Attitude correction apparatus and method for inertial navigation system using camera-type solar sensor
US7805244B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 1, 2007 |
| Grant date | Sep 28, 2010 |
| Priority date | — |
| Expiry date | Jul 4, 2029 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01S3/7864
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
Disclosed herein is an attitude correction apparatus for an Inertial Navigation System (INS) using a camera-type solar sensor. The present invention relates to a system for correcting errors occurring in an inertial navigation system, in which inertial sensors, such as gyroscopes and accelerometers are combined with each other to calculate the attitude, velocity and position of an airplane, and to an apparatus for utilizing a sun-line of sight vector, generated by a camera-type solar sensor, that uses images of the moving sun, and the output value of the inertial navigation system, thus correcting the attitude of an airplane and the errors of sensors. The attitude correction apparatus of the present invention includes a camera-type solar sensor for detecting the sun, a signal processing unit for receiving and synchronizing information, and a data collection processing unit for performing post-processing on information, thus correcting an error.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.