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

Patent metadata

Field	Value
Publication number	US-11077934-B2
Application number	US-201916291527-A
Country	US
Kind code	B2
Filing date	Mar 4, 2019
Priority date	Dec 11, 2014
Publication date	Aug 3, 2021
Grant date	Aug 3, 2021

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 rotary actuator rotatably mounting the control surface to the airframe, the rotary actuator supporting the control surface on the airframe and configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated, the rotary actuator further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator,
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, and
wherein the rotating portion is disposed internally within the fixed portion and is arranged substantially concentric therewith.

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 an approximate longitudinal center of the rotary actuator.

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

6. The aircraft of claim 5 , wherein the control surface is rotatably mounted to the airframe in a manner that is free of hinges.

7. A control surface arrangement comprising:
a control surface; and
a rotary actuator coupled with the control surface and configured to rotatably mount the control surface to an airframe, the rotary actuator 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 deliver torque to the control surface from a intermediate portion of the rotary actuator,
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, and
wherein the rotating portion is disposed internally within the fixed portion and is arranged substantially concentric therewith.

8. The control surface arrangement of claim 7 , 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 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.

9. The control surface arrangement of claim 7 , wherein the rotary actuator has only a single connection point for delivering torque to the control surface.

10. The control surface arrangement of claim 9 , wherein the single connection point is disposed at an approximate longitudinal center of the rotary actuator.

11. The control surface arrangement of claim 7 , further comprising a plurality of the rotary actuators coupled with the control surface and configured to cooperate to rotatably mount the control surface to the airframe.

12. The control surface arrangement of claim 11 , wherein the control surface arrangement is configured to be mounted to the airframe in a manner that is free of hinges.

13. 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 rotary actuator at at least one coupling point of the plurality of coupling points,
wherein the rotary actuator 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 deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator, and
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, and
wherein the rotating portion is disposed internally within the fixed portion and is arranged substantially concentric therewith.

14. The method of claim 13 , 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.

15. The method of claim 14 , further comprising the step of axially aligning the rotary actuator with the hinge.

16. The method of claim 13 , 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

• Y02T50/40

  Weight reduction · CPC title

• B64C13/24

  Transmitting means · CPC title

• B64C13/40

  using fluid pressure · CPC title