Directional gyro indicator system

Claim 2

In an aircraft display including a generally horizontal barrel having a heading card and a bearing supporting the barrel at the rear end thereof for rotation about the axis of the barrel, the improvement comprising: a single roller rotatable about a fixed axis and disposed underneath the barrel to rotatably support the barrel, a pair of rollers spaced apart on the upper portion of the barrel for rotatable support of the barrel, and means for adjusting the relative position of said pair of rollers in order to enable centering of the heading card.

Claim 3

The combination of claim 1 wherein said adjusting means comprises: a fixed bracket, adjustment screws disposed through said fixed bracket, and extensions connected to said pair of rollers for threadedly receiving said screws to enable adjustment of said rollers relative to said fixed bracket.

Claim 4

The combination of claim 2 and further comprising: bracket means for rigidly interconnecting said pair of rollers.

Claim 5

The combination of claim 2 wherein said single roller and said pair of rollers are equally spaced about the periphery of said barrel.

Claim 6

A directional gyro indicator for aircraft comprising: a generally horizontal barrel having a heading card disposed normal to the barrel axis and located at the front end of said barrel, a bearing supporting said barrel at the rear end thereof to enable rotation of said barrel about the barrel axis, a roller rotatable about a fixed axis and disposed underneath said barrel to support said barrel, a plurality of rollers disposed on the upper side of said barrel and adjustable to enable centering of said heading card, a directional gyro supported behind said barrel, a tracking disk rotatably mounted on a vertical outer gimbal axis of said gyro, a pickoff for generating an error signal representative of the angular displacement between said tracking disk and said outer gimbal. transmission means coupling said disk and said barrel for equal rotation of said disk and barrel, and a servo motor drive for said transmission means responsive to an error signal generated from said pickoff for slaving said disk to said gyro.

Claim 7

A directional gyro indicator for aircraft comprising: a generally horizontal barrel having a heading card disposed normal to the barrel axis and located at the front end of said barrel, a bearing supporting said barrel at the rear end thereof to enable rotation of said barrel about the barrel axis, a roller rotatable about a fixed axis and disposed underneath said barrel to support said barrel, a plurality of rollers disposed on the upper side of said barrel and adjustable to enable centering of said heading card, a directional gyro supported behind said barrel, a tracking disk rotatably mounted on a vertical outer gimbal axis of said gyro, a pickoff for generating an error signal representative of the angular displacement between said tracking disk and said outer gimbal. transmission means coupling said disk and said barrel for equal rotation of said disk and barrel, and a servo motor drive for said transmission means responsive to an error signal generated from said pickoff for slaving said disk to said gyro.

Claim 8

The gyro indicator of claim 5 wherein said plurality of rollers comprises: a pair of rollers rotatable about spaced apart axes, and means for adjusting the position of said axes.

Claim 9

The gyro indicator of claim 6 wherein said adjusting means comprises: threaded bolts interconnecting said axes with a fixed housing.

Claim 10

The gyro indicator of claim 6 and further comprising: yoke means for rigidly interconnecting the axes of said pair of rollers.

Claim 11

A directional gyro indicator for aircraft comprising: a generally horizontal barrel having a radial flange intermediate its length and a heading card on the front end of said barrel, a single bearing supporting said barrel at the rear end thereof to enable rotation of said barrel, three rollers spaced about the periphery of said barrel for supporting and positioning said barrel by surface contact therewith, one of said rollers being disposed underneath said barrel and the other two said rollers being disposed on the upper portion of said barrel and being adjustable to enable centering of said heading card, a directional gyro supported behind said barrel, a tracking disk rotatably mounted on a vertical outer gimbal axis of said gyro, a pickoff for detecting the angular displacement between said tracking disk and said outer gimbal, a first flanged cylinder mounted on said barrel with the flanged surface facing one surface of said radial flange on said barrel, compression means normally biasIng said surfaces together to clutch said cylinder to said barrel, a belt coupling said disk and said first flanged cylinder for equal rotation of said cylinder and disk, a servo motor drive for said belt responsive to an error signal from said pickoff for slaving said disk to said gyro, and a rotatable slideable shaft mounted parallel to the axis of said barrel and coupled to said compression means to declutch the flanges upon slide movement of said shaft and coupled to said barrel to rotate said barrel upon rotation of said shaft.

Claim 12

A directional gyro indicator for aircraft comprising: a generally horizontal barrel having a radial flange intermediate its length and a heading card on the front end of said barrel, a single bearing supporting said barrel at the rear end thereof to enable rotation of said barrel, three rollers spaced about the periphery of said barrel for supporting and positioning said barrel by surface contact therewith, one of said rollers being disposed underneath said barrel and the other two said rollers being disposed on the upper portion of said barrel and being adjustable to enable centering of said heading card, a directional gyro supported behind said barrel, a tracking disk rotatably mounted on a vertical outer gimbal axis of said gyro, a pickoff for detecting the angular displacement between said tracking disk and said outer gimbal, a first flanged cylinder mounted on said barrel with the flanged surface facing one surface of said radial flange on said barrel, compression means normally biasIng said surfaces together to clutch said cylinder to said barrel, a belt coupling said disk and said first flanged cylinder for equal rotation of said cylinder and disk, a servo motor drive for said belt responsive to an error signal from said pickoff for slaving said disk to said gyro, and a rotatable slideable shaft mounted parallel to the axis of said barrel and coupled to said compression means to declutch the flanges upon slide movement of said shaft and coupled to said barrel to rotate said barrel upon rotation of said shaft.

Claim 13

The gyro indicator of claim 9 wherein said rollers disposed on the upper portion of said barrel are rotatable about axes rigidly interconnected with one another.

Claim 14

The gyro indicator of claim 9 wherein said three rollers are spaced equidistantly about the periphery of said barrel.