AIRCRAFT ENGINE PYLON TO WING MOUNTING ASSEMBLY

• US 20190100325A1
• Filed: 11/30/2018
• Published: 04/04/2019
• Est. Priority Date: 09/24/2015
• Status: Active Grant

• Current Assignee: Yabora Industria Aeronautica S.A. (Embraer S.A.)
• Original Assignee: Embraer S.A.
• Inventors: DA SILVA, Julio Antonio Beltrami, FERREIRA, Clovis Augusto Eca, MONTORO, Wanderley, CASTELLI, Alberto Dei, FLOR, Jose Darci, NOGUEIRA, Marcelo, SOARES, Cleber
• Granted Patent: US 10,450,081 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 27/18 within, or attached to, wings
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 27/402 comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant

Abstract

Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.

Claims

1. An aircraft wing assembly comprising an aircraft wing having leading and trailing edges and a pylon mounting assembly for mounting an engine to the aircraft wing, wherein the pylon mounting assembly comprises:

an upper pylon connection member which extends forwardly of the leading edge of the aircraft wing relative to an aircraft travel direction, and

a lower pylon connection box having an elongate axis along the aircraft travel direction, wherein

the upper pylon connection member and the lower pylon connection box respectively include a forward opposed upper and lower forward connection lobes, and wherein

the wing box of the aircraft wing and the lower pylon connection box respectively include at least one additional opposed pair of upper and lower additional connection lobes rearwardly positioned relative to the forward pair of opposed upper and lower connection lobes, and wherein

the forward and additional opposed pairs of upper and lower connection lobes are aligned with the elongate axis of the lower pylon connection box; and

wherein

the upper forward connection lobe of the upper pylon connection member is positioned at and extends forwardly of a terminal end of the upper pylon connection member; and

wherein

the lower forward connection lobe of the lower pylon connection member extends upwardly from the lower pylon connection member; and

wherein

at least a first one of the forward and additional pairs of upper and lower connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, and wherein

at least a second one of the forward and additional pairs of upper and lower connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis, and wherein

each of the pin connection and the connection rod comprises a fuse pin capable of rupturing and breaking away in response to a separatory force exceeding a nominal design force to thereby allow separation of the lower pylon connection box from the upper pylon connection member and the wing box of the aircraft wing.

2. The aircraft wing assembly as in claim 1, wherein the upper pylon connection member is a solid structure connected rigidly to a wing box of the aircraft wing.

3. The aircraft wing assembly as in claim 2, wherein the upper forward connection lobe of the upper pylon connection member extends forwardly of and is downwardly dog-legged relative to the leading edge of the aircraft wing.

4. The aircraft wing assembly as in claim 2, wherein the upper forward connection lobe of the upper pylon connection member is connected rigidly to the wing box of the aircraft wing.

5. The aircraft wing assembly as in claim 1, wherein the upper additional connection lobe is connected rigidly to the wing box of the aircraft wing.

6. The aircraft wing assembly as in claim 1, wherein the forward and additional pairs of upper and lower connection lobes include respective connection rods to restrict degrees of freedom thereat along the z-axis.

7. The aircraft wing assembly as in claim 1, wherein the at least one additional opposed pair of upper and lower connection lobes, includes at least intermediate and rearward pairs of opposed upper and lower connection lobes.

8. The aircraft wing assembly as in claim 7, wherein the upper connection lobes of each of the at least intermediate and rearward pairs are connected rigidly to a wing box of the aircraft wing.

9. The aircraft wing assembly as in claim 1, wherein the forward and additional pairs of upper and lower connection lobes include respective connection rods to restrict degrees of freedom thereat along the z-axis, and the intermediate pair of connection lobes includes a pin connection to restrict degrees of freedom thereat along the x-axis and the mutually perpendicular z-axis.

10. The aircraft wing assembly as in claim 7, wherein the at least one additional pair of upper and lower connection lobes includes respective a connection rod to restrict degrees of freedom thereat along the z-axis, and wherein the forward pair of upper and lower connection lobes includes a pin connection to restrict degrees of freedom thereat along the x-axis and the mutually perpendicular z-axis.

11. The aircraft wing assembly as in claim 10, wherein the forward connection lobe of the upper pylon connection member extends forwardly of and is downwardly dog-legged relative to the leading edge of the aircraft wing.

12. The aircraft wing assembly as in claim 7, wherein the forward and intermediate pairs of connection lobes include respective pin connections to restrict degrees of freedom thereat along the x-axis and the mutually perpendicular z-axis, and wherein the rearward pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.

13. The aircraft wing assembly as in claim 12, wherein the forward connection lobe of the upper pylon connection member extends forwardly of and is downwardly dog-legged relative to the leading edge of the aircraft wing.

14. An aircraft comprising the aircraft wing assembly as in claim 1.