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US 12,583,603 B2Granted
Autothrottle system for aircraft
AssigneeTextron Innovations Inc.
InventorsAlec Charles Willford, Ronald J. Parker, Michael R. DePinto
Life of this patent
Estimating the term…
Abstract
Disclosed is an automatic throttle arrangement utilizing a servo which receives commands from a controller on an aircraft and responsively rotates a mechanical device that is linked by a cable arrangement with the aircraft's throttle lever enabling automated throttle control. The mechanical device can be fixed to the throttle lever assembly using rivets designed to fail in case the servo/cable arrangement jams. This leaves the lever able to continue manual function.
Claims21
A throttle system for an aircraft, the throttle system comprising:
- a servo configured to rotate a servo output mechanism in response to autopilot commands received from a controller;
- a throttle lever configured to rotate around a stationary hub, the throttle lever comprising:
- an autopilot activation button electrically connected to the controller;
- and
- an autopilot deactivation button electrically connected to the controller;
- a mechanical connection made between the servo output mechanism and the throttle lever, the mechanical connection being configured to move in response to a rotation of the servo output mechanism in an autopilot mode during an operation;
- and
- a breakable link included in the mechanical connection and configured to disconnect the throttle lever from the servo output mechanism;
- wherein the throttle system is configured to activate the autopilot mode when the throttle lever's autopilot activation button is pressed;
- wherein the throttle system is configured to deactivate the autopilot mode whenever a user either presses the throttle lever's autopilot deactivation button or manually rotates the throttle lever;
- wherein the breakable link is configured to break whenever a predetermined force, which breaks the breakable link, is applied to the throttle lever during a failure mode which is preventing the user from manually rotating the throttle lever to deactivate the autopilot mode;
- and
- wherein manually rotating the throttle lever to deactivate the autopilot mode does not cause the breakable link to break unless the throttle lever is prevented from rotating by the failure mode.
10 more elements
An aircraft system comprising:
- a controller configured to operate a servo to create angular movement of a control lever during an autopilot mode, the control lever comprising:
- an autopilot activation button electrically connected to the controller;
- and
- an autopilot deactivation button electrically connected to the controller;
- a mechanical connection made between the servo and the control lever, the mechanical connection comprising a follower member which rotates with the control lever and on a common axis with the control lever, the follower member receiving rotation from the servo and consequentially imparting rotation into the control lever;
- and
- a breakable link included in the mechanical connection and configured to disconnect the control lever from the servo;
- wherein the aircraft system is configured to activate the autopilot mode when the control lever's autopilot activation button is pressed;
- wherein the aircraft system is configured to deactivate the autopilot mode whenever a user either presses the control lever's autopilot deactivation button or manually adjusts the control lever;
- and
- wherein the breakable link is configured to break whenever a predetermined force, which breaks the breakable link, is applied to the control lever during a failure mode which is preventing the user from manually adjusting the control lever to deactivate the autopilot mode;
- and
- wherein manually adjusting the control lever to deactivate the autopilot mode does not cause the breakable link to break unless the control lever is prevented from rotating by the failure mode.
10 more elements
Dependencies are inferred from the claim text.