Abstract
An inexpensive attitude heading reference system for general aviation applications is developed by fusing automotive grade inertial sensors with global positioning system (GPS). The inertial sensor suit consists of three orthogonally mounted solid state rate gyros. GPS is used for attitude determination in a triple antenna ultra short baseline configuration and a complementary filter is also used to combine the information from the inertial sensors with the attitude information derived from GPS. In a series of ground and flight tests, it was shown that the system has an accuracy better than 0.2 degrees in yaw, pitch and roll. Data collected during laboratory testing is used to construct error models for the inertial sensors.
| Original language | English (US) |
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| Title of host publication | Record - IEEE PLANS, Position Location and Navigation Symposium |
| Editors | Anon |
| Publisher | IEEE |
| Pages | 518-525 |
| Number of pages | 8 |
| State | Published - Jan 1 1998 |
| Event | Proceedings of the 1998 IEEE Position Location and Navigation Symposium - Palm Springs, CA, USA Duration: Apr 20 1996 → Apr 23 1996 |
Other
| Other | Proceedings of the 1998 IEEE Position Location and Navigation Symposium |
|---|---|
| City | Palm Springs, CA, USA |
| Period | 4/20/96 → 4/23/96 |