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CONTROLS ALGORITHM FOR A SATELLITE USING EARTH''S MAGNETIC FIELD: ORBIT MANEUVERS & ATTITUDE POSITIONING
Title
CONTROLS ALGORITHM FOR A SATELLITE USING EARTH''S MAGNETIC FIELD: ORBIT MANEUVERS & ATTITUDE POSITIONING.
Creator
Ganesh, Karthik, Johnson, Roger, University of Central Florida
Abstract / Description
This document describes the design, analysis of Orbit Maneuvers and Attitude Control for NanoSat class satellites, which uses an electro-magnetic force controller which was proposed by the Florida Space Institute (FSI). Orbit Maneuvering and the Attitude Control System (ACS) play a very important role for the success of this mission, as that can allow making the satellite go to the desired orbit as well do the sun pointing of the solar arrays with su¢ cient accuracy to achieve desired...
Show moreThis document describes the design, analysis of Orbit Maneuvers and Attitude Control for NanoSat class satellites, which uses an electro-magnetic force controller which was proposed by the Florida Space Institute (FSI). Orbit Maneuvering and the Attitude Control System (ACS) play a very important role for the success of this mission, as that can allow making the satellite go to the desired orbit as well do the sun pointing of the solar arrays with su¢ cient accuracy to achieve desired power levels. The primary mission would be to attain attitude stabilization using the torque from the coils. This is also used for pointing at the direction of the sun, for achieving desired power levels. The secondary mission would be to use the force of the magnetic field and utilize that for orbit maneuvering, and attain the desired trajectory. This thesis gives a presentation of this detailed analysis with a simulation using Matlab/Simulink. Mathematical model of the actuators and sensors used for this satellite are designed, so that the simulation gives us results very near to the actual ones.Health Monitoring is also one of the main issues addressed in this work. This simulation helps us in understanding the mission as well as the requirements very well, and helps us know all the shortcomings. The FUNSAT satellite is modeled as an example in Simulink together with a Kalman filter for attitude estimation based on all sensor measurements. The theory behind this, and extending the Kalman filter, is also presented.
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Date Issued
2007
Identifier
CFE0001917, ucf:47476
Format
Document (PDF)
PURL
http://purl.flvc.org/ucf/fd/CFE0001917
AN ALGORITHM FOR DETERMINING SATELLITE ATTITUDE BY COMPARING PHYSICAL FEATURE MODELS TO EDGES DETECTED IN SATELLITE OR GROUND-BASED TELESCOPE IMAGERY
Title
AN ALGORITHM FOR DETERMINING SATELLITE ATTITUDE BY COMPARING PHYSICAL FEATURE MODELS TO EDGES DETECTED IN SATELLITE OR GROUND-BASED TELESCOPE IMAGERY.
Creator
Reinhart, Eric, Johnson, Roger, University of Central Florida
Abstract / Description
This thesis discusses the development and performance of an algorithm created to calculate satellite attitude based on the comparison of satellite "physical feature" models to information derived from edge detection performed on imagery of the satellite. The quality of this imagery could range from the very clear, close-up imagery that may come from an unmanned satellite servicing mission to the faint, unclear imagery that may come from a ground-based telescope investigating a satellite...
Show moreThis thesis discusses the development and performance of an algorithm created to calculate satellite attitude based on the comparison of satellite "physical feature" models to information derived from edge detection performed on imagery of the satellite. The quality of this imagery could range from the very clear, close-up imagery that may come from an unmanned satellite servicing mission to the faint, unclear imagery that may come from a ground-based telescope investigating a satellite anomaly. Satellite "physical feature" models describe where an edge is likely to appear in an image. These are usually defined by physical edges on the structure of the satellite or areas where there are distinct changes in material property. The theory behind this concept is discussed as well as two different approaches to implement it. Various simple examples are used to demonstrate the feasibility of the concept. These examples are well-controlled image simulations of simple physical models with known attitude. The algorithm attempts to perform the edge detection and edge registration of the simulated image and calculate the most likely attitude. Though complete autonomy was not achieved during this effort, the concept and approach show applicability.
