US3679156A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fly-by-wire
Assignee: Ltv Electrosystems Inc
•
Filing: 1970-07-20
•
Granted: 1972-07-25
•
Expires: 1990-07-20
Abstract
Abstract Three separately generated electrical control signals are applied to respective electromechanical transducers in a power actuator control system. Each electromechanical transducer generates a mechanical output motion related to the applied control signal and independent of the remaining transducers. A mechanical linkage arrangement coupled to the outputs of each of the three electromechanical transducers combines the motions into a single mechanical movement. This single mechanical movement positions the control element for a servo-pump supplying a power actuator.
Inventors
- 👤 William G Redmond Jr
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 15:52
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/0055; G05D1/0077
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
158 words
A system for positioning a control element in response to electrical control signals, comprising: at least three electro-mechanical transducers each having an output motion related to an electrical signal applied thereto, mechanical summing linkage coupled to the output of each of said transducers such that each transducer contributes to a single mechanical motion by an amount inversely proportional to a number of said transducers, a position transducer at each of said electro-mechanical transducers generating a first feedback signal and a second feedback signal, means for summing said first feedback signal with one of the electrical control signals to selectively control the respective electromechanical transducer, comparing means monitoring each of the second feedback signals and generating an indication when one differs from any combination of at least two of the other second feedback signals, and actuator means responsive to the single mechanical motion of said mechanical summing linkage and having an output controlling the movement of the control elements.
Claim 2
Independent Claim
158 words
A system for positioning a control element in response to electrical control signals, comprising: at least three electro-mechanical transducers each having an output motion related to an electrical signal applied thereto, mechanical summing linkage coupled to the output of each of said transducers such that each transducer contributes to a single mechanical motion by an amount inversely proportional to a number of said transducers, a position transducer at each of said electro-mechanical transducers generating a first feedback signal and a second feedback signal, means for summing said first feedback signal with one of the electrical control signals to selectively control the respective electromechanical transducer, comparing means monitoring each of the second feedback signals and generating an indication when one differs from any combination of at least two of the other second feedback signals, and actuator means responsive to the single mechanical motion of said mechanical summing linkage and having an output controlling the movement of the control elements.
Claim 3
Dependent Claim
27 words
A system as set forth in claim 1 including neutralizing means at each of said transducers to effectively disconnect the associated transducer from said mechanical summing linkage.
Claim 4
Dependent Claim
39 words
A control system as set forth in claim 2 wherein said actuator means includes a duo-tandem hydraulic actuator responsive to the single mechanical motion of said summing linkage and having an output controlling the movement of the control element.
Claim 5
Dependent Claim
199 words
An aircraft control system for positioning a control surface in response to electrical control signals comprising: at least three electro-mechanical transducers having an output motion related to a separate electrical signal applied thereto, mechanical summing linkage coupled to the output of each of said transducers such that each transducer contributes to a single mechanical motion by an amount inversely proportional to the number of said transducers, a position transducer at each of said electro-mechanical transducers generating a first feedback signal and a second feedback signal, means for summing said first feedback signal with one of the electrical control signals to selectively control the respective electromechanical transducer, comparing means monitoring each of the second feedback signals and generating an indication when one differs from any combination of at least two of the other second feedback signals, a duo-tandem hydraulic actuator having an output controlling the movement of the control surface, each section of said actuator supplied operating fluid from a separate source, and pump means for each of said supply sources for controlling the fluid therefrom to the respective actuator stage, said pump means having a positionable swash plate coupled to the single mechanical motion of said displacement summing means.
Claim 6
Dependent Claim
199 words
An aircraft control system for positioning a control surface in response to electrical control signals comprising: at least three electro-mechanical transducers having an output motion related to a separate electrical signal applied thereto, mechanical summing linkage coupled to the output of each of said transducers such that each transducer contributes to a single mechanical motion by an amount inversely proportional to the number of said transducers, a position transducer at each of said electro-mechanical transducers generating a first feedback signal and a second feedback signal, means for summing said first feedback signal with one of the electrical control signals to selectively control the respective electromechanical transducer, comparing means monitoring each of the second feedback signals and generating an indication when one differs from any combination of at least two of the other second feedback signals, a duo-tandem hydraulic actuator having an output controlling the movement of the control surface, each section of said actuator supplied operating fluid from a separate source, and pump means for each of said supply sources for controlling the fluid therefrom to the respective actuator stage, said pump means having a positionable swash plate coupled to the single mechanical motion of said displacement summing means.
Claim 7
Dependent Claim
28 words
An aircraft control system as set forth in claim 4 including neutralizing means at each electromechanical transducer to effectively disconnect the respective transducer from said mechanical summing linkage.
References Cited (Backward Citations)
US2898889A
Cited
US3027878A
Cited
US3469162A
Cited
US3401600A
Cited
US3426650A
Cited
US3422767A
Cited
US3554084A
Cited
US3505929A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-07-25 | 1976-01-24 | 1976-07-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-07-25 | 1980-01-24 | 1980-07-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-07-25 | 1984-01-24 | 1984-07-25 | $7700.00 | Window Closed / Lapsed |