CA2845323C - Integrated surface thermal management system - Google Patents
Integrated surface thermal management system Download PDFInfo
- Publication number
- CA2845323C CA2845323C CA2845323A CA2845323A CA2845323C CA 2845323 C CA2845323 C CA 2845323C CA 2845323 A CA2845323 A CA 2845323A CA 2845323 A CA2845323 A CA 2845323A CA 2845323 C CA2845323 C CA 2845323C
- Authority
- CA
- Canada
- Prior art keywords
- composite
- aircraft
- temperature
- aircraft structure
- heater
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
- B64D15/14—De-icing or preventing icing on exterior surfaces of aircraft by electric heating controlled cyclically along length of surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/20—Ground installations for de-icing aircraft
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B2214/00—Aspects relating to resistive heating, induction heating and heating using microwaves, covered by groups H05B3/00, H05B6/00
- H05B2214/02—Heaters specially designed for de-icing or protection against icing
Abstract
A system and method to apply heat to an aircraft surface are disclosed. The composite aircraft structure comprises a base comprising a plurality of resin impregnated plies 212,214,216,218,220,222), heating layer (230) adjacent the base, wherein the heating layer com prises at least one heater, an adhesive layer (240a, 240b) adjacent the heating layer, a lightning protection layer (250) adjacent the heating layer, and an exterior surface layer (260) adjacent the lightning protection layer.
Description
INTEGRATED SURFACE THERMAL MANAGEMENT SYSTEM
Background Aircraft include flight surfaces (e.g., a wings, stabilizers and control surfaces) and movable control surfaces for directional control in flight. Such control surfaces can include ailerons for roll control, elevators for pitch control, and rudders for yaw control.
In winter conditions flight surfaces and control surfaces may become coated with ice, particularly during layovers on the ground. Present deicing techniques for aircraft include spraying a heated glycol-based solution on the aircraft to clear ice from the flight surfaces and control surfaces and/or exposing the aircraft to infrared (IR) radiation heaters.
Such deicing techniques are expensive and time consuming, and contribute to delays in airport efficiency. Accordingly, additional techniques to deice aircraft surfaces may find utility.
Summary Embodiments of systems and methods in accordance with the present disclosure may provide improved systems and methods to apply heat to aircraft structures.
More specifically, embodiments described herein provide for the construction of aircraft structures which may incorporate integrated heating elements and for methods to apply heat to the structures using the heating elements.
In one embodiment, there is provided an integrated surface thermal management system and a composite aircraft structure, the composite aircraft structure comprising: a base comprising a plurality of resin impregnated plies, and a heating layer adjacent the base, wherein the heating layer comprises a plurality of heaters coupled by a bus network; and the integrated surface thermal management system comprising:
a control circuit coupled to the heating layer, wherein the control circuit comprises a power input panel, a control panel and a regulator module, the power input panel coupled to the control panel and regulator module via a circuit, wherein the power input panel is configured to accept power input from a ground-based power source when an aircraft comprising the composite aircraft structure is on the ground, and wherein the regulator module includes at least one temperature-sensitive circuit breaker that stops a flow of electrical power to at least one of the plurality of heaters when a temperature proximate to the at least one heater exceeds a threshold.
In another embodiment, there is provided a method to apply heat to a composite aircraft structure, the method comprising: receiving, when an aircraft comprising the composite structure is on the ground, in a power input panel, electrical power from a ground-based power source; generating, in a control panel coupled to the power input panel, at least one temperature setting signal representing a desired temperature setting for at least one heater embedded in the aircraft structure; receiving, in a regulator module, at least one temperature setting signal from the control panel and a temperature signal from at least one heater; generating, in the regulator module, an output signal representing a difference between at least one temperature setting signal and the temperature signal;
directing the output signal to at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater embedded in the aircraft; and tripping 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 embedded in the aircraft exceeds a threshold.
In another embodiment, there is provided a system comprising: an aircraft on a ground, the aircraft including a composite aircraft structure comprising: a base comprising a plurality of composite plies; and a 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 at least one 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; and a sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker.
In another embodiment, there is provided an aircraft, comprising: a fuselage;
at least one composite aircraft structure, comprising: a base comprising a plurality of composite plies, and a 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 at least one 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
Background Aircraft include flight surfaces (e.g., a wings, stabilizers and control surfaces) and movable control surfaces for directional control in flight. Such control surfaces can include ailerons for roll control, elevators for pitch control, and rudders for yaw control.
In winter conditions flight surfaces and control surfaces may become coated with ice, particularly during layovers on the ground. Present deicing techniques for aircraft include spraying a heated glycol-based solution on the aircraft to clear ice from the flight surfaces and control surfaces and/or exposing the aircraft to infrared (IR) radiation heaters.
Such deicing techniques are expensive and time consuming, and contribute to delays in airport efficiency. Accordingly, additional techniques to deice aircraft surfaces may find utility.
Summary Embodiments of systems and methods in accordance with the present disclosure may provide improved systems and methods to apply heat to aircraft structures.
More specifically, embodiments described herein provide for the construction of aircraft structures which may incorporate integrated heating elements and for methods to apply heat to the structures using the heating elements.
In one embodiment, there is provided an integrated surface thermal management system and a composite aircraft structure, the composite aircraft structure comprising: a base comprising a plurality of resin impregnated plies, and a heating layer adjacent the base, wherein the heating layer comprises a plurality of heaters coupled by a bus network; and the integrated surface thermal management system comprising:
a control circuit coupled to the heating layer, wherein the control circuit comprises a power input panel, a control panel and a regulator module, the power input panel coupled to the control panel and regulator module via a circuit, wherein the power input panel is configured to accept power input from a ground-based power source when an aircraft comprising the composite aircraft structure is on the ground, and wherein the regulator module includes at least one temperature-sensitive circuit breaker that stops a flow of electrical power to at least one of the plurality of heaters when a temperature proximate to the at least one heater exceeds a threshold.
In another embodiment, there is provided a method to apply heat to a composite aircraft structure, the method comprising: receiving, when an aircraft comprising the composite structure is on the ground, in a power input panel, electrical power from a ground-based power source; generating, in a control panel coupled to the power input panel, at least one temperature setting signal representing a desired temperature setting for at least one heater embedded in the aircraft structure; receiving, in a regulator module, at least one temperature setting signal from the control panel and a temperature signal from at least one heater; generating, in the regulator module, an output signal representing a difference between at least one temperature setting signal and the temperature signal;
directing the output signal to at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater embedded in the aircraft; and tripping 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 embedded in the aircraft exceeds a threshold.
