US3624364A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Parallel speed stabilization system
Assignee: United States Department of the Army
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Filing: 1970-01-28
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Granted: 1971-11-30
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Expires: 1990-01-28
Abstract
Abstract A nonproportional, adaptive, predictive control system for automatically, stabilizing the speed of an aircraft at a pilotselected speed against changes in the trim airspeed of the aircraft. The system is designed to operate in parallel with the pilot so that it can be manually overridden at anytime; however, when the controls are left free, the system will operate the aircraft independently of the pilot.
Inventors
- 👤 Daniel O Dommasch
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 12:43
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
105 words
In an aircraft equipped with longitudinal control surfaces, a parallel speed stabilization system comprising an airspeed sensor means which generates a first signal, speed selection means which generates a second signal, means for combining said first and second signals to produce an error signal, a logic system which produces an output displacement command in response to said error signal, said output displacement command being nonproportional to said error signal, actuating means responsive to said displacement command to effect a displacement in said longitudinal control surfaces, said actuator means connected to said longitudinal control surfaces through clutch means to permit manual override of said stabilization system.
Claim 2
Dependent Claim
105 words
In an aircraft equipped with longitudinal control surfaces, a parallel speed stabilization system comprising an airspeed sensor means which generates a first signal, speed selection means which generates a second signal, means for combining said first and second signals to produce an error signal, a logic system which produces an output displacement command in response to said error signal, said output displacement command being nonproportional to said error signal, actuating means responsive to said displacement command to effect a displacement in said longitudinal control surfaces, said actuator means connected to said longitudinal control surfaces through clutch means to permit manual override of said stabilization system.
Claim 3
Dependent Claim
57 words
The system of claim 1 including means to differentiate said first signal, means to form a signal proportional to the predicted speed change at a future time, means for producing a predicted error signal by combining said error signal and said predicted speed change signal, said predicted error signal forming the input signal to said logic system.
Claim 4
Dependent Claim
23 words
The system of claim 1 which further comprises means to change the system gain in response to changes in said predicted error signal.
Claim 5
Dependent Claim
32 words
The system of claim 3 further comprising voltage ratio detector effective to change the system gain in response to changes in the ratio of said predicted error signal to said error signal.
Claim 6
Dependent Claim
277 words
In an aircraft equipped with longitudinal control surfaces, a parallel speed stabilization system comprising an airspeed sensor means which produces a first signal proportional to the speed of the aircraft, speed selection means which produces a second signal indicative of the desired airspeed, first combining means for summing said first and second signals to produce an error signal, a logic system comprising differentiation means operating on said first signal, filtering means operating on said differentiated first signal, means to form a predicted speed change signal Comprising the product of said differentiated first signal and a time interval, second combining means to form a first predicted error signal by summing said error signal and said predicted speed change signal, means for dividing said first predicted error signal by a time constant to form a second predicted error signal, clipping means connected to said second combining means operating on said second predicted error signal, third combining means for summing said clipped second predicted error signal and said differentiated first signal, amplifier means connected to said third combining means including means to change the gain of said amplifier in response to changes in the ratio of said first predicted error signal to said error signal, integrating means connected to the output of said amplifier means, fourth combining means connected to said integrator output for forming a displacement command signal by summing the output signal from said integrating means and a damping signal, actuator means responsive to said displacement command signal to effect a displacement of said longitudinal control surfaces, said actuator means operatively connected to said longitudinal control surfaces through clutch means to permit manual override of said stabilization system.
Claim 7
Dependent Claim
277 words
In an aircraft equipped with longitudinal control surfaces, a parallel speed stabilization system comprising an airspeed sensor means which produces a first signal proportional to the speed of the aircraft, speed selection means which produces a second signal indicative of the desired airspeed, first combining means for summing said first and second signals to produce an error signal, a logic system comprising differentiation means operating on said first signal, filtering means operating on said differentiated first signal, means to form a predicted speed change signal Comprising the product of said differentiated first signal and a time interval, second combining means to form a first predicted error signal by summing said error signal and said predicted speed change signal, means for dividing said first predicted error signal by a time constant to form a second predicted error signal, clipping means connected to said second combining means operating on said second predicted error signal, third combining means for summing said clipped second predicted error signal and said differentiated first signal, amplifier means connected to said third combining means including means to change the gain of said amplifier in response to changes in the ratio of said first predicted error signal to said error signal, integrating means connected to the output of said amplifier means, fourth combining means connected to said integrator output for forming a displacement command signal by summing the output signal from said integrating means and a damping signal, actuator means responsive to said displacement command signal to effect a displacement of said longitudinal control surfaces, said actuator means operatively connected to said longitudinal control surfaces through clutch means to permit manual override of said stabilization system.
References Cited (Backward Citations)
US3533579A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-11-29 | 1975-05-31 | 1975-11-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-11-29 | 1979-05-31 | 1979-11-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-11-29 | 1983-05-31 | 1983-11-30 | $7700.00 | Window Closed / Lapsed |