Perturbative effects of antenna radiation reaction on artificial satellite orbit

2012 ◽  
Vol 23 (1) ◽  
pp. 352-357 ◽  
Author(s):  
A. Heilmann ◽  
Luiz Danilo Damasceno Ferreira ◽  
C.A. Dartora ◽  
K.Z. Nobrega
Keyword(s):  
Artificial Satellite ◽  
Satellite Orbit ◽  
Radiation Reaction ◽  
Antenna Radiation

Artificial satellite orbit computations

1966 ◽  
Vol 25 ◽  
pp. 363-371
Author(s):  
P. Sconzo
Keyword(s):  
Artificial Satellite ◽  
Satellite Orbit ◽  
Artificial Satellites ◽  
Orbital Elements ◽  
Differential Correction ◽  
Gravitational Effects ◽  
Short Intervals ◽  
The Subject ◽  
Introductory Discussion ◽  
Orbit Computation

In this paper an orbit computation program for artificial satellites is presented. This program is operational and it has already been used to compute the orbits of several satellites.After an introductory discussion on the subject of artificial satellite orbit computations, the features of this program are thoroughly explained. In order to achieve the representation of the orbital elements over short intervals of time a drag-free perturbation theory coupled with a differential correction procedure is used, while the long range behavior is obtained empirically. The empirical treatment of the non-gravitational effects upon the satellite motion seems to be very satisfactory. Numerical analysis procedures supporting this treatment and experience gained in using our program are also objects of discussion.

scholarly journals Effects of radiation pressure and earth’s oblatness on high altitude artificial satellite orbit

10.4081/708 ◽  
2011 ◽  
Vol 1 (1) ◽  
pp. e2
Author(s):  
Khalil I. Khalil ◽  
Mohamed N.S. Ismail
Keyword(s):  
High Altitude ◽  
Radiation Pressure ◽  
Artificial Satellite ◽  
Equations Of Motion ◽  
Satellite Orbit ◽  
Artificial Satellites ◽  
Runge Kutta Method ◽  
Ks Variables ◽  
Effects Of Radiation ◽  
Earth’S Oblateness

This paper is devoted to study the effects of radiation pressure together with tesseral and zonal harmonics on the high altitude artificial satellites orbits. The equations of motion were regularized by using the KS variables and the problem was solved numerically using the fourth order of Runge Kutta method. A numerical testing was performed on Lageos-1 satellite in order to analyze its orbital changes due to effects of both radiation pressure and Earth's oblateness.

scholarly journals Effects of radiation pressure and earth’s oblatness on high altitude artificial satellite orbit

2011 ◽  
Vol 1 (1) ◽  
pp. 2
Author(s):  
Khalil I. Khalil ◽  
Mohamed N.S. Ismail
Keyword(s):  
High Altitude ◽  
Radiation Pressure ◽  
Artificial Satellite ◽  
Equations Of Motion ◽  
Satellite Orbit ◽  
Artificial Satellites ◽  
Runge Kutta Method ◽  
Ks Variables ◽  
Effects Of Radiation ◽  
Earth’S Oblateness

This paper is devoted to study the effects of radiation pressure together with tesseral and zonal harmonics on the high altitude artificial satellites orbits. The equations of motion were regularized by using the KS variables and the problem was solved numerically using the fourth order of Runge Kutta method. A numerical testing was performed on Lageos-1 satellite in order to analyze its orbital changes due to effects of both radiation pressure and Earth's oblateness.

scholarly journals Comparison between Two Methods to Calculate the Transition Matrix of Orbit Motion

2012 ◽  
Vol 2012 ◽  
pp. 1-12 ◽  
Author(s):  
Ana Paula Marins Chiaradia ◽  
Hélio Koiti Kuga ◽  
Antonio Fernando Bertachini de Almeida Prado
Keyword(s):  
Orbit Determination ◽  
Transition Matrix ◽  
Numerical Approximation ◽  
State Transition ◽  
Artificial Satellite ◽  
Computational Cost ◽  
Satellite Orbit ◽  
Computational Costs ◽  
Numerical Integrator ◽  
Determination Procedure

Two methods to evaluate the state transition matrix are implemented and analyzed to verify the computational cost and the accuracy of both methods. This evaluation represents one of the highest computational costs on the artificial satellite orbit determination task. The first method is an approximation of the Keplerian motion, providing an analytical solution which is then calculated numerically by solving Kepler's equation. The second one is a local numerical approximation that includes the effect of . The analysis is performed comparing these two methods with a reference generated by a numerical integrator. For small intervals of time (1 to 10 s) and when one needs more accuracy, it is recommended to use the second method, since the CPU time does not excessively overload the computer during the orbit determination procedure. For larger intervals of time and when one expects more stability on the calculation, it is recommended to use the first method.

scholarly journals Effects of radiation pressure and earth’s oblatness on high altitude artificial satellite orbit

