Aircraft cabin overheating indicator, system and method

Abstract

The invention relates to an aircraft cabin overheating indicator, system and method. A disposable and replaceable self-powered aircraft cabin thermal indicator that delivers a local visually detectable signal that can be perceived by a person external to an aircraft component, and a method of using the same are disclosed. And can be enabled as needed to signal the presence of a temperature in the aircraft cabin exceeding a threshold temperature, and can be tested in situ.

Description

[0001] Government rights This invention was made with government support under a grant granted by the Ministry of Defense (FA8628-19-D-1000-FA810722F0001). The government owns certain rights to this invention. Technical Field

[0002] This disclosure generally relates to the field of aircraft cabin temperature indication. More specifically, this disclosure relates to the specific field of aircraft cabin temperature indication for indicating excessive temperatures in an aircraft cabin. Background Technology

[0003] It can monitor ambient and operating temperatures within the aircraft in the passenger cabin, storage compartment, cargo hold, and machinery compartment to improve safety and otherwise ensure that the temperature within the monitoring compartment is maintained within an acceptable range.

[0004] System feedback from the temperature monitoring system can be relayed to personnel inside the cockpit of the aircraft. In aircraft or other vehicle types, gross weight is a factor, and the use of onboard power and power losses for operating the electrothermal monitoring system, as well as the weight of the monitoring system itself (including monitoring system hardware, linkages, connections, wiring, etc.), can add undesirable additional weight to the aircraft, significantly increasing operating costs. Unless explicitly stated otherwise, the statements herein are not considered prior art solely because they are included in the Technical and / or Background sections. Summary of the Invention

[0005] This invention relates to a self-powered thermal indicator for an aircraft compartment, which can be activated when an area of ​​the thermal indicator is exposed to or otherwise encounters an ambient temperature exceeding a selected threshold temperature, the selected threshold temperature being capable of including a threshold temperature range, wherein at least an area of ​​the thermal indicator is visible from or outside the aircraft.

[0006] This invention relates to a self-powered aircraft cabin thermal indicator (20) for determining above-threshold temperatures in an interior region of an aircraft, wherein the aircraft cabin thermal indicator includes an indicator body comprising an indicator body length (“l”). The indicator body also includes an indicator body interior, an indicator body exterior, an indicator body first end (e.g., an indicator side), an indicator body second end, an indicator body base, and an internal piston. The internal piston further includes a piston base comprising a piston base first side and a piston base second side, wherein the internal piston also includes a piston rod comprising a piston rod first end and a piston rod second end, and wherein the piston rod second end communicates at least with the piston base first side. The indicator body also includes an indicator body wall extending from the indicator body first end along the indicator body length to the indicator body second end, and wherein the indicator body wall comprises an outer surface of the indicator body wall outside the indicator body and an inner surface of the indicator body wall inside the indicator body. The indicator body further includes a battery compartment, wherein the battery compartment includes a battery compartment base and is defined by the battery compartment base and an inner surface of the indicator body wall. The indicator body also includes a first chamber defined by the inner surface of the indicator body wall, a first side of the piston base, and the battery compartment base, wherein the first chamber includes a brittle reservoir containing a volume of battery electrolyte. The indicator body also includes a second chamber defined by the inner surface of the indicator body wall and a second side of the piston base, wherein the second chamber includes a spring, wherein the spring includes a first end fixedly attached to the piston base, and wherein the spring also includes a second end positioned adjacent to the base of the second end of the indicator body. The second chamber of the indicator body further includes a degradable retainer, wherein the degradable retainer is in communication with the spring, wherein the degradable retainer is configured to hold the spring in a compressed spring state within a first temperature range, wherein the degradable retainer is configured to degrade at a threshold temperature within a second temperature range, wherein the degradable retainer is further configured to hold the spring in a compressed spring state within the first temperature range, and wherein the degradable retainer is further configured to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range, wherein the threshold temperature is higher than the first temperature range.

[0007] In another aspect of the invention, the aircraft cabin includes an interior region of the aircraft, which includes a local area within the aircraft cabin.

[0008] In another aspect of the invention, the aircraft cabin thermal indicator is self-powered.

[0009] In another aspect of the invention, the aircraft cabin thermal indicator further includes a light fixture in communication with the first end of the piston rod.

[0010] In another aspect of the invention, the lighting device is a light-emitting diode (LED).

