Highly flexible thermoelectric composite for sensing temperature in aircraft

Abstract

The invention relates to a highly flexible thermoelectric composite for sensing temperature in an aircraft. The present invention relates to apparatus, systems and methods for using at least one highly flexible thermoelectric device placed in contact with and / or adjacent to a surface of a heat dissipating aircraft component for the purpose of collecting and / or converting energy in the form of heat to thereby generate an electrical current for powering the aircraft component.

Description

[0001] Related Applications

[0002] This application claims priority to U.S. Provisional Application Serial No. 63 / 540,727, filed on September 27, 2023, the contents of which are incorporated by reference in their entirety. Technical Field

[0003] The present disclosure generally relates to the field of thermoelectric devices. Specifically, the present disclosure relates to the field of highly flexible thermoelectric devices. Background Art

[0004] Thermal sensors associated with various structures and components in an aircraft can alert aircraft personnel and aircraft operations centers to conditions associated with expected and / or unexpected temperature changes occurring on or near various aircraft structures and / or aircraft components. Such thermal sensors are typically powered and therefore require power to be transferred from the aircraft power supply to the thermal sensor through, for example, an electrical circuit. Typical power supplies are powered by electrical power that can be generated, for example, by an onboard generator, an auxiliary power unit, a dedicated battery, etc. In all cases, powering and operation of the electrical thermal sensor (equivalently referred to herein as a "temperature sensor") results in a net power consumption of one or both of generated electrical energy and / or stored electrical energy, which can be released from the battery and directed to the thermal sensor.

[0005] Unless explicitly stated otherwise, no statement herein is admitted to be prior art merely by virtue of its inclusion in the Technical Field and / or Background sections. Summary of the invention

[0006] The present invention relates to aircraft structures, including aircraft components, sub-assemblies, aircraft equipment (hereinafter referred to as "aircraft components"), which include at least one highly flexible thermoelectric composite device configured to maintain a temperature gradient and convert thermal energy into an electric charge or current, which is directed to power a temperature sensor. According to further aspects of the present invention, the highly flexible thermoelectric composite device itself can be used as a temperature sensor.

[0007] The present aspect relates to an aircraft component on an aircraft, the aircraft component including an aircraft component surface, the aircraft component surface being configured to dissipate heat during operation, the aircraft component surface further including at least one highly flexible thermoelectric composite device positioned adjacent to the aircraft component surface, the highly flexible thermoelectric composite device being configured to convert thermal energy into generated electrical energy.

[0008] In another aspect, at least one highly flexible thermoelectric composite device is placed in direct contact with a surface of an aircraft component.

[0009] In another aspect, at least one highly flexible thermoelectric composite device is configured to generate electrical energy in the presence of a thermal gradient.

[0010] In another aspect, an aircraft component surface is configured to dissipate heat during operation of the aircraft component.

[0011] In another aspect, an aircraft assembly includes at least one of an aircraft engine, an auxiliary power unit, an electrical compartment, a cargo compartment, and combinations thereof.

[0012] In another aspect, the aircraft component surface includes at least one of an aircraft engine surface, an auxiliary power unit surface, an electrical compartment surface, a cargo compartment surface, and combinations thereof.

[0013] Further aspects of the present invention relate to an aircraft including an aircraft component, the aircraft component including an aircraft component surface, the aircraft component surface further including at least one highly flexible thermoelectric composite device positioned adjacent to the aircraft component surface, the highly flexible thermoelectric composite device configured to convert thermal energy into electrical energy.

[0014] Another aspect of the present invention relates to a temperature sensor, which includes at least one highly flexible thermoelectric composite device, the at least one highly flexible thermoelectric composite device includes at least one wire connected to a circuit, the temperature sensor is placed adjacent to the surface of an aircraft component of the aircraft component, the at least one highly flexible thermoelectric device is configured to generate an electric charge in the presence of a thermal gradient, and the at least one highly flexible thermoelectric composite device is configured to transport the electric charge to power the temperature sensor.

[0015] In another aspect, the aircraft component structural surface is configured to dissipate heat during operation of the aircraft component, and the highly flexible thermoelectric composite device is configured to convert thermal energy into electrical energy.

[0016] In another aspect, at least one highly flexible thermoelectric composite device is placed in direct contact with a surface of an aircraft component.

[0017] In another aspect, at least one highly flexible thermoelectric composite device is configured to exclusively power a temperature sensor.

[0018] In another aspect, the highly flexible thermoelectric device is configured to provide auxiliary power to a temperature sensor.

[0019] In another aspect, the electrical energy generated by the highly flexible thermoelectric device is configured to be used exclusively to power a temperature sensor.

[0020] In a further aspect of the present invention, the temperature sensor and the highly flexible thermoelectric composite device are in communication with an electrical circuit.

[0021] In another aspect, at least one highly flexible thermoelectric composite device is in communication with an indicator configured to indicate generation of an electrical charge, the electrical charge being generated by the at least one highly flexible thermoelectric composite device.

[0022] In another aspect, a battery is in communication with the circuit, the battery comprising a chargeable battery configured to receive charge generated by the highly flexible thermoelectric composite device, and the battery is further configured to deliver the charge to the circuit.

[0023] In another aspect, the charge delivered from the battery to the circuit is configured as an auxiliary power source for the temperature sensor.

[0024] In another aspect, the charge delivered from the battery to the circuit is configured to be used exclusively to power the temperature sensor.

[0025] In a further aspect, the highly flexible thermoelectric device is a temperature sensor.

[0026] In another aspect, the battery is a rechargeable lithium-ion battery.

[0027] In a further aspect, the highly flexible thermoelectric composite device is configured to provide electrical energy specifically for powering aircraft components.

[0028] In another aspect, a highly flexible thermoelectric composite device is configured to provide auxiliary power to an aircraft component.

[0029] Further the present aspect relates to an aircraft component on an aircraft, the aircraft component comprising an aircraft component surface and at least one highly flexible thermoelectric composite device, the at least one highly flexible thermoelectric composite device comprising at least one wire connected to an electrical circuit, and wherein the at least one highly flexible thermoelectric composite device is placed in direct contact with the aircraft component surface.

[0030] Further aspects of the present invention relate to an aircraft comprising an aircraft component, the aircraft component comprising an aircraft component surface and at least one highly flexible thermoelectric composite device, the at least one highly flexible thermoelectric composite device comprising at least one wire in communication with an electrical circuit, and

[0031] Another aspect of the present invention relates to a temperature sensor for an aircraft component on an aircraft, the temperature sensor comprising at least one highly flexible thermoelectric composite device, the at least one highly flexible thermoelectric composite device comprising at least one wire connected to an electrical circuit, and wherein the at least one highly flexible thermoelectric composite device is placed in direct contact with an aircraft component surface of the aircraft component, and wherein the at least one highly flexible thermoelectric composite device is configured to generate an electric charge in the presence of a thermal gradient, and wherein the at least one highly flexible thermoelectric device is further configured to deliver the electric charge to power the temperature sensor.

