A composite film including stacking: a first fiber layer, a metal layer with multiple holes, and a second fiber layer, a stitching structure is arranged along the horizontal direction of the first fiber layer and the second fiber layer within areas of the holes of the metal layer; and the stitching structure in each of the holes is connected, but the stitching structures in different holes are not mutually connected. The stitching structures of this invention pass through the first fiber layer and the second fiber layer, fortifying the stress resistant abilities along the radial direction of the composite film, and thus avoid the peeling off of the stacked structure from the radial direction, and with the independent stitching structure formed independently in each of the holes of the metal layer, the stitching structures would not interact with each other, so that even one of the stitching structure is broken, other stitching structures would not be affected, effectively increasing the durability of the product of this invention.

[Front page view] FIG. 1.

[Brief description of the symbols of front page view] 10 composite film 11 first fiber layer 12 metal layer 121 hole 13 second fiber layer 14 stitching structure

A composite film including stacking: a first fiber layer, a metal layer with multiple holes, and a second fiber layer, a stitching structure is arranged along the horizontal direction of the first fiber layer and the second fiber layer within areas of the holes of the metal layer; and the stitching structure in each of the holes is connected, but the stitching structures in different holes are not mutually connected. The stitching structures of this invention pass through the first fiber layer and the second fiber layer, fortifying the stress resistant abilities along the radial direction of the composite film, and thus avoid the peeling off of the stacked structure from the radial direction, and with the independent stitching structure formed independently in each of the holes of the metal layer, the stitching structures would not interact with each other, so that even one of the stitching structure is broken, other stitching structures would not be affected, effectively increasing the durability of the product of this invention.

[Front page view] FIG. 1.

[Brief description of the symbols of front page view] 10 composite film 11 first fiber layer 12 metal layer 121 hole 13 second fiber layer 14 stitching structure

Thermal insulation blankets and methods of using the same to repair articles, such as components of turbine engines are disclosed. The thermal insulation blankets are a multilayer composite material that includes: a first flexible fiberglass fabric layer having two sides that are coated with a coating that covers the fiberglass fibers; an intermediate second fiberglass insulation blanket layer made of continuous glass fibers; and a third layer of flexible heat reflective material. The method involves wrapping a component, such as a component of a turbine engine, with one or more thermal insulation blankets in order to retain heat within the confines of a prescribed area for installing or removing parts with a precision fitment. The blankets allow enough heat to induce even thermal expansion of the components.

Thermal insulation blankets and methods of using the same to repair articles, such as components of turbine engines are disclosed. The thermal insulation blankets are a multilayer composite material that includes: a first flexible fiberglass fabric layer having two sides that are coated with a coating that covers the fiberglass fibers; an intermediate second fiberglass insulation blanket layer made of continuous glass fibers; and a third layer of flexible heat reflective material. The method involves wrapping a component, such as a component of a turbine engine, with one or more thermal insulation blankets in order to retain heat within the confines of a prescribed area for installing or removing parts with a precision fitment. The blankets allow enough heat to induce even thermal expansion of the components.

An object of the present invention is to provide a stitched fiber-reinforced substrate material capable of suppressing the formation of microcracks in a fiber reinforced composite material. The stitched fiber-reinforced substrate material of the present invention is a fiber-reinforced substrate material formed by stitching reinforcement fiber sheets made of reinforcement fibers using stitching yarns, and the stitching yarn has a linear expansion coefficient in the fiber axial direction of −1×10.sup.−6 to 70×10.sup.−6/K after being heated at 180° C. for 2 hours and then cooled. The stitching yarn is preferably a stitching yarn to which an organic compound having a polar group is adhered.

An object of the present invention is to provide a stitched fiber-reinforced substrate material capable of suppressing the formation of microcracks in a fiber reinforced composite material. The stitched fiber-reinforced substrate material of the present invention is a fiber-reinforced substrate material formed by stitching reinforcement fiber sheets made of reinforcement fibers using stitching yarns, and the stitching yarn has a linear expansion coefficient in the fiber axial direction of −1×10.sup.−6 to 70×10.sup.−6/K after being heated at 180° C. for 2 hours and then cooled. The stitching yarn is preferably a stitching yarn to which an organic compound having a polar group is adhered.

A vehicle component has at least one sandwich part which forms a crash element that absorbs kinetic energy. The at least one sandwich part has a layer structure of at least two fiber-reinforced and one synthetic resin matrix-containing cover layer elements and at least one core layer element provided between two adjacent cover layer elements. The at least one core layer element has channels which pass transversely through each cover layer element and/or the core layer element. The at least one core layer element is made of a hard foam material or a softwood, and the channels provided in the core layer element form predetermined breaking points for the core layer element.

A finished floor assembly covers a floor area of an aircraft and includes a subfloor, a padding assembly, and a finish flooring layer. Noise radiates from the subfloor due to vibrations transmitted by an aircraft structure. The padding assembly attenuates the noise and includes a first pad layer, a second pad layer, and a plurality of discontinuous couplings. The first pad layer abuts the subfloor. The second pad layer is adjacent to the first pad layer. The plurality of discontinuous couplings are laterally separated from each other along the floor area by void portions. The discontinuous couplings secure the first pad layer to the second pad layer and the first pad layer and the second pad layer are in contact at the void portions. The finish flooring layer disposed overtop the padding assembly.

A finished floor assembly covers a floor area of an aircraft and includes a subfloor, a padding assembly, and a finish flooring layer. Noise radiates from the subfloor due to vibrations transmitted by an aircraft structure. The padding assembly attenuates the noise and includes a first pad layer, a second pad layer, and a plurality of discontinuous couplings. The first pad layer abuts the subfloor. The second pad layer is adjacent to the first pad layer. The plurality of discontinuous couplings are laterally separated from each other along the floor area by void portions. The discontinuous couplings secure the first pad layer to the second pad layer and the first pad layer and the second pad layer are in contact at the void portions. The finish flooring layer disposed overtop the padding assembly.

A composite product substantially reduced the impact force imposed by hard impactor which travelled at the speed in the range of 400 m/s to 1400 m/s simultaneously damping the vibrations and shocks appeared therein is disclosed. At the same time it is light weight with the weight lower than that of 22 to 38 kg/m2and is flexible to adopt the shape suitable for the end applications. A method of manufacturing the composite product of the invention is also disclosed.