초록 ▼

Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between t

Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.

대표청구항 ▼

1. An apparatus, comprising: a nacelle;a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine;a first engine mount link to pivotably couple the first support structure and the engine at a first position;a second support structure coupled bet

1. An apparatus, comprising: a nacelle;a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine;a first engine mount link to pivotably couple the first support structure and the engine at a first position;a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing;a second engine mount link to pivotably couple the second support structure and the engine at a second position; anda third engine mount link to pivotably couple the second support structure and the engine at a third position, a first plane intersecting the first position and the thrust axis of the engine, the second position and the third position being radially spaced apart from the plane, the first, second, and third positions being asymmetrically disposed relative to a lateral axis of the engine that extends through the thrust axis. 2. The apparatus of claim 1, wherein the first support structure and the second structure support structure do not substantially extend into a dimensional envelope of the nacelle. 3. The apparatus of claim 1, wherein a space defined between the first support structure and the second support structure is free of any additional support structures directly coupling the nacelle to the wing to enable a thrust reverser cover to move to enable the engine to provide reverse thrust to increase braking of an aircraft. 4. An apparatus, comprising: an engine;a nacelle surrounding the engine;a wing; andmeans for substantially reducing a bending moment from being imparted on the wing by the engine, the means for substantially reducing the bending moment being non-actuatable, the means for substantially reducing the bending moment including a first support structure and a second support structure;a first engine mount link to pivotably couple the first support structure and the engine at a first position;a second engine mount link to pivotably couple the second support structure and the engine at a second position; anda third engine mount link to pivotably couple the second support structure and the engine at a third position, a plane intersecting the first position and a thrust axis of the engine, the second position and the third position being radially spaced apart from the plane, the first, second, and third positions being asymmetrically disposed relative to a lateral axis of the engine that extends through the thrust axis. 5. The apparatus of claim 4, wherein the means for substantially reducing the bending moment includes a first support structure coupled between the wing and a first side of the nacelle along a thrust axis of the engine and a second support structure coupled between the wing and a second side of the nacelle along the thrust axis. 6. The apparatus of claim 5, wherein the first support structure is coupled to the wing at a first position and the second support structure is coupled to the wing at a second position, the first position is spaced from the second position to enable a top central portion of the nacelle to be free of any supports directly coupling the top central portion of the nacelle to the wing. 7. The apparatus of claim 5, wherein the first support structure includes a first thrust beam and the second support structure includes a second thrust beam, the first and second thrust beams coupled to the nacelle, the first and second thrust beams being diametrically opposed relative to a longitudinal plane of the engine that intersects the thrust axis. 8. The apparatus of claim 7, wherein the first support includes a first pylon stub coupled at a first end of the first thrust beam and the second support includes a second pylon stub coupled at a second end of the second thrust beam, the first pylon stub extending between the first thrust beam and the wing at a non-perpendicular angle, the second pylon stub extending between the second thrust beam and the wing at a non-perpendicular angle, the first pylon stub coupling the first thrust beam and the wing, the second pylon stub coupling the second thrust beam and the wing. 9. The apparatus of claim 7, wherein the first and second thrust beams extend along sides of a thrust reverser cover of the engine. 10. The apparatus of claim 4, further including links that rotationally couple the engine to the means for substantially reducing the bending moment. 11. The apparatus of claim 4, wherein the nacelle includes a hinged portion to enable access to the engine. 12. The apparatus of claim 4, further including an aircraft to which the wing is coupled. 13. The apparatus of claim 4, further including a space defined by the wing and the means for substantially reducing the bending moment, the space being free of any support structures directly coupling an upper surface of the nacelle to the wing to enable a thrust reverser cover to move to enable the engine to provide reverse thrust to increase braking of an aircraft. 14. The apparatus of claim 5, further including a space defined by the first support structure, the second support structure, and the wing, the space being free of any additional support structures directly coupling an upper surface of the nacelle to the wing to enable a thrust reverser cover to move to enable the engine to provide reverse thrust to increase braking of an aircraft. 15. The apparatus of claim 4, wherein the means for substantially reducing the bending moment is rigidly fixed to the wing to substantially prevent movement of the engine.