US 12,600,099 B2 · Method and device for joining composite material elements

Abstract

A method of joining a first element in composite material with a second element in composite material to define a structural component of an aircraft comprising arranging the first element in contact on the second element; applying a non-rigid heating layer on the first element; applying a layer of shape memory thermoplastic polymer, pre-loaded in a compressed non-equilibrium condition, onto the heating layer; applying a vacuum bag to the assembly thus obtained; sealing the vacuum bag to define a vacuum chamber housing the first element, at least part of the second element, the heating layer and the shape memory layer; applying vacuum inside the vacuum chamber; applying heat to the first element, to the second element and to the shape memory layer by activating the heating layer; expanding the shape memory layer from the compressed non-equilibrium condition to an expanded equilibrium condition by means of the step of applying heat.

Claims14

Dependent claims

A method of joining a first element in composite material with a second element in composite material to define a structural component of an aircraft, the method comprising the steps of:

a) arranging the first element in contact on the second element;
b) applying a non-rigid heating layer on the first element;
c) applying a layer of shape memory thermoplastic polymer, pre-loaded in a compressed non-equilibrium condition, onto the heating layer to obtain an assembly;
d) applying a vacuum bag to the assembly thus obtained;
e) sealing the vacuum bag to define a vacuum chamber housing the first element, at least part of the second element, the heating layer and the shape memory layer;
f) applying vacuum inside the vacuum chamber;
g) applying heat to the first element, to the second element and to the shape memory layer by activating the heating layer;
h) expanding the shape memory layer from the compressed non-equilibrium condition to an expanded equilibrium condition by means of the step g) of applying heat;
i) applying pressure to the first element for compacting it against the second element by means of the step h) of expanding.

6 more elements

A device for joining a first element in composite material with a second element in composite material to define a structural component of an aircraft, the device comprising:

a non-rigid heating layer configured to be applied on the first element when the latter is arranged in use in contact onto the second element;
a layer of shape memory thermoplastic polymer controllable between a compressed non-equilibrium condition and an expanded equilibrium condition, and configured to be arranged pre-loaded in the compressed condition onto the heating layer to obtain an assembly and to be expanded by supplying heat by activating the heating layer;
and
a vacuum bag configured to be applied to the assembly thus obtained to define a vacuum chamber housing the shape memory layer, the heating layer, the first element and at least part of the second element;
wherein the heating layer is configured to apply heat to the first element and to the second element;
and wherein the shape memory layer is configured to apply pressure to the first element for compacting it against the second element by passing from the compressed condition to the expanded condition.

3 more elements

Dependencies are inferred from the claim text.

Method and device for joining composite material elements

Life of this patent

Method and device for joining composite material elements

Life of this patent

Abstract

Claims14