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Daniel Guggenheim School of Aerospace Engineering
Daniel Guggenheim School of Aerospace Engineering
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ItemRelative Positioning and Tracking of Tethered Small Spacecraft Using Optical Sensors(Georgia Institute of Technology, 2018-12) Guo, Yanjie
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ItemA Preliminary Assessment of the RANGE Mission's Orbit Determination Capabilities(Georgia Institute of Technology, 2018-08) Claybrook, Austin W.
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ItemA scalable hardware-in-the-Loop simulation for satellite constellations and other multi-agent networks(Georgia Institute of Technology, 2018-05-01) DeGraw, Christopher F.
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ItemAttitude Dynamics of a Tethered CubeSat-Inflatable System in Low Earth Orbi(Georgia Institute of Technology, 2018-04-26) Boisvert, Alexander J.This paper analyzes the attitude dynamics of an inflatable tetrahedron tethered to a 3U CubeSat via a 10 meter tether. In previously flown space tether missions the primary moment on the system being considered is the gravity gradient torque. In this analysis, however, the large area to mass ratio of the target increases the impact of drag and solar radiation moments so they are also examined. The dynamics of the deployed system was analyzed using the 42 spacecraft simulator, an open source simulation software developed by NASA Goddard. Both single and 10 element tethers were analyzed at altitudes ranging from 300 kilometers to 600 kilometers. They system showed the potential to develop unstable oscillations when uncontrolled but an active damping control scheme shows potential for maintaining the stability of the system. The deployment of the tether is analyzed as a damped spring system in SIMULINK. The deployment is analyzed for three deployment speeds and three potential damping ratios. The impact of this analysis on the requirements for the attitudedetermination and control subsystem are also considered.
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ItemAttitude Dynamics of a Tethered CubeSat-Inflatable System in Low Earth Orbit(Georgia Institute of Technology, 2018-04) Boisvert, Alexander J.
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ItemA Preliminary Assessment of the RANGE Mission’s Orbit Determination Capabilities(Georgia Institute of Technology, 2018-03-08) Claybrook, Austin W.The primary mission object of the Ranging And Nanosatellite Guidance Experiment (RANGE) is the demonstration of precision position determination on the nanosatellite platform expected to launch in late 2018. RANGE consists of two 1.5U CubeSats each with a high precision GNSS receiver. The GNSS receiver on each satellite receives GPS pseudoranges and phases in the civilian L1 and L2 frequencies, which will be used for precision orbit determination. The re ceiver clocks are supplemented by high precision atomic clocks to reduce timing uncertainties. The satellites also host a near proximity laser ranging system to reduce relative in-track orbit uncertainties. A preliminary examination of the RANGE mission’s orbit capabilities suggests a 3σ position uncertainty of less than 10 cm in the radial, intrack and crosstrack direction when taking GPS measurement once per minute. During select times of higher frequency 1 second logging, the 3σ position uncertainty in the radial, intrack and cross track directions may be driven down to the 2.5 cm, 1 cm and 1.5 cm level, respectively. Hardware in the loop simu lations with a GPS signal generator have verified the performance of the CubeSat hardware against the hardware spec sheets and show increased clock stability when the atomic clock is used. Once the RANGE missios has launched, ground based laser ranging measurements provided by the NRL and ILRS will be used to independantly validate the post processed precision orbit determination solutions of the RANGE mission.
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ItemAn Evaluation of Spacecraft Pointing Requirements for Optically Linked Satellite Systems(Georgia Institute of Technology, 2017-08) Dahl, Trevor A.
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ItemAn Evaluation of Spacecraft Pointing Requirements for Optically Linked Satellite Systems(Georgia Institute of Technology, 2017-04-08) Dahl, Trevor A.This study evaluates pointing requirements for free space optical data links of a satellite network. For many applications, optical links pose a distinct advantage over radio frequency (RF) links for their far higher data transmission rates. They can also be much lighter than RF antennas and require far less power, making them ideal transmission methods for small satellites and CubeSats. While more power efficiency is achieved thru narrow beam divergence, the narrower beams pose a technical challenge due to the higher pointing accuracy required for effective transmission. A general method for characterizing pointing tolerance, angular rates and angular accelerations for Line-of-Site (LoS) vectors is devised. Several case studies involving different (single-layer) constellation designs were evaluated. Varying degrees of inclination and offset of true anomaly from one plane to a connecting plane were evaluated and corresponding angular velocity and accelerations are reported. The study finds that the methodology outlined gives crucial information to assess pointing requirements against various constellation designs. This assessment can then drive the trade space for designs for optically linked networks from the hardware aboard each satellite, to the design of the satellite constellation itself.
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ItemThe 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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ItemDesign and Application of a Circular Aperture Sun Sensor(Georgia Institute of Technology, 2016-12) Herman, Michael