In another embodiment, there is provided a system comprising: an aircraft on a ground, the aircraft including a composite aircraft structure comprising: a base comprising a plurality of composite plies; and a 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 at least one 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; and a sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker.
In another embodiment, there is provided an aircraft, comprising: a fuselage;
at least one composite aircraft structure, comprising: a base comprising a plurality of composite plies, and a 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 at least one 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
-2-least one resistive heating element exceeds a threshold; and a sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker.
In another embodiment, there is provided 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 a 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; 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 at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater; and tripping 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.
In another embodiment there is provided 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; and a 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; and a 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 -2a-device to generate a heat setting for the at least one resistive heating element; and a 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; and a 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.
Further areas of applicability will become apparent from the description provided herein. It should be understood that the description and specific examples are intended for purposes of illustration only and are not intended to limit the scope of the present disclosure or application of the technology.
BRIEF DESCRIPTION OF THE DRAWINGS
Embodiments of methods and systems in accordance with the teachings of the present disclosure are described in detail below with reference to the following drawings.
Fig. 1 is a schematic, perspective view of an aircraft having an integrated surface thermal management system in accordance with embodiments.
-2b-Fig. 2 is a schematic, cross-sectional illustration of an aircraft structure adapted to include a heating layer, according to embodiments.
Fig. 3 is a schematic illustration of a control circuit which may be used with an integrated surface thermal management system, according to embodiments.
Fig. 4 is a flowchart illustrating high-level operations of a method to heat an aircraft structure, according to embodiments.
DETAILED DESCRIPTION
Systems and methods to for thermal management on aircraft structures are described herein. Specific details of certain embodiments are set forth in the following description and in Figs. 1-3 to provide a thorough understanding of such embodiments. One skilled in the art will understand, however, that alternate embodiments may be practiced without several of the details described in the following description.
Fig. 1 is a partially schematic, top view of an aircraft 100 having one or more control, lifting and actuation surfaces 102 configured in accordance with an embodiment of the invention. In one aspect of this embodiment, the aircraft includes a fuselage 104, forward wings 106 (shown as first and second wings 106a and 106b) and horizontal stabilizer 114 (shown as first and second wings 114a, and 114b) fixedly attached to the fuselage. Each wing 106 can include a number of movable control surfaces for controlling the aircraft 100 during flight. These control surfaces may include flaperons 108a, 108b, collectively referred to by reference numeral 108, elevators 110a, 110b, collectively referred to as 110, and ailerons 112a, 112b, collectively referred to as 112. In operation, a flight control actuation system can extend or retract linear actuators to deflect the elevators up or down, which actions cause the aircraft to pitch nose up or down. Similarly, the ailerons, rudder, flaperons, and spoilers, may be deflected to generate the desired effects on the airplane.
In accordance with embodiments described herein, portions of the wings 106, horizontal stabilizer 114, fuselage 104 or other aircraft structures may be formed
In another embodiment, there is provided 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 a 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; 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 at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater; and tripping 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.
In another embodiment there is provided 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; and a 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; and a 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 -2a-device to generate a heat setting for the at least one resistive heating element; and a 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; and a 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.
Further areas of applicability will become apparent from the description provided herein. It should be understood that the description and specific examples are intended for purposes of illustration only and are not intended to limit the scope of the present disclosure or application of the technology.
BRIEF DESCRIPTION OF THE DRAWINGS
Embodiments of methods and systems in accordance with the teachings of the present disclosure are described in detail below with reference to the following drawings.
Fig. 1 is a schematic, perspective view of an aircraft having an integrated surface thermal management system in accordance with embodiments.
-2b-Fig. 2 is a schematic, cross-sectional illustration of an aircraft structure adapted to include a heating layer, according to embodiments.
Fig. 3 is a schematic illustration of a control circuit which may be used with an integrated surface thermal management system, according to embodiments.
Fig. 4 is a flowchart illustrating high-level operations of a method to heat an aircraft structure, according to embodiments.
DETAILED DESCRIPTION
Systems and methods to for thermal management on aircraft structures are described herein. Specific details of certain embodiments are set forth in the following description and in Figs. 1-3 to provide a thorough understanding of such embodiments. One skilled in the art will understand, however, that alternate embodiments may be practiced without several of the details described in the following description.
Fig. 1 is a partially schematic, top view of an aircraft 100 having one or more control, lifting and actuation surfaces 102 configured in accordance with an embodiment of the invention. In one aspect of this embodiment, the aircraft includes a fuselage 104, forward wings 106 (shown as first and second wings 106a and 106b) and horizontal stabilizer 114 (shown as first and second wings 114a, and 114b) fixedly attached to the fuselage. Each wing 106 can include a number of movable control surfaces for controlling the aircraft 100 during flight. These control surfaces may include flaperons 108a, 108b, collectively referred to by reference numeral 108, elevators 110a, 110b, collectively referred to as 110, and ailerons 112a, 112b, collectively referred to as 112. In operation, a flight control actuation system can extend or retract linear actuators to deflect the elevators up or down, which actions cause the aircraft to pitch nose up or down. Similarly, the ailerons, rudder, flaperons, and spoilers, may be deflected to generate the desired effects on the airplane.
In accordance with embodiments described herein, portions of the wings 106, horizontal stabilizer 114, fuselage 104 or other aircraft structures may be formed
- 3 -from a composite construction and may include heating elements integrated into the composite structure of the wings 106 or, horizontal stabilizer 114 to define heated regions, which are illustrated in shading in Fig. 1.
Fig. 2 is a schematic, cross-sectional illustration of an aircraft structure 200 adapted to include a heating layer, according to embodiments. In some embodiments the structure 200 may be an aircraft wing such as one of the wings 106 or horizontal stabilizer 114. In other embodiments the aircraft structure may be a fuselage such as fuselage 104. Referring to Fig. 2, in some embodiments the structure comprises a base section 210 which is formed from a plurality of resin impregnated plies. In the embodiment depicted in Fig. 2 the base includes six layers of composite resin plies which are arranged in different orientations, including a first layer 212 in which the fibers are disposed at an orientation of zero degrees (0 ) with respect to a reference axis, a second layer 214 in which the fibers are disposed at an orientation of forty-five degrees (45 ) with respect to the reference axis, a third layer 216 in which the fibers are disposed at an orientation of zero degrees (0 ) with respect to the reference axis, a fourth layer 218 in which the fibers are disposed at an orientation of negative forty-five degrees (-45 ) with respect to the reference axis, a fifth layer 220 in which the fibers are disposed at an orientation of ninety degrees (90 ) with respect to the reference axis, and a sixth layer 222 in which the fibers are disposed at an orientation of forty-five degrees (45 ) with respect to the reference axis. One skilled in the art will recognize that the base depicted in Fig. 2 is merely exemplary; and that other ply materials and orientations may be used.
