# US 11,077,934 B2 · Aircraft, control surface arrangements, and methods of assembling an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,077,934 B2 - Document ID: US11077934B2 - Status: Granted - Kind: B2 - Application number: 16/291,527 - Filed: 2019-03-04 - Published: 2019-06-27 - Granted: 2021-08-03 - Earliest claimed: 2014-12-11 - Assignees: Gulfstream Aerospace Corporation - Applicants: Gulfstream Aerospace Corporation - Inventors: Michael Knight; James Grieco - Web page: https://patentgrep.com/patent/US11077934B2 ## CPC - B64C 13/38: with power amplification - B64C 9/02: Mounting or supporting thereof - B64C 13/24: Transmitting means - Y02T 50/40: Weight reduction - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein the rotary actuator has only a single connection point for delivering torque to the control surface. ### Claim 4 (depends on 3) The aircraft of claim 3, wherein the single connection point is disposed at an approximate longitudinal center of the rotary actuator. ### Claim 5 (depends on 1) The aircraft of claim 1, further comprising a plurality of the rotary actuators cooperating to rotatably mount the control surface to the airframe. ### Claim 6 (depends on 5) The aircraft of claim 5, wherein the control surface is rotatably mounted to the airframe in a manner that is free of hinges. ### Claim 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. ### Claim 8 (depends on 7) 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. ### Claim 9 (depends on 7) The control surface arrangement of claim 7, wherein the rotary actuator has only a single connection point for delivering torque to the control surface. ### Claim 10 (depends on 9) The control surface arrangement of claim 9, wherein the single connection point is disposed at an approximate longitudinal center of the rotary actuator. ### Claim 11 (depends on 7) 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. ### Claim 12 (depends on 11) 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. ### Claim 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. ### Claim 14 (depends on 13) 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. ### Claim 15 (depends on 14) The method of claim 14, further comprising the step of axially aligning the rotary actuator with the hinge. ### Claim 16 (depends on 13) 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.