Apparatuses and methods for attaching engine nacelles to aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-003/32
B64D-027/18
출원번호
US-0278382
(2002-10-22)
발명자
/ 주소
Harrison, Kenneth M.
Powell, Donald T.
Schnelz, James R.
Whitmer, Brett D.
출원인 / 주소
The Boeing Company
대리인 / 주소
Perkins Coie LLP
인용정보
피인용 횟수 :
9인용 특허 :
5
초록▼
Aircraft engine nacelles and methods for structurally attaching them to aircraft structures, such as aircraft wings. In one embodiment, an aircraft engine nacelle is attached to a wing between a trailing edge region of the wing and an aft deck region of the wing. In one aspect of this embodiment, th
Aircraft engine nacelles and methods for structurally attaching them to aircraft structures, such as aircraft wings. In one embodiment, an aircraft engine nacelle is attached to a wing between a trailing edge region of the wing and an aft deck region of the wing. In one aspect of this embodiment, the engine nacelle includes a forward portion having first and second structural attach points offset from each other in a first direction at least generally perpendicular to a central axis of the engine nacelle. The first and second structural attach points can be configured to fixedly attach the engine nacelle to the wing at least proximate to the trailing edge region. In another aspect of this embodiment, the engine nacelle includes a side portion having at least a third structural attach point offset from the first and second structural attach points in a second direction at least generally parallel to the central axis. The third structural attach point can be configured to fixedly attach the engine nacelle to the wing at least proximate to the aft deck region.
대표청구항▼
1. An engine nacelle for use with an aircraft having a wing with a trailing edge region, the engine nacelle comprising:an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis;a forward portion configured to fixedl
1. An engine nacelle for use with an aircraft having a wing with a trailing edge region, the engine nacelle comprising:an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis;a forward portion configured to fixedly attach the engine nacelle to the wing and transfer at least approximately all of a torsional load component from the engine nacelle to the wing, the torsional load component acting about an axis at least generally parallel to the central axis; anda side portion configured to fixedly attach the engine nacelle to the wing at least generally aft of the trailing edge region, the side portion being further configured to transfer vertical and lateral load components to the wing, the vertical and lateral load components acting in directions at least generally perpendicular to the central axis. 2. The engine nacelle of claim 1 wherein the wing includes an aft deck region extending aft of the trailing edge region inboard of the trailing edge region, and wherein the engine nacelle is configured to be attached to the wing between the trailing edge region and the aft deck region. 3. The engine nacelle of claim 1 wherein the wing includes an aft deck region extending aft of the trailing edge region inboard of the trailing edge region, wherein the forward portion of the engine nacelle is configured to be attached at least proximate to the trailing edge region, and wherein the side portion of the engine nacelle is configured to be attached at least proximate to the aft deck region. 4. The engine nacelle of claim 1 wherein the wing of the aircraft includes a rear wing spar and the forward portion of the engine nacelle is configured to be fixedly attached at least proximate to the rear wing spar. 5. The engine nacelle of claim 1 wherein the side portion is further configured to transfer an axial load component to the wing, wherein the axial load component includes a thrust load from the engine. 6. An engine nacelle for use with an aircraft having a wing with a trailing edge region, the engine nacelle comprising:an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis;a forward portion configured to fixedly attach the engine nacelle to the wing and transfer a torsional load component from the engine nacelle to the wing, the torsional load component acting about an axis at least generally parallel to the central axis, wherein the forward portion includes first and second single-pin fittings configured to transfer the torsional load component to the wing; anda side portion configured to fixedly attach the engine nacelle to the wing at least generally aft of the trailing edge region, the side portion being further configured to transfer vertical and lateral load components to the wing, the vertical and lateral load components acting in directions at least generally perpendicular to the central axis. 7. An engine nacelle for use with an aircraft having a wing with a trailing edge region, the engine nacelle comprising:an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis;a forward portion configured to fixedly attach the engine nacelle to the wing and transfer a torsional load component from the engine nacelle to the wing, the torsional load component acting about an axis at least generally parallel to the central axis; anda side portion configured to fixedly attach the engine nacelle to the wing at least generally aft of the trailing edge region, the side portion being further configured to transfer vertical and lateral load components to the wing, the vertical and lateral load components acting in directions at least generally perpendicular to the central axis, wherein the side portion includes at least one double-pin fitting configured to transfer the vertical and lateral load components to the wing. 8. An engine nacelle for use with an aircraft having a wing with a trailing edge region, the engine nacelle comprising:an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis;a forward portion configured to fixedly attach the engine nacelle to the wing and transfer a torsional load component from the engine nacelle to the wing, the torsional load component acting about an axis at least generally parallel to the central axis; anda side portion configured to fixedly attach the engine nacelle to the wing at least generally aft of the trailing edge region, the side portion being further configured to transfer vertical and lateral load components to the wing, the vertical and lateral load components acting in directions at least generally perpendicular to the central axis, wherein the side portion includes at least one single-pin fitting configured to transfer an axial load component to the wing, wherein the axial load includes a thrust load from the engine. 