Effect of an oblate rotating atmosphere on the orientation of a satellite orbit

1961 ◽  
Vol 261 (1305) ◽  
pp. 246-258 ◽  
Keyword(s):  
Orbital Plane ◽  
Satellite Orbit ◽  
Major Axis ◽  
Earth Satellite ◽  
Semi Major Axis ◽  
Orbital Inclination ◽  
Small Eccentricity ◽  
Earth Satellite Orbit ◽  
The Right ◽  
Right Ascension

For an earth satellite orbit of small eccentricity ( e < 0·2) formulae are derived for the changes per revolution produced by the atmosphere in the argument of perigee, in the right ascension of the ascending node, and in the orbital inclination. These changes are then expressed in terms of the change in length of the semi-major axis, and numerical values are obtained for satellite 1957 β . It is found that the rotation of the major axis in the orbital plane due to the atmosphere is significant, being most important for inclinations between 60 and 70°. The total rotation, due both to the gravitational potential and to the atmosphere, agrees reasonably well with the observed values. The oblateness of the atmosphere is found to have only a small effect on the changes in the orbital inclination and the right ascension of the ascending node.

scholarly journals Generalized algorithm for determining AES orbit parameters based on quadratic functionals.

2021 ◽  
Vol 2021 (2) ◽  
Author(s):  
D.D. Gabriel’yan ◽  
◽  
A.N. Gorbachev ◽  
V.I. Demchenko ◽  
◽  
...  
Keyword(s):  
Dimensional Space ◽  
Satellite Orbit ◽  
Major Axis ◽  
Earth Satellite ◽  
Orbital Elements ◽  
Semi Major Axis ◽  
Orbital Inclination ◽  
Quadratic Functionals ◽  
Adopted Model ◽  
Basic Parameters

The questions of development a generalized algorithm for determining the parameters of the low circular orbit (LCO) of an Earth satellite (ES) based on the use of quadratic functionals are in the focus of this paper. The functionals represent the square of the differences between the measured values of the ES sighting angles and the frequency of the received signal with the values of the same parameters obtained for the assumed values of the Keplerian orbital elements in accordance with the adopted model of the ES motion. Estimates of the orbit parameters are formed from the condition of the minimum of the proposed quality functionals. The proposed algorithm is aimed at the developing two equations for the relationship between the measured values of the azimuth and elevation angles, as well as the frequency of the received satellite signal and the parameters of the satellite orbit. The use of the indicated constraint equations makes it possible to pass from the six-dimensional space of the Keplerian orbital elements to the four-dimensional space of the Keplerian orbital elements when constructing the algorithm and choosing the initial approximations of the orbit parameters. Such a reduction in the dimension of space makes it possible to significantly reduce the amount of computational expenditure, which ensures the stability of the algorithm and expands the possibilities of its practical use with limited resources (computing power and restrictions on the permissible processing time). The following Keplerian orbital elements are proposed as four basic parameters: eccentricity, ascending node longitude, orbital inclination, and perigee argument. The other two elements, the semi-major axis of the orbit and the mean anomaly, are expressed as functions of four basic parameters. This choice is determined by the fact that, in the case of LCO, the pivoting of the initial values of the eccentricity and the argument of perigee is quite simple, which makes it possible to ensure convergence to the exact values of the orbit parameters in a wide value of the initial approximations. Within the Keplerian approximation of the satellite's orbital motion, mathematical relations are presented that determine the operations performed within the framework of the considered algorithm. However, a more complete consideration of the factors influencing the motion of the satellite only leads to more volumetric relations, but does not fundamentally affect the construction of the algorithm itself.

Effect of J3 perturbation on satellite position in LEO

2018 ◽  
Vol 90 (1) ◽  
pp. 74-86
Author(s):  
Nai-ming Qi ◽  
Qilong Sun ◽  
Yong Yang
Keyword(s):  
Satellite Orbit ◽  
Major Axis ◽  
Variation Method ◽  
Semi Major Axis ◽  
Content Type ◽  
The Difference ◽  
The Right ◽  
Perturbation Effect ◽  
Earth’S Oblateness ◽  
Right Ascension

