Heat-generating tooling systems
Methods of manufacturing composite workpieces that include positioning a heat-generating element proximate to an uncured composite workpiece, triggering the heat-generating element to produce an exothermic chemical reaction or exothermic physical reaction so that the temperature of the uncured composite workpiece is raised to a predetermined first temperature, and curing the composite workpiece while it is at a temperature that is at least the predetermined first temperature.
1. A system for curing a composite workpiece, the system comprising:
a constraining container, containing the composite workpiece;
a heat-generating element adjacent the composite workpiece in the constraining container and capable of undergoing an exothermic chemical reaction or an exothermic physical reaction when triggered; and
a plurality of thermally expandable pellets in the constraining container, configured to soften and undergo volumetric expansion by foaming to apply at least a predetermined pressure to the composite workpiece when heated to a predetermined first temperature by the heat-generating element.
2. The system of claim 1 , further including a rigid form in the constraining container, the composite workpiece being disposed on the rigid form.
3. The system of claim 1 , wherein the heat-generating element is configured to undergo an exothermic physical reaction that is an exothermic change of state.
4. The system of claim 1 , wherein the heat-generating element is configured to undergo an exothermic chemical reaction.
5. The system of claim 1 , further including a mixture of the heat- generating element and a heating mediation agent.
6. The system of claim 5 , wherein the heating mediation agent is configured to undergo an endothermic physical reaction or an endothermic chemical reaction to decrease a maximum temperature reached proximate the composite workpiece after the heat-generating element is triggered.
7. The system of claim 1 , further comprising a removable barrier film applied to an outer surface of the composite workpiece.
8. The system of claim 1 , wherein the heat-generating element has the form of a plurality of pellets.
9. The system of claim 8 , wherein the plurality of pellets forming the heat-generating element are contained within one or more flexible bags.
10. The system of claim 9 , wherein the one or more flexible bags further contain a pelletized heating mediation agent.
11. The system of claim 9 , wherein the one or more flexible bags further contain the plurality of thermally expandable pellets.
12. The system of claim 8 , wherein the plurality of pellets forming the heat-generating element are disposed above, beneath, and around the composite workpiece.
13. The system of claim 1 , wherein pellets of the plurality of thermally expandable pellets are in direct contact with a wall of the constraining container after the plurality of thermally expandable pellets have undergone volumetric expansion by foaming.
14. The system of claim 1 , wherein the plurality of thermally expandable pellets includes a thermoplastic material having a glass transition temperature and a melting temperature, and the predetermined first temperature is above the glass transition temperature and below the melting temperature.
15. An aircraft component manufacturing assembly, comprising:
an uncured composite aircraft component; and
a curing apparatus, including:
one or more flexible bags containing a plurality of pellets, the pellets including a mixture of a heat-generating element, a heating mediation agent, and a thermally-expanding element, the flexible bags being disposed proximate to the uncured composite aircraft component;
wherein the heat-generating element is capable of undergoing an exothermic chemical reaction or an exothermic physical reaction to raise a temperature of the uncured composite aircraft component to at least a predetermined first temperature when triggered, the heating mediation agent undergoes an endothermic physical reaction or an endothermic chemical reaction to decrease a maximum temperature of the uncured composite aircraft component reached after triggering the heat-generating element, and the thermally-expanding element softens and undergoes volumetric expansion by foaming when heated to a predetermined second temperature.
16. The assembly of claim 15 , wherein the thermally-expanding element is configured to apply pressure to the uncured composite aircraft component during curing.
17. A curing apparatus, comprising:
one or more flexible bags containing a plurality of pellets, the pellets including:
a heat-generating element capable of undergoing an exothermic chemical reaction or an exothermic physical reaction when triggered;
a heating mediation agent configured to undergo an endothermic physical reaction or an endothermic chemical reaction after the heat-generating element is triggered; and
a thermally-expanding element configured to soften and undergo volumetric expansion by foaming when heated to a predetermined first temperature.
18. The aircraft component manufacturing assembly of claim 15 , further including a rigid form, the uncured composite aircraft component being disposed on the rigid form.
19. The aircraft component manufacturing assembly of claim 15 , further comprising a removable barrier film applied to an outer surface of the uncured composite aircraft component.
20. The aircraft component manufacturing assembly of claim 15 , wherein the thermally-expanding element includes a thermoplastic material having a glass transition temperature and a melting temperature, and the predetermined second temperature is above the glass transition temperature and below the melting temperature.