Patent US4120540A successfully refreshed from Google Patents.
US4120540A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft automatic braking system
Assignee: Boeing Co
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Filing: 1977-02-17
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Granted: 1978-10-17
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Expires: 1997-02-17
Abstract
Abstract An automatic braking system for automatically controlling aircraft braking to maintain a pilot-selected deceleration level, having improved hydraulic apparatus responsive to the signal control channel. Valve apparatus are provided which combine and process commanded automatic braking pressures and pilot brake pedal forces to generate metered braking pressures. Valve apparatus providing AND, OR, and AND/OR control of metered braking pressure are provided.
Inventors
- 👤 Garrett Howard DeVlieg
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 11:56
CPC Classifications
B; B60; B60T; B60T13/00; B60T13/10; B60T13/12; B64; B64C; B64C25/00; B64C25/32; B64C25/42; B64C25/426; Y; Y10; Y10T; Y10T137/00; Y10T137/8593; Y10T137/86493; Y10T137/86574; Y10T137/8667; Y10T137/86694; Y10T137/8671
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
227 words
An aircraft automatic braking system comprising in combination; means for generating a brake pressure control signal; automatic braking pressure modulating valve means responsive to said brake pressure control signal for metering automatic braking pressure command pressure at an output of said automatic braking pressure modulating valve means; first valve means including a housing, a plunger extending through said housing, a metering spool with first and second inputs and an output, and pedal means disposed outside said housing for applying an axial force on said plunger, said first and second inputs of said metering spool of said first valve means being responsive to said axially applied force and said automatic braking pressure command pressure respectively; second valve means including a further housing, a further plunger extending through said further housing, a metering spool with first and second inputs and an output, and further pedal means disposed outside said further housing for applying a further axial force on said further plunger, said first and second inputs of said metering spool of said second valve means being responsive to said further axially applied force and said automatic braking pressure command pressure respectively; first braking means on one side of the aircraft responsive to the output of said first valve means; and, second braking means on the other side of the aircraft responsive to the output of said second valve means.
Claim 2
Dependent Claim
227 words
An aircraft automatic braking system comprising in combination; means for generating a brake pressure control signal; automatic braking pressure modulating valve means responsive to said brake pressure control signal for metering automatic braking pressure command pressure at an output of said automatic braking pressure modulating valve means; first valve means including a housing, a plunger extending through said housing, a metering spool with first and second inputs and an output, and pedal means disposed outside said housing for applying an axial force on said plunger, said first and second inputs of said metering spool of said first valve means being responsive to said axially applied force and said automatic braking pressure command pressure respectively; second valve means including a further housing, a further plunger extending through said further housing, a metering spool with first and second inputs and an output, and further pedal means disposed outside said further housing for applying a further axial force on said further plunger, said first and second inputs of said metering spool of said second valve means being responsive to said further axially applied force and said automatic braking pressure command pressure respectively; first braking means on one side of the aircraft responsive to the output of said first valve means; and, second braking means on the other side of the aircraft responsive to the output of said second valve means.
Claim 3
Dependent Claim
245 words
An aircraft automatic braking system comprising in combination: means for generating a brake pressure control signal; automatic braking pressure modulating valve means responsive to said brake pressure control signal for metering automatic braking pressure command pressure at an output of said automatic braking pressure modulating valve means; first valve means including a housing, a plunger extending through said housing, a metering spool with first and second inputs and an output, and pedal means disposed outside said housing for applying an axial force on said plunger, said first and second inputs of said metering spool of said first valve means being responsive to said axially applied force and said automatic braking pressure command presure respectively; second valve means including a further housing, a further plunger extending through said futher housing, a metering spool with first and second inputs and an output, and further pedal means disposed outside said further housing for applying a further axial force on said further plunger, said first and second inputs of said metering spool of said second valve means being responsive to said further axially applied force and said automatic braking pressure command pressure respectively; first braking means on one side of said aircraft; second braking means on the other side of said aircraft; first anti-skid valve means coupled between said first braking means and said output of said first valve means; and, second anti-skid valve means coupled between said second braking means and said output of said second valve means.
Claim 4
Dependent Claim
245 words
An aircraft automatic braking system comprising in combination: means for generating a brake pressure control signal; automatic braking pressure modulating valve means responsive to said brake pressure control signal for metering automatic braking pressure command pressure at an output of said automatic braking pressure modulating valve means; first valve means including a housing, a plunger extending through said housing, a metering spool with first and second inputs and an output, and pedal means disposed outside said housing for applying an axial force on said plunger, said first and second inputs of said metering spool of said first valve means being responsive to said axially applied force and said automatic braking pressure command presure respectively; second valve means including a further housing, a further plunger extending through said futher housing, a metering spool with first and second inputs and an output, and further pedal means disposed outside said further housing for applying a further axial force on said further plunger, said first and second inputs of said metering spool of said second valve means being responsive to said further axially applied force and said automatic braking pressure command pressure respectively; first braking means on one side of said aircraft; second braking means on the other side of said aircraft; first anti-skid valve means coupled between said first braking means and said output of said first valve means; and, second anti-skid valve means coupled between said second braking means and said output of said second valve means.
Claim 5
Dependent Claim
118 words
In combination in an aircraft braking system: first means for providing an electrically controlled hydraulic pressure command; second means for generating a manually controlled hydraulic pressure command; valve means responsive to said first and second means for providing hydraulic pressure to control aircraft braking; said hydraulic pressure being exclusively responsive to said electrically controlled hydraulic pressure command when a proportional part of said electrically controlled hydraulic pressure command is greater than the force applied for generating said manually controlled hydraulic pressure command, said hydraulic pressure being representative of the sum of said applied force and said electrically controlled hydraulic pressure command when said proportional part of said electrically controlled hydraulic pressure command is less than said applied force.
Claim 6
Dependent Claim
118 words
In combination in an aircraft braking system: first means for providing an electrically controlled hydraulic pressure command; second means for generating a manually controlled hydraulic pressure command; valve means responsive to said first and second means for providing hydraulic pressure to control aircraft braking; said hydraulic pressure being exclusively responsive to said electrically controlled hydraulic pressure command when a proportional part of said electrically controlled hydraulic pressure command is greater than the force applied for generating said manually controlled hydraulic pressure command, said hydraulic pressure being representative of the sum of said applied force and said electrically controlled hydraulic pressure command when said proportional part of said electrically controlled hydraulic pressure command is less than said applied force.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1981-10-16 | 1982-04-17 | 1982-10-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-10-16 | 1986-04-17 | 1986-10-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-10-16 | 1990-04-17 | 1990-10-17 | $7700.00 | Window Closed / Lapsed |