It will be appreciated that a variety of alternate embodiments can be conceived, and that the base section 210 is not limited to the particular embodiment shown in Fig. 2. For example, in alternate embodiments, the base section 210 may have a greater or fewer number of composite layers than are shown in Fig. 2.
For example, while the base section 210 in Fig. 2 includes a total of six composite layers oriented in an alternating manner, in alternate embodiments, additional composite layers may be added either asymmetrically or symmetrically, with the result that the base section 210 may be a symmetric or an asymmetric section. Furthermore, the reinforcing fibers in the layers composite component may be oriented in any desired manner, and are not limited to the particular angular values and materials described above and shown in Fig. 2.
Fig. 2 is a schematic, cross-sectional illustration of an aircraft structure 200 adapted to include a heating layer, according to embodiments. In some embodiments the structure 200 may be an aircraft wing such as one of the wings 106 or horizontal stabilizer 114. In other embodiments the aircraft structure may be a fuselage such as fuselage 104. Referring to Fig. 2, in some embodiments the structure comprises a base section 210 which is formed from a plurality of resin impregnated plies. In the embodiment depicted in Fig. 2 the base includes six layers of composite resin plies which are arranged in different orientations, including a first layer 212 in which the fibers are disposed at an orientation of zero degrees (0 ) with respect to a reference axis, a second layer 214 in which the fibers are disposed at an orientation of forty-five degrees (45 ) with respect to the reference axis, a third layer 216 in which the fibers are disposed at an orientation of zero degrees (0 ) with respect to the reference axis, a fourth layer 218 in which the fibers are disposed at an orientation of negative forty-five degrees (-45 ) with respect to the reference axis, a fifth layer 220 in which the fibers are disposed at an orientation of ninety degrees (90 ) with respect to the reference axis, and a sixth layer 222 in which the fibers are disposed at an orientation of forty-five degrees (45 ) with respect to the reference axis. One skilled in the art will recognize that the base depicted in Fig. 2 is merely exemplary; and that other ply materials and orientations may be used.
It will be appreciated that a variety of alternate embodiments can be conceived, and that the base section 210 is not limited to the particular embodiment shown in Fig. 2. For example, in alternate embodiments, the base section 210 may have a greater or fewer number of composite layers than are shown in Fig. 2.
For example, while the base section 210 in Fig. 2 includes a total of six composite layers oriented in an alternating manner, in alternate embodiments, additional composite layers may be added either asymmetrically or symmetrically, with the result that the base section 210 may be a symmetric or an asymmetric section. Furthermore, the reinforcing fibers in the layers composite component may be oriented in any desired manner, and are not limited to the particular angular values and materials described above and shown in Fig. 2.
- 4 -A heating layer 230 is disposed adjacent the base 210. In some embodiments the heating layer 230 may comprise a plurality of heating elements. By way of example, heating elements may be embodied as heaters encased in a sheeting material such as an Omega KH-405/5 resistive heating element manufactured and distributed by Omega.
One or more layers of adhesive 240a, 240b, may be disposed adjacent the heater 230. In some embodiments the adhesive may be embodied as a nylon adhesive such as a BMS/160 nylon adhesive.
A layer of conductive foil 250 may be disposed adjacent the adhesive layer 240 or the heater. In some embodiments the conductive foil 250 may be embodied as a conductive mesh or prepreg incorporating copper, bronze or other conductive foil or mesh. The conductive foil is not related to the operation of the heating elements, but is often used for lightning strike protection. Other techniques for lightning strike protection may be used alone or in conjunction with conductive foils.
Lightning protection foil may be combined with the heater. All layers may be combined in any layup order. Any two or more layers may be combined into a single layer. Any layer may not be used over the entire structure.
A layer of ply material (e.g. fiberglass) 260 may be disposed adjacent to the foil 250, or the heater or the adhesive. In the embodiment depicted in Fig. 2 the ply material 260 includes fibers oriented in multiple directions with respect to the reference axis.
An aircraft structure in accordance with the embodiment depicted in Fig. 2 may be constructed in accordance with composite manufacturing techniques. In general, the respective layers, or plies, are laid up against a tool formed in the shape of the structure, e.g., a wing section, a section of a fuselage, or the like, and cured.
The heaters on a finished aircraft structure may be coupled to a control circuit to manage heat transfer operations. Fig. 3 is a schematic illustration of an integrated surface thermal management system 300, according to embodiments.
Referring to Fig. 3, in some embodiments the system 300 comprises an input power panel 310, a control panel 320, a regulator, 330, and a heater array 340 comprising a plurality of heaters 342a-342j coupled by a bus network 344. In use, the system 300 may be installed on an aircraft such that one or more heater arrays 340 are disposed on
One or more layers of adhesive 240a, 240b, may be disposed adjacent the heater 230. In some embodiments the adhesive may be embodied as a nylon adhesive such as a BMS/160 nylon adhesive.
A layer of conductive foil 250 may be disposed adjacent the adhesive layer 240 or the heater. In some embodiments the conductive foil 250 may be embodied as a conductive mesh or prepreg incorporating copper, bronze or other conductive foil or mesh. The conductive foil is not related to the operation of the heating elements, but is often used for lightning strike protection. Other techniques for lightning strike protection may be used alone or in conjunction with conductive foils.
Lightning protection foil may be combined with the heater. All layers may be combined in any layup order. Any two or more layers may be combined into a single layer. Any layer may not be used over the entire structure.
A layer of ply material (e.g. fiberglass) 260 may be disposed adjacent to the foil 250, or the heater or the adhesive. In the embodiment depicted in Fig. 2 the ply material 260 includes fibers oriented in multiple directions with respect to the reference axis.
An aircraft structure in accordance with the embodiment depicted in Fig. 2 may be constructed in accordance with composite manufacturing techniques. In general, the respective layers, or plies, are laid up against a tool formed in the shape of the structure, e.g., a wing section, a section of a fuselage, or the like, and cured.
The heaters on a finished aircraft structure may be coupled to a control circuit to manage heat transfer operations. Fig. 3 is a schematic illustration of an integrated surface thermal management system 300, according to embodiments.