Purpose The purpose of this paper is to study the effect of J3 perturbation of the Earth’s oblateness on satellite orbit compared with J2 perturbation. Design/methodology/approach Based on the parametric variation method in the time domain, considering more accurate Earth potential function by considering J3-perturbation effect, the perturbation equations about satellite’s six orbital elements (including semi-major axis, orbit inclination, right ascension of the ascending node, true anomaly, eccentricity and argument of perigee) has been deduced theoretically. The disturbance effects of J2 and J3 perturbations on the satellite orbit with different orbit inclinations have been studied numerically. Findings With the inclination increasing, the maximum of the semi-major axis increases weakly. The difference of inclination disturbed by the J2 and J3 perturbation is relative to orbit inclinations. J3 perturbation has weak effect on the right ascension and argument of perigee. The critical angle of the right ascension and argument of perigee which decides the precession direction is 90° and 63.43°, respectively. The disturbance effects of J2 and J3 perturbations on the argument of perigee, right ascension and eccentricity are weakened when the eccentricity increases, simultaneously, the difference of J2 and J3 perturbations on argument of perigee, right ascension and argument of perigee decreases with eccentricity increasing, respectively. Practical implications In the future, satellites need to orbit the Earth much more precisely for a long period. The J3 perturbation effect and the weight compared to J2 perturbation in LEO can provide a theoretical reference for researchers who want to improve the control accuracy of satellite. On the other hand, the theoretical analysis and simulation results can help people to design the satellite orbit to avoid or diminish the disturbance effect of the Earth’s oblateness. Originality/value The J3 perturbation equations of satellite orbit elements are deduced theoretically by using parametric variation method in this paper. Additionally, the comparison studies of J2 perturbation and J3 perturbation of the Earth’s oblateness on the satellite orbit with different initial conditions are presented.

scholarly journals Analytical Study of Earth Tides on Low Orbits Satellites

2020 ◽  
pp. 453-461
Author(s):  
Ahmed K. Izzet ◽  
Mayada J. Hamwdi ◽  
Abed T. Jasim
Keyword(s):  
Analytical Study ◽  
Satellite Orbit ◽  
Major Axis ◽  
Earth Tides ◽  
Orbital Elements ◽  
Semi Major Axis ◽  
Tidal Perturbation ◽  
Right Ascension ◽  
Tide Effect

     The main objective of this paper is to calculate the perturbations of tide effect on LEO's satellites . In order to achieve this goal, the changes in the orbital elements which include the semi major axis (a) eccentricity (e) inclination , right ascension of ascending nodes ( ), and fifth element argument of perigee ( ) must be employed. In the absence of perturbations, these element remain constant. The results show that the effect of tidal perturbation on the orbital elements depends on the inclination of the satellite orbit. The variation in the ratio  decreases with increasing the inclination of satellite, while it increases with increasing the time.

The effect of a meridional wind on a satellite orbit

1966 ◽  
Vol 294 (1438) ◽  
pp. 261-272 ◽  
Keyword(s):  
Aerodynamic Force ◽  
Satellite Orbit ◽  
Ambient Air ◽  
Meridional Wind ◽  
Upper Atmosphere ◽  
Orbital Inclination ◽  
Meridional Motion ◽  
The Right ◽  
Right Ascension ◽  
Direction Opposite

In this paper theoretical formulae are derived which show the effect of a meridional (south to north) wind on a satellite orbit of eccentricity less than 0.2. The aerodynamic force acting on the satellite, which is normally important only over a small section of the orbit near perigee, is assumed to be in the direction opposite to the satellite’s motion relative to the ambient air, so that meridional motion of the upper atmosphere slightly alters the direction of the drag. The resulting changes in the satellite’s orbital inclination and the right ascension of the node are evaluated. For a satellite whose perigee remains near the equator, a consistent meridional wind of 100 m/s in the vicinity of perigee can change the orbital inclination by 0.02° as the orbital period decreases by 10 min ; but when perigee moves widely, the effect is generally much smaller.

scholarly journals A dynamical study of the Gefion asteroid family

2019 ◽  
Vol 622 ◽  
pp. A39 ◽  
Author(s):  
S. Aljbaae ◽  
J. Souchay ◽  
A. F. B. A. Prado ◽  
T. G. G. Chanut
Keyword(s):  
Target Function ◽  
Orbital Plane ◽  
Major Axis ◽  
Symplectic Integrators ◽  
Ejection Velocity ◽  
Semi Major Axis ◽  
Dynamical Study ◽  
Mean Motion Resonances ◽  
Yorp Effect ◽  
The Right

The Gefion asteroid family is a group of S-type asteroids located between the 8J:-3A and 5J:-2A mean-motion resonances. The 5J:-2A resonance seems to be responsible for the absence of the right side of the V-shape of this family. We aim in this work to present a detailed study on the Gefion family, motivated by the incompatibility found in previous family age estimations and the fact that this family could be seen as one of the most probable sources of L-chondrite meteorites. After eliminating all possible taxonomical and dynamical interlopers, we use a Monte Carlo method to analyze the semi-major axis evolution of several fictitious families under the influence of the Yarkovsky and Yarkovsky-O’Keefe-Radzievsky-Paddack (YORP) effects. We also perform simulations using symplectic integrators to account for the Yarkovsky effect (diurnal and seasonal versions) and the stochastic YORP effect. We make use of the distribution of the component of the ejection velocity field (vW) perpendicular to the orbital plane and the time dependence of the asymmetry of the distribution of the target function of a fictitious family generated with ejection velocity parameter 20+55−15 m s−1 to obtain an age estimate of 1030+19−67 Myr. We find that 6.5% of asteroids from the Gefion family can reach orbits similar to particles in the current near-Earth objects space; 73% of them are among the Amors asteroids, and the remaining ones are among the Apollos. We only found 0.5% from the Gefion family reaching the Mars-crossing space.