[0032] In another aspect, at least one highly flexible thermoelectric composite device is in communication with an indicator configured to indicate generation of an electrical charge.

[0033] In another aspect, the circuit is in communication with a rechargeable battery.

[0034] Further, the present aspect relates to an aircraft, comprising a temperature sensor for an aircraft component on the aircraft, the temperature sensor comprising at least one highly flexible thermoelectric composite device, the highly flexible thermoelectric composite device comprising at least one wire connected to an electrical circuit, and wherein the at least one highly flexible thermoelectric composite device is placed in direct contact with an aircraft component surface of the aircraft component, and wherein the at least one highly flexible thermoelectric composite device is configured to generate an electric charge in the presence of a thermal gradient, wherein the at least one highly flexible thermoelectric device is further configured to deliver the electric charge to power the temperature sensor.

[0035] Another aspect of the present invention relates to a power source for an aircraft component in an aircraft, the power source comprising at least one flexible thermoelectric composite device positioned adjacent to an aircraft component surface of the aircraft component on the aircraft, at least one highly flexible thermoelectric composite device configured to maintain a temperature gradient while the aircraft is operating, at least one highly flexible thermoelectric composite device comprising at least one wire in communication with an electrical circuit, and at least one highly flexible thermoelectric composite device configured to convert thermal energy from the thermal gradient into electrical energy.

[0036] In another aspect, at least one flexible thermoelectric composite device is placed in direct contact with an aircraft component surface of an aircraft component on an aircraft.

[0037] In another aspect, the power supply is an auxiliary power supply.

[0038] In another aspect, the auxiliary power supply is configured to power a temperature sensor in communication with the circuit.

[0039] In another aspect, the power supply is configured to exclusively power a temperature sensor, the temperature sensor being in communication with the circuit.

[0040] In another aspect, the power source further includes a battery in communication with the circuit, the battery configured to receive charge from the circuit, and the battery further configured to direct the charge from the battery to the circuit.

[0041] In a further aspect, the circuit is an auxiliary circuit.

[0042] Another aspect of the present invention relates to an aircraft, the aircraft including a power source, the power source including at least one highly flexible thermoelectric composite device adjacent to a surface of an aircraft component on the aircraft, the at least one highly flexible thermoelectric composite device including at least one wire connected to an electrical circuit, the at least one highly flexible thermoelectric composite device configured to generate electrical energy when exposed to a temperature gradient, and the at least one highly flexible thermoelectric composite device configured to convert thermal energy from the thermal gradient into electrical energy.

[0043] The present invention relates to a method for sensing the temperature of an aircraft component surface of an aircraft component, the method comprising placing at least one highly flexible thermoelectric composite device adjacent to the aircraft component surface of the aircraft component, the highly flexible thermoelectric composite device comprising at least one wire in communication with an electrical circuit, the highly flexible thermoelectric composite device being configured to generate electrical energy when exposed to a thermal gradient. The method further comprises providing a thermal gradient on the highly flexible thermoelectric composite device, the highly flexible thermoelectric composite device generating a certain amount of electrical energy, and directing the generated electrical energy from the highly flexible thermoelectric composite device to the electrical circuit.

[0044] In another aspect, at least one highly flexible thermoelectric composite device is in direct contact with an aircraft component surface of an aircraft component on an aircraft.

[0045] In another aspect, an aircraft component surface is configured to maintain a temperature variation between a non-operational state and an operational state.

[0046] In another aspect, an aircraft structural surface is configured to maintain a temperature variation between an aircraft non-operational state and an aircraft operational state, the temperature variation ranging from about 5°C to about 60°C.

[0047] In another aspect, the method further includes determining the presence of an amount of electrical energy delivered by the highly flexible thermoelectric composite device to the circuit.

[0048] In another aspect, the highly flexible thermoelectric composite device is configured to withstand a service flex life of 15,000 cycles at a strain of 30% and fully retain functionality after the strain text when exposed to a temperature of about 40°C.

[0049] In another aspect, the method further includes determining and / or detecting a temperature change in at least one of an aircraft component surface of an aircraft component of the aircraft and an area of ​​the aircraft component surface located proximate to the aircraft component of the aircraft, and wherein the determined and / or detected temperature change corresponds to the presence of a certain amount of electrical energy delivered to the circuit by the highly flexible thermoelectric composite device.

[0050] In another aspect, the method further includes detecting electrical energy generated by the highly flexible thermoelectric composite device and delivered to the circuit, the detected electrical energy evidencing a temperature change in at least one of the aircraft component and an area proximate to the aircraft structure.

[0051] In another aspect, the method further includes powering an aircraft component with electrical energy directed from the highly flexible thermoelectric composite device to the circuit, the aircraft component being in communication with the circuit.

[0052] In another aspect, the method further includes charging a battery with at least a portion of the electrical energy directed from the highly flexible thermoelectric composite device, the battery being in communication with the circuit.

[0053] In another aspect, the method further includes positioning a plurality of highly flexible thermoelectric composite devices adjacent to the aircraft component surface.

[0054] In another aspect, the method further includes placing a plurality of highly flexible thermoelectric composite devices in direct contact with the aircraft component surface.

[0055] In another aspect, the aircraft component is at least one of an aircraft engine, an aircraft auxiliary power unit, an electrical compartment, a cargo compartment, and combinations thereof.

[0056] In another aspect, the method further includes powering an aircraft component with electrical energy directed from the battery, the aircraft component being in communication with the electrical circuit.

[0057] In another aspect, the aircraft component is a temperature sensor.

[0058] In a further aspect, the highly flexible thermoelectric composite device includes a temperature sensor.

[0059] In another aspect, the highly flexible thermoelectric composite device is a temperature sensor.

[0060] On the other hand, highly flexible thermoelectric composite devices are specifically designed to provide electrical energy to power aircraft components.

[0061] In another aspect, a highly flexible thermoelectric composite device provides auxiliary power to an aircraft component.

[0062] In another aspect, the method further includes powering the aircraft component with electrical energy directed from the battery to the aircraft component.

[0063] In another aspect, the method further includes powering an aircraft component with electrical energy directed from the battery, the aircraft component being in communication with the electrical circuit.

[0064] In another aspect, the battery comprises a rechargeable battery.

