SPEED CONTROLLER FOR AIRCRAFT
First Claim
1. In a speed controller for an aircraft having a servo speed control loop and including a controller means for providing speed regulation in accordance with variations in airspeed from a command speed, the improvement comprising means for causing the servo controller to become unresponsive to an aircraft disturbance during the occurance of an aircraft disturbance for a predetermined period of time upon initiation of the disturbance, means for simultaneously causing an extension of an aircraft control surface and an alteration of the response of the servo controller, said last named means comprising a switching means having a plurality of contacts each of which is coupled to an associated prime mover for establishing a predetermined extension of a landing flap, a plurality of unidirectional electrical elements each coupled to an associated contact of said switching means and having a common output junction coupled to a monostable multivibrator for triggering said vibrator to provide an output pulse therefrom when a prime mover energizing potential is applied to a one of said contacts, and switching means coupled between said multivibrator and said controller and operative in response to said multivibrator pulse for altering the response of said controller.
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Accused Products
Abstract
A speed controller for an aircraft is described, having a servo speed control loop and means for altering the response of the servo controller to an aircraft disturbance for a predetermined period of time upon initiation of the disturbance.
11 Citations
4 Claims
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1. In a speed controller for an aircraft having a servo speed control loop and including a controller means for providing speed regulation in accordance with variations in airspeed from a command speed, the improvement comprising means for causing the servo controller to become unresponsive to an aircraft disturbance during the occurance of an aircraft disturbance for a predetermined period of time upon initiation of the disturbance, means for simultaneously causing an extension of an aircraft control surface and an alteration of the response of the servo controller, said last named means comprising a switching means having a plurality of contacts each of which is coupled to an associated prime mover for establishing a predetermined extension of a landing flap, a plurality of unidirectional electrical elements each coupled to an associated contact of said switching means and having a common output junction coupled to a monostable multivibrator for triggering said vibrator to provide an output pulse therefrom when a prime mover energizing potential is applied to a one of said contacts, and switching means coupled between said multivibrator and said controller and operative in response to said multivibrator pulse for altering the response of said controller.
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2. The aircraft controller of claim 1 wherein means are provided for automatically returning said multivibrator to its stable state prior to a termination of said output pulse when an error signal Delta v of the servo controller exceeds a predetermined value.
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3. The speed controller of claim 1 wherein said switching means for altering the response of said controller iS arranged for short circuiting an input of a component of said controller.
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4. The speed controller of claim 1 wherein said switching means for altering the response of said controller is adapted for interrupting a coupling between components of said controller.
Specification
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Current AssigneeHans-Dieter Buchholz, Hans-Peter Reerink
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Original AssigneeHans-Dieter Buchholz, Hans-Peter Reerink
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InventorsBuchholz, Hans-Dieter, Reerink, Hans-Peter
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Primary Examiner(s)Buchler, Milton
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Assistant Examiner(s)Forman, Jeffrey L.
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Application NumberUS04/820,430Time in Patent Office937 DaysField of Search244/77,77A,77D,42.1,77M,77S 318/621US Class Current244/182CPC Class CodesG05D 1/063 by acting on the motors