The effect of atmospheric rotation on the orbital plane of a near-earth satellite

1960 ◽  
Vol 258 (1295) ◽  
pp. 516-528 ◽  
Keyword(s):  
Gravitational Field ◽  
Orbital Plane ◽  
Earth Satellite ◽  
Theoretical Curve ◽  
Orbital Inclination ◽  
Small Eccentricity ◽  
Earth’S Atmosphere ◽  
The Earth ◽  
Earth’S Gravitational Field ◽  
Good Agreement

Besides the perturbations due to the gravitational field of the earth, the rotation of the earth’s atmosphere produces a perturbing force on a satellite which affects the motion of its orbital plane. Theoretical formulae are derived for the rotation of the orbital plane about the earth’s axis and the change in orbital inclination of a near-earth satellite of small eccentricity (< 0.2) due to the influence of the atmosphere. It is assumed that the atmosphere is spherically symmetrical and has a density which varies exponentially with altitude. Comparison of the theoretical changes in orbital inclination show reasonably good agreement with those estimated from kinetheodolite observations, although the need for a slightly steeper theoretical curve is indicated. Although the rotation of the orbital plane is small, allowance must be made for it when making estimates of the harmonics of the earth's gravitational field.

scholarly journals γ DOR: A PULSATING COMPONENT OF KIC 8043961 IN A STELLAR TRIPLE SYSTEM

2020 ◽  
Vol 56 (2) ◽  
pp. 179-191
Author(s):  
C. Kamil ◽  
H. A. Dal ◽  
O. Özdarcan ◽  
E. Yoldaş
Keyword(s):  
Major Axis ◽  
Primary Component ◽  
Mass Ratio ◽  
Third Body ◽  
Semi Major Axis ◽  
Orbital Inclination ◽  
The Third ◽  
New Findings ◽  
Effective Temperatures ◽  
Orbit Model

We present new findings about KIC 8043961. We find the effective temperatures of the components as 6900 ± 200 K for the primary, and 6598 ± 200 K for the secondary, while the logarithm of the surface gravities are found to be 4.06 cm s-2 and 3.77 cm s-2, respectively. Combination of the light curve with the spectroscopic orbit model results leads to a mass ratio of 1.09 ± 0.07 with an orbital inclination of 73.71 ± 0.14 and a semi-major axis of 8.05 ± 0.22 R⨀ . Masses of the primary and secondary components are calculated as 1.379 ± 0.109 M⨀ and 1.513 ± 0.181 M⨀, while the radii are found to be 1.806 ± 0.084 R⨀ and 2.611 ± 0.059 R⨀. In addition, we obtain a considerable light contribution (≈0.54%) of a third body. We compute a possible mass for the third body as 0.778 ± 0.002 M⨀. We find that the primary component exhibits γ Dor type pulsations with 137 frequencies.

scholarly journals Ring dynamics around an oblate body with an inclined satellite: the case of Haumea

2020 ◽  
Vol 643 ◽  
pp. A67
Author(s):  
Francesco Marzari
Keyword(s):  
Equatorial Plane ◽  
Protective Factor ◽  
Central Body ◽  
Orbital Plane ◽  
Major Axis ◽  
The Body ◽  
Triaxial Ellipsoid ◽  
Semi Major Axis ◽  
Short Timescale ◽  
The Impact

Context. The recent discovery of rings and massive satellites around minor bodies and dwarf planets suggests that they may often coexist, as for example around Haumea. Aims. A ring perturbed by an oblate central body and by an inclined satellite may disperse on a short timescale. The conditions under which a ring may survive are explored both analytically and numerically. Methods. The trajectories of ring particles are integrated under the influence of the gravitational field of a triaxial ellipsoid and (a) massive satellite(s), including the effects of collisions. Results. A ring initially formed in the equatorial plane of the central body will be disrupted if the satellite has an inclination in the Kozai–Lidov regime (39.2° < i < 144.8). For lower inclinations, the ring may relax to the satellite orbital plane thanks to an intense collisional damping. On the other hand, a significant J2 term easily suppresses the perturbations of an inclined satellite within a critical semi-major axis, even in the case of Kozai–Lidov cycles. However, if the ring is initially inclined with respect to the equatorial plane, the same J2 perturbations are not a protective factor but instead disrupt the ring on a short timescale. The ring found around Haumea is stable despite the rise in the impact velocities that is due to the asymmetric shape of the body and the presence of a 3:1 resonance with the rotation of the central body. Conclusions. A ring close to an oblate central body should be searched for in the proximity of the equatorial plane, where the J2 perturbations protect it against the perturbations of an external inclined satellites. In an inclined configuration, the J2 term is itself disruptive.

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