Referring to Fig. 3, in some embodiments the system 300 comprises an input power panel 310, a control panel 320, a regulator, 330, and a heater array 340 comprising a plurality of heaters 342a-342j coupled by a bus network 344. In use, the system 300 may be installed on an aircraft such that one or more heater arrays 340 are disposed on
- 5 -the wings of the aircraft, as depicted in Fig. 1, or on portions of the fuselage or on control surfaces of the aircraft.
Power input panel 310 may be configured to accept power input from a ground-based power source, for example a portable power unit or a ground-based power supply coupled to an aircraft gate, when the aircraft is on the ground.
By contrast, when the aircraft is in flight input power panel 310 may receive power from the aircraft's generator. Power input panel 310 is coupled to control panel 320 and regulator 330 via circuit 312.
Control panel 320 may be mounted on the flight deck or elsewhere and may comprise a switch 322 in which selectively opens and closes circuit 312 to enable and disable current flow through circuit 312. Control panel 320 may further comprise an input device 324 to generate a heat setting signal based on an input from a user of the system 300. In the embodiment depicted in Fig. 3 the input device is embodied as a pin slideable along an axis. However, other input devices, e.g., buttons, touch screens, etc., may be used. The specific input device is not critical. Control panel 320 further comprises controller 328 and a display panel 326 to provide an indication of the state of heaters 342. Control panel 320 is coupled to one or more heater arrays 340 via lines 328, which carry control signals between control panel 320 and heaters 342a-342j.
When the switch 322 is closed, power from the power source flows through circuit 312 to regulator 330. Regulator 330 may include one or more temperature-sensitive circuit breakers 332, 334. In normal operating circumstances circuit breakers 332, 334 remain closed to provide electrical power to heating array(s) 340. However, in the event a temperature proximate to a heater 342 exceeds a threshold then one or more of the circuit breakers may be tripped to stop the flow of electrical power to heating array(s) 340. Electrical power from regulator 330 is directed to one or more heater arrays 340, and directed to individual heaters 342a-342j by bus network 344.
In operation, the system 300 implements a process to heat an aircraft structure. Fig. 4 is a flowchart illustrating high-level operations of a method to heat an aircraft structure, according to embodiments. Referring to Fig. 4, at operation 410 the power input panel 310 receives electrical power from a power source. As described above, the power source may be either external or internal. When switch 322 is closed, power from the power source flows to control panel 320 (operation 415). Some or all of
Power input panel 310 may be configured to accept power input from a ground-based power source, for example a portable power unit or a ground-based power supply coupled to an aircraft gate, when the aircraft is on the ground.
By contrast, when the aircraft is in flight input power panel 310 may receive power from the aircraft's generator. Power input panel 310 is coupled to control panel 320 and regulator 330 via circuit 312.
Control panel 320 may be mounted on the flight deck or elsewhere and may comprise a switch 322 in which selectively opens and closes circuit 312 to enable and disable current flow through circuit 312. Control panel 320 may further comprise an input device 324 to generate a heat setting signal based on an input from a user of the system 300. In the embodiment depicted in Fig. 3 the input device is embodied as a pin slideable along an axis. However, other input devices, e.g., buttons, touch screens, etc., may be used. The specific input device is not critical. Control panel 320 further comprises controller 328 and a display panel 326 to provide an indication of the state of heaters 342. Control panel 320 is coupled to one or more heater arrays 340 via lines 328, which carry control signals between control panel 320 and heaters 342a-342j.
When the switch 322 is closed, power from the power source flows through circuit 312 to regulator 330. Regulator 330 may include one or more temperature-sensitive circuit breakers 332, 334. In normal operating circumstances circuit breakers 332, 334 remain closed to provide electrical power to heating array(s) 340. However, in the event a temperature proximate to a heater 342 exceeds a threshold then one or more of the circuit breakers may be tripped to stop the flow of electrical power to heating array(s) 340. Electrical power from regulator 330 is directed to one or more heater arrays 340, and directed to individual heaters 342a-342j by bus network 344.
In operation, the system 300 implements a process to heat an aircraft structure. Fig. 4 is a flowchart illustrating high-level operations of a method to heat an aircraft structure, according to embodiments. Referring to Fig. 4, at operation 410 the power input panel 310 receives electrical power from a power source. As described above, the power source may be either external or internal. When switch 322 is closed, power from the power source flows to control panel 320 (operation 415). Some or all of
- 6 -the functions of the power panel 310, control panel 320 and regulator 330 may be combined in a single or multiple unit system.
At operation 420 the control panel generates one or more temperature setting signals. In some embodiments a user of the system 300 directs the control panel to generate a temperature setting signal using the input device 324. In some embodiments a single input device 324 generates a single temperature setting signal applicable to the entire system 300. In other embodiments the input device may generate discrete signals for individual heaters 342.
Heaters 342 may include a thermistor, thermocouple, or other device to output a voltage that is proportional to a temperature proximate to the heater. In some embodiments each heater 342a-342 j generates an independent signal which is transmitted to the control panel on one of the lines 328 (operation 430). In alternate embodiments the heater array 340 may generate a single temperature signal or may integrate a plurality of temperature signals from temperature sensors proximate to the heater array 340.
At operation 435 the controller in the control panel generates one or more output signals that are proportional to a difference between the temperature setting signals generated in response to the input device and the temperature signals from the heaters 342. The output signals may be converted to a voltage (operation 440) and placed on lines 328, such that the voltage is input (operation 445) to the respective heaters 342a-342j to drive the heaters 342a-342j.
The operations depicted in Fig. 4 may be embodied as logic executable in controller 328 such that controller 328 may continuously monitor and regulate the temperature of heaters 342a-342 to apply heat to an aircraft structure. In some embodiments the logic may be implemented as logic instructions which may be stored in a computer-readable memory, e.g., software, and executed by a processing device.
In other embodiments the logic may be reduced to firmware or even to hardwired circuitry. Thus, described herein are multilayer, composite structures which comprise an integrated heating layer and a control system which may be coupled to the integrated heating layer to selectively apply heat to the aircraft structure. The heating layer and control system may used in any composite or non-composite structure, fixed or moveable, whether in flight or on/under the surface.
At operation 420 the control panel generates one or more temperature setting signals. In some embodiments a user of the system 300 directs the control panel to generate a temperature setting signal using the input device 324. In some embodiments a single input device 324 generates a single temperature setting signal applicable to the entire system 300. In other embodiments the input device may generate discrete signals for individual heaters 342.
