| 摘要 |
Method of determination, by an inertial system, of a measurement of the attitude of an aircraft consisting at least in determining the angle of pitch .theta. and/or the angle of heading .PSI. and/or the angle of roll .phi. of the said aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative, the said second derivative being determined as the difference between the acceleration measurements delivered by two matched accelerometers, divided by the sum of the respective distances between the said accelerometers and the centre of gravity G of the said inertial system, the pair of accelerometers used for the determination of the angle of pitch .theta. being disposed on either side of the centre of gravity G along an axis x substantially merged with the longitudinal axis of the aircraft, the pair of accelerometers used for the determination of the angle of heading .PSI. being disposed on either side of the centre of gravity G along an axis y substantially merged with the transverse axis of the aircraft, the pair of accelerometers used for the determination of the angle of roll .phi. being disposed on either side of the centre of gravity G along a vertical axis z perpendicular to the plane formed by the x and y axes.
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