Aircraft, control surface arrangements, and methods of assembling an aircraft

Patent metadata

Field	Value
Publication number	US-10220938-B2
Application number	US-201414567771-A
Country	US
Kind code	B2
Filing date	Dec 11, 2014
Priority date	Dec 11, 2014
Publication date	Mar 5, 2019
Grant date	Mar 5, 2019

Abstract

An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

First claim

What is claimed is:

1. An aircraft comprising:
an airframe;
a control surface; and
a plurality of rotary actuators cooperating to rotatably mount the control surface to the airframe, the plurality of rotary actuators being directly mounted to the airframe and supporting the control surface on the airframe and configured to rotate the control surface with respect to the airframe when the plurality of rotary actuators is actuated, the plurality of rotary actuators further configured to be coupled to the control surface at a longitudinally intermediate position along an output shaft of each rotary actuator.

2. The aircraft of claim 1 , further comprising a hinge mounting the control surface to the airframe, the hinge cooperating with the rotary actuator to support the control surface on the airframe, wherein a first longitudinal axis of the rotary actuator and a second longitudinal axis of the hinge are axially aligned.

3. The aircraft of claim 1 , wherein the rotary actuator has only a single connection point for delivering torque to the control surface.

4. The aircraft of claim 3 , wherein the single connection point is disposed at a position substantially spaced apart from a longitudinal end of the output shaft.

5. The aircraft of claim 1 , wherein the rotary actuator includes a fixed portion that remains stationary with respect to the airframe when the rotary actuator is actuated, and further includes a rotating portion that is configured to rotate with respect to the airframe when the rotary actuator is actuated, and wherein rotation of the rotating portion causes the rotary actuator to deliver torque to the control surface.

6. The aircraft of claim 5 , wherein the rotating portion is disposed internally within the fixed portion and is arranged substantially concentric therewith.

7. The aircraft of claim 1 , further comprising a plurality of the rotary actuators cooperating to rotatably mount the control surface to the airframe.

8. The aircraft of claim 7 , wherein the control surface is rotatably mounted to the airframe solely by the plurality of rotary actuators.

9. A control surface arrangement comprising:
a control surface; and
a plurality of rotary actuators coupled with the control surface and configured to be directly mounted to an airframe and to cooperate to rotatably mount the control surface to the airframe, the plurality of rotary actuators further configured to support the control surface on the airframe, to rotate the control surface with respect to the airframe when the plurality of rotary actuators are actuated, and to be coupled to the control surface at a longitudinally centered position along an output shaft of each rotary actuator of the plurality of rotary actuators.

10. The control surface arrangement of claim 9 , further comprising a hinge coupled with the control surface, the hinge configured to mount the control surface to the airframe and to cooperate with the plurality of rotary actuators to support the control surface on the airframe, wherein a first longitudinal axis of each rotary actuator and a second longitudinal axis of the hinge are axially aligned.

11. The control surface arrangement of claim 9 , wherein each rotary actuator has only a single connection point for delivering torque to the control surface.

12. The control surface arrangement of claim 11 , wherein the single connection point is disposed at an approximate longitudinal center of each rotary actuator.

13. The control surface arrangement of claim 9 , wherein each rotary actuator includes a fixed portion that is configured to remain stationary with respect to the airframe when the rotary actuator is actuated, and further includes a rotating portion that is configured to rotate with respect to the airframe when the rotary actuator is actuated, and wherein rotation of the rotating portion causes the rotary actuator to deliver torque to the control surface.

14. The control surface arrangement of claim 13 , wherein the rotating portion is disposed internally within the fixed portion and is arranged substantially concentric therewith.

15. The control surface arrangement of claim 9 , wherein the control surface arrangement is configured to be mounted to the airframe solely by the plurality of rotary actuators.

16. A method of assembling an aircraft, the method comprising the steps of:
providing an airframe and a control surface;
positioning the control surface with respect to the airframe to form a plurality of coupling points; and
attaching the control surface to the airframe with a plurality of rotary actuators at least one coupling point of the plurality of coupling points,
wherein each actuator of the plurality of actuators is directly mounted to the airframe, wherein the plurality of rotary actuators is configured to support the control surface on the airframe, to rotate the control surface with respect to the airframe when the rotary actuator is actuated, and to be coupled to the control surface at a longitudinally centered position along an output shaft of each rotary actuator, the control surface being rotably mounted to the airframe by the plurality of actuators.

17. The method of claim 16 , further comprising the step of attaching the control surface to the airframe with a hinge at another coupling point of the plurality of coupling points.

18. The method of claim 17 , further comprising the step of axially aligning the rotary actuator with the hinge.

19. The method of claim 16 , further comprising the step of attaching the control surface to the airframe with an additional rotary actuator at each remaining coupling point.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Knight Michael
• Grieco James

Classifications

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C13/38 Primary

  with power amplification · CPC title

• B64C13/40

  using fluid pressure · CPC title

• B64C13/24

  Transmitting means · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic