Show simple item record

dc.contributor.authorKeil, Elizabeth Marieen
dc.date.accessioned2014-06-24T08:00:37Zen
dc.date.available2014-06-24T08:00:37Zen
dc.date.issued2014-06-23en
dc.identifier.othervt_gsexam:3092en
dc.identifier.urihttp://hdl.handle.net/10919/49102en
dc.description.abstractThis thesis details the development and implementation of an attitude and orbit determining Kalman filter algorithm for a satellite in a Molniya orbit. To apply the Kalman Filter for orbit determination, the equations of motion of the two body problem were propagated using Cowell's formulation. Four types of perturbing forces were added to the propagated model in order to increase the accuracy of the orbit prediction. These four perturbing forces are Earth oblateness, atmospheric drag, lunar gravitational forces and solar radiation pressure. Two cases were studied, the first being the implementation of site track measurements when the satellite was over the ground station. It is shown that large errors, upwards of ninety meters, grow as time from last measurement input increases. The next case studied was continuous measurement inputs from a GPS receiver on board the satellite throughout the orbit. This algorithm greatly decreased the errors seen in the orbit determining algorithm due to the accuracy of the sensor as well as the continuous measurement inputs throughout the orbit. It is shown that the accuracy of the orbit determining Kalman filter also depends on the length of time between each measurement update. The errors decrease as the time between measurement updates decreases. Next the Kalman filter is applied to determine the satellite attitude. The rotational equations of motion are propagated using Cowell's Formulation and numerical integration. To increase the fidelity of the model four disturbing torques are included in the rotational equations of motion model: gravity gradient torque, solar pressure torque, magnetic torque, and aerodynamic torque. Four cases were tested corresponding to four different on board attitude determining sensors: magnetometer, Earth sensor, sun sensor, and star tracker. A controlled altitude path was chosen to test the accuracy of each of these cases and it was shown that the algorithm using star tracker measurements was three hundred times more accurate than that of the magnetometer algorithm.en
dc.format.mediumETDen
dc.publisherVirginia Techen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectAttitudeen
dc.subjectOrbiten
dc.subjectDeterminationen
dc.subjectKalman Filteren
dc.titleKalman Filter Implementation to Determine Orbit and Attitude of a Satellite in a Molniya Orbiten
dc.typeThesisen
dc.contributor.departmentAerospace and Ocean Engineeringen
dc.description.degreeMaster of Scienceen
thesis.degree.nameMaster of Scienceen
thesis.degree.levelmastersen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.disciplineAerospace Engineeringen
dc.contributor.committeechairMcGwier, Robert W.en
dc.contributor.committeememberWoolsey, Craig A.en
dc.contributor.committeememberSultan, Cornelen


Files in this item

Thumbnail

This item appears in the following Collection(s)

Show simple item record