The invention relates to an aircraft attitude measurement method based on apparent acceleration coordinate
system registration, which is suitable for a sensor limited or external
signal interference environment. The method comprises the following steps: firstly, acquiring an apparent acceleration
point set of an aircraft under a body coordinate
system and an east-north-
sky coordinate
system, and carrying out
centroid calculation and decentration
processing to obtain standardized data; obtaining an optimal
rotation matrix of the two coordinate systems through
covariance matrix construction and
singular value decomposition; and finally, the
pitch angle, the
yaw angle and the
rolling angle of the aircraft are solved through the
rotation matrix by taking Z-Y-X as a rotation sequence. The method does not depend on an external
satellite signal and a high-precision inertial device, avoids the accumulative error of a traditional
inertial navigation system and the anti-interference defect of a
satellite navigation system, and has the advantages of high
measurement precision (the error is less than or equal to + / -1 degree), high stability, wide adaptability and good
engineering realizability; the method can be widely applied to attitude measurement of various aircrafts such as unmanned aerial vehicles, satellites and missiles.