[0011] In another aspect of the invention, the battery compartment further includes a plurality of battery panels.

[0012] In another aspect of the invention, the degradable retainer comprises at least one of a cryogenic alloy and a wax, wherein the cryogenic alloy and the wax, and the degradable retainer, comprise a melting point ranging from about 140℉ to about 165℉.

[0013] In another aspect of the invention, the cryogenic alloy comprises a cryogenic metal alloy comprising at least one of the following: bismuth, lead, tin, indium, cadmium, thallium, gallium, and combinations thereof, wherein the cryogenic alloy has a melting point ranging from about 140℉ to about 165℉.

[0014] In another aspect of the invention, the cryogenic alloy comprises at least one of the following: rose's metal, cerrosafe, wood's metal, field's metal, cerrolow 136, cerrolow 117, gallium, and combinations thereof.

[0015] In a further aspect of the invention, the battery panel is configured in the presence of the electrolyte (34a) to form a battery configured to deliver current.

[0016] In another aspect of the invention, the battery is a fuze battery.

[0017] In another aspect of the invention, the aircraft cabin thermal indicator further includes an integrated thermal guide tube in close contact with the degradable retainer.

[0018] In another aspect of the invention, the aircraft cabin thermal indicator is detachably attached to the aircraft substrate.

[0019] In another aspect of the invention, the aircraft cabin thermal indicator is capable of being tested and inspected in situ.

[0020] In another aspect of the invention, the aircraft cabin thermal indicator further includes an integrated thermal guide tube, the integrated thermal guide tube including a first end of the thermal guide tube fixedly extending into a second chamber of the indicator body, and a second end of the thermal guide tube extending a selected distance from the base of the second end of the indicator body.

[0021] In another aspect of the invention, the heat-conducting tube further includes a heat-conducting tube wall, wherein the heat-conducting tube wall includes a heat-conducting tube wall periphery, the heat-conducting tube wall periphery being positioned substantially adjacent to the degradable retainer in the second chamber of the indicator body.

[0022] A further aspect of the invention relates to an aircraft component comprising a self-powered aircraft cabin thermal indicator for determining above-threshold temperatures in an interior region of the aircraft, wherein the aircraft cabin thermal indicator comprises an indicator body including an indicator body length (“l”). The indicator body further comprises an indicator body interior, an indicator body exterior, an indicator body first end (e.g., an indicator side), an indicator body second end, an indicator body second end base, and an internal piston. The internal piston further comprises a piston base, wherein the piston base includes a piston base first side and a piston base second side, wherein the internal piston further comprises a piston rod, and wherein the piston rod includes a piston rod first end and a piston rod second end, and wherein the piston rod second end communicates at least with the piston base first side. The indicator body further comprises an indicator body wall, wherein the indicator body wall extends from the indicator body first end along the indicator body length to the indicator body second end, and wherein the indicator body wall comprises an outer surface of the indicator body wall outside the indicator body and an inner surface of the indicator body wall inside the indicator body. The indicator body further includes a battery compartment, wherein the battery compartment includes a battery compartment base and is defined by the battery compartment base and an inner surface of the indicator body wall. The indicator body also includes a first chamber defined by the inner surface of the indicator body wall, a first side of the piston base, and the battery compartment base, wherein the first chamber includes a brittle reservoir containing a volume of battery electrolyte. The indicator body further includes a second chamber defined by the inner surface of the indicator body wall and a second side of the piston base, wherein the second chamber includes a spring, wherein the spring includes a first end fixedly attached to the piston base, and wherein the spring also includes a second end positioned adjacent to the base of the second end of the indicator body. The second chamber of the indicator body further includes a degradable retainer, wherein the degradable retainer communicates with the spring, wherein the degradable retainer is configured to hold the spring in a compressed spring state within a first temperature range, wherein the degradable retainer is configured to degrade at a threshold temperature within a second temperature range, wherein the degradable retainer is further configured to hold the spring in a compressed spring state within the first temperature range, and wherein the degradable retainer is further configured to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range, wherein the threshold temperature is higher than the first temperature range.

[0023] In another aspect of the invention, the aircraft component is an aircraft wing component.

