Rotary actuated spoiler configuration
AssigneeThe Boeing Company
InventorsJoli K. Umetsu, Kevin Tsai
Life of this patent
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Abstract
An aerial vehicle control surface actuation system comprises a rotary actuator having opposing output shaft ends that are coupled to first and second torque tubes via actuator universal joints. The first and second torque tubes extend angularly from the rotary actuator. The system further comprises first and second pivot joints that are coupled to a hinged end of a control surface. The first and second pivot joints are coupled to the first and second torque tubes, respectively, via control surface universal joints. In this configuration, rotation of the first and second torque tubes causes rotation of the control surface relative to a hinge axis.
Claims21
An aerial vehicle control surface actuation system, comprising:
- a rotary actuator having opposing output shaft ends coupled via actuator universal joints to first and second torque tubes extending angularly from substantially obliquely relative to the rotary actuator;
- a control surface;
- and
- first and second pivot joints coupled to a hinged end of the control surface, each of the first and second pivot joints being respectively coupled to the first and second torque tubes via control surface universal joints such that rotation of the first and second torque tubes causes rotation of the control surface relative to a hinge axis.
An aerial vehicle comprising:
- a fuselage;
- a wing including a rear spar;
- a control surface actuation system mounted on the wing comprising:
- an actuator support fitting mounted on the rear spar;
- a rotary actuator mounted on the actuator support fitting and having opposing output shaft ends, the rotary actuator defining an actuator axis;
- first and second torque tubes coupled via actuator universal joints to the opposing output shaft ends and extending substantially obliquely relative to the opposing output shaft ends;
- first and second pivot mountings mounted on the rear spar on opposing sides of the rotary actuator;
- a control surface;
- and
- first and second pivot joints coupled to a hinged end of the control surface and respectively connected to the first and second pivot mountings, each joint being coupled to one of the first and second torque tubes via control surface universal joints, such that rotation of the first and second torque tubes causes rotation of the control surface relative to a hinge axis.
A method of providing a rotary-actuated control surface comprising:
- securing a rotary actuator having opposing output shaft ends to an aft portion of a wing structure;
- coupling, via actuator universal joints, the opposing output shaft ends to first and second torque tubes extending angularly from substantially obliquely relative to the rotary actuator;
- coupling first and second pivot joints respectively to the first and second torque tubes via control surface universal joints;
- coupling the first and second pivot joints to a hinged end of the control surface;
- securing first and second pivot mountings on the aft portion of the wing structure, each having one or more holes that define a hinge axis and are configured to support the first and second pivot joints about which the control surface rotates;
- and
- coupling the first and second pivot joints to the one or more holes in the first and second pivot mountings.
Dependencies are inferred from the claim text.