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Date Issued
2007
Identifier
CFE0001942, ucf:47450
Format
Document (PDF)
PURL
http://purl.flvc.org/ucf/fd/CFE0001942
MODELING SATELLITE FORMATIONS IN THE PRESENCE OF PERTURBATIONS
Title
MODELING SATELLITE FORMATIONS IN THE PRESENCE OF PERTURBATIONS.
Creator
Cannaday, Robert, Johnson, Roger, University of Central Florida
Abstract / Description
The potential benefits of autonomous satellite formation flying in such areas as high- resolution remote sensing, and sparse aperture radar, has stimulated interest in modeling the satellite environment for feasibility and simulation studies to help explore and define the technical challenges that must be solved in order to achieve successful autonomous satellite formations. The purpose of this paper is to develop and describe a numerical simulation of the orbital environment including...
Show moreThe potential benefits of autonomous satellite formation flying in such areas as high- resolution remote sensing, and sparse aperture radar, has stimulated interest in modeling the satellite environment for feasibility and simulation studies to help explore and define the technical challenges that must be solved in order to achieve successful autonomous satellite formations. The purpose of this paper is to develop and describe a numerical simulation of the orbital environment including central force field perturbations and atmospheric drag effects which will be a useful analytical tool for investigating issues relating to maintaining satellite formations in low-earth-orbit. Many of the studies done in this area confine their research to circular orbits, with and without perturbation effects. This study will investigate apply orbital dynamic equations to the problem of maintaining satellite formations in both circular and elliptical orbits, with and without the presence of J2 gravity perturbation effects and atmospheric drag. This effort is primarily focused on modeling the orbital mechanics of one and two satellites in the presence of J2 and drag perturbations This effort is being performed as part of a multi-disciplined University of Central Florida KnightSat project, sponsored by the Air Force, to develop a two-satellite formation in the nanosatellite class, for investigating issues related to using formation satellites for remote earth sensing, to develop three-dimensional mapping.
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Date Issued
2005
Identifier
CFE0000898, ucf:46639
Format
Document (PDF)
PURL
http://purl.flvc.org/ucf/fd/CFE0000898
AUTONOMOUS CONTROLS ALGORITHMFOR FORMATION FLYING OF SATELLITES
Title
AUTONOMOUS CONTROLS ALGORITHMFOR FORMATION FLYING OF SATELLITES.
Creator
Santiago, Luis, Johnson, Roger, University of Central Florida
Abstract / Description
This document describes the design and analysis of the Navigation, Guidance and Control System for the KnightSat project. The purpose for the project is to test and demonstrate new technologies the Air Force would be interested in for research and development. The primary mission of KnightSat is to show how a constellation of satellites can maintain relative position with each other autonomously using the Microwave Electro Thermal (MET) thruster. The secondary mission is to use multiple...
Show moreThis document describes the design and analysis of the Navigation, Guidance and Control System for the KnightSat project. The purpose for the project is to test and demonstrate new technologies the Air Force would be interested in for research and development. The primary mission of KnightSat is to show how a constellation of satellites can maintain relative position with each other autonomously using the Microwave Electro Thermal (MET) thruster. The secondary mission is to use multiple satellite imagery to obtain 3 dimensional stereo photographs of observable terrain. Formation flying itself has many possible uses for future applications. Selected missions that require imaging or data collection can be more economically accomplished using smaller multiple satellites. The MET thruster is a very efficient, but low thrust alternative that can provide thrust for a very long time, hence provide the low thrust necessary to maintain the satellites at a constant separation. The challenge is to design a working control algorithm to provide the desired output data to be used to command the MET thrusters. The satellites are to maintain a constant relative distance from each other, and use the least amount of fuel possible. If one satellite runs out of fuel before the other, it would render the constellation less useful or useless. Hence, the satellites must use the same amount of fuel in order to maintain an optimal operational duration on orbit.
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Date Issued
2006
Identifier
CFE0001171, ucf:46854
Format
Document (PDF)
PURL
http://purl.flvc.org/ucf/fd/CFE0001171