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Title:  Solar radiation pressure, drag and gravitational effects on a dust particle in Earth orbit 
Author(s):  Jagannatha, Bindu 
Advisor(s):  Coverstone, Victoria L. 
Department / Program:  Aerospace Engineering 
Discipline:  Aerospace Engineering 
Degree Granting Institution:  University of Illinois at UrbanaChampaign 
Degree:  M.S. 
Genre:  Thesis 
Subject(s):  Solar Radiation Pressure
Gravitational perturbations Dust particle orbit Montecarlo simulations 
Abstract:  This work aims to further the research done on evaluating the effects of various perturbing forces on Earthorbiting particles by numerical integration. One of the predominant perturbations on particle orbits is the solar radiation pressure (SRP), which is defined as the pressure exerted by the photons constituting the light from the Sun. Colombo et. al studied the orbital dynamics of ``smartdust'' under the effects of SRP and atmospheric drag. The numerical model developed here will expand on that work, but will use Hamiltonian equations of motion instead of Gauss’ equations. This approach easily incorporates forces such as drag, SRP and J2 perturbations. Solar radiation pressure is switched off while the particle passes through the Earth's shadow. The model is developed in an EarthCentric Inertial frame, where the Sun and the Moon are averaged to lie in the ecliptic plane with an obliquity of 23.6 degrees. None of the effects of perturbation are averaged, thus this study can provide the entire set of initial orbital elements of particles in Earthorbit required to ensure a long lifespan. The differential equations of motion are numerically integrated using MATLAB's prepackaged ode45. These formulations and assumptions are tested against results found in existing literature. The application of this model so far described is to select a set of initial orbital elements that will balance the dissipative effects of drag with coupling of SRP, J2 and Moon's gravity, thereby ensuring longer orbital lifetimes. The methodology employs Montecarlo simulations over the possible regime of some known initial conditions, while varying the others. A ``goldilocks'' region is chosen by superimposing the results from different Montecarlo runs that produce the least departure from the initial set of orbital elements at the end of one simulated orbit. These orbits are conjectured to have the longest lifespans; in a sample calculation, the orbital lifetime was increased by ~30 times by selecting a set of initial elements from this ``goldilocks'' region, as compared to an arbitrary set of initial conditions outside it. The eventual goal of this work is to aid precise orbital propagation of swarms of nanosatellites through the use of heavier computational resources. Due to the nonspecific nature of all parameters used, this model can also be utilized for missions at other planetary bodies or those in lunar orbit. Inclusion of higherorder integrators or variational integrators (over the RungeKutta methods used here) may improve accuracy. 
Issue Date:  201212 
URI:  http://hdl.handle.net/2142/42385 
Rights Information:  Copyright 2012 Bindu Jagannatha 
Date Available in IDEALS:  20130203 
Date Deposited:  201212 
This item appears in the following Collection(s)

Dissertations and Theses  Aerospace Engineering

Graduate Dissertations and Theses at Illinois
Graduate Theses and Dissertations at Illinois