US3765624A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fluidically augmented variable gain artificial feel system
Assignee: United States Department of the Navy
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Filing: 1971-09-29
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Granted: 1973-10-16
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Expires: 1991-09-29
Abstract
Abstract A fluidic artifical feel system responsive to the rotational and vertical accelerations and the speed of an aircraft along its flight path, including fluidic angular and vertical accelerators, an air data sensor and fluidic variable gain amplifiers gain modulated according to the signal received from the air data sensor. The accelerometers and the air data sensor are connected through respective variable gain amplifiers to a summing amplifier, the output signal thereof being connected to a fluidic valve which provides a pressure differential across a piston connected to the control stick of the aircraft.
Inventors
- 👤 W Kaniuka
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 15:26
CPC Classifications
B; B64; B64C; B64C13/00; B64C13/24; Y; Y02; Y02T; Y02T50/00; Y02T50/40
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
282 words
An aircraft artificial feel system for providing a control stick feel force responsive to the motions of the aircraft, comprising: a control stick adapted to be connected to an aerodynamic control surface of the aircraft; air data sensing means adapTed to be mounted on the aircraft for providing a first output signal indicative of the aerodynamic conditions adjacent to the aircraft; angular acceleration sensing means adapted to be affixed to the aircraft for providing a second output signal indicative of the angular acceleration of the aircraft; linear acceleration sensing means adapted to be affixed to the aircraft for providing a third output signal indicative of the linear acceleration of the aircraft; amplifying means operatively connected to receive said first, second and third output signals for producing a fourth output signal indicative of a combination of said second and third output signals at respective gains corresponding to said first output signal, said amplifying means including a first variable gain amplifier operatively connected to receive said first and second output signals indicative of said second output signal at a gain corresponding to a predetermined function of said first output signal, a second variable gain amplifier operatively connected to receive said first and third output signals for producing an output signal indicative of said third output signal at a gain corresponding to a predetermined function of said first output signal, and a summing amplifier connected to receive said first and second variable gain amplifier output signals for producing an output signal indicative of a sum thereof; and force producing means operatively connected to said control stick of the aircraft and connected to receive said fourth output signal for producing a resistive force indicative of feel.
Claim 2
Dependent Claim
282 words
An aircraft artificial feel system for providing a control stick feel force responsive to the motions of the aircraft, comprising: a control stick adapted to be connected to an aerodynamic control surface of the aircraft; air data sensing means adapTed to be mounted on the aircraft for providing a first output signal indicative of the aerodynamic conditions adjacent to the aircraft; angular acceleration sensing means adapted to be affixed to the aircraft for providing a second output signal indicative of the angular acceleration of the aircraft; linear acceleration sensing means adapted to be affixed to the aircraft for providing a third output signal indicative of the linear acceleration of the aircraft; amplifying means operatively connected to receive said first, second and third output signals for producing a fourth output signal indicative of a combination of said second and third output signals at respective gains corresponding to said first output signal, said amplifying means including a first variable gain amplifier operatively connected to receive said first and second output signals indicative of said second output signal at a gain corresponding to a predetermined function of said first output signal, a second variable gain amplifier operatively connected to receive said first and third output signals for producing an output signal indicative of said third output signal at a gain corresponding to a predetermined function of said first output signal, and a summing amplifier connected to receive said first and second variable gain amplifier output signals for producing an output signal indicative of a sum thereof; and force producing means operatively connected to said control stick of the aircraft and connected to receive said fourth output signal for producing a resistive force indicative of feel.
Claim 3
Dependent Claim
29 words
An artificial feel system according to claim 1, further comprising: delay means connected to receive said second output signal for delaying said second output signal a predetermined time interval.
Claim 4
Dependent Claim
18 words
An artificial feel system according to claim 2, wherein: said air data sensing means comprises a pitot tube.
Claim 5
Dependent Claim
22 words
An artificial feel system according to claim 3, wherein: said first, second, third and fourth output signals comprise fluidic pressure differential signals.
Claim 6
Dependent Claim
146 words
An artificial feel system according to claim 4, further comprising: first and second variable gain amplifiers including a shunting unit having two chambers, an orificed wall separating said chambers, bellows sealably mounted across each chamber disposed in opposing relationship and dividing each chamber into subchambers, a conically shaped valve member extending through said orifice and attached at either end to said bellows, first connectors formed in the distal subchambers on the opposite sides of said bellows connected to receive said first sensing means output signals, second connectors formed in the adjacent subchambers intermediate said bellows and on either side of said separating wall respectively connected to receive corresponding ones of said first and second output signals and an operational amplifier connected to said second connectors for providing an output signal indicative of respective ones of said first and second output signals shunted by said shunting unit.
Claim 7
Dependent Claim
137 words
An artificial feel system according to claim 5, wherein: said force producing means comprises a first housing, a flexible flapper attached at one end to said first housing, first opposing bellows abutting said flapper proximate the free end thereof connected to receive said fourth outputt signal, two orifices disposed in opposing relationship on either side of the free end of said flapper, a source of pressure connected in common to said orifices, second opposing bellows disposed in abutting relationship on either side of said flapper and connected to respective ones of said orifices, a second housing forming a cylindrical enclosure connected at the distal ends thereof to respective ones of said orifices, a piston disposed within said second housing and a connecting rod attached to said piston and operatively connected to the control stick of the aircraft.
Claim 8
Dependent Claim
145 words
An artificial feel system according to claIm 2, wherein: said air data sensing means comprising a pitot tube mounted on the exterior of the aircraft for providing respective output signals indicative of the static and dynamic pressures on the aircraft, a linear actuator connected to receive the pitot tube output signals for providing a linear displacement indicative of the pressure differential between the static and the dynamic pressures, a rotary actuator connected to receive the static pressure for providng an angular displacement output signal indicative of the altitude of the aircraft, a three dimensional cam formed to correspond to the Mach number at preselected altitudes and dynamic pressures, movable in rotation and translation according to the displacement of said linear and rotary actuator means, and a cam follower mounted to contact said cam for providing a linear displacement indicative of the position of the cam.
Claim 9
Dependent Claim
21 words
An artificial feel system according to claim 7, wherein: said second, third and fourth output signals comprise fluidic pressure differential signals.
Claim 10
Dependent Claim
98 words
An artificial feel system according to claim 8, further comprising: said first and second variable gain amplifiers including a shunting unit having two chambers, an orificed wall separating said chambers, a conically shaped valve member extending through said orifice and operatively connected at one end thereof to said cam follower, connectors formed in the respective chambers respectively connected to receive corresponding ones of said first and second output signals and an operational amplifier connected to said connectors for producing an output signal indicative of respective ones of said first and second output signals shunted by said shunting units.
Claim 11
Dependent Claim
137 words
An artificial feel system according to claim 9, wherein: said force producing means comprises a first housing, a flexible flapper attached at one end to said first housing, first opposing bellows abutting said flapper proximate the free end thereof connected to receive said fourth output signal, two orifices disposed in opposing relationship on either side of the free end of said flapper, a source of pressure connected in common to said orifices, second opposing bellows disposed in abutting relationship on either side of said flapper and connected to respective ones of said orifices, a second housing forming a cylindrical enclosure connected at the distal ends thereof to respective ones of said orifices, a piston disposed within said second housing and a connecting rod attached to said piston and operatively connected to the control stick 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) | 1976-10-15 | 1977-04-16 | 1977-10-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-10-15 | 1981-04-16 | 1981-10-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-10-15 | 1985-04-16 | 1985-10-16 | $7700.00 | Window Closed / Lapsed |