[0065] In another aspect, the battery comprises a rechargeable lithium-ion battery.

[0066] The features, functions, and advantages that have been discussed may be achieved independently in various aspects or may be combined in yet other aspects, further details of which may be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0067] Having described various variations of the present disclosure in general terms, reference will now be made to the accompanying drawings, which are not necessarily drawn to scale, and in which:

[0068] Figure 1 is an illustration of a vehicle in the form of an aircraft according to the present invention;

[0069] Figure 2 is an illustration of an aircraft component in the form of an aircraft engine according to the present invention, comprising a highly flexible thermoplastic composite device located in direct contact with an engine surface;

[0070] Figure 3 is an illustration of an aircraft assembly in the form of an auxiliary power unit according to the present invention, comprising a highly flexible thermoplastic composite device located in direct contact with a surface of the auxiliary power unit;

[0071] Figure 4 is an illustration of an aircraft component in the form of an avionics bay according to the present invention, comprising a highly flexible thermoplastic composite material device located in direct contact with a surface of the avionics bay;

[0072] Figure 5A is a circuit diagram including a highly flexible thermoplastic composite device according to the present aspect;

[0073] Figure 5B is a circuit diagram including a highly flexible thermoplastic composite device according to the present aspect;

[0074] Fig. 6A is a block diagram illustrating an aircraft assembly including a highly flexible thermoelectric composite device according to the present invention;

[0075] Figure 6B is a block diagram illustrating an aircraft assembly including a highly flexible thermoelectric composite device in communication with circuits and aircraft components according to the present invention;

[0076] Figure 6C is a block diagram of an aircraft component including a highly flexible thermoelectric composite device configured to power an aircraft component according to the present invention;

[0077] Figure 7 is a view of a manufacturing process for a highly flexible thermoelectric composite material device according to the present invention;

[0078] Figure 8is an exploded view of a highly flexible thermoelectric composite device according to the present invention;

[0079] Fig. 9 is a perspective view of a highly flexible thermoelectric composite device according to the present invention;

[0080] Fig.10 is a perspective view of a highly flexible thermoelectric composite device according to the present invention;

[0081] Fig.11 is a perspective view of a highly flexible thermoelectric composite device according to the present invention in a highly deformed state;

[0082] Fig.12 is a perspective view of a highly flexible thermoelectric composite device according to the present invention in a highly deformed state;

[0083] Fig.13 is a view of a plurality of highly flexible thermoelectric composite devices placed in series according to the present invention;

[0084] Fig.14 is a schematic diagram of a plurality of highly flexible thermoplastic composite devices placed in series according to the present invention;

[0085] Fig.15 is a schematic diagram of a plurality of highly flexible thermoplastic composite devices placed in series according to the present invention;

[0086] Fig.16 is a flow chart outlining a method according to the present aspect;

[0087] Fig.17 is a flow chart outlining a method according to the present aspect;

[0088] Fig.18 is a flow chart outlining a method according to the present aspect;

[0089] Fig.19 is a flow chart outlining a method according to the present aspect;

[0090] Fig. 20 is a flow chart outlining a method according to the present aspect; and

[0091] Fig.21 is a flow chart outlining a method according to the present aspect. DETAILED DESCRIPTION

[0092] Aircraft structures on an aircraft (e.g., structures including aircraft components, subassemblies, aircraft equipment, referred to herein equivalently as "aircraft components") can generate significant amounts of heat and experience significant temperature gradients during operation. Additionally, aircraft component surfaces can include aircraft component surfaces that can sustain elevated temperatures and dissipate heat from the aircraft component surfaces.

[0093] For example, aircraft engines generate a large amount of heat during operation, which heat can be partially used as exhaust air, which can help heat the aircraft cabin, and / or other heating functions. In addition, other aircraft components that generate heat can include, for example, auxiliary power units, electronic equipment bays / panels, etc. The present aspect is related to collecting, capturing, removing waste heat from aircraft component surfaces and converting such waste heat into electrical energy by positioning highly flexible thermoplastic composite devices (herein equivalently referred to as "TE devices") to aircraft structure surfaces and / or reusing at least a portion of the thermal energy emitted from the heat-generating aircraft component surfaces during operation.

[0094] The present apparatus, systems and methods involve the use of at least one highly flexible thermoelectric device placed in contact with and / or adjacent to a heat generating aircraft component surface for the purpose of harvesting and / or converting energy in the form of heat to generate electrical current for powering aircraft components.

[0095] Further aspects of the present apparatus, systems and methods involve the use of at least one highly flexible thermoelectric device as a power source positioned in contact with and / or adjacent to a heat generating aircraft component surface for the purpose of collecting and / or converting energy in the form of heat to generate an electric current that is directed to an aircraft component via an electrical circuit that is in communication with the aircraft component, and the electrical circuit is further in communication with the highly flexible thermoelectric composite device.

[0096] Further aspects of the present apparatus, systems and methods involve the use of at least one highly flexible thermoelectric device that is placed in contact with and / or adjacent to a heat-generating aircraft component surface and collects and / or converts energy in the form of heat to generate an electric current that is directed to a circuit including a rechargeable battery that is further connected along the circuit to an aircraft component, which may be an electrically powered aircraft component.

[0097] According to a further aspect of the present invention, the charge generated by the highly flexible thermoelectric composite device is directed to an electrical circuit, thereby, for example, charging a battery in communication with the electrical circuit, and powering an aircraft component in communication with the electrical circuit, the aircraft component including, for example, a temperature sensor. In a further aspect, the highly flexible thermoelectric composite device itself is a temperature sensor, includes a temperature sensor, and / or acts as a temperature sensor by indicating a temperature change at or near a surface of an aircraft component, because it indicates and / or otherwise detects that electricity is produced and / or generated and delivered to a circuit or indicator in communication with the electrical circuit or TE device.

[0098] Figure 1 A vehicle is shown in the form of an aircraft 10 having an aircraft component in the form of an aircraft engine 12 . Figure 2FIG. 1 is a partially exposed view of an aircraft component 14 in the form of an aircraft engine 12 having an engine surface 12a emitting heat from an aircraft component surface 14a during operation. Figure 2 As shown, a highly flexible thermoelectric composite device (herein equivalently referred to as a "TE device") 18 is placed in contact with and adjacent to the aircraft component surface 14a of the aircraft component 14, and is further in direct contact with the aircraft component surface 14a of the aircraft component 14, and dissipates heat during operation. Figure 2 As further shown in , the aircraft component surface may be or may otherwise include a non-planar surface having a regular or irregular geometry, and the surface may present, for example, a contoured (eg, non-planar) surface on which the TE device 18 may be placed and / or otherwise incorporated.

