Systems to apply heat to an aircraft surface are disclosed. In some embodiments, heaters are embedded in a composite structure of an aircraft. In one embodiment, a composite aircraft structure comprises a base comprising a plurality of resin impregnated plies, a heating layer adjacent the base, wher
Systems to apply heat to an aircraft surface are disclosed. In some embodiments, heaters are embedded in a composite structure of an aircraft. In one embodiment, a composite aircraft structure comprises a base comprising a plurality of resin impregnated plies, a heating layer adjacent the base, wherein the heating layer comprises at least one heater, an adhesive layer adjacent the heating layer, a lightning protection layer adjacent the heating layer, and an exterior surface layer adjacent the lightning protection layer. Other embodiments may be described.
대표청구항▼
1. A system comprising: an aircraft on a ground, the aircraft including a composite aircraft structure comprising: a base comprising a plurality of composite plies;a heating layer adjacent the base, wherein the heating layer comprises at least one resistive heating element; anda power input panel co
1. A system comprising: an aircraft on a ground, the aircraft including a composite aircraft structure comprising: a base comprising a plurality of composite plies;a heating layer adjacent the base, wherein the heating layer comprises at least one resistive heating element; anda power input panel configured to receive power for the resistive heating element;a ground-based power source connected to the power input panel;a voltage regulator configured to regulate electrical power from the ground-based power source, the voltage regulator including a temperature-sensitive circuit breaker that stops a flow of electrical power to the at least one resistive heating element embedded in the aircraft structure when a temperature proximate to the at least one resistive heating element exceeds a threshold; anda sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker. 2. The system of claim 1, wherein the composite aircraft structure further comprises: a first adhesive layer adjacent the heating layer;a lightning protection layer adjacent the heating layer;an exterior surface layer adjacent the lightning protection layer; anda second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies adjacent the second adhesive layer. 3. The system of claim 1, wherein the plurality of composite plies are arranged in a plurality of different orientations. 4. The system of claim 1, wherein the heating layer comprises a plurality of separately controllable heating elements. 5. The system of claim 1, further comprising a control circuit, wherein the control circuit comprises: a control panel coupled to the power input panel to generate at least one heat setting signal representing a desired heat setting for at least one heater;a regulator module to: receive at least one heat setting signal from the control panel;receive a temperature signal from at least one heater and;generate an output signal representing a difference between the at least one heat setting signal and the temperature signal. 6. The system of claim 5, wherein the output signal is fed back to the at least one heater to regulate a current flow through the at least one heater. 7. The system of claim 1, wherein the composite aircraft structure forms a portion between a leading edge and a trailing edge of one or more of a wing and a horizontal stabilizer of the aircraft. 8. An aircraft, comprising: a fuselage;at least one composite aircraft structure, comprising: a base comprising a plurality of composite plies; anda heating layer adjacent the base, wherein the heating layer comprises at least one resistive heating element;a power input panel configured to receive power for the resistive heating element, wherein the power input panel is configured to receive power from both an on-ground power source and an internal power source of the aircraft;a voltage regulator configured to regulate electrical power from the on-ground power source and the internal power source, the voltage regulator including a temperature-sensitive circuit breaker that stops a flow of electrical power to the at least one resistive heating element embedded in the aircraft structure when a temperature proximate to the at least one resistive heating element exceeds a threshold; anda sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker. 9. The aircraft of claim 8, wherein the at least one composite aircraft structure further comprises: a first adhesive layer adjacent the heating layer;a lightning protection layer adjacent the heating layer;an exterior surface layer adjacent the lightning protection layer; anda second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies adjacent the second adhesive layer. 10. The aircraft of claim 8, wherein the plurality of composite plies are arranged in a plurality of different orientations. 11. The aircraft of claim 8, wherein the heating layer comprises a plurality of separately controllable sealed heating elements. 12. The aircraft of claim 11, further comprising a control circuit, wherein the control circuit comprises: a control panel coupled to the power input panel to generate at least one heat setting signal representing a desired heat setting for at least one heater; anda regulator module configured to: receive at least one heat setting signal from the control panel;receive a temperature signal from at least one heater; andgenerate an output signal representing a difference between at least one heat setting signal and the temperature signal. 