초록 ▼

A flight director type of aircraft control or guidance display and mechanism for pilot reference which provides a composite integrated display of roll, pitch and heading with a sensing relationship approximating what the pilot sees through the windshield in the real world environment. The visual cue

A flight director type of aircraft control or guidance display and mechanism for pilot reference which provides a composite integrated display of roll, pitch and heading with a sensing relationship approximating what the pilot sees through the windshield in the real world environment. The visual cue relationship is retained when the display is viewed during flight in obscure visibility with resulting elimination of vertigo and disorientation. The display is remote from its sensors of aircraft control and guidance and may be positioned in a head erect location in the instrument panel. The electro-mechanical display of roll, pitch and heading embodies a roll symbol which is positioned in front of a rotating dial displaying heading that enables control coordination during turns. An associated horizon bar remains parallel to the display base while rising and falling past the roll symbol to indicate a glide or climb respectively. The integrated indicia of aircraft control are closely associated with guidance indications to facilitate effective and precise control or guidance of the aircraft in the approach/landing.

대표청구항 ▼

In an aircraft control and guidance system, an avionics display structure including a base having a plurality of synchro receivers mounted thereon, one synchro receiver including a rotatable shaft having a transverse axis of rotation, arm means affixed to each end of said rotatable shaft, said arm m

In an aircraft control and guidance system, an avionics display structure including a base having a plurality of synchro receivers mounted thereon, one synchro receiver including a rotatable shaft having a transverse axis of rotation, arm means affixed to each end of said rotatable shaft, said arm means having inwardly bent horizontal portions providing a substantially continuous horizon bar for up and down movement parallel to said base for indicating pitch with reference to a horizontally disposed lubbers line, a tandem pair of synchro receivers, each having a shaft, the shaft of one said tandem pair of synchro receivers passing through the shaft of the other along a common longitudinal axis, an aircraft symbol pointer mounted on the shaft of one said tandem pair of synchro receivers for portraying aircraft roll to the right by clockwise rotation thereof and aircraft roll to the left on counterclockwise rotation thereof, the shaft of the other of said tandem pair of synchro receivers having affixed thereto a circular dial for clockwise rotation in response to left aircraft turns and counterclockwise rotation in response to right aircraft turns, said circular dial having delineated thereon a compass rose for indication of aircraft heading and an associated lubbers line; an upstanding fixed partial dial interposed between said circular dial and said horizon bar for partially obscuring the substantive lower portion of said circular dial; a first microammeter, scale and pointer and comprising a course direction indicator; and a second microammeter, vertical scale, and vertically moving pointer and comprising means for selective indication of glide slope, vertical speed and height above touchdown; a first vertical gyro having synchro output for driving said one synchro receiver; a second vertical gyro having synchro output for driving said one of said tandem pair of synchro receivers having said aircraft symbol pointer mounted on the shaft thereof; a directional gyro having synchro output for driving said one of said tandem synchro receivers having said circular dial mounted on the shaft thereof; a VOR/LAC navigation receiver having output for operating said course direction indicator; a glide slope receiver having output for operation of second microammeter in indicating glide slope; a vertical speed sensor having output for operation of said second microammeter in indicating vertical speed; a height-above-touchdown landing altimeter having output for operation of said second microammeter in indicating height above touchdown; switch means for selective operation of said second microammeter by said glide slope receiver and vertical speed sensor; said avionics display structure being contained with a case for viewing thereof; and