Patent US3852710A successfully refreshed from Google Patents.
US3852710A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft gyrohorizon indicator with signal lamp positional attitude indicating means
Assignee: Aircraft Instruments Inc
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Filing: 1972-06-13
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Granted: 1974-12-03
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Expires: 1992-06-13
Abstract
Abstract A combination gyrohorizon instrument for aircraft which visually indicates in addition to the dial display presentation of the instrument, by means of signal lamps appropriately placed with respect to the instrument dial and an audible signal indicative of energization of any one of the signal lamps, departures from straight and level flight that exceed reasonable limits of pitch and bank. The signal lamps, indicating ''''nose up,'''' ''''nose down, '''' ''''left wing down'''' and ''''right wing down'''' are in circuits energized by a first switching means controlled by the relative rotational position of the inner and outer gimbals of the instrument for sensing departure beyond reasonable safety limits in one direction or the other in the pitch axis, i.e., either ''''nose up'''' or ''''nose down'''' flight, and a second switch means controlled by the relative rotation position of the outer gimbal and the instrument casing for sensing departure beyond reasonable limits in the roll axis, i.e., either ''''left wing down'''' or ''''right wing down'''' flight.
Inventors
- 👤 R Hernandez
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 21:42
CPC Classifications
G; G01; G01C; G01C19/00; G01C19/02; G01C19/44
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
367 words
A device for signalling departure beyond predetermined limits from straight and level flight as indicated by the dial of 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, and 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 pair of signal lamps being mounted directly above and below the indicating dial of the gyrohorizon instrument in an aircraft panel, and said second pair of signal lamps being mounted directly at each side of said instrument dial, said first and second energizing means including an audible signal device and means for simultaneously energizing said audible signal device upon the energization of any one of the said signal lamps, both said audible signal device and said first and second pair of signal lamps thereby serving as a warning that the aircraft has departed from safe flight parameters, said first and second pair of signal lamps also serving to indicate the direction of aircraft deviation and whether such deviation is in pitch or in roll, or both pitch and roll.
Claim 2
Independent Claim
367 words
A device for signalling departure beyond predetermined limits from straight and level flight as indicated by the dial of 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, and 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 pair of signal lamps being mounted directly above and below the indicating dial of the gyrohorizon instrument in an aircraft panel, and said second pair of signal lamps being mounted directly at each side of said instrument dial, said first and second energizing means including an audible signal device and means for simultaneously energizing said audible signal device upon the energization of any one of the said signal lamps, both said audible signal device and said first and second pair of signal lamps thereby serving as a warning that the aircraft has departed from safe flight parameters, said first and second pair of signal lamps also serving to indicate the direction of aircraft deviation and whether such deviation is in pitch or in roll, or both pitch and roll.
Claim 3
Dependent Claim
131 words
A device for signalling departure beyond predetermined limits from straight and level flight as defined in claim 1 wherein said first energizing means comprises 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, and 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.
References Cited (Backward Citations)
US3723963A
Cited
US3737846A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-12-02 | 1978-06-03 | 1978-12-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-12-02 | 1982-06-03 | 1982-12-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-12-02 | 1986-06-03 | 1986-12-03 | $7700.00 | Window Closed / Lapsed |