Navigation instrument

Claim 2

An aircraft instrument for generating navigation information comprising: a first element; means for coupling said first element to a gyro to be driven thereby; first transducer means for generating a signal representative of the position of said first element relative to a reference; a second element; means for coupling said second element to said first element for co-movement therewith, said means for coupling including means for de-coupling and relatively rotating said second element with reference to said first element; second transducer means for generating a signal representative of the position of said second element relative to said reference; and means for generating a signal varying with the differential between said first and second transducer means signals and varying with the relative position of said first and second elements.

Claim 3

The aircraft instrument of claim 1 wherein said first element is an aircraft heading card and said second element is an omni needle, and wherein said means for coupling includes means for positioning said omni needle relative to said aircraft heading card to select an omni bearing.

Claim 4

The aircraft instrument of claim 1 wherein said first element is an aircraft heading card and said second element is a navigation indicator, and wherein said means for coupling includes means for positioning said navigation indicator relative to said aircraft heading card to select a navigation course.

Claim 5

The aircraft instrument of claim 1 further comprising: a third element; means for coupling said third element to said first element for co-movement therewith, said means for coupling said third element including means for de-coupling and relatively rotating said third element with reference to said first element; and third transducer means for generating a signal representative of the positioning of said third element relative to a fixed third element reference.

Claim 6

The aircraft instrument of claim 4 wherein said first element is an aircraft heading card, said second element is an omni needle, and said third element is an autopilot command heading marker, said omni needle and said autopilot command heading marker being positionable by said means for coupling said second element and said means for coupling said third element, respectively, relative to said aircraft heading card.

Claim 7

The aircraft instrument of claims 2, 3 or 5 further comprising gear transmission means for coupling said gyro to said aircraft heading card.

Claim 8

The aircraft instrument as set forth in claim 4 wherein said means for de-coupling includes a clutch for coupling said third element to said first element, and means for energizing said clutch to disengage the coupling between the first element and the third element.

Claim 9

An aircraft instrument for generating navigation information comprising: (a) a frame; (b) an aircraft heading card mounted in said frame for rotation about a main axis; (c) a gyro supported in said frame behind said aircraft heading card having an outer gimbal disposed on a first axis; (d) gear drive means for coupling said gyro to said heading card, such that said heading card rotates with said gyro in a one-to-one relationship; (e) a heading transducer coupled to said gear drive means which generates a signal varying with the position of said heading card relative to said frame; (f) a navigation indicator mounted in said frame for rotation about said main axis; (g) a navigation indicator transducer coupled to said navigation indicator for generating a signal varying with the position of said navigation indicator relative to said frame; and (h) means for coupling said navigation indicator to said heading card for co-rotation, said coupling means including means for disengaging and relatively positioning said navigation indicator relative to said heading card such that the position of said navigation indicator relative to said heading card may be determined by sensing a differential between said heading transducer signal and said navigation indicator transducer signal.

Claim 10

An aircraft instrument for generating navigation information comprising: (a) a frame; (b) an aircraft heading card mounted in said frame for rotation about a main axis; (c) a gyro supported in said frame behind said aircraft heading card having an outer gimbal disposed on a first axis; (d) gear drive means for coupling said gyro to said heading card, such that said heading card rotates with said gyro in a one-to-one relationship; (e) a heading transducer coupled to said gear drive means which generates a signal varying with the position of said heading card relative to said frame; (f) a navigation indicator mounted in said frame for rotation about said main axis; (g) a navigation indicator transducer coupled to said navigation indicator for generating a signal varying with the position of said navigation indicator relative to said frame; and (h) means for coupling said navigation indicator to said heading card for co-rotation, said coupling means including means for disengaging and relatively positioning said navigation indicator relative to said heading card such that the position of said navigation indicator relative to said heading card may be determined by sensing a differential between said heading transducer signal and said navigation indicator transducer signal.

Claim 11

The aircraft instrument of claim 8 wherein said coupling means includes a spring-loaded friction clutch such that during normal operation a high friction relationship exists between said heading card and said navigation indicator thereby causing co-rotation, and said navigation course selector means being operable to disengage said friction clutch to allow low-friction relative rotation between said heading card and said navigation indicator.

Claim 12

The aircraft instrument of claim 8 further comprising: (a) a heading marker disengagably coupled to said aircraft heading card for co-movement therewith; and (b) means for disengaging the heading marker from said aircraft heading card to vary the relative position therebetween.

Claim 13

The aircraft instrument as set forth in claim 10 wherein said means for disengaging includes a clutch for coupling said heading marker to said heading card, and means for energizing said clutch to disengage the coupling between the heading card and the heading marker.

Claim 14

A horizontal situation indicator for an aircraft, said indicator having a frame, a rotatable gyro-driven heading card, and a rotatable navigation indicator, and coupling means for disengaging and relatively positioning the navigation indicator relative to the heading card, comprising: (a) first signal generating means engaged with the heading card and providing an output varying with the heading card position relative the frame; (b) second signal generating means engaged with the navigation indicator and providing an output varying with the navigation indicator position relative the frame; and (c) means responsive to the differential between the output of said first and second signal generating means to indicate the relative position of said heading card with reference to said navigation indicator.

Claim 15

A horizontal situation indicator for an aircraft, said indicator having a frame, a rotatable gyro-driven heading card, and a rotatable navigation indicator, and coupling means for disengaging and relatively positioning the navigation indicator relative to the heading card, comprising: (a) first signal generating means engaged with the heading card and providing an output varying with the heading card position relative the frame; (b) second signal generating means engaged with the navigation indicator and providing an output varying with the navigation indicator position relative the frame; and (c) means responsive to the differential between the output of said first and second signal generating means to indicate the relative position of said heading card with reference to said navigation indicator.

Claim 16

The horizontal situation indicator of claim 12 further comprising drive means for coupling said heading card to the gyro for synchronous movement and nonslippage therebetween.

Claim 17

The horizontal situation indicator of claim 13 further comprising selectively disengagable friction clutch means between said heading card and said navigation indicator disposed such that said setting means is operable to disengage said clutch means before setting force is applied to said navigation indicator.

Claim 18

The horizontal situation indicator of claim 12 further including an autopilot command heading marker mounted for co-movement with the heading card and further comprising: means for disengageably coupling the command heading marker to the heading card for co-movement therewith; means for moving the heading marker relative to the heading card when said heading marker has been disengaged from co-movement with said heading card; and third signal generating means for generating a signal representative of the position of the command heading marker relative to the frame.

Claim 19

The horizontal situation indicator as set forth in claim 15 wherein said means for disengagably coupling includes means for moving the heading marker relative to the heading card.

Claim 20

The horizontal situation indicator as set forth in claim 15 wherein said means for disengagably coupling includes a clutch for coupling the heading marker to the heading card, and means for energizing said clutch to disengage the coupling between the heading marker and the heading card.