[0099] Figure 3 1 is a partially exposed view of an auxiliary power unit 13 as another example of an aircraft component 14 having an aircraft component surface 14a in the form of an auxiliary power surface 13a that can dissipate heat during operation and on which a TE device 18 can be placed, for example, in direct contact. In another example, Figure 4 An electrical equipment bay 15 having an electrical equipment bay surface 16 is shown as another example of an aircraft component 14 having an aircraft structure surface 14a upon which a TE device 18 may be placed, such as in direct contact therewith.

[0100] According to the present aspect, an aircraft component (of an aircraft) includes an aircraft component surface on which is placed at least one TE device in direct contact with the aircraft component surface. The aircraft component surface may be planar, and further, the aircraft structure surface may be contoured (e.g., non-planar), and the highly flexible TE device is configured to be flexible to a selectable degree to conform to the contour of the aircraft component surface in shape and to maintain the TE device in direct contact with the contour of the aircraft component surface.

[0101] In one example, the TE device includes wires connected to an electrical circuit. When the aircraft is in operation, the surface of the aircraft component dissipates heat and experiences thermal changes. As the temperature of the surface of the aircraft component rises, the TE device in direct contact with the surface of the aircraft component will experience a thermal gradient on its structure and convert a certain amount of "waste heat" from the surface of the aircraft component into electric charge. When the TE device is connected to the circuit, the TE device transfers the generated charge to the circuit.

[0102] According to this aspect, the circuit in communication with the TE device may be an existing circuit that is, for example, part of a typical aircraft electrical architecture. In a further example, the circuit in communication with the TE device may be an additional circuit dedicated to loading and directing the current generated by the TE device. That is, according to this aspect, in addition to being an auxiliary power source for the TE device, the circuit may also include or otherwise be in communication with a conventional power source. In this example, the TE device may be an auxiliary power source in the circuit, and in the absence of a conventional power source (for example, when the conventional power source on the aircraft is interrupted, etc.), the TE device continues to supply electrical energy to the circuit. In other examples, the circuit may be an additional circuit dedicated to the TE device, and the TE device serves as an exclusive power source for the dedicated circuit.

[0103] According to this aspect, an aircraft component (which may be an electrically powered aircraft component) may be in communication with a TE device via a circuit and powered by the TE device. For example, an electrically powered aircraft component may include a temperature sensor powered by the TE device via a circuit. In the event of a power outage in the aircraft, the power supplied by the TE device to the circuit may continue to power the temperature sensor, for example, the temperature sensor function remains uninterrupted during such an aircraft power outage. In this example, the TE device provides a continuous source of power, at least when the TE device is placed on a heat-generating aircraft component surface, so that conventional power generated on the aircraft or delivered by existing aircraft batteries does not need to be diverted (e.g., in the form of a "backup power supply" or the like) to operate the aircraft component that is in communication with the TE device via the circuit.

[0104] In addition, according to further aspects of the present invention, a rechargeable battery (e.g., a rechargeable lithium-ion battery, etc.) can be connected to the present electrical circuit, and the TE device delivers current to charge the battery and to power the TE device that powers the electrical components. In further examples of the present invention, when the aircraft is not operating (e.g., when the surface of the aircraft component is not experiencing a thermal gradient to "operate" the TE device), the electrical energy stored in the battery can be delivered to power the electrically powered aircraft components. In further examples of the present invention, the charged battery can be connected to further dedicated circuits to operate additional aircraft electrical drive components, etc.

[0105] The circuit in communication with the present TE device may further be in communication with an indicator that is powered by the circuit and indicates power generated by the TE device, or indicates that electrical energy is being delivered from a battery, or has been supplied to a battery. Figure 5A and Figure 5B is a circuit diagram illustrating this aspect.

[0106] Figure 5A shows that, for example, it is possible to exist and be located Figure 1 Electrical circuitry 30 within the electrical architecture of an aircraft of the type shown. Figure 5A As shown, the electrical circuit 30 includes at least one highly flexible thermoelectric composite device ("TE device") 18 in communication with an indicator 32 and a booster 36 along the circuit 30. When the TE device 18 operates, converts heat into electricity and generates current, the TE device 18 experiences a thermal gradient; it is an indication that a temperature change / increase is occurring across the area, and indicates that a temperature change / increase is occurring in an area on or near the surface of the aircraft component in contact with the TE device. The booster 36 in the circuit 30 can further enhance the voltage generated by the TE device in the circuit 30.

[0107] Figure 5B An optional circuit 40 according to the present aspect is shown, in which the TE device 18 is connected to the circuit 40, and the circuit 40 further includes a booster 36, which can be placed in the circuit 40 between, for example, the TE device 18 and a rechargeable battery 42 (for example, it can be a rechargeable lithium-ion battery, etc.), and the circuit 40 is further connected to an electrical component 34, which can be, for example, a temperature sensor.

[0108] In further aspects of the present invention, the TE device can be placed in contact with or near an aircraft component surface that is not typically configured for heat dissipation and in an aircraft location that is conducive to rapid detection of undesirable temperature changes (e.g., rapid detection of temperature increases, such as real-time detection, where real-time is defined herein as a duration range from about 0.5 seconds to about 10 seconds). At these aircraft component surface locations that are not expected to experience temperature increases, when the TE device experiences even a minimal thermal gradient from about 3°C ​​to about 5°C, the TE device will begin to convert heat to generate current, which can be directed to, for example, a circuit including an electrically driven indicator. The power generated by the TE device can be detected and indicated by an indicator, for example, as an alert that a particular aircraft component surface or an area near an aircraft component surface is experiencing a temperature increase that may be undesirable. In this mode, the TE device itself can act as a temperature sensor.

[0109] Fig. 6A , 6B and 6C are diagrams outlining further aspects of the present invention. Fig. 6A is a block diagram illustrating an aircraft component having an aircraft component surface that includes or otherwise incorporates the present TE device 18 . Figure 6B Shown Fig. 6A The aircraft assembly 60 (including the TE device 18), the TE device 18 is connected to the circuit 30, and the aircraft assembly 60 (including the TE device 18) is shown as described herein and as shown in FIG. Figure 5A Components shown in connection with circuit 30. When battery 42 is placed in connection with the circuit, the circuit may be designated as circuit 40, which illustrates components as described herein and as Figure 5B Components shown are in communication with circuit 40.

[0110] like Figure 6C As shown, this further aspect relates to an electric drive component 34, which may be, for example, a temperature sensor or the like. Figure 6C As shown, electrically powered aircraft components may be in direct contact with the present TE device 18 , for example, to directly power the component 34 .

