公开(公告)号：US11299266B2

公开(公告)日：2022-04-12

申请号：US15793682

申请日：2017-10-25

Applicant: Gulfstream Aerospace Corporation

Inventor： George Hicks ,  Donald Howe ,  Gregory Howe ,  Joe Gavin

IPC: B64C30/00 ,  B64C23/06 ,  B64C3/10

Abstract: A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge.

公开(公告)号：US20190118931A1

公开(公告)日：2019-04-25

申请号：US15793682

申请日：2017-10-25

Applicant: Gulfstream Aerospace Corporation

Inventor： George Hicks ,  Donald Howe ,  Gregory Howe ,  Joe Gavin

IPC: B64C3/28

Abstract: A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge.

公开(公告)号：US11686246B2

公开(公告)日：2023-06-27

申请号：US17451137

申请日：2021-10-15

Applicant: Gulfstream Aerospace Corporation

Inventor： Shawn Bennett ,  Joe Gavin ,  Nicholas Powell ,  Donald Freund ,  Derek Muzychka ,  John Louis

IPC: F02C7/042 ,  F02C7/057 ,  F02K1/16 ,  B64D33/02

CPC classification number: F02C7/042 ,  F02C7/057 ,  F02K1/165 ,  B64D2033/0206 ,  B64D2033/026 ,  B64D2033/0226 ,  F05D2220/323 ,  F05D2270/122

Abstract: An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.

公开(公告)号：US20230120249A1

公开(公告)日：2023-04-20

申请号：US17451137

申请日：2021-10-15

Applicant: Gulfstream Aerospace Corporation

Inventor： Shawn Bennett ,  Joe Gavin ,  Nicholas Powell ,  Donald Freund ,  Derek Muzychka ,  John Louis

IPC: F02C7/042 ,  B64D27/20 ,  F02K1/72 ,  F02K1/76 ,  F02K1/12 ,  F02C7/057

Abstract: An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.