13. The aircraft of claim 12, wherein the output signal is fed back to the at least one heater to regulate a current flow through the at least one heater. 14. A method to apply heat to a composite aircraft structure of an aircraft while the aircraft is on a ground, comprising: receiving, in a power input panel, electrical power from ground-based power source;generating, in a control panel coupled to the power input panel, at least one heat setting signal representing a desired heat setting for at least one heater embedded in the aircraft structure;receiving, in a regulator module, at least one heat setting signal from the control panel and a temperature signal from at least one heater and;generating, in the regulator module, an output signal representing a difference between at least one heat setting signal and the temperature signal;directing the output signal to the at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater; andtripping at least one temperature-sensitive circuit breaker to stop a flow of electrical power to the at least one heater embedded in the aircraft structure when a temperature proximate to the at least one heater exceeds a threshold. 15. The method of claim 14, wherein receiving, in a power input panel, electrical power from a power source comprises receiving electrical power from a remote power source coupled to the power input panel. 16. The method of claim 14, wherein generating, in a control panel coupled to the power input panel, at least one heat setting signal comprises receiving an input from an input device on the control panel. 17. The method of claim 14, wherein generating, in the regulator module, an output signal representing a difference between at least one heat setting signal and the temperature signal comprises subtracting the output signal from the heat setting signal. 18. The method of claim 14, further comprising presenting on the control panel, an indicator of a temperature proximate to at least one heater. 19. The method of claim 14, wherein composite aircraft structure comprises: a base comprising a plurality of composite plies; anda heating layer adjacent the base, wherein the heating layer comprises at least one heater. 20. The method of claim 19, wherein composite aircraft structure further comprises: a first adhesive layer adjacent the heating layer;a lightning protection layer adjacent the heating layer;an exterior surface layer adjacent the lightning protection layer; anda second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies adjacent the second adhesive layer. 21. An aircraft comprising: a composite aircraft structure comprising: a base section comprising: a first composite ply with fibers disposed at an orientation of zero degrees with respect to a reference axis;a second composite ply disposed on the first composite ply and with fibers at an orientation of forty-five degrees with respect to the reference axis;a third composite ply disposed on the second composite ply and with fibers at an orientation of zero degrees with respect to the reference axis;a fourth composite ply disposed on the third composite ply and with fibers at an orientation of negative forty-five degrees with respect to the reference axis;a fifth composite ply disposed on the fourth composite ply and with fibers at an orientation of ninety degrees with respect to the reference axis; anda sixth composite ply disposed on the fifth composite ply and with fibers at an orientation of forty-five degrees with respect to the reference axis;a first adhesive layer disposed on the base section;a heating layer disposed on the first adhesive layer, the heating layer comprising at least one resistive heating element;a second adhesive layer disposed on the heating layer;a lightning protection layer disposed on the second adhesive layer; anda seventh composite ply disposed on the lightning protection layer with fibers in multiple directions with respect to the reference axis;a power input panel, wherein the at least one resistive heating element is configured to receive power from a ground-based power source and a generator of the aircraft via the power input panel;a control panel mounted on a flight deck of the aircraft and coupled to the at least one resistive heating element via at least one control signal line, the control panel comprising: an input device to generate a heat setting for the at least one resistive heating element; anda display panel to provide an indication of a state of the at least one resistive heating element;a voltage regulator configured to regulate electrical power for the at least one resistive heating element, the voltage regulator including a temperature-sensitive circuit breaker; anda sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker;wherein the composite aircraft structure forms a portion between a leading edge and a trailing edge of one or more of a wing and a horizontal stabilizer of the aircraft.
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이 특허에 인용된 특허 (9)
Hubert,Claude M.; Christy,Daniel P., Composite ice protection heater and method of producing same.
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