Heaters 342 may include a thermistor, thermocouple, or other device to output a voltage that is proportional to a temperature proximate to the heater. In some embodiments each heater 342a-342 j generates an independent signal which is transmitted to the control panel on one of the lines 328 (operation 430). In alternate embodiments the heater array 340 may generate a single temperature signal or may integrate a plurality of temperature signals from temperature sensors proximate to the heater array 340.
At operation 435 the controller in the control panel generates one or more output signals that are proportional to a difference between the temperature setting signals generated in response to the input device and the temperature signals from the heaters 342. The output signals may be converted to a voltage (operation 440) and placed on lines 328, such that the voltage is input (operation 445) to the respective heaters 342a-342j to drive the heaters 342a-342j.
The operations depicted in Fig. 4 may be embodied as logic executable in controller 328 such that controller 328 may continuously monitor and regulate the temperature of heaters 342a-342 to apply heat to an aircraft structure. In some embodiments the logic may be implemented as logic instructions which may be stored in a computer-readable memory, e.g., software, and executed by a processing device.
In other embodiments the logic may be reduced to firmware or even to hardwired circuitry. Thus, described herein are multilayer, composite structures which comprise an integrated heating layer and a control system which may be coupled to the integrated heating layer to selectively apply heat to the aircraft structure. The heating layer and control system may used in any composite or non-composite structure, fixed or moveable, whether in flight or on/under the surface.
- 7 -The terms "logic instructions" as referred to herein relates to expressions which may be understood by one or more machines for performing one or more logical operations. For example, logic instructions may comprise instructions which are interpretable by a processor compiler for executing one or more operations on one or more data objects. However, this is merely an example of machine-readable instructions and embodiments are not limited in this respect.
The terms "computer readable medium" as referred to herein relates to media capable of maintaining expressions which are perceivable by one or more machines. For example, a computer readable medium may comprise one or more storage devices for storing computer readable instructions or data. Such storage devices may comprise storage media such as, for example, optical, magnetic or semiconductor storage media. However, this is merely an example of a computer readable medium and embodiments are not limited in this respect.
The term "logic" as referred to herein relates to structure for performing one or more logical operations. For example, logic may comprise circuitry which provides one or more output signals based upon one or more input signals. Such circuitry may comprise a finite state machine which receives a digital input and provides a digital output, or circuitry which provides one or more analog output signals in response to one or more analog input signals. Such circuitry may be provided in an application specific integrated circuit (ASIC) or field programmable gate array (FPGA).
Also, logic may comprise machine-readable instructions stored in a memory in combination with processing circuitry to execute such machine-readable instructions.
However, these are merely examples of structures which may provide logic and embodiments are not limited in this respect.
Various functional components of the system 300 may be implemented as logic instructions which may be executed on a general purpose processor or on a configurable flight control electronics. By way of example, in some embodiments the operations depicted in Fig. 4 may be implemented as logic instructions executable on the controller 328 of control panel 320. When executed on a processor, the logic instructions cause a processor to be programmed as a special-purpose machine that implements the described methods. The processor, when configured by the logic instructions to execute the methods described herein, constitutes structure for performing the described methods. Alternatively, the methods described herein may be
The terms "computer readable medium" as referred to herein relates to media capable of maintaining expressions which are perceivable by one or more machines. For example, a computer readable medium may comprise one or more storage devices for storing computer readable instructions or data. Such storage devices may comprise storage media such as, for example, optical, magnetic or semiconductor storage media. However, this is merely an example of a computer readable medium and embodiments are not limited in this respect.
The term "logic" as referred to herein relates to structure for performing one or more logical operations. For example, logic may comprise circuitry which provides one or more output signals based upon one or more input signals. Such circuitry may comprise a finite state machine which receives a digital input and provides a digital output, or circuitry which provides one or more analog output signals in response to one or more analog input signals. Such circuitry may be provided in an application specific integrated circuit (ASIC) or field programmable gate array (FPGA).
Also, logic may comprise machine-readable instructions stored in a memory in combination with processing circuitry to execute such machine-readable instructions.
However, these are merely examples of structures which may provide logic and embodiments are not limited in this respect.
Various functional components of the system 300 may be implemented as logic instructions which may be executed on a general purpose processor or on a configurable flight control electronics. By way of example, in some embodiments the operations depicted in Fig. 4 may be implemented as logic instructions executable on the controller 328 of control panel 320. When executed on a processor, the logic instructions cause a processor to be programmed as a special-purpose machine that implements the described methods. The processor, when configured by the logic instructions to execute the methods described herein, constitutes structure for performing the described methods. Alternatively, the methods described herein may be
- 8 -reduced to logic on, e.g., a field programmable gate array (FPGA), an application specific integrated circuit (ASIC) or the like.
For example, in some embodiments a computer program product may comprise logic instructions stored on a computer-readable medium which, when executed, configure a flight control electronics to detect whether a system management memory module is in a visible state, in response to a determination that system management memory is in a visible state, direct one or more system management memory input/output operations to a system management memory module, and in response to a determination that system management memory is in an invisible state, direct system management memory cache write back operations to the system management memory module and direct other system management memory input/output operations to another location in a system memory.
In the description and claims, the terms coupled and connected, along with their derivatives, may be used. In particular embodiments, connected may be used to indicate that two or more elements are in direct physical or electrical contact with each other. Coupled may mean that two or more elements are in direct physical or electrical contact. However, coupled may also mean that two or more elements may not be in direct contact with each other, but yet may still cooperate or interact with each other.
Reference in the specification to "one embodiment" or "some embodiments" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least an implementation. The appearances of the phrase "in one embodiment" in various places in the specification may or may not be all referring to the same embodiment. In the foregoing discussion, specific implementations of exemplary processes have been described, however, it should be understood that in alternate implementations, certain acts need not be performed in the order described above. In alternate embodiments, some acts may be modified, performed in a different order, or may be omitted entirely, depending on the circumstances. Moreover, in various alternate implementations, the acts described may be implemented by a computer, flight control electronics, processor, programmable device, firmware, or any other suitable device, and may be based on instructions stored on one or more computer-readable media or otherwise stored or programmed into such devices (e.g. including transmitting computer-readable instructions in real time to such
For example, in some embodiments a computer program product may comprise logic instructions stored on a computer-readable medium which, when executed, configure a flight control electronics to detect whether a system management memory module is in a visible state, in response to a determination that system management memory is in a visible state, direct one or more system management memory input/output operations to a system management memory module, and in response to a determination that system management memory is in an invisible state, direct system management memory cache write back operations to the system management memory module and direct other system management memory input/output operations to another location in a system memory.