[0024] Another aspect of the invention relates to an aircraft comprising a self-powered aircraft cabin thermal indicator for determining above-threshold temperatures in an interior region of the aircraft, wherein the aircraft cabin thermal indicator comprises an indicator body including an indicator body length (“l”). The indicator body further comprises an indicator body interior, an indicator body exterior, an indicator body first end (e.g., an indicator side), an indicator body second end, an indicator body second end base, and an internal piston. The internal piston further comprises a piston base, wherein the piston base includes a piston base first side and a piston base second side, wherein the internal piston further comprises a piston rod, and wherein the piston rod includes a piston rod first end and a piston rod second end, and wherein the piston rod second end communicates at least with the piston base first side. The indicator body further comprises an indicator body wall, wherein the indicator body wall extends from the indicator body first end along the indicator body length to the indicator body second end, and wherein the indicator body wall comprises an outer surface of the indicator body wall outside the indicator body and an inner surface of the indicator body wall inside the indicator body. The indicator body further includes a battery compartment, wherein the battery compartment includes a battery compartment base and is defined by the battery compartment base and an inner surface of the indicator body wall. The indicator body also includes a first chamber defined by the inner surface of the indicator body wall, a first side of the piston base, and the battery compartment base, wherein the first chamber includes a brittle reservoir containing a volume of battery electrolyte. The indicator body further includes a second chamber defined by the inner surface of the indicator body wall and a second side of the piston base, wherein the second chamber includes a spring, wherein the spring includes a first end fixedly attached to the piston base, and wherein the spring also includes a second end positioned adjacent to the base of the second end of the indicator body. The second chamber of the indicator body further includes a degradable retainer, wherein the degradable retainer communicates with the spring, wherein the degradable retainer is configured to hold the spring in a compressed spring state within a first temperature range, wherein the degradable retainer is configured to degrade at a threshold temperature within a second temperature range, wherein the degradable retainer is further configured to hold the spring in a compressed spring state within the first temperature range, and wherein the degradable retainer is further configured to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range, wherein the threshold temperature is higher than the first temperature range.

[0025] Another aspect of the invention relates to an aircraft cabin thermal indication system (referred to herein as an "aircraft cabin temperature indication system") for visually detecting above-threshold temperatures within an aircraft cabin near the exterior of the aircraft. The aircraft cabin thermal indication system includes a self-powered aircraft cabin thermal indicator attached to an aircraft component, wherein the self-powered aircraft cabin thermal indicator is configured to determine above-threshold temperatures in an area within the aircraft cabin. The self-powered aircraft cabin thermal indicator includes an indicator body with an indicator body length ("l"). The indicator body also includes an indicator body interior, an indicator body exterior, an indicator body first end, an indicator body second end, an indicator body second end base, and an internal piston. The internal piston further includes a piston base, wherein the piston base includes a piston base first side and a piston base second side. The internal piston also includes a piston rod, wherein the piston rod includes a piston rod first end and a piston rod second end, and wherein the piston rod second end communicates at least with the piston base first side. The indicator body further includes an indicator body wall extending from a first end of the indicator body along the length of the indicator body to a second end of the indicator body, and wherein the indicator body wall includes an outer surface of the indicator body outside the indicator body and an inner surface of the indicator body inside the indicator body. The indicator body also includes a battery compartment including a battery compartment base, and wherein the battery compartment is defined by the battery compartment base and the inner surface of the indicator body wall. The indicator body further includes a first chamber of the indicator body defined by the inner surface of the indicator body wall, a first side of the piston base, and the battery compartment base, wherein the first chamber of the indicator body includes a brittle reservoir, and wherein the brittle reservoir contains a volume of battery electrolyte. The indicator body also includes a second chamber of the indicator body defined by the inner surface of the indicator body wall and a second side of the piston base, wherein the second chamber of the indicator body includes a spring, wherein the spring includes a first end fixedly attached to the piston base, and wherein the spring also includes a second end positioned adjacent to the base of the second end of the indicator body. The second chamber of the indicator body further includes a degradable retainer, wherein the degradable retainer is in communication with the spring, wherein the degradable retainer is configured to hold the spring in a compressed spring state within a first temperature range, wherein the degradable retainer is configured to degrade at a threshold temperature within a second temperature range, wherein the degradable retainer is further configured to hold the spring in a compressed spring state within the first temperature range, and wherein the degradable retainer is further configured to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range.The system also includes a visually detectable signal transmission device located at and integrated within the first end of the indicator body, wherein the visually detectable signal transmission device communicates with a circuit, and wherein the visually detectable signal transmission device is also located outside the aircraft, and wherein the signal transmission device is configured to be activated at and above a threshold temperature, wherein the threshold temperature is above a first temperature range.

