Patent US3640137A successfully refreshed from Google Patents.
US3640137A
Expired / Lapsed
US
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Erection cutoff system for plural gyroscopes
Assignee: Honeywell Inc
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Filing: 1969-06-24
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Granted: 1972-02-08
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Expires: 1989-06-24
Abstract
Abstract A system for ensuring that the long term erection sensors of a plurality of gyroscopes installed in the same aircraft and providing substantially identical attitude reference information are cut off simultaneously to thereby reduce discrepancies in the information supplied by each of the gyroscopes due to tolerances in the cutoff thresholds of the long term reference sensors of each gyroscope.
Inventors
- 👤 Terry S Allen
- 👤 Lynn R Lane
- 👤 Harold Lee Swartz
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 12:38
CPC Classifications
G; G01; G01C; G01C21/00; G01C21/10; G01C21/12; G01C21/16; G01C21/18; Y; Y10; Y10T; Y10T74/00; Y10T74/12; Y10T74/1221; Y10T74/1229; Y10T74/1232
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
84 words
An aircraft flight reference system comprising a. a plurality of gyroscopes each providing separate and substantially identical measures of aircraft attitude, each of said gyroscopes including means for normally slaving its spin axis to a common reference direction, said slaving means being responsive to accelerations of said aircraft tending to change said reference direction, and b. means interconnecting all of said gyroscopes for simultaneously interrupting the operation of the slaving control means of each of said gyroscopes when said accelerations exceed a predetermined value.
Claim 2
Dependent Claim
84 words
An aircraft flight reference system comprising a. a plurality of gyroscopes each providing separate and substantially identical measures of aircraft attitude, each of said gyroscopes including means for normally slaving its spin axis to a common reference direction, said slaving means being responsive to accelerations of said aircraft tending to change said reference direction, and b. means interconnecting all of said gyroscopes for simultaneously interrupting the operation of the slaving control means of each of said gyroscopes when said accelerations exceed a predetermined value.
Claim 3
Dependent Claim
130 words
An aircraft flight reference system comprising a. a plurality of gyroscopes each providing separate and substantially identical indications of aircraft attitude, each of said gyroscopes including erection control means for normally slaving the gyroscope spin axis to a common predetermined reference direction, each of said gyroscopes also including erection cutoff sensor means responsive to a predetermined nominal threshold acceleration value for supplying an erection cutoff signal, and each of said gyroscopes further including cutoff actuation means for cutting out the said erection control means, and b. means responsive to at least one said cutoff signals for operating all of said erection cutoff actuation means simultaneously whereby discrepancies between the indications provided by each of said gyroscopes due to cutoff sensor threshold tolerance of each of said gyroscopes are substantially eliminated.
Claim 4
Dependent Claim
130 words
An aircraft flight reference system comprising a. a plurality of gyroscopes each providing separate and substantially identical indications of aircraft attitude, each of said gyroscopes including erection control means for normally slaving the gyroscope spin axis to a common predetermined reference direction, each of said gyroscopes also including erection cutoff sensor means responsive to a predetermined nominal threshold acceleration value for supplying an erection cutoff signal, and each of said gyroscopes further including cutoff actuation means for cutting out the said erection control means, and b. means responsive to at least one said cutoff signals for operating all of said erection cutoff actuation means simultaneously whereby discrepancies between the indications provided by each of said gyroscopes due to cutoff sensor threshold tolerance of each of said gyroscopes are substantially eliminated.
Claim 5
Dependent Claim
22 words
The flight reference system as set forth in claim 2 wherein said last-mentioned means is responsive to all of said cutoff signals.
Claim 6
Dependent Claim
23 words
The flight reference system as set forth in claim 2 wherein said last-mentioned means is responsive tO any one of said cutoff signals.
Claim 7
Dependent Claim
45 words
The flight reference system as set forth in claim 2 wherein said last-mentioned means comprises AND logic circuit means having its output coupled with each of said erection cutoff actuation means, and means supplying all of said cutoff signals to said AND logic circuit means.
Claim 8
Dependent Claim
63 words
The flight reference system as set forth in claim 2 wherein each of said gyroscopes further includes timing means adapted upon initiation to reinstate said erection control means after a predetermined time period, and further means responsive to the reinstatement of the erection control means of one of said gyroscopes for simultaneously reinstating the erection control means of all other of said gyroscopes.
References Cited (Backward Citations)
US2949786A
Cited
US3276269A
Cited
US2995040A
Cited
US3466935A
Cited
US3401549A
Cited
US3456513A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-02-07 | 1975-08-09 | 1976-02-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-02-07 | 1979-08-09 | 1980-02-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-02-07 | 1983-08-09 | 1984-02-08 | $7700.00 | Window Closed / Lapsed |