Aircraft component with fiber-reinforced elastic expansion section
An apparatus is provided for an aircraft which includes an aircraft component. The aircraft component includes a first plate section, a second plate section and an elastic expansion section laterally between the first plate section and the second plate section. The elastic expansion section is configured to elastically deform to increase a lateral width between the first plate section and the second plate section. The aircraft component is formed from at least an elastomeric matrix and a fiber layer at least partially embedded within the elastomeric matrix. A bead is formed in the fiber layer laterally between a first portion of the fiber layer and a second portion of the fiber layer. The first portion of the fiber layer is disposed in the first plate section. The second portion of the fiber layer is disposed in the second plate section. The bead is disposed in the elastic expansion section.
1 . An apparatus for an aircraft, comprising:
an aircraft component including a first plate section, a second plate section and an elastic expansion section laterally between the first plate section and the second plate section, the elastic expansion section configured to elastically deform to increase a lateral width between the first plate section and the second plate section;
the aircraft component formed from at least an elastomeric matrix and a fiber layer at least partially embedded within the elastomeric matrix, a bead formed in the fiber layer laterally between a first portion of the fiber layer and a second portion of the fiber layer, the first portion of the fiber layer disposed in the first plate section, the second portion of the fiber layer disposed in the second plate section, and the bead disposed in the elastic expansion section;
wherein an inner channel of the bead is completely filled with the elastomeric matrix.
2 . The apparatus of claim 1 , wherein at least one of
the first portion of the fiber layer is arranged in the first plate section to provide the first plate section with a non-variable first lateral width; or
the second portion of the fiber layer is arranged in the second plate section to provide the second plate section with a non-variable second lateral width.
3 . The apparatus of claim 1 , wherein at least one of
the first plate section has a uniform first thickness as the first plate section extends laterally along a first lateral width of the first plate section; or
the second plate section has a uniform second thickness as the second plate section extends laterally along a second lateral width of the second plate section.
4 . The apparatus of claim 1 , wherein at least one of
a plurality of fibers in the first portion of the fiber layer project laterally out from the bead into the first plate section; or
a plurality of fibers in the second portion of the fiber layer project laterally out from the bead into the second plate section.
5 . The apparatus of claim 1 , wherein the elastic expansion section is configured to elastically deform to variably increase the lateral width between the first plate section and the second plate section along a longitudinal length of the elastic expansion section.
6 . The apparatus of claim 1 , wherein a lateral width of the bead changes as the bead extends longitudinally along the first portion of the fiber layer and the second portion of the fiber layer.
7 . The apparatus of claim 1 , wherein
the bead projects vertically out from the first portion of the fiber layer and the second portion of the fiber layer; and
a vertical height of the bead changes as the bead extends longitudinally along the first portion of the fiber layer and the second portion of the fiber layer.
8 . The apparatus of claim 1 , wherein the bead has a curved cross-sectional geometry extending from the first portion of the fiber layer to the second portion of the fiber layer.
9 . The apparatus of claim 1 , wherein the bead has a polygonal cross-sectional geometry extending from the first portion of the fiber layer to the second portion of the fiber layer.
10 . The apparatus of claim 1 , wherein a plurality of fibers in the fiber layer extend laterally across the bead into the first portion of the fiber layer and the second portion of the fiber layer.
11 . The apparatus of claim 10 , wherein
the elastic expansion section extends longitudinally along the first plate section and the second plate section;
the plurality of fibers in the fiber layer include a first fiber, a second fiber and a third fiber longitudinally between and adjacent the first fiber and the second fiber;
the first fiber and the third fiber are longitudinally separated by a first inter-fiber distance; and
the second fiber and the third fiber are longitudinally separated by a second inter-fiber distance that is different than the first inter-fiber distance.
12 . The apparatus of claim 10 , wherein
the elastic expansion section extends longitudinally along the first plate section and the second plate section;
the plurality of fibers in the fiber layer include a first fiber, a second fiber and a third fiber longitudinally between and adjacent the first fiber and the second fiber;
the first fiber and the third fiber are longitudinally separated by a first inter-fiber distance; and
the second fiber and the third fiber are longitudinally separated by a second inter-fiber distance that is equal to the first inter-fiber distance.
13 . The apparatus of claim 1 , wherein
a first section of the fiber layer is formed by unidirectional fibers; and
a second section of the fiber layer is formed by multi-directional fibers.
14 . The apparatus of claim 1 , wherein the aircraft component further includes an anti-erosion elastomeric film bonded to and covering the elastomeric matrix along at least one of the first plate section, the second plate section or the elastic expansion section.
15 . The apparatus of claim 1 , further comprising
a variable area nozzle;
the aircraft component configured as an inter-nozzle panel seal in the variable area nozzle.
16 . An apparatus for an aircraft, comprising:
an aircraft component including a first plate section, a second plate section and an elastic expansion section laterally between the first plate section and the second plate section, the elastic expansion section extending longitudinally along the first plate section and the second plate section, and the elastic expansion section configured to elastically deform to increase a lateral width between the first plate section and the second plate section when the aircraft component is placed laterally in tension;
the aircraft component formed from at least an elastomeric matrix and a fiber layer at least partially embedded within the elastomeric matrix, the fiber layer including a plurality of fibers extending laterally across the elastic expansion section into the first plate section and the second plate section; and
the plurality of fibers including a first fiber and a second fiber longitudinally adjacent the first fiber, the first fiber longitudinally spaced from the second fiber at a first lateral intersection between the first plate section and the elastic expansion section by a first longitudinal distance, the first fiber longitudinally spaced from the second fiber at a second lateral intersection between the second plate section and the elastic expansion section by a second longitudinal distance, and the first fiber longitudinally spaced from the second fiber at location laterally between the first lateral intersection and the second lateral intersection by a third longitudinal distance that is greater than the first longitudinal distance and the second longitudinal distance;
wherein the elastic expansion section is planar when in a relaxed state.
17 . An apparatus for an aircraft, comprising:
an aircraft component including a first plate section, a second plate section and an elastic expansion section laterally between the first plate section and the second plate section, the elastic expansion section configured to elastically deform to increase a lateral width between the first plate section and the second plate section, and the elastic expansion section extending longitudinally along the first plate section and the second plate section;
the aircraft component formed from at least an elastomeric matrix and a fiber layer at least partially embedded within the elastomeric matrix, a bead formed in the fiber layer laterally between a first portion of the fiber layer and a second portion of the fiber layer, the first portion of the fiber layer disposed in the first plate section, the second portion of the fiber layer disposed in the second plate section, the bead disposed in the elastic expansion section, a plurality of fibers in the fiber layer extend laterally across the bead into the first portion of the fiber layer and the second portion of the fiber layer, the plurality of fibers in the fiber layer include a first fiber, a second fiber and a third fiber longitudinally between and adjacent the first fiber and the second fiber, the first fiber and the third fiber longitudinally separated by a first inter-fiber distance, the second fiber and the third fiber are longitudinally separated by a second inter-fiber distance that is different than the first inter-fiber distance.
18 . The apparatus of claim 17 , wherein an open volume is disposed in an inner channel of the bead.