[0111] As mentioned herein, the TE device can be a dedicated power source for an aircraft component, and the TE device can also be configured in a circuit to serve as an auxiliary power source, wherein the TE device is configured in either mode to direct the charge generated by the TE device to a (re)chargeable battery that can be adjusted to deliver electrical energy from the battery as needed.

[0112] The present TE device can be manufactured as an extremely thin device having an overall thickness ranging from about 2 mm to about 2.4 mm, facilitating placement of the present TE device in various locations on an aircraft and in contact with aircraft structures on an aircraft that was previously not possible (e.g., inaccessible locations, etc.), and / or placement in various locations between components that exhibit significant spatial constraints and / or tolerances between structures, where the available space (e.g., "gap") between structures is only a little or only a few millimeters wide. According to this aspect, the width of the present TE device (having a width ranging from about 10 mm for the TE sample to about 32 mm for the TE device), for example, allows such present TE device to occupy previously unoccupied space between closely positioned aircraft components and component surfaces.

[0113] According to the present apparatus, system and method, a "self-sustaining" power generation device is disclosed to reduce weight and energy consumption, and to facilitate autonomous sensing, thereby improving safety and reliability. The highly flexible thermoelectric composite device (herein equivalently referred to as a "TE device") of the present disclosure is very suitable for generating electricity from the hot surfaces of aircraft components, and for powering temperature sensors of aircraft components, because during aircraft operation, energy conversion / power generation will continue to occur due to the heat flux provided by the hot surfaces of aircraft components, and the heat flux generated to the area close to the surface of such aircraft components.

[0114] That is, according to the present aspect, heat can be collected from, for example, an engine casing or other heat-generating aircraft component surfaces (for example, during aircraft operation) by the TE devices of the present disclosure, which can, for example, power microelectromechanical system (MEMS) sensors or monitor changes in temperature gradients while withstanding structural deformations caused by repeated mechanical loads and / or repeated thermal expansion.

[0115] The present power generation / energy collection application is achieved by the highly flexible TE device of the present disclosure, which provides a conformable thermal contact between the highly flexible TE device and the heat source. The present highly flexible TE device provides a repeatable and reliable scalable TE device that avoids the limitations of typical semiconductors welded to non-flexible electrodes, and instead provides a TE device with high efficiency and is not prone to mechanical and electrical failure. The present highly flexible thermoelectric composite device includes soft multifunctional composite materials, the synthesis of which can provide enhanced thermal transfer and have excellent conformability in the contact area between the device and the heat source. The present TE device can generate record high power; at ΔT equal to 60°C, it produces an open circuit voltage of 392mV and approximately 650μW / cm -2 The power density is 2.3W while being able to stretch to more than 30% tensile strain for at least about 15,000 load cycles.

[0116] The present aspect contemplates incorporating a highly flexible thermoelectric (TE) composite device of the present disclosure into an aircraft environment, which itself acts as a thermal sensor. In an optional aspect of the present aspect, the highly flexible TE composite device is placed in a circuit connected thereto and configured to power the thermal sensor in the event of a power outage on the aircraft. The "high flexibility" of the present highly flexible TE composite device is defined as the ability of the TE composite device to maintain power generation capabilities and structural integrity (e.g., by converting thermal gradients into electrical energy) while being able to withstand structural deformation in the form of stretching the area of ​​the TE composite device by 30% (e.g., 30% strain) within 15,000 cycles while achieving a slight change in resistance magnitude. The property of the present TE composite device to withstand repeated structural deformation without affecting performance is referred to herein as the "stretchability" of the present highly flexible TE composite device; "stretchability" includes deformations such as stretching, twisting, and bending.

[0117] The present TE composite device may include a printed liquid metal that can form a "self-healing" composite material that can withstand, for example, a puncture, but still maintain the ability to effectively convert thermal gradients into electrical energy. That is, the present TE device may include at least one layer that, if damaged, such as in the form of a puncture, the present TE device observes fluid-like properties that promote "self-healing" of the at least one layer, allowing electrical conductivity to continue to exist in the TE device and allowing the power generation function of the TE device to continue to effectively convert thermal gradients into electricity.

[0118] The present highly flexible TE composite device comprises an elastomer-based substrate material, which further comprises a conductive material, which not only has high flexibility, but also significantly improves the performance and durability of the TE composite device by maintaining a high level of thermal gradient to electrical energy performance during a selected life of the TE composite device, thereby enabling the TE composite device to surpass the known structural deformation tests described herein.

[0119] The present TE composite device overcomes previous problems with the use of elastomers that exhibit undesirably low thermal conductivity, which previously resulted in inefficient conduction across thermal gradients. The present TE composite device overcomes previously unacceptable TE device architectures by incorporating new functional filler materials into the TE composite device structure. Such functional filler materials include liquid metal alloys of gallium (e.g., eutectic gallium indium (EGaIn)) for forming flowable electrical interconnects within the TE composite device.

[0120] According to this aspect, the selected liquid metal incorporated into the TE composite device structure includes high thermal conductivity (20-30 Wm - 1 K -1 ) to enhance selected thermal management. According to this aspect, liquid metal droplets are provided as a dispersion in an elastomeric composite to provide selected thermal conductivity and electrical insulation, in addition to providing selected physical properties, enabling the present TE composite device to be used for the first time in selected applications and selected locations for selected applications that were not previously possible.

[0121] According to the present invention, the liquid metal elastomer composite can be used as both a thermal interface material and an electrical interconnect layer, and their surface can be selectively patterned to create conductive traces. In some examples, the improved TE composite device can produce a peak open circuit voltage of 440mV and a power of 550μW cm at a temperature gradient of about 60°C. -2 power density.

[0122] According to this aspect, in some examples, 3D printing technology is incorporated to manufacture the present TE composite device, and the printed TE device includes multiple layers, in one example, including two thermal interface elastomer layers separated by an insulating layer, which insulating layer can, for example, encapsulate bismuth telluride (Bi 2 Te 3 ) Thermoelectric semiconductor. According to this example, a printed liquid metal elastomer composite with high thermal conductivity is used as a thermal interface material, an insulating layer is printed with hollow microspheres embedded in an elastomer to reduce density and thermal bypass around the TE semiconductor, and the sprayed liquid metal is used as a stretchable electrical interconnect layer between the semiconductors.

[0123] According to the present aspect, the highly flexible TE composite device exhibits significantly high steady-state voltage, and the high heat sink performance achievable is believed to be due to the increased surface area resulting in enhanced heat dissipation on the side not directly connected to the aircraft component surface; ie, the "cold side".