9. The engine nacelle of claim 1, further comprising an aerodynamic control surface extending from the engine nacelle at least generally perpendicular to the central axis. 10. The engine nacelle of claim 1, further comprising an aerodynamic fin extending at least generally vertically from the engine nacelle. 11. An engine nacelle for use with an aircraft having a wing with a rear wing spar, wherein the engine nacelle is configured to be attached to the aircraft at least generally aft of the rear wing spar, the engine nacelle comprising:an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis;a forward portion having first and second structural attach points, the first and second structural attach points being offset from each other in a first direction at least generally perpendicular to the central axis, the first and second structural attach points being configured to fixedly attach the engine nacelle to the aircraft and transfer vertical and lateral load components from the engine nacelle to the aircraft, the vertical and lateral load components acting in directions perpendicular to the central axis; anda side portion positioned aft of the forward portion and having at least a third structural attach point, the third structural attach point being offset from the first and second structural attach points in a second direction at least generally parallel to the central axis, the third structural attach point being configured to fixedly attach the engine nacelle to the aircraft and transfer an axial load component from the engine nacelle to the aircraft, the axial load component acting in a direction parallel to the central axis. 12. The engine nacelle of claim 11 wherein the first direction is at least generally parallel to the rear wing spar, and wherein the first and second structural attach points are configured to be attached at least proximate to the rear wing spar. 13. The engine nacelle of claim 11 wherein the wing includes an aft deck region extending aft of the rear wing spar, and wherein the third structural attach point is configured to be attached at least proximate to the aft deck region. 14. The engine nacelle of claim 11 wherein the side portion further includes a fourth structural attach point, the fourth structural attach point being configured to fixedly attach the engine nacelle to the aircraft and transfer a vertical load component from the engine nacelle to the aircraft, the vertical load component acting in a direction perpendicular to the central axis. 15. The engine nacelle of claim 11 wherein the first and second structural attach points are single-pin attach points. 16. The engine nacelle of claim 11 wherein the third structural attach point is a single-pin attach point. 17. The engine nacelle of claim 11 wherein the side portion further includes at least a fourth structural attach point and a fifth structural attach point, wherein the fourth and fifth structural attach points are configured to form a couple capable of transferring a bending moment component from the engine nacelle to the aircraft. 18. A system for structurally attaching an engine nacelle to an aircraft, the engine nacelle configured to house an engine at least generally aligned with a central axis, the aircraft having a wing with a trailing edge region and an aft deck region, the aft deck region being positioned inboard of the trailing edge region and extending aft of the trailing edge region, the system comprising:means for transferring a torsional load component from the engine nacelle to the wing at least proximate to the trailing edge region of the wing, wherein the torsional load component acts at least generally about the central axis of the engine nacelle; andmeans for transferring a nontorsional load component from the engine nacelle into the wing at least proximate to the aft deck region of the wing, wherein the nontorsional load component acts in a direction at least generally perpendicular to the central axis. 19. The system of claim 18, further comprising means for transferring a thrust load component from the engine into the aft deck region of the wing, the thrust load component acting in a direction at least generally parallel to the central axis. 20. The system of claim 18 wherein the wing of the aircraft includes a wing spar positioned at least proximate to the trailing edge region, and wherein the means for transferring a torsional load component includes means for transferring a torsional load component from the engine nacelle into the wing spar. 21. The system of claim 18 wherein the means for transferring a torsional load component are first means for transferring a first torsional load component, and wherein the system further comprises second means for transferring a second torsional load component from the engine nacelle to the wing at least proximate to the aft deck region of the wing. 22. The system of claim 18 wherein the engine nacelle further includes an aerodynamic control surface extending outwardly from the engine nacelle at least generally perpendicular to the central axis, and wherein the means for transferring a torsional load component from the engine nacelle include means for transferring a torsional load component caused by the control surface. 