Aircraft position integrity for Differential Satellite-based Navigation in the presence of both bias and noise errors

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dc.contributor.advisor van Graas, Frank en_US
dc.contributor.author Suddapalli, Rajesh en_US
dc.date.accessioned 2008-07-08T17:20:36Z
dc.date.available 2008-07-08T17:20:36Z
dc.date.created 2004 en_US
dc.date.issued 2008-07-08T17:20:36Z
dc.identifier.uri http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1108478721 en_US
dc.identifier.uri http://hdl.handle.net/2374.OX/13642
dc.description To provide integrity for differential satellite-based navigation, the Navigation Sensor Error (NSE) must be bounded. To accommodate non-zero ranging bias errors, a new approach is introduced, which treats ranging noise and bias errors separately. Both weighted and unweighted least squares solutions are evaluated with respect to the bounding of noise and bias errors. Various worst cases of satellite geometries are investigated through computer simulation by implementing the current 24 optimized GPS satellite constellation. en_US
dc.format application/pdf en_US
dc.format 79p. en_US
dc.rights unrestricted en_US
dc.rights Copyright and permissions information available at the source archive en_US
dc.subject LAAS en_US
dc.subject Integrity Monitoring en_US
dc.subject Satellite Ranging Errors en_US
dc.subject GPS - LAAS en_US
dc.subject Compiling Biases en_US
dc.subject LAAS Monitoring en_US
dc.title Aircraft position integrity for Differential Satellite-based Navigation in the presence of both bias and noise errors en_US
dc.type Electronic Thesis or Dissertation en_US
dc.degree.name MS en_US
dc.degree.level masters en_US
dc.degree.discipline Electrical Engineering (Engineering) en_US
dc.degree.grantor Ohio University en_US
dc.contributor.publisher Ohio University / OhioLINK en_US

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