Of Motion ◽  
Solar Radiation Pressure ◽  
Libration Points ◽  
Restricted Three Body Problem ◽  
Three Body Problem ◽  
Zero Velocity Curves ◽  
Three Body

This paper presents the dynamics in the restricted problem with perturbations i.e. the circular restricted three body problem by considering one of the primaries as oblate and other one having the solar radiation pressure and all the masses are variable (primaries and infinitesimal body). For finding the autonomized equations of motion, we have used the Meshcherskii transformation. We have drawn the libration points, the time series, the zero velocity curves and Poincare surface of sections for the different values of the oblateness and solar radiation pressure. Finally, we have examined the stability and found that all the libration points are unstable.

scholarly journals Dynamic Response of Solar Power Satellite Considering Solar Radiation Pressure

2018 ◽  
Vol 36 (3) ◽  
pp. 590-596 ◽  
Author(s):  
Fangnuan Xu ◽  
Zichen Deng ◽  
Bo Wang ◽  
Yi Wei ◽  
Qingjun Li
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Solar Power ◽  
Equations Of Motion ◽  
Solar Radiation Pressure ◽  
Structural Vibration ◽  
Bernoulli Beam ◽  
Runge Kutta Method ◽  
Proposed Model ◽  
Euler Bernoulli Beam

The attitude and structural vibration of tethered solar power satellite were studied considering solar radiation pressure. Firstly, the simplified model of tethered solar power satellite was established. The solar panel was modeled as an Euler-Bernoulli Beam, the bus was modeled as a particle, and the tethers were modeled as massless springs. The equations of motion were derived based on absolute nodal coordinate formulation and Hamilton’s principle. Then, Symplectic Runge-Kutta method was adopted to solve the differential equations. The proposed model and numerical algorithm were validated through a numerical example. Finally, numerical simulations were carried out. Simulation results showed that solar radiation pressure as well as structural vibration cause small fluctuation of the attitude angle. Moreover, the effect of solar radiation pressure on structural vibration can be neglected.

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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