[0026] In another aspect of the invention, the battery compartment includes a plurality of battery panels.

[0027] In another aspect of the invention, the visually detectable signal transmission device includes an illumination device.

[0028] In another aspect of the invention, the visually detectable signal transmission device includes a light-emitting diode (LED).

[0029] In another aspect of the invention, the signal transmission device is configured to emit a light beam in response to the second end of the indicator being exposed to a threshold temperature ranging from about 140℉ to about 165℉.

[0030] In another aspect of the invention, the self-powered aircraft cabin thermal indicator is detachably attached to the aircraft component.

[0031] In another aspect of the invention, the self-powered aircraft cabin thermal indicator is configured to be detached from the aircraft component from a location outside the aircraft.

[0032] In another aspect of the invention, the self-powered aircraft cabin thermal indicator is accessible for inspection from the outside of the aircraft.

[0033] In another aspect of the invention, the battery is a fuze battery, wherein the fuze battery is configured to be activated at the threshold temperature.

[0034] Another aspect of the invention relates to a method for detecting a threshold temperature in an internal region of an aircraft component outside an aircraft, the internal region of which may include an aircraft cabin located near the exterior of the aircraft. The method includes positioning a self-powered aircraft cabin thermal indicator within the aircraft component, wherein the aircraft component includes an outer surface (e.g., an external aircraft surface) located adjacent to the internal region of the aircraft component, the internal region including the aircraft cabin, and wherein the aircraft cabin thermal indicator includes an indicator body including an indicator body length (“l”). The indicator body also includes an indicator body interior, an indicator body exterior, a first end (e.g., an indicator side), a second end, a base of the second end, and an internal piston. The internal piston further includes a piston base including a first side and a second side, and a piston rod including a first end and a second end, the second end of which communicates at least with the first side of the piston base. The indicator body further includes an indicator body wall extending from a first end of the indicator body along the length of the indicator body to a second end of the indicator body, and wherein the indicator body wall includes an outer surface of the indicator body outside the indicator body and an inner surface of the indicator body inside the indicator body. The indicator body also includes a battery compartment including a battery compartment base, and wherein the battery compartment is defined by the battery compartment base and the inner surface of the indicator body wall. The indicator body further includes a first chamber of the indicator body defined by the inner surface of the indicator body wall, a first side of the piston base, and the battery compartment base, wherein the first chamber of the indicator body includes a brittle reservoir, and wherein the brittle reservoir contains a volume of battery electrolyte. The indicator body also includes a second chamber of the indicator body defined by the inner surface of the indicator body wall and a second side of the piston base, wherein the second chamber of the indicator body includes a spring, wherein the spring includes a first end fixedly attached to the piston base, and wherein the spring also includes a second end positioned adjacent to the base of the second end of the indicator body.The second chamber of the indicator body further includes a degradable retainer, wherein the degradable retainer communicates with the spring, wherein the degradable retainer is configured to hold the spring in a compressed spring state within a first temperature range, wherein the degradable retainer is configured to degrade at a threshold temperature within a second temperature range, wherein the degradable retainer is further configured to hold the spring in a compressed spring state within the first temperature range, and wherein the degradable retainer is further configured to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range, wherein the threshold temperature is higher than the first temperature range. The method further includes degrading the degradable retainer in the presence of a cabin temperature exceeding a threshold temperature, releasing the spring from the compressed spring state to the expanded spring state, conveying the piston from an initial piston position to a deployed piston position, fracturing the brittle reservoir to form a fractured brittle reservoir, releasing at least a portion of the predetermined volume of battery electrolyte from the fractured brittle reservoir, guiding at least a portion of the predetermined volume of battery electrolyte into the battery compartment to form a battery, wherein the battery is configured to deliver a generated current, guiding the first end of the piston rod through a first end through-hole of the indicator body to a selected distance beyond the outer surface of the aircraft component, and guiding the current from the battery to a light emitting device to emit light from the light emitting device.

[0035] In another aspect of the invention, the method further includes visually detecting light emitted from the light-emitting device from outside the aircraft.

[0036] In another aspect of the invention, the method further includes removably positioning the self-powered aircraft cabin thermal indicator within the aircraft component.

