US3773282A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Vehicle control system
Assignee: McDonnell Douglas Corp
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Filing: 1971-12-27
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Granted: 1973-11-20
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Expires: 1991-12-27
Abstract
Abstract A control system for vehicles capable of travel at high speeds on land, and in the air or water, in which the operator of such a vehicle is provided with means to regulate his capabilities to the loads imposed on the vehicle control surface subjected to a wide range of loads. The system involves a parallel related arrangement of a spring damper device, and a trim actuator and feel spring, with a ratio changer device in series that operates to provide the operator with a substantially constant control load for ''''G'''' forces acting on the vehicle control surface for the full range of surface deflection and throughout the vehicle operating range. The system includes a mass which is sensitive to the acceleration of the vehicle and to the normal translation of the vehicle. This gives the operator a way of matching his capabilities to the loads imposed throughout the operating range of the vehicle.
Inventors
- 👤 R Sands
- 👤 D Young
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 17:12
CPC Classifications
B; B64; B64C; B64C13/00; B64C13/24
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
161 words
In an aircraft control system having an operator''s control means and a control surface; the improved combination of means operatively interconnecting the operator''s control with the control surface, including spring damper means connected into said operative means, trim actuator feel spring means connected into said operative means in parallel relation with said spring damper means, ratio changer means disposed in said operative means in series with said spring damper means, pressure transducer means responsive to dynamic and static pressure conditions of the aircraft when in flight, said transducer means have operative connection with said ratio changer means to impose on said ratio changer means a ratio of control means deflection to control surface deflection commensurate with the speed and altitude of the aircraft and within the operator''s ability to fly the aircraft, and means under the control of the operator and connected to said transducer means to selectively cut-in and cutout said pressure transducer operative connection with said ratio changer means.
Claim 2
Dependent Claim
161 words
In an aircraft control system having an operator''s control means and a control surface; the improved combination of means operatively interconnecting the operator''s control with the control surface, including spring damper means connected into said operative means, trim actuator feel spring means connected into said operative means in parallel relation with said spring damper means, ratio changer means disposed in said operative means in series with said spring damper means, pressure transducer means responsive to dynamic and static pressure conditions of the aircraft when in flight, said transducer means have operative connection with said ratio changer means to impose on said ratio changer means a ratio of control means deflection to control surface deflection commensurate with the speed and altitude of the aircraft and within the operator''s ability to fly the aircraft, and means under the control of the operator and connected to said transducer means to selectively cut-in and cutout said pressure transducer operative connection with said ratio changer means.
Claim 3
Dependent Claim
38 words
The improvement set forth in claim 1 and including operator emergency control means connected to said ratio changer means to over-ride the latter means and select a one-to-one ratio between said operator''s control means and control surface deflection.
Claim 4
Dependent Claim
191 words
In aircraft flight control apparatus the improved combination with a movable control surface and a pilot''s control stick of means operably interconnecting said stick and control surface to permit the pilot to fly the aircraft in any flight condition with substantially the same stick feel and aircraft response commensurate with the speed and altitude of the aircraft, said improved combination consisting of trim actuator means and motion damper means operably connected into said operable interconnecting means, acceleration sensing means in said operable interconnecting means, ratio changer means in said operable interconnecting means between said acceleration sensing means and said control surface to vary the stick to control surface deflection ratio, ratio changing actuator means connected into said ratio changer means, and static and dynamic pressure transducer means operably connected to said actuator means to monitor the operation of said actuator means in response to the static and dynamic conditions of the aircraft flight regime, said ratio changer means having a non-linear unit connected to said actuator means, and an isolation unit connected between said non-linear unit and said ratio changer operable to control the ratio of stick to control surface deflection.
Claim 5
Dependent Claim
191 words
In aircraft flight control apparatus the improved combination with a movable control surface and a pilot''s control stick of means operably interconnecting said stick and control surface to permit the pilot to fly the aircraft in any flight condition with substantially the same stick feel and aircraft response commensurate with the speed and altitude of the aircraft, said improved combination consisting of trim actuator means and motion damper means operably connected into said operable interconnecting means, acceleration sensing means in said operable interconnecting means, ratio changer means in said operable interconnecting means between said acceleration sensing means and said control surface to vary the stick to control surface deflection ratio, ratio changing actuator means connected into said ratio changer means, and static and dynamic pressure transducer means operably connected to said actuator means to monitor the operation of said actuator means in response to the static and dynamic conditions of the aircraft flight regime, said ratio changer means having a non-linear unit connected to said actuator means, and an isolation unit connected between said non-linear unit and said ratio changer operable to control the ratio of stick to control surface deflection.
Claim 6
Dependent Claim
40 words
The improved combination set forth in claim 3 and including pilot operated means to disable the connection between said pressure transducer means and said actuator means, whereby to permit the pilot to manually monitor the operation of said actuator means.
Claim 7
Dependent Claim
45 words
The improved combination set forth in claim 3 and including a pilot actuated emergency control connected into said ratio changer means to adjust said isolation unit whereby said ratio changer means sets the movement of said stick and control surface deflection in a one-to-one ratio.
Claim 8
Dependent Claim
27 words
The improved combination set forth in claim 3 and including pilot actuated means connected to said trim actuator means to permit the pilot to trim the aircraft.
References Cited (Backward Citations)
US2652994A
Cited
US2674900A
Cited
US2667315A
Cited
US2680581A
Cited
US2796774A
Cited
US2940697A
Cited
US2974908A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-11-19 | 1977-05-21 | 1977-11-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-11-19 | 1981-05-21 | 1981-11-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-11-19 | 1985-05-21 | 1985-11-20 | $7700.00 | Window Closed / Lapsed |