US3658280A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Altitude and glide slope track controller
Assignee: McDonnell Douglas Corp
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Filing: 1970-10-29
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Granted: 1972-04-25
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Expires: 1990-10-29
Abstract
Abstract Aircraft flight control system providing rapid aircraft responses when controlling aircraft altitude, glide slope tracking and flare by the coordinated and combined use of spoilers and elevators in a closed loop control system. The system utilizes both spoiler-generated direct lift and elevatorgenerated lift due to rotation wherein the spoilers provide immediate changes in aircraft normal acceleration in response to an acceleration command and the elevators provide similar but longer term changes in response to an associated pitch rate command. The closed loop control system includes a common accelerometer feedback path to provide acceleration control through both spoilers and elevators, and a crossfeed path between the spoilers and elevators to cancel undesirable pitching moments produced by the spoilers.
Inventors
- 👤 John D Mcdonnell
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 02:17
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
204 words
In an aircraft including a spoiler and an elevator, a flight control system comprising: a spoiler branch including spoiler control means for driving said spoiler; an elevator branch including elevator control means for driving said elevator; means for providing an acceleration command signal; a normal acceleration feedback path including means for sensing normal acceleration of said aircraft and providing a normal acceleration signal therefrom; means for algebraically summing said acceleration command signal and said normal acceleration signal to provide an acceleration error signal; means for applying said acceleration error signal to said spoiler branch to drive said spoiler, said spoiler being driven to provide a direct lift to said aircraft; a pitch rate feedback path including means for sensing pitch rate of said aircraft and providing a pitch rate signal therefrom; means for algebraically summing said acceleration error signal and said pitch rate signal to provide a pitch rate error signal; and means for applying said pitch rate error signal to said elevator branch to drive said elevator, said elevator being driven to provide rotation-caused lift to said aircraft whereby the spoiler-generated direct lift complements the elevatorgenerated lift due to rotation and said acceleration error and pitch rate error signals are reduced to zero.
Claim 2
Dependent Claim
204 words
In an aircraft including a spoiler and an elevator, a flight control system comprising: a spoiler branch including spoiler control means for driving said spoiler; an elevator branch including elevator control means for driving said elevator; means for providing an acceleration command signal; a normal acceleration feedback path including means for sensing normal acceleration of said aircraft and providing a normal acceleration signal therefrom; means for algebraically summing said acceleration command signal and said normal acceleration signal to provide an acceleration error signal; means for applying said acceleration error signal to said spoiler branch to drive said spoiler, said spoiler being driven to provide a direct lift to said aircraft; a pitch rate feedback path including means for sensing pitch rate of said aircraft and providing a pitch rate signal therefrom; means for algebraically summing said acceleration error signal and said pitch rate signal to provide a pitch rate error signal; and means for applying said pitch rate error signal to said elevator branch to drive said elevator, said elevator being driven to provide rotation-caused lift to said aircraft whereby the spoiler-generated direct lift complements the elevatorgenerated lift due to rotation and said acceleration error and pitch rate error signals are reduced to zero.
Claim 3
Dependent Claim
31 words
The invention as defined in claim 1 wherein said spoiler control means includes washout means for returning said spoiler to its nominal position after a predetermined elapsed time following actuation thereof.
Claim 4
Dependent Claim
32 words
The invention as defined in claim 1 further comprising a crossfeed path between said spoiler and elevator branches, said crossfeed path including means for canceling undesirable pitching moments produced by said spoiler.
Claim 5
Dependent Claim
92 words
The invention as defined in claim 1 wherein said acceleration command signal is an altitude rate error signal, and said means for providing said altitude rate error signal includes: means for providing a system error signal; means for providing an altitude rate command signal from said system error signal; an altitude Rate feedback path including means for sensing altitude rate of said aircraft and providing an altitude rate signal therefrom; and means for algebraically summing said altitude rate command signal and said altitude rate signal to provide said altitude rate error signal.
Claim 6
Dependent Claim
18 words
The invention as defined in claim 4 wherein said system error signal is a glide slope error signal.
Claim 7
Dependent Claim
31 words
The invention as defined in claim 5 wherein said spoiler control means includes washout means for returning said spoiler to its nominal position after a predetermined elapsed time following actuation thereof.
Claim 8
Dependent Claim
32 words
The invention as defined in claim 5 further comprising a crossfeed path between said spoiler and elevator branches, said crossfeed path including means for canceling undesirable pitching moments produced by said spoiler.
Claim 9
Dependent Claim
61 words
The invention as defined in claim 4 wherein said means for providing a system error signal includes: means for providing an altitude command signal; an altitude feedback path including means for sensing altitude of said aircraft and providing an altitude signal therefrom; and means for algebraically summing said altitude command signal and said altitude signal to provide said system error signal.
Claim 10
Dependent Claim
31 words
The invention as defined in claim 8 wherein said spoiler control means includes washout means for returning said spoiler to its nominal position after a predetermined elapsed time following actuation thereof.
Claim 11
Dependent Claim
32 words
The invention as defined in claim 9 further comprising a crossfeed path between said spoiler and elevator branches, said crossfeed path including means for canceling undesirable pitching moments produced by said spoiler.
References Cited (Backward Citations)
US2943823A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-04-25 | 1975-10-25 | 1976-04-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-04-25 | 1979-10-25 | 1980-04-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-04-25 | 1983-10-25 | 1984-04-25 | $7700.00 | Window Closed / Lapsed |