A New Navigation Force Model for the Earth’s Albedo and Its Effects on the Orbital Motion of an Artificial Satellite

Abdel‐Aziz, Yehia A.; Abdel-Hameed, Afaf M.; Khalil, Khalil I.

doi:10.4236/am.2011.27107

Cited by 4 publications

(3 citation statements)

References 7 publications

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“…Since it is impossible to find an exact answer to the three-body problem, we are not exploring this further (Our limitations have been explained by chaos theory [7]). An example of post-Newtonian work on the three-body problem can be found in Fawzy A. Abd El-Salam, et al (2011) [8] The Lagrangian points are commonly used to calculate many of the orbital properties of celestial bodies [9]. This paper focuses on celestial planetary mechanics, most of which was developed by Sir Isaac Newton.…”

Section: Review Of Literature On Trojan Asteroids and Lagrangian Pointsmentioning

confidence: 99%

Study and Analysis of the Orbital and Physical Properties of 2010 TK<sub>7</sub>

Giovannetti-Singh¹

2011

JMP

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In this paper we calculate the volume, mass, gravitational attraction to the Earth, angular momentum the orbit of the Trojan asteroid (TK 7) [1]. In this paper, we use classical Newtonian mechanics to analyse some of the physical and orbital properties of the Trojan asteroid, which are still experimentally unknown. The asteroid should remain in Earth's orbit for the next 100 years. We conclude by providing informed estimates of 2010 TK 7 's yet unknown physical properties: i.e. mass, volume, gravitational attraction to Earth and angular momentum.

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Section: Review Of Literature On Trojan Asteroids and Lagrangian Pointsmentioning

confidence: 99%

Study and Analysis of the Orbital and Physical Properties of 2010 TK<sub>7</sub>

Giovannetti-Singh¹

2011

JMP

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“…Various approaches have been used to develop numerical models of satellite orbit. They include; Euler's method [9,10], Runge-Kutta method [10,11], power series methods [12] and Lagrangian methods [13,14] among others. The Euler, Runge-Kutta and power series methods are based on, or derived from, infinite series method.…”

Section: Introductionmentioning

confidence: 99%

“…At the same time, when the terms are reduced, the method becomes faster but less accurate. Lagrangian methods, on the other hand, are direct, but difficult to solve [13,14]. Thus, there is a need for a simple, faster and accurate numerical solution to model the interaction of the satellite with other celestial bodies which is what this study sought to address.…”

Section: Introductionmentioning

confidence: 99%

Numerical Model of Perturbated Earth’s Satellite Orbit

Makhanya¹

2019

IJAMTP

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The study aimed to develop a two-dimensional numerical model of a perturbed Earth's satellite orbit under the influence of the Moon. The first step was to model, numerically, the Earth-satellite orbit. The interaction was assumed to be first order. The basis of the model was that for two-dimensional motion, influence in the radial direction does not affect the motion in the tangential direction and vice versa. Based on this, the satellite's motion was decomposed into radial and tangential directions. The trajectory was segmented into time intervals and the curve swept over each interval was approximated as a straight line with the assumption that acceleration in each interval was constant. Equations of constant accelerated motion were used to describe the motion of the satellite over each interval. When the model results were compared with the exact solution, for an elliptical orbit, they matched perfectly well over the entire orbit with a maximum relative error of 0.079%. When it was tested for other orbits, circular, hyperbolic, etc., it retained all of them according to theoretical predictions. The model was then extended to incorporate the effects of the Moon by launching the satellite at quarter, half and three-quarter distance from Earth to Moon. A circular orbit was used to model the effects of the Moon. The acceleration results of the model were compared with theoretical predictions. The corresponding errors in the acceleration for the three positions of launch were 0.019% and 0.20%. This showed that this model is applicable for predicting perturbated satellite orbit and it can be applied with any extra force to describe perturbated orbit of the satellite. It can also be used to model the trajectory of projectile motion, of which the exact solution is incapable of generating. Since this model gives the speed of the satellite at any instant, it can be applied when the orbit needs to be changed as it can be used to compute the required new speed.

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New Composites from Waste Polypropylene/Eggshell Characterized by High Flame Retardant and Mechanical Properties

Younis

El-Wakil

2021

Fibers Polym

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This manuscript aimed to enhance the mechanical, ignition properties of polypropylene (PP). To reduce waste pollution of the environment, recycled waste polypropylene (WPP), and waste chicken eggshell (WCES) were used. WCES was used as a bio-filler to form new WPP composites. The effect of the addition of magnesium hydroxide (MOH) and monoammonium phosphate (MAP) on the properties of WPP/WCES composites has been studied. The structure of the composites was characterized by Fourier-transform infrared spectroscopy (FTIR), and X-ray diffraction (XRD). The mechanical and dynamic mechanical properties of the composites were investigated. The morphology and the thermal properties of the composites were investigated using a scanning electron microscope (SEM), thermal shrinkage %, and thermal analysis (TGA, DTA). The flame retardancy of the composites was assessed using limiting oxygen index (LOI) and flame chamber (UL/94) according to standard test methods. The results indicated that the 10 phr of the WCES enhanced the tensile strength and flexural strength of WPP/WCES composites by 15 and 8 % compared to the neat WPP composite, respectively. In the case of MAP and MOH fillers, the 5 and 10 phr of MOH enhanced the tensile strength and flexural strength of WPP/WCES composites by 8.3, 25, 51.1, and 65.0 % compared to the WPP/WCES composite containing 30 phr of WCES, respectively. The organic matter of WCES is a natural antioxidant for WPP/WCES composites. The limiting oxygen index (LOI) for a composition containing 30 parts per hundred resin (phr) of WCES is 20.8, slightly greater than that for neat WPP (17.9 %). While the LOI value of WPP composite containing 30 phr of mono-ammonium phosphate is 26 %.

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A New Navigation Force Model for the Earth’s Albedo and Its Effects on the Orbital Motion of an Artificial Satellite

Cited by 4 publications

References 7 publications

Study and Analysis of the Orbital and Physical Properties of 2010 TK<sub>7</sub>

Study and Analysis of the Orbital and Physical Properties of 2010 TK<sub>7</sub>

Numerical Model of Perturbated Earth’s Satellite Orbit

New Composites from Waste Polypropylene/Eggshell Characterized by High Flame Retardant and Mechanical Properties

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A New Navigation Force Model for the Earth’s Albedo and Its Effects on the Orbital Motion of an Artificial Satellite

Cited by 4 publications

References 7 publications

Study and Analysis of the Orbital and Physical Properties of 2010 TK&lt;sub&gt;7&lt;/sub&gt;

Study and Analysis of the Orbital and Physical Properties of 2010 TK&lt;sub&gt;7&lt;/sub&gt;

Numerical Model of Perturbated Earth’s Satellite Orbit

New Composites from Waste Polypropylene/Eggshell Characterized by High Flame Retardant and Mechanical Properties

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Product

Resources

About

Study and Analysis of the Orbital and Physical Properties of 2010 TK<sub>7</sub>

Study and Analysis of the Orbital and Physical Properties of 2010 TK<sub>7</sub>