Shimming welded interface(s) between thermoplastic components
AssigneeRohr, Inc.
InventorsSarah Lohman, Noushin Bahramshahi, Michael van Tooren
Life of this patent
Estimating the term…
Abstract
A method is provided for joining thermoplastic components. During this method, a skin is provided that is configured from or otherwise includes a skin fiber-reinforced thermoplastic composite. A support member is provided that is configured from or otherwise includes a support member fiber-reinforced thermoplastic composite. A shim is arranged at an interface between the skin and the support member. The shim is configured from or otherwise includes a shim fiber-reinforced thermoplastic composite. The support member is welded to the skin through the shim at the interface.
Claims19
A method for joining thermoplastic components, comprising:
- providing a skin comprising a skin fiber-reinforced thermoplastic composite;
- providing a support member comprising a support member fiber-reinforced thermoplastic composite;
- arranging a shim at an interface between the skin and the support member, the shim comprising a shim fiber-reinforced thermoplastic composite;
- and
- welding the support member to the skin through the shim at the interface,
- wherein the support member is welded directly to the skin along a first portion of the interface, and
- wherein the support member is welded to the skin through the shim along a second portion of the interface.
A method for joining thermoplastic components for an aircraft, comprising:
- arranging a first component with a second component, the first component comprising a first fiber-reinforced thermoplastic composite, the second component comprising a second fiber-reinforced thermoplastic composite, and a gap between the first component and the second component at an interface between the first component and the second component;
- determining a parameter of the gap;
- selecting one of a plurality of shims based on the parameter to provide a selected shim, the selected shim comprising a shim fiber-reinforced thermoplastic composite;
- arranging the selected shim between the first component and the second component at the interface;
- and
- welding the first component to the second component through the selected shim at the interface, the welding comprising vibration welding, ultrasonic welding or induction welding,
- wherein the first component is welded directly to the second component along a first portion of the interface, and
- wherein the first component is welded to the second component through the selected shim along a second portion of the interface.
A method for joining thermoplastic component for an aircraft, comprising:
- arranging a first component with a second component, the first component comprising a first fiber-reinforced thermoplastic composite, the second component comprising a second fiber-reinforced thermoplastic composite, and a gap between the first component and the second component at an interface between the first component and the second component;
- determining a parameter of the gap;
- forming a shim based on the parameter, the shim comprising a shim fiber-reinforced thermoplastic composite;
- arranging the shim between the first component and the second component at the interface;
- and
- welding the first component to the second component through the shim at the interface, the welding comprising vibration welding, ultrasonic welding or induction welding,
- wherein the first component is welded directly to the second component along a first portion of the interface, and
- wherein the first component is welded to the second component through the shim along a second portion of the interface.
Dependencies are inferred from the claim text.