US4617633A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Direct lift command blending
Assignee: United States Department of the Air Force
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Filing: 1984-05-29
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Granted: 1986-10-14
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Expires: 2004-05-29
Abstract
Abstract The rapid and precise control of an aircraft flight path is obtained by a continuous blending of direct lift and conventional longitudinal control system commands by a unit that consists of a combination of a linear gradient and breakout element, a blending integrator, a nonlinear element, a Direct Lift Limit element, an interconnect gain element, and three summing junctions. Direct lift is blended with conventional control as the pilot manual command is conditioned by the linear gradient and breakout element to provide the command signal to the first summing junction. The difference between this command and the output of the blending integrator is applied to the recentering nonlinear element. The direct lift command is obtained by passing the output of the recentering nonlinear element through the direct lift limit element. The second summing junction is used to reform the total system command which is applied to the third summing junction. The conventional longitudinal command is the output of the third summing junction; this output being the difference between the total system command and the direct lift command as modified by the interconnect gain.
Inventors
- 👤 Jack D. McAllister
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 21:00
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0615; G05D1/0623; B; B64; B64C; B64C13/00
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
85 words
An aircraft flight control corcuit receiving a system command signal and generating direct lift and longitudinal command signals, said flight control circuit comprising: a direct lift command signal circuit receiving said system command signal and developing a direct lift command signal as a function thereof, subtraction means differencing said system command signal and said direct lift command signal to provide a longitudinal command signal, and a blending circuit, said blending circuit constraining said longitudinal comman signal as a function of said direct lift command signal.
Claim 2
Dependent Claim
85 words
An aircraft flight control corcuit receiving a system command signal and generating direct lift and longitudinal command signals, said flight control circuit comprising: a direct lift command signal circuit receiving said system command signal and developing a direct lift command signal as a function thereof, subtraction means differencing said system command signal and said direct lift command signal to provide a longitudinal command signal, and a blending circuit, said blending circuit constraining said longitudinal comman signal as a function of said direct lift command signal.
Claim 3
Dependent Claim
145 words
An aircraft flight control circuit receiving a system command signal and generating direct lift and longitudinal command signals as described in claim 1 wherein said direct lift command signal circuit comprises: a blending integrator, generating automatic direct lift command signals during an initial system transient response to a pilot manual command signal, a first summing junction, said first summing junction generating an output signal by subtracting the output of said blending integrator from the pilot manual command signal, a recentering nonlinear element, receiving said output signal from said first summing junction and producing a recentering signal that produces differences in system sensitivity in said direct lift command signal circuit between conditions of large and small pilot manual command inputs, and a direct lift element, said direct lift element receiving said recentering signal produced by said recentering nonlinear element and generating the direct lift command signal.
Claim 4
Dependent Claim
67 words
An aircraft flight control circuit receiving a system command signal and generating direct lift and longitudinal command signals as described in claim 2 wherein said blending circuit comprises an interconnected gain circuit, said interconnected gain circuit receiving said direct lift command signal generated by said direct lift element and processing said direct lift command signal with a gain of less than unity to guicken the transient response.
Claim 5
Dependent Claim
98 words
An aircraft flight control circuit receiving a system command and generating direct lift and longitudinal command signals as described in claim 3 wherein said subtraction means comprises: second and third summing junction, said second summing junction producing a total system command signal by combining said automatic direct lift command signals, generated by said blending integrator, with said recentering signal produced by said recentering nonlinear element, said third summing junction generating the longitudinal command signal by subtracting said direct lift command signal, processed by said blending circuit, from said total system command signal produced by said second summing junction.
Claim 6
Dependent Claim
162 words
An aircraft flight control circuit receiving a system command and generating direct lift and longitudinal command signals as described in claim 4, including first and second air data gain circuits, said air data gain circuits modifying said aircraft flight control circuit for use with aircraft having pitch rate command flight control systems, said first air data gain receiving said system command signal and applying an air data gain equal to the airspeed velocity of the host aircraft to said system command signal, said first air data gain generating a normal acceleration command signal for input to said aircraft flight control circuit, said second air data gain receiving the output signal of said third summing junction in said subtraction means, said second air data gain applying a gain of inverse value of said airspeed velocity of said host aircraft, said second air data gain reconverting the output of said third summing junction to the proper value for pitch rate command flight control systems.
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) | 1989-10-13 | 1990-04-14 | 1990-10-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-10-13 | 1994-04-14 | 1994-10-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-10-13 | 1998-04-14 | 1998-10-14 | $7700.00 | Window Closed / Lapsed |