Curing thermoset material using electric heater(s) for thermal anti-icing system
AssigneeRohr, Inc.
InventorJennifer Davis
Life of this patent
Estimating the term…
Abstract
A method is provided during which a composite preform is provided that includes an electric heater, fiber-reinforcement and thermoset material. The composite preform is consolidated to provide a composite aircraft component. The consolidating includes heating the thermoset material using the electric heater to cure the thermoset material. The electric heater and the fiber-reinforcement are embedded within the cured thermoset material. The electric heater is configured as a part of a thermal anti-icing system for melting and/or preventing ice accumulation on an exterior surface of the composite aircraft component.
Claims20
A method, comprising:
- providing a composite preform that includes an electric heater, fiber-reinforcement and thermoset material;
- and
- consolidating the composite preform to provide a composite aircraft component, the consolidating comprising heating the thermoset material using the electric heater to cure the thermoset material, the electric heater and the fiber-reinforcement embedded within the cured thermoset material, and the electric heater configured as a part of a thermal anti-icing system for melting and/or preventing ice accumulation on an exterior surface of the composite aircraft component.
A method, comprising:
- arranging a first member of a composite aircraft component and a second member of the composite aircraft component together, the first member including an electric heater, first fiber-reinforcement and cured first thermoset material, the electric heater and the first fiber-reinforcement embedded within the cured first thermoset material, and the electric heater configured as a part of a thermal anti-icing system for melting and/or preventing ice accumulation on an exterior surface of the composite aircraft component;
- and
- heating the second member using the electric heater to bond the second member to the first member.
A method, comprising:
- providing a first member of a composite aircraft component, the first member including cured first thermoset material and first fiber-reinforcement embedded within the cured first thermoset material;
- providing a second member of the composite aircraft component;
- disposing the second member with the first member;
- and
- heating the second member using an electric heater to bond the second member to the first member, the electric heater configured as a part of a thermal anti-icing system for melting and/or preventing ice accumulation on an exterior surface of the composite aircraft component.
Dependencies are inferred from the claim text.