Andere Kunden interessierten sich auch für
![Osculating Relative Orbit Elements Resulting from Chief Eccentricity and J2 Perturbing Forces]( "Osculating Relative Orbit Elements Resulting from Chief Eccentricity and J2 Perturbing Forces")
Osculating Relative Orbit Elements Resulting from Chief Eccentricity and J2 Perturbing Forces60,99 €![Optimal Control Strategies for Constrained Relative Orbits]( "Optimal Control Strategies for Constrained Relative Orbits")
Optimal Control Strategies for Constrained Relative Orbits60,99 €![Estimation of Relative Satellite Formation Element Positions in Near Circular Orbits]( "Estimation of Relative Satellite Formation Element Positions in Near Circular Orbits")
Estimation of Relative Satellite Formation Element Positions in Near Circular Orbits60,99 €![Estimation of Relative Satellite Formation Element Positions in Near Circular Orbits]( "Estimation of Relative Satellite Formation Element Positions in Near Circular Orbits")
Estimation of Relative Satellite Formation Element Positions in Near Circular Orbits60,99 €![Maneuver Estimation Model for Relative Orbit Determination]( "Maneuver Estimation Model for Relative Orbit Determination")
Maneuver Estimation Model for Relative Orbit Determination60,99 €![Modeling GPS Satellite Orbits Using KAM Tori]( "Modeling GPS Satellite Orbits Using KAM Tori")
Modeling GPS Satellite Orbits Using KAM Tori60,99 €![Timing of Increasing Electron Counts from Geosynchronous Orbit to Low Earth Orbit]( "Timing of Increasing Electron Counts from Geosynchronous Orbit to Low Earth Orbit")
Timing of Increasing Electron Counts from Geosynchronous Orbit to Low Earth Orbit60,99 €
The purpose of this research was to describe the unperturbed relative motion of Earth satellites in elliptical orbits using a simple dynamics model whose parameters allow significant geometrical insight and operational efficacy. The goal was to retain the advantages of the Relative Orbit Elements (ROE) realization of the Hill-Clohessy-Wiltshire (HCW) equations, a linearized dynamics model for circular reference orbits. Specifically, this thesis analyzed the geometry of satellite rendezvous and proximity operations using the ROE parameters to characterize the model's utility. Next, through a comprehensive literature review, this thesis sought possible approaches for developing a similarly useful parameterization for chief orbits with nonzero eccentricity. The approach selected was a novel linear time-varying system which requires both chief and deputy satellites to remain close to a virtual chief on a known circular orbit.