US4009464A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apparatus for indicating attitude failure
Assignee: Honeywell Inc
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Filing: 1976-01-16
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Granted: 1977-02-22
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Expires: 1996-01-16
Abstract
Abstract Apparatus for indicating attitude failure in an attitude indicator system in which energy is stored and isolated from all other apparatus during normal operation and transferred to the attitude indicator when attitude failure is detected, resulting in an indication of attitude failure.
Inventors
- 👤 Terrence L. Grimes
- 👤 Thomas W. Neis
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 18:21
CPC Classifications
G; G01; G01C; G01C19/00; G01C19/02; G01C19/04; G01C19/32
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
214 words
In an aircraft indicator system operable from an electrical energy source and having a panel mounted indicator display for indicating to the pilot the attitude of the craft relative to the horizon and a remote vertical gyroscope for providing a horizon reference, electrical control apparatus for positioning said indicator display comprising: motor means responsive to said vertical gyroscope and coupled through gears to said indicator display for normally positioning said indicator display in accordance with the position of said vertical gyroscope, storage means coupled to said electrical energy source for storing electrical energy, isolation means for isolating said storage means from said motor means during normal operation of said attitude indicator system, sensing means responsive to a failure in said attitude indicator system, and transfer means responsive to said sensing means for transferring the stored energy within said storage means to said motor means after a failure, the magnitude of the stored energy being sufficient to drive said indicator display to a position corresponding to an attitude indicating position greatly exaggerated from a normal aircraft attitude and wherein the motor means and the gears maintain said indicator display in said exaggerated position after dissipation of the stored energy thereby indicating a failure and warning the pilot not to rely on said attitude indicator system.
Claim 2
Dependent Claim
214 words
In an aircraft indicator system operable from an electrical energy source and having a panel mounted indicator display for indicating to the pilot the attitude of the craft relative to the horizon and a remote vertical gyroscope for providing a horizon reference, electrical control apparatus for positioning said indicator display comprising: motor means responsive to said vertical gyroscope and coupled through gears to said indicator display for normally positioning said indicator display in accordance with the position of said vertical gyroscope, storage means coupled to said electrical energy source for storing electrical energy, isolation means for isolating said storage means from said motor means during normal operation of said attitude indicator system, sensing means responsive to a failure in said attitude indicator system, and transfer means responsive to said sensing means for transferring the stored energy within said storage means to said motor means after a failure, the magnitude of the stored energy being sufficient to drive said indicator display to a position corresponding to an attitude indicating position greatly exaggerated from a normal aircraft attitude and wherein the motor means and the gears maintain said indicator display in said exaggerated position after dissipation of the stored energy thereby indicating a failure and warning the pilot not to rely on said attitude indicator system.
Claim 3
Dependent Claim
17 words
In an attitude indicator system, the apparatus of claim 1 wherein the sensing means includes a relay.
Claim 4
Dependent Claim
23 words
In an attitude indicator system, the apparatus of claim 1 wherein the means for storing electrical energy consists of a plurality of capacitors.
Claim 5
Dependent Claim
74 words
In an attitude indicator system, the apparatus as described in claim 1 wherein: said sensing means includes the coil of a relay coupled to the electrical energy source, said isolation means and said transfer means are comprised of a set of relay contacts responsive to said relay coil and coupled between said motor means and said storage means, and said storage means includes a plurality of capacitors normally coupled to said electrical energy source.
Claim 6
Dependent Claim
25 words
The apparatus of claim 4 wherein the sensing means further includes a gating device disposed such that said relay coil detects a plurality of malfunctions.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-02-22 | 1980-08-23 | 1981-02-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-02-22 | 1984-08-23 | 1985-02-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-02-22 | 1988-08-23 | 1989-02-22 | $7700.00 | Window Closed / Lapsed |