[0124] Example 1 demonstrates an exemplary method for fabricating the present TE composite device.

[0125] Example 1

[0126] like Figure 7 As shown, the additive manufacturing printing step is performed on the TE particle array. The inorganic p / n-type thermoelectric semiconductors are arranged in pairs, for example diagonally in the mold, and assembled in an alternating order to form a complete circuit after printing the electrical interconnects. 2 Te 3 ) has low lattice thermal conductivity and high electrical conductivity at room temperature and is therefore selected as a TE material. 2 Te 3 After the particles are arranged, an insulating layer is printed to fill the gaps between the particles. The ink selected for the insulating layer (e.g., the middle layer) contains uniformly dispersed hollow thermoplastic microspheres (e.g., Nouryon Chemicals, Chicago, IL). The embedded microspheres reduce the thermal density and the hollow microsphere elastomer composite (HMEC) with low thermal conductivity helps transfer most of the heat through the thermoelectric semiconductor to the cold side of the thermoelectric device. The increased heat flux thus contributes to higher power generation of the TE composite device.

[0127] After the insulating layer is cured, liquid metal (eutectic indium gallium) is sprayed on the TE particles using an air brush to form interconnections between the P-type and N-type TE particles. An electrically insulating liquid metal-elastomer composite (LMEC) with high thermal conductivity is printed on it as a stretchable thermal interface layer. The liquid metal inclusions embedded in this layer are very small (less than 8μm in diameter) to ensure electrical insulation, eliminate LM leakage and improve the durability of the device. The same steps are then applied to the other side to complete the fabrication of this highly flexible, highly deformable and stretchable TE composite device.

[0128] This representative TE composite device includes 120 TE particles with a final size of 51.5 x 32 x 2.2 mm 3 , the calculated fill factor is 14.27%; indicating the area fraction filled by the TE material. The highly flexible TE composite device has a selected flexibility, can be directly in contact with a contoured surface, has a fill factor of about 14%, has high energy harvesting performance and structural integrity, and does not sacrifice the desired and selected stretchability. In further examples, even if a certain degree of stretchability is sacrificed, the energy harvesting capability can be improved.

[0129] Functional elastomer composites can be formulated to print components of TE devices, for example, including: 1) 50% volume fraction of hollow microsphere elastomer composite (incorporated into the TE device as a thermal insulation layer between the hot and cold sides of the final TE composite device); 2) 50% volume fraction of liquid metal elastomer composite with inclusions less than 5μm. Ecoflex00-30 is used as the matrix phase, while fillers and processing parameters are adjusted to make two composites in order to tailor selected properties and achieve the desired uniformity within the printed layer (e.g., avoiding dispersion sedimentation, etc.).

[0130] According to this aspect, the high flexibility of the highly flexible TE composite device allows the present TE device to be used for energy harvesting in areas and locations on aircraft structures, such as contoured (e.g., non-planar) aircraft structural surfaces located in areas that were previously difficult to access and / or difficult to install, such as high-efficiency thermoelectric devices that do not have high flexibility and strain resistance and maintain performance capabilities over a large number of "stretch cycles." As described herein, when the present highly flexible TE composite device continues to survive and complete 15,000 cycles at a maximum strain of 30% as the present device does, and remains fully functional without suffering obvious electrical or mechanical failure, the device is considered to have a suitable lifespan and a period of use. Tensile sample V of the present highly flexible TE composite device before (32 mV before test) and after (approximately 32 mV after test) testing of 15,000 cycles at 30% strain (mechanical load) at ΔT = 40°C OC Electrical stability was demonstrated; the TE composite device was further shown to be fully intact after 15,000 load cycles.

[0131] Furthermore, regarding the structural integrity of the stretchable and highly flexible TE composite devices, the printed TE devices remained functional over time, with the internal resistance and open-circuit voltage measured three months after fabrication showing no change compared to the initial measurements.

[0132] Examples of this TE device include Figure 7 , 8 , 9, 10, 11 and 12. Figure 7 The layer-by-layer manufacturing / fabrication process 70 of the present TE device 18 is shown. In one example, Figure 7 As shown, in step "A" of process 70, TE particles are arranged and a hollow microsphere elastomer composite (HMEC) is printed as a thermal insulation layer 70a. In step "B", a liquid metal interconnect 70b is formed on the layer by screen printing. In step "C", a liquid metal elastomer composite (LMEC) thermal interface layer 70c is printed. Figure 8is an exploded view of a TE device stack 80 of the TE device 18 , illustrating the stacking direction of the molded / printed layers 70 a , 70 b , 70 c of the present TE device 18 .

[0133] Fig. 9 and Fig.10 A TE device 18 is shown that includes an electrical wire 20 that may be positioned and otherwise formed into the TE device 18 and has non-limiting dimensions selected based on end-use constraints, the electrical wire 20 being configured to contact an electrical circuit (not shown). Fig. 9 and Fig.10 ), the purpose of which is to direct the power generated by the TE device 18 to such a circuit. Fig. 9 and Fig.10 Further illustrated (although not necessarily drawn to scale) are various dimensions of TE devices made and used in accordance with the present invention; Fig. 9 The TE device 18 shown in FIG. 1 has a significantly greater length than width (e.g., a length:width ratio greater than about 5:1, and as shown, about 7:1). Fig.10 As shown, Fig.10 The TE device 18 shown in FIG. 1 is presented as having a length:width ratio of less than about 2:1, and for non-limiting illustrative purposes only, is presented as about 1.5:1.

[0134] According to this aspect, and as described herein, when such a device, such as the present device, survives and completes 15,000 cycles at a maximum strain of 30%, and remains fully functional without suffering significant electrical or mechanical failure, the present highly flexible TE composite device is considered to have a suitable lifespan and usable lifespan. Fig.11 and Fig.12 As shown, the highly flexible thermoelectric composite device 18 incorporating the wire 20 is configured to be used in a case where the following Fig.11 and Fig.12 The ability to deform significantly of the type shown while maintaining its power generation capability and functionality makes the present TE device very useful and capable of being incorporated into and onto complex aircraft component surfaces, which may include curved surfaces, surfaces with irregular and / or complex geometries, and the like.

[0135] Fig.13 , 14 15 depicts a TE device array, which includes a plurality of TE devices 18 connected in series via wires 20. Fig.13 As shown, the TE devices 18 are configured to be connected in series and are interconnected with each other through electrical wires 20 to form a TE device array 18a. Fig.14It is shown that the TE devices 18 connected in series to form the TE device array 18a are deployed at a position facing the aircraft component surface 14a of the aircraft structure 14, which surface may be a heat-generating aircraft component / aircraft component surface. When the aircraft component 14 dissipates heat, a thermal gradient is formed on the TE devices 18, so that the TE devices 18 constituting the TE device array 18a convert the heat energy emitted from the aircraft component surface structure 14a into electrical energy, and the TE device array 18a generates more electricity than a single TE device 18 generates.