In the description and claims, the terms coupled and connected, along with their derivatives, may be used. In particular embodiments, connected may be used to indicate that two or more elements are in direct physical or electrical contact with each other. Coupled may mean that two or more elements are in direct physical or electrical contact. However, coupled may also mean that two or more elements may not be in direct contact with each other, but yet may still cooperate or interact with each other.
Reference in the specification to "one embodiment" or "some embodiments" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least an implementation. The appearances of the phrase "in one embodiment" in various places in the specification may or may not be all referring to the same embodiment. In the foregoing discussion, specific implementations of exemplary processes have been described, however, it should be understood that in alternate implementations, certain acts need not be performed in the order described above. In alternate embodiments, some acts may be modified, performed in a different order, or may be omitted entirely, depending on the circumstances. Moreover, in various alternate implementations, the acts described may be implemented by a computer, flight control electronics, processor, programmable device, firmware, or any other suitable device, and may be based on instructions stored on one or more computer-readable media or otherwise stored or programmed into such devices (e.g. including transmitting computer-readable instructions in real time to such
- 9 -devices). In the context of software, the acts described above may represent computer instructions that, when executed by one or more processors, perform the recited operations. In the event that computer-readable media are used, the computer-readable media can be any available media that can be accessed by a device to implement the instructions stored thereon.
While various embodiments have been described, those skilled in the art will recognize modifications or variations which might be made without departing from the present disclosure. The examples illustrate the various embodiments and are not intended to limit the present disclosure. Therefore, the description and claims should be interpreted liberally with only such limitation as is necessary in view of the pertinent prior art.
While various embodiments have been described, those skilled in the art will recognize modifications or variations which might be made without departing from the present disclosure. The examples illustrate the various embodiments and are not intended to limit the present disclosure. Therefore, the description and claims should be interpreted liberally with only such limitation as is necessary in view of the pertinent prior art.
- 10 -
Claims (34)
1. An integrated surface thermal management system and a composite aircraft structure, the composite aircraft structure comprising:
a base comprising a plurality of resin impregnated plies, and a heating layer adjacent the base, wherein the heating layer comprises a plurality of heaters coupled by a bus network; and the integrated surface thermal management system comprising:
a control circuit coupled to the heating layer, wherein the control circuit comprises a power input panel, a control panel and a regulator module, the power input panel coupled to the control panel and regulator module via a circuit, wherein the power input panel is configured to accept power input from a ground-based power source when an aircraft comprising the composite aircraft structure is on the ground, and wherein the regulator module includes at least one temperature-sensitive circuit breaker that stops a flow of electrical power to at least one of the plurality of heaters when a temperature proximate to the at least one heater exceeds a threshold.
a base comprising a plurality of resin impregnated plies, and a heating layer adjacent the base, wherein the heating layer comprises a plurality of heaters coupled by a bus network; and the integrated surface thermal management system comprising:
a control circuit coupled to the heating layer, wherein the control circuit comprises a power input panel, a control panel and a regulator module, the power input panel coupled to the control panel and regulator module via a circuit, wherein the power input panel is configured to accept power input from a ground-based power source when an aircraft comprising the composite aircraft structure is on the ground, and wherein the regulator module includes at least one temperature-sensitive circuit breaker that stops a flow of electrical power to at least one of the plurality of heaters when a temperature proximate to the at least one heater exceeds a threshold.
2. The integrated surface thermal management system and composite aircraft structure of claim 1, wherein the composite aircraft structure further comprises:
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.
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.
3. The integrated surface thermal management system and composite aircraft structure of claim 1 or 2, wherein the base comprises a plurality of composite plies arranged in a plurality of different orientations.
4. The integrated surface thermal management system and composite aircraft structure of any one of claims 1 to 3, wherein the heating layer comprises a plurality of separately controllable heating elements.
5. The integrated surface thermal management system and composite aircraft structure of any one of claims 1 to 4, wherein:
the control panel coupled to the power input panel is configured to generate at least one heat setting signal representing a desired heat setting for at least one other heater of the plurality of heaters; and the regulator module is configured to:
receive the at least one heat setting signal from the control panel;
receive a temperature signal from the at least one other heater; and generate an output signal representing a difference between the at least one heat setting signal and the temperature signal.
the control panel coupled to the power input panel is configured to generate at least one heat setting signal representing a desired heat setting for at least one other heater of the plurality of heaters; and the regulator module is configured to:
receive the at least one heat setting signal from the control panel;
receive a temperature signal from the at least one other heater; and generate an output signal representing a difference between the at least one heat setting signal and the temperature signal.
6. The integrated surface thermal management system and composite aircraft structure of claim 5, wherein the output signal is fed back to the at least one other heater to regulate a current flow through the at least one other heater.
7. An aircraft comprising the integrated surface thermal management system and composite aircraft structure of any one of claims 1 to 6.
8. A method to apply heat to a composite aircraft structure, the method comprising:
receiving, when an aircraft comprising the composite structure is on the ground, in a power input panel, electrical power from a ground-based power source;
generating, in a control panel coupled to the power input panel, at least one temperature setting signal representing a desired temperature setting for at least one heater embedded in the aircraft structure;
receiving, in a regulator module, at least one temperature setting signal from the control panel and a temperature signal from at least one heater;
generating, in the regulator module, an output signal representing a difference between at least one temperature setting signal and the temperature signal;
directing the output signal to at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater embedded in the aircraft; and tripping 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 embedded in the aircraft exceeds a threshold.
receiving, when an aircraft comprising the composite structure is on the ground, in a power input panel, electrical power from a ground-based power source;
generating, in a control panel coupled to the power input panel, at least one temperature setting signal representing a desired temperature setting for at least one heater embedded in the aircraft structure;
receiving, in a regulator module, at least one temperature setting signal from the control panel and a temperature signal from at least one heater;
generating, in the regulator module, an output signal representing a difference between at least one temperature setting signal and the temperature signal;
directing the output signal to at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater embedded in the aircraft; and tripping 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 embedded in the aircraft exceeds a threshold.
9. The method of claim 8, wherein receiving, in the power input panel, electrical power from the power source comprises receiving electrical power from a remote power source coupled to the power input panel.
10. The method of claim 8 or 9, wherein generating, in the control panel coupled to the power input panel, at least one temperature setting signal comprises receiving an input from an input device on the control panel.
11. The method of any one of claims 8 to 10, further comprising presenting on the control panel an indicator of a temperature proximate to at least one heater.
