Aircraft gyrohorizon indicator with signal lamp positional attitude indicating means

Claim 1

A device for signalling departure beyond predetermined limits from straight and level flight as indicated by a gyrohorizon instrument having a casing, an outer gimbal pivotally journalled within the casing, the relative rotational position thereof, with respect to the casing, being determinative of deviation of an aircraft in the roll axis, and an inner gimbal, pivotally journalled within the outer gimbal about an axis perpendicular to the journal axis of the outer gimbal, the relative rotational position thereof, with respect to the outer gimbal, being determinative of deviation of an aircraft in the pitch axis; the combination comprising, a first pair of signal lamps indicating, when energized, ''''nose up'''' and ''''nose down'''' aircraft positional attitude, respectively, in the pitch axis, a second pair of signal lamps for indicating, when energized, ''''left wing down'''' and ''''right wing down'''' aircraft positional attitude, respectively, in the roll axis, a first means controlled by the relative position of said inner gimbal with respect to said outer gimbal for selectively energizing one or the other of said first signal lamps in accordance with corresponding ''''nose up'''' and ''''nose down'''' aircraft positional attitude, a second means controlled by the relative position of said outer gimbal with respect to said casing for selectively energizing one or the other of said second pair of signal lamps in accordance with corresponding ''''left wing down'''' and ''''right wing down'''' aircraft positional attitude, said first energizing means comprising a first energizing circuit for each of said first pair of signal lamps, normally open-circuit first switch means in each of said first energizing circuits, means controlled by the relative movement of said inner gimbal with respect to said outer gimbal in one direction or the other to selectively actuate said first switch means, second energizing circuits for each of said second pair of signal lamps, normally open-circuit second switch means in each of said second energizing circuits, means controlled by the relative movement of said outer gimbal with respect to said casing in one direction or the other to selectively actuate said second switch means, said means for actuating said first switch means comprising a first arcuate contact member coaxially arranged with respect to the axis of rotation of said inner gimbal and fixed thereto for rotation in unison therewith, and a first pair of electrical brush members, one at each side of said first arcuate conductor and adapted to make selective contact therewith at their outer ends said brush members being indiviDually adjustably secured at their inner ends with respect to said outer gimbal.

Claim 2

A device for signalling departure beyond predetermined limits from straight and level flight as indicated by a gyrohorizon instrument having a casing, an outer gimbal pivotally journalled within the casing, the relative rotational position thereof, with respect to the casing, being determinative of deviation of an aircraft in the roll axis, and an inner gimbal, pivotally journalled within the outer gimbal about an axis perpendicular to the journal axis of the outer gimbal, the relative rotational position thereof, with respect to the outer gimbal, being determinative of deviation of an aircraft in the pitch axis; the combination comprising, a first pair of signal lamps indicating, when energized, ''''nose up'''' and ''''nose down'''' aircraft positional attitude, respectively, in the pitch axis, a second pair of signal lamps for indicating, when energized, ''''left wing down'''' and ''''right wing down'''' aircraft positional attitude, respectively, in the roll axis, a first means controlled by the relative position of said inner gimbal with respect to said outer gimbal for selectively energizing one or the other of said first signal lamps in accordance with corresponding ''''nose up'''' and ''''nose down'''' aircraft positional attitude, a second means controlled by the relative position of said outer gimbal with respect to said casing for selectively energizing one or the other of said second pair of signal lamps in accordance with corresponding ''''left wing down'''' and ''''right wing down'''' aircraft positional attitude, said first energizing means comprising a first energizing circuit for each of said first pair of signal lamps, normally open-circuit first switch means in each of said first energizing circuits, means controlled by the relative movement of said inner gimbal with respect to said outer gimbal in one direction or the other to selectively actuate said first switch means, second energizing circuits for each of said second pair of signal lamps, normally open-circuit second switch means in each of said second energizing circuits, means controlled by the relative movement of said outer gimbal with respect to said casing in one direction or the other to selectively actuate said second switch means, said means for actuating said first switch means comprising a first arcuate contact member coaxially arranged with respect to the axis of rotation of said inner gimbal and fixed thereto for rotation in unison therewith, and a first pair of electrical brush members, one at each side of said first arcuate conductor and adapted to make selective contact therewith at their outer ends said brush members being indiviDually adjustably secured at their inner ends with respect to said outer gimbal.