Turn rate indicator of aircraft using gyroscope

Claim 1

An aircraft turn rate indicator including a gyroscope having freedom of rotation around at least one axis, comprising: a housing including an annular member adapted to be secured to the body of said aircraft; a gimbal mounted within said housing and rotatable with respect to said annular member, said gimbal being returnable to a reference position; a motor stator having a central axle supported by said gimbal, said stator including a plurality of coils and Hall elements, the central axle of said motor stator being parallel to the pitch axis of said aircraft when said aircraft is not turning; an outer motor rotor rotatably supported by the central axle of said motor stator at the outer periphery of said stator; a Hall motor control circuit integrally supported by said gimbal, said control circuit including a plurality of semiconductor devices each thermally coupled to said gimbal and electrically connected to corresponding coils and Hall elements of said motor stator, said semiconductor devices controlling the current through said stator coils in response to signals from said Hall elements; a plurality of connecting lines for electrically connecting the coils and Hall elements of said stator to said control circuit; power supply lines for connecting said control circuit to a power source terminal integrally mounted to said housing; and a pointer driven by said gimbal in accordance with the angular displacement of said gimbal with respect to said annular member.