US3570788A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Flight aid systems
Assignee: Ferranti International PLC
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Filing: 1969-01-31
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Granted: 1971-03-16
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Expires: 1989-01-31
Abstract
Abstract A flight aid system is provided for an aircraft having a control system in which two parallel control rods move together in the same or in opposite directions to control movement of the aircraft about a first or a second control axis respectively. The system includes, for each control rod, a closed-loop autostabilizer including a rate gyroscope. The two rate gyroscopes are mounted with their sensitive axes coplanar with the two control axes and displaced by equal and opposite angles about the second control axis.
Inventors
- 👤 Joe Cox
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 08:39
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/82; B64C27/54; B64C27/56; G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; G05D1/0816; G05D1/0833
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
157 words
A flight air system for an aircraft having two attitude functions controlled by two substantially parallel control rods so arranged that simultaneous movement of the two rods in the same direction and to the same extent controls one attitude function and simultaneous movement of the two rods in opposite directions and to the same extent control the other attitude function, which system includes, for each of the two control rods, a limited authority autostabilizer actuator, an autostabilizer computer operable to control the operation of the autostabilizer actuator, and a rate gyroscope operable to derive rate error signals for application to the autostabilizer computer, the two rate gyroscopes being mounted with their sensitive axes coplanar with the axes of the two attitude functions and displaced by equal and opposite angles about one of said attitude function axes, the angle of displacement being such that the desired ratio of controlled movements for the two controlled attitude functions is obtained.
Claim 2
Dependent Claim
157 words
A flight air system for an aircraft having two attitude functions controlled by two substantially parallel control rods so arranged that simultaneous movement of the two rods in the same direction and to the same extent controls one attitude function and simultaneous movement of the two rods in opposite directions and to the same extent control the other attitude function, which system includes, for each of the two control rods, a limited authority autostabilizer actuator, an autostabilizer computer operable to control the operation of the autostabilizer actuator, and a rate gyroscope operable to derive rate error signals for application to the autostabilizer computer, the two rate gyroscopes being mounted with their sensitive axes coplanar with the axes of the two attitude functions and displaced by equal and opposite angles about one of said attitude function axes, the angle of displacement being such that the desired ratio of controlled movements for the two controlled attitude functions is obtained.
Claim 3
Dependent Claim
25 words
A flight air system as claimed in Claim 1 in which said one of said attitude function axes is the roll axis of the aircraft.
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) | 1974-03-15 | 1974-09-14 | 1975-03-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-03-15 | 1978-09-14 | 1979-03-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-03-15 | 1982-09-14 | 1983-03-16 | $7700.00 | Window Closed / Lapsed |