Method and system for determining the attitude of an aircraft by multi-axis accelerometric measurements
US8655511B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 29, 2012 |
| Grant date | Feb 18, 2014 |
| Priority date | — |
| Expiry date | Aug 9, 2032 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01C21/188
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.