Patent US3617848A successfully refreshed from Google Patents.
US3617848A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Synchronization and attitude command nulling apparatus
Assignee: Honeywell Inc
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Filing: 1968-10-10
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Granted: 1971-11-02
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Expires: 1988-10-10
Abstract
Abstract A pitch axis flight control having a single motor to provide preengagement synchronization of the pitch axis manual controller and automatic nulling of the control after a control mode change from an attitude hold mode to an altitude hold mode. Preengagement synchronization is provided by electrically summing outputs of a vertical gyro and the manual controller, and using the summed signal to control an amplifier and motor combination, which drives the manual controller to a position such that the vertical gyro output signal is nullified by the manual controller output. Upon switching of the system from an attitude hold mode to an altitude hold mode, a switching relay actuates an altitude error device whose signal is combined with the vertical gyro signal and the pitch controller signal to derive a control error signal. To insure levelling off of the craft in altitude hold, a switching relay disconnects the vertical gyro signal from the amplifier and motor combination, thereby causing the pitch control potentiometer to be driven to a null output. Apparatus for automatically switching the flight control from an altitude to an attitude hold mode upon repositioning the pitch control potentiometer is also disclosed.
Inventors
- 👤 Robert E Friday
- 👤 Clyde M Kobe
- 👤 James W Locker
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 10:37
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/0055; G05D1/0061
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
343 words
In combination with a dirigible craft automatic control system of the type wherein an attitude hold servo actuator control signal is derived from an attitude error output signal of a vertical gyro and an attitude command output signal from a manual controller and also wherein an altitude hold servo actuator control signal is derived from an altitude error output signal of an altimeter, the improvement which comprises: electromechanical means, including input means and output means connected to said manual controller to vary the output therefrom in accordance with the algebraic sum of the signals applied to the input means; connecting means for conducting the command output signal of said manual controller to the input means of said electromechanical means; first switchable means connected between said vertical gyro and said electromechanical means, said first switchable means operable in a first condition to conduct the attitude error output signal of said vertical gyro to the input means of said electromechanical means and operable in a second condition to disconnect the attitude error output signal of said vertical gyro from the input means of said electromechanical means; second switchable means operative in a first condition to conduct said servo actuator control signal to said servo actuators, and operative in a second condition to disconnect the servo actuator control signal from said servo actuators; means for enabling the output of said altimeter; and mode selection means for enabling the automatic control system in an attitude synchronization mode by placing said first switchable means in the first condition while said second switchable means is in the second condition and for enabling the automatic control system in an attitude control mode by switching said first switchable means from the first condition to the second condition and switching said second switchable means to the first condition while simultaneously disabling said electromechanical means, said mode selection means also operative to enable the automatic control system in an altitude hold mode by actuating the means for enabling the output of said altimeter and placing said first switchable means in the second condition.
Claim 2
Dependent Claim
343 words
In combination with a dirigible craft automatic control system of the type wherein an attitude hold servo actuator control signal is derived from an attitude error output signal of a vertical gyro and an attitude command output signal from a manual controller and also wherein an altitude hold servo actuator control signal is derived from an altitude error output signal of an altimeter, the improvement which comprises: electromechanical means, including input means and output means connected to said manual controller to vary the output therefrom in accordance with the algebraic sum of the signals applied to the input means; connecting means for conducting the command output signal of said manual controller to the input means of said electromechanical means; first switchable means connected between said vertical gyro and said electromechanical means, said first switchable means operable in a first condition to conduct the attitude error output signal of said vertical gyro to the input means of said electromechanical means and operable in a second condition to disconnect the attitude error output signal of said vertical gyro from the input means of said electromechanical means; second switchable means operative in a first condition to conduct said servo actuator control signal to said servo actuators, and operative in a second condition to disconnect the servo actuator control signal from said servo actuators; means for enabling the output of said altimeter; and mode selection means for enabling the automatic control system in an attitude synchronization mode by placing said first switchable means in the first condition while said second switchable means is in the second condition and for enabling the automatic control system in an attitude control mode by switching said first switchable means from the first condition to the second condition and switching said second switchable means to the first condition while simultaneously disabling said electromechanical means, said mode selection means also operative to enable the automatic control system in an altitude hold mode by actuating the means for enabling the output of said altimeter and placing said first switchable means in the second condition.
Claim 3
Dependent Claim
37 words
Apparatus of the class described in claim 1 wherein said mode selection means includes means for returning said automatic control systEm from an altitude hold mode to an attitude hold mode when said manual controller is actuated.
Claim 4
Dependent Claim
203 words
An automatic flight control system wherein a control surface servo amplifier receives its input signals from an altimeter, a vertical gyro, and a manual controller, means for synchronizing the position of said manual controller with the output of said vertical gyro before enabling said servo amplifier and also for nulling the output of said controller when an altitude hold mode is engaged, said means comprising in combination: motor means connected to vary the position of said manual controller in response to an input; amplifier means connected to the input of said motor means, said amplifier means operable to deliver the drive signal to said motor means in response to an input; and signal selection means connected to the input of said amplifier means and the output of said manual controller and said vertical gyro, said signal selection means operative to conduct a signal to the input of said amplifier means representative of the output signal of said vertical gyro and said manual controller to provide an attitude synchronization function before said servo amplifier is enabled, said signal selection means operative to conduct the output signal of said controller to the input means of said amplifier means, when an altitude hold mode is selected.
Claim 5
Dependent Claim
203 words
An automatic flight control system wherein a control surface servo amplifier receives its input signals from an altimeter, a vertical gyro, and a manual controller, means for synchronizing the position of said manual controller with the output of said vertical gyro before enabling said servo amplifier and also for nulling the output of said controller when an altitude hold mode is engaged, said means comprising in combination: motor means connected to vary the position of said manual controller in response to an input; amplifier means connected to the input of said motor means, said amplifier means operable to deliver the drive signal to said motor means in response to an input; and signal selection means connected to the input of said amplifier means and the output of said manual controller and said vertical gyro, said signal selection means operative to conduct a signal to the input of said amplifier means representative of the output signal of said vertical gyro and said manual controller to provide an attitude synchronization function before said servo amplifier is enabled, said signal selection means operative to conduct the output signal of said controller to the input means of said amplifier means, when an altitude hold mode is selected.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-11-01 | 1975-05-03 | 1975-11-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-11-01 | 1979-05-03 | 1979-11-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-11-01 | 1983-05-03 | 1983-11-02 | $7700.00 | Window Closed / Lapsed |