[0136] According to the present aspect, the flexibility achieved within the TE device is achieved at least in part by the composite components within the composite layer exhibiting fluid-like behavior, allowing such TE devices to withstand a certain degree of damage (e.g., puncture), which can be "self-healed" as the components within the composite layer rearrange to reform and maintain the ability to conduct electricity. In addition, connecting the TE devices in series can further ensure that if one TE device is damaged, the entire TE device array can continue to convert heat into electricity and maintain uninterrupted delivery of the manufactured charge from the TE device to, for example, a circuit. Fig.15 As shown, the TE device array 18a includes a plurality of TE devices 18 placed in series, and the "shadow" TE device in the middle is damaged to a certain extent, but the TE device array 18a can still operate normally.

[0137] Fig.16 , 17 , 18, 19, 20 and 21 are flow charts outlining methods according to the present invention. Fig.16 A method 100 for sensing a temperature of an aircraft structure of an aircraft is summarized, the method 100 comprising placing at least one highly flexible thermoelectric composite device 102 in direct contact with an aircraft component surface of an aircraft component, the highly flexible thermoelectric composite device comprising at least one wire in communication with an electrical circuit, the highly flexible thermoelectric composite device being configured to generate electrical energy when exposed to a thermal gradient. The method further comprises providing 104 a thermal gradient across the highly flexible thermoelectric composite device, generating 106 an amount of electrical energy, and directing 108 the generated electrical energy from the highly flexible thermoelectric composite device to the electrical circuit.

[0138] On the other hand, Fig.17 As shown, method 200 includes Fig.16 The method 100 steps shown further include determining 202 a temperature change of at least one of a surface of the aircraft component and a region located proximate to the surface of the aircraft component by detecting an amount of current generated by the TE device, wherein the generation of the current corresponds to a detected increase in temperature of at least one of the surface of the aircraft component and the region located proximate to the surface of the aircraft component.

[0139] In another aspect, the method further includes detecting electrical energy generated by the highly flexible thermoelectric composite device and delivered to the circuit, the detected electrical energy evidencing a temperature change of at least one of a surface of the aircraft component and a region located proximate to the surface of the aircraft component.

[0140] Fig.18 A method 300 according to the present aspect is summarized, the method 300 includes the steps summarized in the method 100 and further includes powering 302 an aircraft component with electrical energy directed from the highly flexible thermoelectric composite device to the circuit, the aircraft component being in communication with the circuit.

[0141] Fig.19 A method 400 according to the present aspect is summarized, the method 400 includes the steps summarized in method 100, and further includes charging a battery 402 with at least a portion of the electrical energy directed from the highly flexible thermoelectric composite device, the battery being in communication with the circuit.

[0142] Fig. 20 A method 500 according to the present aspect is summarized and includes the steps outlined in method 100 and further includes placing 502 a plurality of highly flexible thermoelectric composite devices in direct contact with a surface of an aircraft component.

[0143] Fig.21 A method 600 according to the present aspect is summarized, the method 600 includes the steps summarized in the method 100 and further includes powering an aircraft component 602 with power from a battery, the aircraft component being in communication with the circuit. According to the present aspect, the aircraft component is a temperature sensor.

[0144] Fig.16 , 17 , 18, 19, 20 and 21 may be understood to incorporate the TE device disclosed herein for harvesting energy from the surface of an aircraft component, the harvested energy being used to power the aircraft component, as disclosed herein and in accordance with the present aspect, and as in at least Figure 1 , 2 , 3, 4, 5A, 5B, 6A, 6B, 6C, 7, 8, 9, 10, 11, 12, 13, 14 and 15.

[0145] Furthermore, the present disclosure includes embodiments according to the following clauses:

[0146] 1. An aircraft assembly (14) on an aircraft, the aircraft assembly comprising:

[0147] Aircraft component surface (14a);

[0148] At least one highly flexible thermoelectric composite device (18), the at least one highly flexible thermoelectric composite device comprising at least one wire (20) in communication with an electrical circuit (30); and

[0149] Wherein the at least one highly flexible thermoelectric composite device is positioned adjacent to the aircraft component surface.

[0150] 2. The aircraft component of clause 1, wherein the at least one highly flexible thermoelectric composite device is placed in direct contact with a surface of the aircraft component.

[0151] 3. The aircraft assembly of clause 1, wherein the at least one highly flexible thermoelectric composite device is configured to generate electrical energy in the presence of a thermal gradient.

[0152] 4. The aircraft component of clause 1, wherein the aircraft component surface is configured to dissipate heat during operation.

[0153] 5. The aircraft component of clause 1, wherein the aircraft component surface comprises at least one of an aircraft engine surface, an auxiliary power unit surface, an electrical compartment surface, a cargo compartment surface, and combinations thereof.

[0154] 6. An aircraft (10) comprising an aircraft assembly as claimed in clause 1.

[0155] 7. A temperature sensor (34) for an aircraft component (60), the temperature sensor comprising:

[0156] at least one highly flexible thermoelectric composite device comprising at least one wire, the at least one wire being in communication with an electrical circuit; and

[0157] wherein the at least one highly flexible thermoelectric composite device is positioned adjacent to an aircraft component surface of the aircraft component; and

[0158] The at least one highly flexible thermoelectric composite device is configured to generate electrical energy in the presence of a thermal gradient, and the at least one highly flexible thermoelectric composite device is further configured to deliver charge to power the temperature sensor.

[0159] 8. The temperature sensor of clause 7, wherein the at least one highly flexible thermoelectric composite device is placed in direct contact with the aircraft component surface of the aircraft component.

[0160] 9. The temperature sensor of clause 7, wherein the at least one highly flexible thermoelectric composite device is in communication with an indicator (32) configured to indicate generation of an electric charge.

[0161] 10. The temperature sensor of clause 7, wherein the circuit is in communication with a rechargeable battery (42).

[0162] 11. An aircraft component (14) comprising a temperature sensor as claimed in clause 7.

[0163] 12. An aircraft (10) comprising a temperature sensor as claimed in clause 7.