12. The method of any one of claims 8 to 11, wherein the composite aircraft structure comprises:
a base comprising a plurality of resin impregnated plies; and a heating layer adjacent the base, wherein the heating layer comprises at least one heater.
a base comprising a plurality of resin impregnated plies; and a heating layer adjacent the base, wherein the heating layer comprises at least one heater.
13. The method of claim 12, wherein the composite aircraft structure further comprises:
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.
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.
14. A system comprising:
an aircraft on a ground, the aircraft including a composite aircraft structure comprising:
a base comprising a plurality of composite plies; and a 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 at least one 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; and a sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker.
an aircraft on a ground, the aircraft including a composite aircraft structure comprising:
a base comprising a plurality of composite plies; and a 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 at least one 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; and a sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker.
15. The system of claim 14, 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; and a second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies being adjacent the second adhesive layer.
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; and a second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies being adjacent the second adhesive layer.
16. The system of claim 14 or 15, wherein the plurality of composite plies are arranged in a plurality of different orientations.
17. The system of any one of claims 14 to 16, wherein the heating layer comprises a plurality of separately controllable resistive heating elements.
18. The system of any one of claims 14 to 17, further comprising a control circuit comprising:
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 resistive heating element; and a regulator module to:
receive at least one heat setting signal from the control panel, receive a temperature signal from at least one resistive heating element, and generate an output signal representing a difference between at least one heat setting signal and the temperature signal.
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 resistive heating element; and a regulator module to:
receive at least one heat setting signal from the control panel, receive a temperature signal from at least one resistive heating element, and generate an output signal representing a difference between at least one heat setting signal and the temperature signal.
19. The system of claim 18, wherein the output signal is fed back to at least one heater to regulate a current flow through the at least one resistive heating element.
20. The system of any one of claims 14 to 19, 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.
21. An aircraft, comprising:
a fuselage;
at least one composite aircraft structure, comprising:
a base comprising a plurality of composite plies, and a 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 at least one 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; and a sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker.
a fuselage;
at least one composite aircraft structure, comprising:
a base comprising a plurality of composite plies, and a 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 at least one 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; and a sensor included with the heating layer and configured to supply a signal indicating a measured temperature to the temperature-sensitive circuit breaker.
22. The aircraft of claim 21, 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; and a second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies being adjacent the second adhesive layer.
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; and a second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies being adjacent the second adhesive layer.
23. The aircraft of claim 21 or 22, wherein the plurality of composite plies are arranged in a plurality of different orientations.
24. The aircraft of any one of claims 21 to 23, wherein the heating layer comprises a plurality of separately controllable, sealed, resistive heating elements.
25. The aircraft of claim 24, further comprising a control circuit comprising:
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 resistive heating element; and a regulator module configured to:
receive at least one heat setting signal from the control panel, receive a temperature signal from at least one heating element, and generate an output signal representing a difference between at least one heat setting signal and the temperature signal.
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 resistive heating element; and a regulator module configured to:
receive at least one heat setting signal from the control panel, receive a temperature signal from at least one heating element, and generate an output signal representing a difference between at least one heat setting signal and the temperature signal.
26. The aircraft of claim 25, wherein the output signal is fed back to at least one heating element to regulate a current flow through the at least one resistive heating element.
27. 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 a 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;
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 at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater; and tripping 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.
receiving, in a power input panel, electrical power from a 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;
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 at least one heater embedded in the aircraft structure to regulate a current flow through the at least one heater; and tripping 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.
28. The method of claim 27, wherein receiving, in the power input panel, electrical power from the power source comprises receiving electrical power from a remote power source coupled to the power input panel.
29. The method of claim 27 or 28, wherein generating, in the 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.
30. The method of any one of claims 27 to 29, wherein generating, in the regulator module, the output signal representing the difference between at least one heat setting signal and the temperature signal comprises subtracting the output signal from the heat setting signal.
31. The method of any one of claims 27 to 30, further comprising presenting on the control panel, an indicator of a temperature proximate to at least one heater.
32. The method of any one of claims 27 to 31, wherein the composite aircraft structure comprises:
a base comprising a plurality of composite plies; and a heating layer adjacent the base, wherein the heating layer comprises at least one heater.
a base comprising a plurality of composite plies; and a heating layer adjacent the base, wherein the heating layer comprises at least one heater.
33. The method of claim 32, 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; and a second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies being adjacent the second adhesive layer.
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; and a second adhesive layer adjacent the heating layer and opposite the first adhesive layer, the plurality of composite plies being adjacent the second adhesive layer.
34. 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;
and a 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; and a 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; and a 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; and a 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.
