Electronically Controlled Rotary Actuator for an Aircraft Control Surface
AssigneeThe Boeing Company
InventorsNeal Van Huynh, Patrick Joseph McCormick
Life of this patent
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Abstract
A method and apparatus for positioning a control surface. A desired position for the control surface associated with an aerodynamic aircraft structure is identified. The control surface is moved to the desired position using an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.
Claims25
An aircraft control surface system comprising:
- a control surface associated with an aerodynamic aircraft structure;
- and
- an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein the electronically controlled rotary actuator system is associated with the control surface and moves with variable pressure to position the control surface during operation of the electronically controlled rotary actuator system, and wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.
An aircraft control surface system comprising:
- a control surface that is associated with an aerodynamic aircraft structure;
- a rotary actuator having an output shaft that is moveable;
- a hydraulic pump that is connected to the rotary actuator, wherein the hydraulic pump sends fluid into the rotary actuator;
- an electric motor system that is operable to cause the hydraulic pump to send the fluid into the rotary actuator resulting in the output shaft moving the control surface with a variable pressure towards a desired position;
- a housing containing the rotary actuator, the hydraulic pump, and the electric motor system;
- and
- a controller that receives a position command comprising the desired position for the control surface and sends a command to the electric motor system using the position command, wherein the command is selected to cause the electric motor system to operate the hydraulic pump to send the fluid into the rotary actuator such that the output shaft moves the control surface towards the desired position.
A method for positioning a control surface, the method comprising:
- identifying a desired position for the control surface that is associated with an aerodynamic aircraft structure;
- and
- moving the control surface to the desired position using an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.
A hybrid rotary actuator system comprising:
- a hydraulic rotary actuator system comprising:
- a rotary actuator that is connected to a control surface, wherein the rotary actuator is configured to move the control surface;
- an electrohydraulic servo valve that controls fluid sent into and out of the rotary actuator;
- a remote electronic unit that controls the electrohydraulic servo valve using a position command;
- and
- an electric hydraulic backup system comprising:
- a hydraulic pump that pumps fluid through the electrohydraulic servo valve;
- an electric motor system that is configured to control the hydraulic pump;
- an inlet shutoff valve that connects a central hydraulics systems to the electrohydraulic servo valve;
- and
- a motor driver that is controlled by the remote electronic unit when the hydraulic rotary actuator system does not operate as desired, wherein the remote electronic unit is configured to shutoff a connection to the central hydraulics systems;
- the motor driver is configured to control the electric motor system;
- and the electric hydraulic backup system is a backup to the hydraulic rotary actuator system.
Dependencies are inferred from the claim text.