Movable pylon

Patent metadata

Field	Value
Publication number	US-10301030-B2
Application number	US-201414513737-A
Country	US
Kind code	B2
Filing date	Oct 14, 2014
Priority date	Oct 14, 2013
Publication date	May 28, 2019
Grant date	May 28, 2019

Abstract

It is described a movable pylon, associated with a lower portion of aircraft wing and with an aircraft engine to change the height of this engine between a flying position and a ground position, the movable pylon comprising: a main unique structure formed by a first movable structure pivoted to a second fixed structure, the first movable structure associated with the engine, the second fixed structure associated with the wing, and a pivot mechanism connecting the first movable structure to at least one point on the wing.

First claim

The invention claimed is:

1. An aircraft comprising:
an aircraft wing;
a turbofan aircraft engine; and
a moveable aircraft engine pylon assembly having a lower portion attached to the aircraft engine for mounting the aircraft engine below the aircraft wing, and an upper portion which is pivotally mounted below the aircraft wing to allow pivotal movement of the engine pylon assembly and the aircraft engine attached to the lower portion of the engine pylon assembly about a pivot axis which is positionally fixed relative to the aircraft wing such that the aircraft engine attached to the lower portion of the engine pylon assembly is pivotally tiltable with the engine pylon assembly between a lowered flying position and a raised ground position to thereby provide increased ground clearance for the aircraft engine, wherein the engine pylon assembly includes:
(i) a pivot mechanism for pivotally attaching a first portion of the engine pylon assembly to the aircraft wing at a pivot point defining the positionally fixed pivot axis to thereby allow pivotal displacement of the engine pylon assembly about the positionally fixed pivot axis between the lowered flying and raised ground positions, and
(ii) a pivot drive mechanism operatively connecting a second portion of the engine pylon assembly to the aircraft wing, wherein the pivot drive mechanism is moveable between extended and retracted positions to responsively cause the second portion of the engine pylon assembly to pivot about the positionally fixed pivot axis to pivotally displace the aircraft engine into one of the lowered flying and raised ground positions, respectively, wherein the pivot drive mechanism comprises:
a pair of parallel linkage bar assemblies each including first and second linkage bars having opposing proximal ends pivotally connected together at a pivot connection and having distal ends opposite to the proximal ends which are pivotally connected respectively to the aircraft wing and the second portion of the engine pylon assembly, and
an actuator which includes an actuator rod that is moveable between extended and retracted positions, wherein the actuator rod is operatively connected to the pivot connection of the opposed proximal ends of the first and second linkage bars such that movement of the actuator rod between the retracted and extended positions causes the first and second linkage bars to articulate about the pivot connection between first and second angular relationships to responsively cause the engine pylon assembly and the aircraft engine mounted to the lower portion of the engine pylon assembly to pivot about the positionally fixed pivot axis such that the aircraft engine is pivotally displaced into one of the lowered flying and raised ground positions, respectively.

2. The aircraft according to claim 1 , wherein the actuator is a hydraulic or electric actuator.

3. The aircraft according to claim 1 , wherein the engine pylon assembly further comprises a fixed aft pylon member which is immovably mounted to the aircraft wing, and a forward pylon member which is pivotally attached to the fixed aft pylon member by the pivot mount of the engine pylon assembly.

4. The aircraft according to claim 3 , wherein the pivot drive mechanism comprises:
first and second sets of parallel linkage bar assemblies, wherein
each of the first and second sets of parallel linkage bar assemblies includes first and second linkage bars having opposed proximal first ends pivotally connected together at first and second pivot connections and second distal ends opposite to the proximal first ends, wherein
the second distal ends of the first and second linkage bars of the first set of parallel linkage bar assemblies are pivotally connected to the fixed aft pylon member and to the second set of parallel linkage bar assemblies at the second pivot connections, respectively, and wherein
the second distal ends of the first and second linkage bars of the second set of parallel linkage bar assemblies are pivotally connected to the forward pylon member and the aircraft wing, respectively.

5. The aircraft according to claim 4 , wherein the actuator is operatively connected to the first pivot connection of the first and second linkage bars of the first set of parallel linkage bar assemblies, such that angular displacement of first and second linkage bars of the first set of parallel linkage bar assemblies at the first pivot connection causes pivotal movement and angular displacement of the first and second linkage bars of the second set of parallel linkage bar assemblies about the second pivot connection to thereby pivotally move the aircraft engine between the lowered flying position and the raised ground position, respectively.

Assignees

• Embraer Sa

Inventors

• Castelli Alberto Dei

Classifications

• B64D2027/262

  Operations & Transport · mapped topic

• B64C15/12 Primary

  the power plant being tiltable · CPC title

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title