2011 ◽  
Vol 1 (1) ◽  
pp. e2
Author(s):  
Khalil I. Khalil ◽  
Mohamed N.S. Ismail
Keyword(s):  
High Altitude ◽  
Radiation Pressure ◽  
Artificial Satellite ◽  
Equations Of Motion ◽  
Satellite Orbit ◽  
Artificial Satellites ◽  
Runge Kutta Method ◽  
Ks Variables ◽  
Effects Of Radiation ◽  
Earth’S Oblateness

This paper is devoted to study the effects of radiation pressure together with tesseral and zonal harmonics on the high altitude artificial satellites orbits. The equations of motion were regularized by using the KS variables and the problem was solved numerically using the fourth order of Runge Kutta method. A numerical testing was performed on Lageos-1 satellite in order to analyze its orbital changes due to effects of both radiation pressure and Earth's oblateness.

scholarly journals Onboard and Real-Time Artificial Satellite Orbit Determination Using GPS

2013 ◽  
Vol 2013 ◽  
pp. 1-8 ◽  
Author(s):  
Ana Paula Marins Chiaradia ◽  
Hélio Koiti Kuga ◽  
Antonio Fernando Bertachini de Almeida Prado
Keyword(s):  
Real Time ◽  
Orbit Determination ◽  
Artificial Satellite ◽  
Time Estimation ◽  
Satellite Orbit ◽  
Estimation Algorithm ◽  
Measurement Model ◽  
Integration Scheme ◽  
Force Model ◽  
Step Size

An algorithm for real-time and onboard orbit determination applying the Extended Kalman Filter (EKF) method is developed. Aiming at a very simple and still fairly accurate orbit determination, an analysis is performed to ascertain an adequacy of modeling complexity versus accuracy. The minimum set of to-be-estimated states to reach the level of accuracy of tens of meters is found to have at least the position, velocity, and user clock offset components. The dynamical model is assessed through several tests, covering force model, numerical integration scheme and step size, and simplified variational equations. The measurement model includes only relevant effects to the order of meters. The EKF method is chosen to be the simplest real-time estimation algorithm with adequate tuning of its parameters. In the developed procedure, the obtained position and velocity errors along a day vary from 15 to 20 m and from 0.014 to 0.018 m/s, respectively, with standard deviation from 6 to 10 m and from 0.006 to 0.008 m/s, respectively, with the SA either on or off. The results, as well as analysis of the final adopted models used, are presented in this work.

The motion of a lunar orbiter

1966 ◽  
Vol 25 ◽  
pp. 373
Author(s):  
Y. Kozai
Keyword(s):  
Degrees Of Freedom ◽  
Dimensional Space ◽  
Artificial Satellite ◽  
Equations Of Motion ◽  
Triaxial Ellipsoid ◽  
The Moon ◽  
Secular Motion ◽  
The Earth ◽  
Close Satellite ◽  
The Mean

The motion of an artificial satellite around the Moon is much more complicated than that around the Earth, since the shape of the Moon is a triaxial ellipsoid and the effect of the Earth on the motion is very important even for a very close satellite.The differential equations of motion of the satellite are written in canonical form of three degrees of freedom with time depending Hamiltonian. By eliminating short-periodic terms depending on the mean longitude of the satellite and by assuming that the Earth is moving on the lunar equator, however, the equations are reduced to those of two degrees of freedom with an energy integral.Since the mean motion of the Earth around the Moon is more rapid than the secular motion of the argument of pericentre of the satellite by a factor of one order, the terms depending on the longitude of the Earth can be eliminated, and the degree of freedom is reduced to one.Then the motion can be discussed by drawing equi-energy curves in two-dimensional space. According to these figures satellites with high inclination have large possibilities of falling down to the lunar surface even if the initial eccentricities are very small.The principal properties of the motion are not changed even if plausible values ofJ3andJ4of the Moon are included.This paper has been published in Publ. astr. Soc.Japan15, 301, 1963.

Zonal and tesseral harmonic perturbations of an artificial satellite

1966 ◽  
Vol 25 ◽  
pp. 323-325 ◽  
Author(s):  
B. Garfinkel
Keyword(s):  
Angular Velocity ◽  
Spherical Harmonics ◽  
Artificial Satellite ◽  
Compact Form ◽  
Earth’S Rotation ◽  
Earth's Rotation ◽  
Secular Variations ◽  
Tesseral Harmonics

The paper extends the known solution of the Main Problem to include the effects of the higher spherical harmonics of the geopotential. The von Zeipel method is used to calculate the secular variations of orderJmand the long-periodic variations of ordersJm/J2andnJm,λ/ω. HereJmandJm,λare the coefficients of the zonal and the tesseral harmonics respectively, withJm,0=Jm, andωis the angular velocity of the Earth's rotation. With the aid of the theory of spherical harmonics the results are expressed in a most compact form.

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