23. An aircraft comprising:a wing having a trailing edge region; andan engine nacelle fixedly attached to the wing, the engine nacelle having:an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis;a forward portion configured to fixedly attach the engine nacelle to the wing and transfer at least approximately all of a torsional load component from the engine nacelle to the wing, the torsional load component acting about an axis at least generally parallel to the central axis; anda side portion configured to fixedly attach the engine nacelle to the wing at least generally aft of the trailing edge region, the side portion being further configured to transfer vertical and lateral load components to the wing, the vertical and lateral load components acting in directions at least generally perpendicular to the central axis. 24. The aircraft of claim 23, further comprising:a fuselage having a forward portion and an aft portion, wherein the wing is a first wing fixedly attached to the aft portion of the fuselage; anda second wing fixedly attached to the forward portion of the fuselage, the second wing being smaller than the first wing. 25. The aircraft of claim 23 wherein the wing further includes an aft deck region, the aft deck region extending aft of the trailing edge region and inboard of the trailing edge region, and wherein the engine nacelle is fixedly attached to the wing between the trailing edge region and the aft deck region. 26. The aircraft of claim 23, further comprising an inlet positioned forward of the engine nacelle and configured to provide air to the engine. 27. The aircraft of claim 23, further comprising an inlet positioned forward of the engine nacelle and at least generally below the wing, the inlet being configured to provide air to the engine. 28. The aircraft of claim 23 wherein the forward portion of the engine nacelle is fixedly attached at least proximate to a rear wing spar. 29. The aircraft of claim 23 wherein the wing further includes an aft deck region, the aft deck region extending aft of the trailing edge region and inboard of the trailing edge region, wherein the forward portion of the nacelle includes first and second structural attach points fixedly attached at least proximate to the trailing edge region, and wherein the side portion of the nacelle includes a third structural attach point fixedly attached at least proximate to the aft deck region. 30. The aircraft of claim 23 wherein the wing further includes an aft deck region extending aft of the trailing edge region, wherein the forward portion of the nacelle includes first and second structural attach points fixedly attached at least proximate to the trailing edge region, and wherein the side portion of the engine nacelle includes a third structural attach point fixedly attached at least proximate to the aft deck region to transfer a load component acting perpendicular to the central axis from the engine nacelle into the aft deck region. 31. The aircraft of claim 23, further comprising an aerodynamic control surface extending from the engine nacelle at least generally perpendicular to the central axis. 32. A method for structurally attaching an engine nacelle to an aircraft having a wing with a trailing edge region, wherein the engine nacelle includes an interior portion having a central axis, the interior portion configured to house an engine at least generally aligned with the central axis, the method comprising:attaching first and second structural attach points of a forward nacelle portion to the wing, the first and second structural attach points being offset from each other in a first direction at least generally perpendicular to the central axis, the first and second structural attach points being configured to transfer a torsional load component from the engine nacelle to the wing, the torsional load component acting about an axis at least generally parallel to the central axis; andattaching a third structural attach point of a side nacelle portion to the aircraft aft of the trailing edge region of the wing, the third structural attach point being offset from the first and second structural attach points in a second direction at least generally parallel to the central axis, the third structural attach point being configured to transfer vertical and lateral load components from the engine nacelle to the aircraft, the vertical and lateral load components acting in directions at least generally perpendicular to the central axis. 33. The method of claim 32 wherein the wing includes a rear wing spar, and wherein attaching the first and second structural attach points to the wing includes fixedly attaching the first and second structural attach points at least proximate to the rear wing spar. 34. The method of claim 32 wherein the wing includes an aft deck region extending aft of the trailing edge region and inboard of the trailing edge region, and wherein attaching the third structural attach point to the aircraft includes fixedly attaching the third structural attach point at least proximate to the aft deck region. 35. The method of claim 32, further comprising attaching a fourth structural attach point to the aircraft aft of the trailing edge region of the wing, wherein the fourth structural attach point is configured to transfer an axial load component from the engine nacelle to the aircraft, the axial load component acting in a direction parallel to the central axis. 36. The met hod of claim 32 wherein attaching the first and second structural attach points to the wing includes making first and second single-pin attachments between the engine nacelle and the wing. 37. The method of claim 32 wherein the wing includes a wing spar and an aft deck region extending aft of the wing spar, and wherein the method further comprises positioning the engine nacelle at least generally aft of the wing spar and adjacent to the aft deck region.
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이 특허에 인용된 특허 (5)
O\Brien Michael T. (Cincinnati OH) Bobo ; deceased Melvin (late of Cincinnati OH by Beatrice L. Bobo ; executor), Aircraft gas turbine engine sideways mount.
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