[0164] 13. A power source for an aircraft component, the power source comprising:

[0165] At least one highly flexible thermoelectric composite device (18) is positioned adjacent to an aircraft component surface of an aircraft component on an aircraft, the at least one highly flexible thermoelectric composite device being configured to maintain a temperature gradient when the aircraft is in operation, the at least one highly flexible thermoelectric composite device comprising at least one wire in communication with an electrical circuit, the at least one highly flexible thermoelectric composite device being configured to convert heat from the thermal gradient into electrical energy.

[0166] 14. The power source of clause 13, wherein the highly flexible thermoelectric composite device is in direct contact with the aircraft component surface (14a) of the aircraft component (14).

[0167] 15. The power supply of clause 13, wherein the power supply is an auxiliary power supply.

[0168] 16. The power supply of clause 13, wherein the power supply is configured to exclusively power a temperature sensor, the temperature sensor being in communication with the circuit.

[0169] 17. The power supply according to clause 13 further comprises a battery (42) in communication with the circuit (30), the battery being configured to receive charge from the circuit, the battery being further configured to direct the charge from the battery to the circuit.

[0170] 18. The power supply of clause 13, wherein the circuit is an auxiliary circuit.

[0171] 19. An aircraft assembly comprising the power supply of clause 13.

[0172] 20. An aircraft comprising the power supply of clause 13.

[0173] 21. A method (100) for sensing the temperature of a surface of an aircraft component in an aircraft, the method comprising:

[0174] placing (102) at least one highly flexible thermoelectric composite device in direct contact with a surface of an aircraft component of the aircraft, the highly flexible thermoelectric composite device comprising at least one electrical wire in communication with an electrical circuit, the highly flexible thermoelectric composite device being configured to generate electrical energy when exposed to a thermal gradient;

[0175] Providing (104) the thermal gradient on the highly flexible thermoelectric composite device;

[0176] generating (106) a certain amount of electrical energy; and

[0177] The electrical energy generated by the highly flexible thermoelectric composite device is directed (108) to the circuit.

[0178] 22. The method of clause 20, wherein the aircraft component surface is configured to maintain a temperature variation.

[0179] 23. The method of clause 20, wherein the aircraft component surface is configured to maintain a temperature variation between a non-operational state and an operation state, the temperature variation ranging from about 5°C to about 60°C.

[0180] 24. The method (200) according to clause 20, further comprising:

[0181] The presence of an amount of electrical energy delivered by the highly flexible thermoelectric composite device to the circuit is determined (202).

[0182] 25. The method of clause 20, wherein the highly flexible thermoelectric composite device is configured to withstand 15,000 cycles at a maximum strain of 30% and remain fully functional when exposed to a temperature of about 40°C.

[0183] 26. The method (200) according to clause 20, further comprising:

[0184] determining (202) a temperature change in at least one of the aircraft component and a region proximate to the aircraft component; and

[0185] The temperature change corresponds to the electrical energy delivered by the highly flexible thermoelectric composite device to the circuit.

[0186] 27. The method (300) according to clause 20, further comprising:

[0187] An aircraft component is powered (302) with electrical energy directed from the highly flexible thermoelectric composite device to the circuit, the aircraft component being in communication with the circuit.

[0188] 28. The method (400) of clause 20, further comprising:

[0189] A battery is charged (402), the battery being in communication with the circuit, wherein at least a portion of the electrical energy is directed from the highly flexible thermoelectric composite device through the circuit to the battery.

[0190] 29. The method (500) according to clause 20, further comprising:

[0191] A plurality of highly flexible thermoelectric composite devices are placed (502) in direct contact with a surface of the aircraft component.

[0192] 30. The method of clause 20, wherein the aircraft component is at least one of an aircraft engine, an aircraft auxiliary power unit, an electrical compartment, a cargo compartment, and combinations thereof.

[0193] 31. The method of clause 20, wherein the highly flexible thermoelectric composite device is a temperature sensor.

[0194] 32. The method of clause 20, wherein the highly flexible thermoelectric composite device provides the electrical energy exclusively for powering aircraft components.

[0195] 33. The method of clause 20, wherein the highly flexible thermoelectric composite device provides auxiliary power to an aircraft component.

[0196] 34. The method of clause 31, wherein the aircraft component is a temperature sensor.

[0197] 35. The method of clause 32, wherein the aircraft component is a temperature sensor.

[0198] 36. The method (600) of clause 27, further comprising:

[0199] An aircraft component is powered (602) with electrical energy directed from the battery, the aircraft component being in communication with the circuit.

[0200] 37. The method of clause 27, wherein the battery is a rechargeable lithium-ion battery.

[0201] Of course, without departing from the essential features of the present disclosure, the present invention may be implemented in other ways than those specifically described herein. The present invention should be considered illustrative and non-restrictive in all aspects, and all changes within the meaning and equivalent range of the claims should be included therein.

Claims

1. An aircraft assembly (14) on an aircraft, the aircraft assembly comprising: Aircraft component surface (14a); At least one highly flexible thermoelectric composite device (18), the at least one highly flexible thermoelectric composite device comprising at least one electrical wire (20) in communication with the electrical circuit (30); and Wherein the at least one highly flexible thermoelectric composite device is positioned adjacent to the aircraft component surface.

2. The aircraft component of claim 1, wherein the at least one highly flexible thermoelectric composite device is placed in direct contact with a surface of the aircraft component. 3 . The aircraft assembly of claim 1 , wherein the at least one highly flexible thermoelectric composite device is configured to generate electrical energy in the presence of a thermal gradient. The aircraft component of claim 1 , wherein the aircraft component surface is configured to dissipate heat during operation.

5. The aircraft component of claim 1, wherein the aircraft component surface comprises at least one of an aircraft engine surface, an auxiliary power unit surface, an electrical compartment surface, a cargo compartment surface, and combinations thereof.

6. An aircraft (10) comprising the aircraft assembly of claim 1.

7. A temperature sensor (34) for an aircraft component (60), the temperature sensor comprising: at least one highly flexible thermoelectric composite device, comprising at least one wire, the at least one wire being in communication with an electrical circuit; and wherein the at least one highly flexible thermoelectric composite device is positioned adjacent to an aircraft component surface of the aircraft component; and The at least one highly flexible thermoelectric composite device is configured to generate electrical energy in the presence of a thermal gradient, and the at least one highly flexible thermoelectric composite device is further configured to deliver charge to power the temperature sensor.

8. The temperature sensor of claim 7, wherein the at least one highly flexible thermoelectric composite device is placed in direct contact with the aircraft component surface of the aircraft component.

9. The temperature sensor of claim 7, wherein the at least one highly flexible thermoelectric composite device is in communication with an indicator (32) configured to indicate generation of an electric charge.

10. The temperature sensor of claim 7, wherein the circuit is in communication with a rechargeable battery (42).

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