US4326253A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Lift control system for aircraft vertical path guidance
Assignee: Boeing Co
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Filing: 1980-03-31
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Granted: 1982-04-20
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Expires: 2000-03-31
Abstract
Abstract A system for providing an optimum lift demand signal for aircraft maneuvers such as "go-around" includes a computer for generating a reference angle of attack signal which is functionally related to the aircraft's vertical velocity. The reference signal is compared with a signal corresponding to the aircraft's actual angle of attack, thereby producing an error signal. The error signal is utilized as a control to the aircraft's dynamics for optimizing the aircraft's climb-out performance.
Inventors
- 👤 Michael G. Cooper
- 👤 Alessandro P. Sassi
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 16:05
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
142 words
An aircraft vertical path guidance system comprising: means for producing a signal h corresponding to the aircraft's vertical velocity; lift computer means for producing a reference lift demand angle of attack signal α ref , said α ref signal being a continuously variable function of h between predetermined maximum and minimum angle of attack values, α max and α min , respectively, said function of h being independent of other aircraft parameters; means for producing a signal α corresponding to the aircraft's actual angle of attack; error signal means for producing an error signal α.sub.ε corresponding to the difference between said reference lift demand angle of attack signal α ref and said actual angle of attack signal α; and utilization means for utilizing said α.sub.ε signal as a control to the aircraft's dynamics for controlling the vertical lift characteristic of the aircraft.
Claim 2
Dependent Claim
142 words
An aircraft vertical path guidance system comprising: means for producing a signal h corresponding to the aircraft's vertical velocity; lift computer means for producing a reference lift demand angle of attack signal α ref , said α ref signal being a continuously variable function of h between predetermined maximum and minimum angle of attack values, α max and α min , respectively, said function of h being independent of other aircraft parameters; means for producing a signal α corresponding to the aircraft's actual angle of attack; error signal means for producing an error signal α.sub.ε corresponding to the difference between said reference lift demand angle of attack signal α ref and said actual angle of attack signal α; and utilization means for utilizing said α.sub.ε signal as a control to the aircraft's dynamics for controlling the vertical lift characteristic of the aircraft.
Claim 3
Dependent Claim
66 words
The aircraft vertical path guidance control system of claim 1 wherein said lift computer means further comprises: means for limiting said α ref signal to said maximum level α max corresponding to a predetermined margin of angle of attack within stall of the aircraft; and means for limiting said α ref signal to said minimum level α min corresponding to the aircraft's maximum desired forward velocity.
Claim 4
Independent Claim
139 words
A method for producing an aircraft lift control vertical path guidance signal comprising the steps of: (a) providing a signal h corresponding to the aircraft's actual vertical velocity; (b) generating a reference lift demand angle of attack signal α ref which is a continuously variable function of h between predetermined maximum and minimum angle of attack values, α max and α min , respectively, said function of h being independent of other aircraft parameters; (c) providing a signal α corresponding to the aircraft's actual angle of attack; (d) producing an error signal α.sub.ε corresponding to the difference between said reference lift demand angle of attack signal α ref and said actual angle of attack signal α; and (e) utilizing said error signal α.sub.ε as a control to the aircraft's dynamics for controlling the vertical lift characteristic of the aircraft.
Claim 5
Independent Claim
139 words
A method for producing an aircraft lift control vertical path guidance signal comprising the steps of: (a) providing a signal h corresponding to the aircraft's actual vertical velocity; (b) generating a reference lift demand angle of attack signal α ref which is a continuously variable function of h between predetermined maximum and minimum angle of attack values, α max and α min , respectively, said function of h being independent of other aircraft parameters; (c) providing a signal α corresponding to the aircraft's actual angle of attack; (d) producing an error signal α.sub.ε corresponding to the difference between said reference lift demand angle of attack signal α ref and said actual angle of attack signal α; and (e) utilizing said error signal α.sub.ε as a control to the aircraft's dynamics for controlling the vertical lift characteristic of the aircraft.
Claim 6
Dependent Claim
59 words
The method of claim 3 wherein step (b) comprises the further steps of: (i) limiting said α ref signal to said maximum level α max corresponding to a predetermined margin of angle of attack within stall of the aircraft; and (ii) limiting said α ref signal to said minimum level α min corresponding to the aircraft's desired forward velocity.
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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) | 1985-04-19 | 1985-10-19 | 1986-04-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-04-19 | 1989-10-19 | 1990-04-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-04-19 | 1993-10-19 | 1994-04-20 | $7700.00 | Window Closed / Lapsed |