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;
and a 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; and a 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; and a 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; and a 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.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/237,437 | 2011-09-20 | ||
| US13/237,437 US9221544B2 (en) | 2011-09-20 | 2011-09-20 | Integrated surface thermal management system |
| PCT/US2012/046096 WO2013043251A1 (en) | 2011-09-20 | 2012-07-10 | Integrated surface thermal management system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2845323A1 CA2845323A1 (en) | 2013-03-28 |
| CA2845323C true CA2845323C (en) | 2017-06-27 |
Family
ID=46583018
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2845323A Active CA2845323C (en) | 2011-09-20 | 2012-07-10 | Integrated surface thermal management system |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US9221544B2 (en) |
| EP (1) | EP2758308B1 (en) |
| JP (1) | JP6352187B2 (en) |
| CN (1) | CN103930346B (en) |
| CA (1) | CA2845323C (en) |
| WO (1) | WO2013043251A1 (en) |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2993241B1 (en) * | 2012-07-13 | 2017-03-24 | Mra Systems Inc | SYSTEM AND METHOD FOR AIRCRAFT PROTECTION AGAINST IRONING |
| US9193466B2 (en) | 2012-07-13 | 2015-11-24 | Mra Systems, Inc. | Aircraft ice protection system and method |
| US9253823B2 (en) * | 2013-02-10 | 2016-02-02 | The Boeing Company | Metal matrix composite used as a heating element |
| US9321536B2 (en) * | 2013-03-15 | 2016-04-26 | Unmanned Aerospace Technologies Ltd. | Methods and system for deicing a surface |
| WO2014143255A1 (en) * | 2013-03-15 | 2014-09-18 | United Technologies Corporation | De-icing by integral electric heat generation |
| US10167550B2 (en) | 2014-06-03 | 2019-01-01 | Aurora Flight Sciences Corporation | Multi-functional composite structures |
| US10368401B2 (en) * | 2014-06-03 | 2019-07-30 | Aurora Flight Sciences Corporation | Multi-functional composite structures |
| US9354621B2 (en) | 2014-06-16 | 2016-05-31 | General Electric Company | Systems and methods for control of an adaptive-cycle engine with power-thermal management system |
| US10285219B2 (en) | 2014-09-25 | 2019-05-07 | Aurora Flight Sciences Corporation | Electrical curing of composite structures |
| CN104331362B (en) * | 2014-10-17 | 2015-11-11 | 宝鸡文理学院 | A kind of software fault prediction method |
| US9919444B2 (en) * | 2015-07-10 | 2018-03-20 | Wichita State University | System for developing composite repair patches on aircraft or other composite structures |
| KR20240000625A (en) * | 2018-04-24 | 2024-01-02 | 카본 에어로스페이스 (파운데이션), 엘엘씨 | Composite aerostructure with integrated heating element |
| US11198513B1 (en) * | 2018-08-03 | 2021-12-14 | Astroseal Products Mfg. Corporation | Anti-icing/de-icing system and method |
| US11427335B2 (en) | 2018-11-13 | 2022-08-30 | Textron Innovations Inc. | Enclosure for contacts of aircraft wing heater blanket |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1483033A (en) * | 1976-02-11 | 1977-08-17 | Ford Motor Co | Vehicle window heating circuit |
| WO1995005308A1 (en) | 1993-08-13 | 1995-02-23 | Madsen Robert C | Infrared aircraft deicers positioned on a taxiway |
| US5746396A (en) | 1994-10-21 | 1998-05-05 | Baltab Holdings, Ltd. | Deicer |
| US6047926A (en) | 1996-06-28 | 2000-04-11 | Alliedsignal Inc. | Hybrid deicing system and method of operation |
| US6092765A (en) | 1997-06-09 | 2000-07-25 | White; Richard P. | Infrared deicing system for aircraft |
| US7588212B2 (en) * | 2003-07-08 | 2009-09-15 | Rohr Inc. | Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip |
| BRPI0512380A (en) | 2004-06-22 | 2008-03-11 | Trustees Of Darmouth College | pulse systems and methods for ice detachment |
| US7157663B1 (en) | 2005-10-12 | 2007-01-02 | The Boeing Company | Conducting-fiber deicing systems and methods |
| US7708227B2 (en) | 2006-01-06 | 2010-05-04 | Cox & Company, Inc. | Energy-efficient electro-thermal ice-protection system |
| US7923668B2 (en) | 2006-02-24 | 2011-04-12 | Rohr, Inc. | Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein |
| US7291815B2 (en) | 2006-02-24 | 2007-11-06 | Goodrich Corporation | Composite ice protection heater and method of producing same |
| WO2007107732A1 (en) | 2006-03-17 | 2007-09-27 | Ultra Electronics Limited | Ice protection system |
| FR2930234B1 (en) * | 2008-04-21 | 2010-07-30 | Aircelle Sa | DEFROSTING AND / OR ANTI-FRICTION SYSTEM FOR AIRCRAFT BOAT ATTACK. |
| CN201195594Y (en) * | 2008-04-30 | 2009-02-18 | 凌云科技集团有限责任公司 | Apparatus of electric heating exterior edge of ice-proof system of airplane |
| EP2340686B1 (en) * | 2008-10-14 | 2014-12-03 | Airbus Operations GmbH | Heating system with at least an electrothermal heating layer, a structural piece with such heating layer, an heating process and also a manufacturing process of intermediate piece or of a piece inside a heating apparatus |
| US20100123044A1 (en) | 2008-11-17 | 2010-05-20 | Botura Galdemir C | Aircraft Ice Protection System |
| US20100206990A1 (en) | 2009-02-13 | 2010-08-19 | The Trustees Of Dartmouth College | System And Method For Icemaker And Aircraft Wing With Combined Electromechanical And Electrothermal Pulse Deicing |
| AU2010245098B2 (en) | 2009-04-27 | 2014-11-13 | Applied Nanostructured Solutions, Llc. | CNT-based resistive heating for deicing composite structures |
| US20110006049A1 (en) * | 2009-07-09 | 2011-01-13 | Thompson Jr John | Roof heater |
-
2011
- 2011-09-20 US US13/237,437 patent/US9221544B2/en active Active
-
2012
- 2012-07-10 CN CN201280045925.7A patent/CN103930346B/en active Active
- 2012-07-10 CA CA2845323A patent/CA2845323C/en active Active
- 2012-07-10 WO PCT/US2012/046096 patent/WO2013043251A1/en active Application Filing
- 2012-07-10 EP EP12740435.8A patent/EP2758308B1/en active Active
- 2012-07-10 JP JP2014530665A patent/JP6352187B2/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CA2845323A1 (en) | 2013-03-28 |
| EP2758308A1 (en) | 2014-07-30 |
| JP2014531361A (en) | 2014-11-27 |
| WO2013043251A1 (en) | 2013-03-28 |
| CN103930346B (en) | 2017-02-08 |
| CN103930346A (en) | 2014-07-16 |
| US9221544B2 (en) | 2015-12-29 |
| US20130068747A1 (en) | 2013-03-21 |
| EP2758308B1 (en) | 2017-05-31 |
| JP6352187B2 (en) | 2018-07-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2845323C (en) | Integrated surface thermal management system | |
| JP6887576B1 (en) | Composite aircraft structure with integrated heating elements | |
| US9914522B2 (en) | Floor panel for an aircraft, and an aircraft comprising such a floor panel | |
| EP2428447B1 (en) | Ice detection system and method | |
| US7854548B2 (en) | Integrated total air temperature probe and electronics | |
| CA3034546A1 (en) | Icing control system | |
| US10822097B2 (en) | Ice formation detection and removal system for an aerial vehicle and method | |
| GB2509729A (en) | Ice detection on an aircraft | |
| WO2007107732A1 (en) | Ice protection system | |
| EP3704022A1 (en) | Ice protection system and controller | |
| US20130292511A1 (en) | Dielectric barrier discharge flight control system through modulated boundary layer transition | |
| US20220411079A1 (en) | Apparatus and method for detecting water or ice | |
| US20230202660A1 (en) | Ice protection system for an aircraft | |
| JP2012514289A (en) | Heating system comprising at least one electrothermal heating layer and a structural component having the heating layer, a heating method, and a method for producing a semi-finished or finished component having a heating mechanism | |
| US20180321134A1 (en) | Bondline Sensors |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request |
Effective date: 20140213 |