US3805033A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Autopilot go-around mode pitch command signal computations
Assignee: Collins Radio Co
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Filing: 1972-11-20
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Granted: 1974-04-16
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Expires: 1992-11-20
Abstract
Abstract In a pitch command signal formulation where command error is damped by longitudinal acceleration, negative angular acceleration experienced during throttle retard in flare mode is precluded from effecting a pitch-down command upon go-around mode initiation by inclusion of a nominal pitch-up bias in conjunction with a synchronizer fader in the command signal formulation.
Inventors
- 👤 G Manke
- 👤 T Schuldt
- 👤 R Tribuno
- 👤 E Hattendorf
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 21:32
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607; G05D1/0653; G05D1/0676; G06; G06G; G06G7/00; G06G7/48; G06G7/78
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
184 words
In a pitch command signal development system for developing a command signal for go-around mode in an aircraft control system which system includes an error command signal input parameter corresponding to the discrepancy between a commanded condition and an experienced condition and including signal adding means for additively summing therewith a signal proportional to the longitudinal acceleration of said aircraft; means for precluding negatively sensed longitudinal acceleration signals experienced at the initiation of go-around flight control mode from producing a pitch-down command signal comprising; signal synchronizing means receiving said longitudinal acceleration signal and a reference pitch-up command bias as inputs thereto, said signal synchronizing means including means for producing an output signal, said output signal being input to said signal adding means for combining with said longitudinal acceleration signal. synchronizing said error command signal to said reference pick-up command bias signal prior to go-around initiation, and further including signal fading means operative at go-around initiation to fade out said reference pitch-up command bias signal at a predetermined rate while simultaneously fading said longitudinal acceleration signal into said additive summation with said error command signal.
Claim 2
Dependent Claim
184 words
In a pitch command signal development system for developing a command signal for go-around mode in an aircraft control system which system includes an error command signal input parameter corresponding to the discrepancy between a commanded condition and an experienced condition and including signal adding means for additively summing therewith a signal proportional to the longitudinal acceleration of said aircraft; means for precluding negatively sensed longitudinal acceleration signals experienced at the initiation of go-around flight control mode from producing a pitch-down command signal comprising; signal synchronizing means receiving said longitudinal acceleration signal and a reference pitch-up command bias as inputs thereto, said signal synchronizing means including means for producing an output signal, said output signal being input to said signal adding means for combining with said longitudinal acceleration signal. synchronizing said error command signal to said reference pick-up command bias signal prior to go-around initiation, and further including signal fading means operative at go-around initiation to fade out said reference pitch-up command bias signal at a predetermined rate while simultaneously fading said longitudinal acceleration signal into said additive summation with said error command signal.
Claim 3
Dependent Claim
194 words
A control means as defined in claim 1 wherein said signal means comprises a first signal combining means to which said error command signal is applied as a first input, the output of said first signal combining means comprising said output command signal, a second signal combining means receiving said longitudinal acceleration signal as a first input thereto and providing an output applied as a second input to said first signal combining means; said synchronizing means comprising a third signal combining means receiving said longitudinal acceleration signal and said reference pitch-up bias command signal as mutually subtractive inputs thereto, integrating means, switching means to which the output of said third signal combining means is selectively applied as input to said integrating means, the output from said integrating means being applied as a subtractive third input to said third signal combining means, signal translating means, said signal translating means having a predetermined time constant, and said switching means selectively connecting said signal translating meanS between the input and output of said integrating means while disconnecting the output of said third signal combining means, from the input to said integrating means upon go-around mode being effected.
Claim 4
Dependent Claim
179 words
In a pitch command signal development system for developing an output command signal for go-around mode in an aircraft control system which system includes an error command signal input parameter corresponding to the discrepancy between a commanded condition and an experienced condition and including the summation therewith of a signal proportional to the longitudinal acceleration of said aircraft; means for precluding negatively sensed longitudinal acceleration signals experienced at the initiation of go-around flight control mode from producing a pitch-down output command signal comprising; signal synchronizing means receiving said summation of error command signal and longitudinal acceleration signal and a reference pitch-up command bias as inputs thereto, said signal synchronizing means including means for producing an output signal for combining with said aforedefined summation which is synchronized to the difference between said reference pitch-up command bias signal and said summation signal prior to go-around initiation, and further including signal fading means operative upon go-around initiation to fade out said difference signal at a predetermined rate while simultaneously fading said longitudinal acceleration signal into said summation with said error command signal.
Claim 5
Dependent Claim
179 words
In a pitch command signal development system for developing an output command signal for go-around mode in an aircraft control system which system includes an error command signal input parameter corresponding to the discrepancy between a commanded condition and an experienced condition and including the summation therewith of a signal proportional to the longitudinal acceleration of said aircraft; means for precluding negatively sensed longitudinal acceleration signals experienced at the initiation of go-around flight control mode from producing a pitch-down output command signal comprising; signal synchronizing means receiving said summation of error command signal and longitudinal acceleration signal and a reference pitch-up command bias as inputs thereto, said signal synchronizing means including means for producing an output signal for combining with said aforedefined summation which is synchronized to the difference between said reference pitch-up command bias signal and said summation signal prior to go-around initiation, and further including signal fading means operative upon go-around initiation to fade out said difference signal at a predetermined rate while simultaneously fading said longitudinal acceleration signal into said summation with said error command signal.
Claim 6
Dependent Claim
168 words
A control means as defined in claim 3 wherein said signal synchronizing means comprises a first signal combining means to which the summation of said error command signal and said longitudinal acceleration signal is applied as a first input, the output of said first signal combining means comprising said output command signal, a second signal combining means receiving said output command signal and said reference pitch-up command bias signal as mutually subtractive inputs thereto, integrating means, switching means through which the output of said second signal combining means is selectively applied as input to said integrating means, the output from said integrating means being applied as a subtractive input to said first signal combining means, signal translating means, said signal translating means having a predetermined time constant, and said switching means selectively connecting said signal translating means between the input and output of said integrating means while disconnecting the output of said second signal combining means from the input to said integrating means upon go-around mode being effected.
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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) | 1977-04-15 | 1977-10-15 | 1978-04-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-04-15 | 1981-10-15 | 1982-04-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-04-15 | 1985-10-15 | 1986-04-16 | $7700.00 | Window Closed / Lapsed |