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Master's Projects

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search.filters.applied.f.advisor: Gunter, Brian C. × End date: 2016 × Start date: 2010 × Item Type: Publication ×

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Now showing 1 - 10 of 11
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    The Development and Characterization of the Laser Ranging System on the RANGE CubeSat Mission
    (Georgia Institute of Technology, 2016-12-15) Levine, Zachary A.
    In Spring 2016, Georgia Tech Space Systems Design Laboratory (SSDL) will begin operations on the Ranging And Nanosatellite Guidance Experiment (RANGE) Mission. A crucial element of this mission is the Inter satellite ranging system. This system will determine the relative distance between the two RANGE sister CubeSats providing validation that such a system can function in orbit on a CubeSat. This document describes the factors considered in choosing the Voxtel Laser Range Finder (LRF) Module as the flight unit for both satellites, the integration and testing of this system, and the preliminary analysis of laboratory testing data to predict on-orbit performance.
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    Initial Characterization for LIDAR Remote Sensing from an UAV Platform
    (Georgia Institute of Technology, 2016-12) Lacerda, Michel Alves
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    Initial Characterization for LIDAR Remote Sensing from an UAV Platform
    (Georgia Institute of Technology, 2016-12) Lacerda, Michel Alves
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    Design and Application of a Circular Aperture Sun Sensor
    (Georgia Institute of Technology, 2016-12) Herman, Michael
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    The Development and Characterization of the Laser Ranging System on the RANGE CubeSat Mission
    (Georgia Institute of Technology, 2016-12) Levine, Zachary A.
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    Design and Application of a Circular Aperture Sun Sensor
    (Georgia Institute of Technology, 2016-12) Herman, Michael
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    The Development and Characterization of the Laser Ranging System on the RANGE CubeSat Mission
    (Georgia Institute of Technology, 2016-12) Levine, Zachary A.
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    Refinements to the General Methodology Behind Strapdown Airborne Gravimetry
    (Georgia Institute of Technology, 2016-08-05) Seywald, Kevin Lee
    Measuring Earth’s gravitational field has important applications in fields ranging from geodesy to exploration geophysics. Gravity field disturbances are typically no more than 100 mGal, hence requiring extremely precise sensors. The estimation of error sources inherent in these sensors, such as bias, scale factor, and drift rate, significantly improve the accuracy of these measurements, allowing for more precise gravity estimates. This research builds upon prior work using a strapdown Inertial Navigation System (INS) paired with Global Positioning Systems (GPS) for airborne platforms. In order to test and validate the processing algorithms, various simulated test cases were created. Several refinements were made to the traditional approach found in the literature, making the process more robust. Most notably, an analytical solution was developed for the quaternion integration problem, which is typically implemented using numerical methods. The analytical solution limits the integration error to machine precision, and removes any error propagation. Furthermore, the error equations implemented in the Kalman Filter were refined such that they better capture the true dynamics of the error-states. These changes to the existing methodology were validated by the proposed algorithm’s ability to accurately estimate the parameters used to generate the simulated flight data.
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    Refinements to the General Methodology Behind Strapdown Airborne Gravimetry
    (Georgia Institute of Technology, 2016-08) Seywald, Kevin Lee
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    Orbit Design for a Phobos-Deimos Cycler Mission
    (Georgia Institute of Technology, 2016-04-16) Sabitbek, Bolys
    Little is know about the Martian moons Phobos and Deimos, even though they have the potential to provide insight into the evolution of the Martian system, and could potentially serve as a staging site for a future Mars manned mission. While attempts to visit Phobos with dedicated missions have been attempted, to date none have been successful, and no dedicated mission to Deimos has been flown. As such, much of what is known about the structure and composition of either moon comes from a small collection of images. This study explores a class of stable cycler orbits that could visit both moons on a regular cadence, and can be tuned to fly-by one moon more frequently, or to vary the ground track coverage to obtain improved surface coverage. While the orbits described can be reached by a dedicated spacecraft with sufficient delta-V for a Mars insertion, the moti vation here is that the spacecraft is already in an initial insertion orbit, such as a small-satellite rideshare on an existing Mars mission. Under this assumption, the results presented illustrate that the exploration of both Phobos and Deimos can be achieved with a spacecraft with capabilities of modern nanosatellites (cubesats).