Patent ID: 10415995

Abstract:
An inertial measurement system for aircraft, the system comprising at least one processor unit connected to at least two inertial units, namely at least one inertial unit of a first type having at least three angular sensors and three linear sensors aligned on three substantially distinct sensing axes, and an inertial unit of a second type comprising at least four angular sensors and four linear sensors aligned on four substantially distinct sensing axes. The system is arranged to calculate one piece of inertial data from the six sensors of the inertial unit of the first type and four pieces of inertial data from four distinct combinations of three angular sensors and three linear sensors selected from the sensors of the inertial unit of the second type, and the processor unit is arranged to compare the four pieces of inertial data from the measurements of the inertial unit of the second type with one another so as to determine whether the inertial unit of the second type has failed.