[0037] In another aspect of the invention, in a method, visual detection from the exterior of the aircraft of illumination from the aircraft cabin thermal indicator indicates that the temperature inside at least one of the aircraft components exceeds a threshold temperature.

[0038] The features, functions, and advantages already discussed can be realized independently in each aspect or in combination in other aspects, further details of which can be seen in the following description and figures. Attached Figure Description

[0039] Having thus described the various modifications of this disclosure in general terms, reference will now be made to the accompanying drawings, which are not necessarily drawn to scale, wherein: Figure 1 Examples of vehicles in the form of aircraft according to aspects of the present invention; Figure 2This is a cross-sectional side view of a self-powered aircraft cabin thermal indicator according to aspects of the present invention; Figure 3 According to the present invention Figure 2 Cross-sectional side view of a thermal indicator for a self-powered aircraft cabin of the type shown; Figure 4A This is a cross-sectional side view of a self-powered aircraft cabin thermal indicator according to aspects of the present invention; Figure 4B It is incorporated into the thermal indicator of a self-powered aircraft cabin according to aspects of the present invention. Figure 4A A partial 3D view of the type of heat-conducting pipe shown; Figure 4C This is a box diagram illustrating an aircraft cabin temperature indication system according to aspects of the present invention for visually detecting temperatures above a threshold inside the aircraft cabin near the outside of the aircraft. Figure 5A This is an example of a test system and method for a self-powered aircraft cabin thermal indicator according to aspects of the present invention; Figure 5B This is an example of a test system for a self-powered aircraft cabin thermal indicator according to aspects of the present invention; Figure 6 This is a cross-sectional side view of an aircraft component in the form of an aircraft wing component including the self-powered aircraft cabin thermal indicator of the present invention, according to an aspect of the present invention. Figure 7 This is an example of a wing leading edge component according to aspects of the present invention; Figure 8 This is a flowchart outlining the method according to aspects of the present invention; Figure 9 This is a flowchart outlining the method according to aspects of the present invention; and Figure 10 This is a flowchart outlining a method according to aspects of the present invention. Detailed Implementation

[0040] The aim is to detect unwanted levels of temperature rise in various compartments and interior areas of an aircraft (e.g., which can be demonstrated by quantitative and / or qualitative temperature measurements), including detecting temperature rises caused by, for example, fire, and temperatures that may occur just before ignition, such temperature rises above and / or exceed expected and / or acceptable temperatures—equivalently referred to herein as “threshold temperatures,” etc. According to aspects of the invention, a self-powered aircraft compartment thermal indicator (equivalently referred to herein as “aircraft compartment thermal indicator,” “aircraft thermal indicator,” and “thermal indicator”) is disclosed, which can be detachably mounted into an aircraft substrate and / or aircraft components (e.g., aircraft parts)—including aircraft compartment components. According to aspects of the invention, the self-powered aircraft compartment thermal indicator includes a portion of the thermal indicator exposed on the exterior of the aircraft and a portion otherwise visible on the exterior of the aircraft and visible from a viewing position outside the aircraft, wherein the thermal indicator is also positioned as a portion extending into an interior area of ​​the aircraft, which may be a partial interior area and may also be at least partially enclosed aircraft compartment.

[0041] According to aspects of the invention, the term "aircraft cabin" includes a completely enclosed interior area within an aircraft, and also includes an interior area within an aircraft that is at least partially enclosed. That is, according to aspects of the invention, an aircraft cabin may not be a completely and / or totally enclosed cabin. In another aspect of the invention, the aircraft cabin may be a substantially totally enclosed interior aircraft cabin.

[0042] According to a further aspect of the invention, a "self-powered" thermal indicator means that the thermal indicator of the present invention includes an internal and / or independent indicator power source and / or power supply, which can be activated when the temperature is equal to or above a selected threshold temperature. The self-powered aircraft cabin thermal indicator of the present invention does not generate and / or otherwise cause power loss to the aircraft power supply and / or the aircraft power grid during operation. That is, the self-powered thermal indicator of the present invention forms an independent battery as needed during operation, and the thermal indicator operates separately from the aircraft power supply, aircraft auxiliary power supply, etc., without being connected to or otherwise communicating with them.

[0043] Figure 1 This is a representative and non-limiting example of an aircraft of the type that may include the self-powered aircraft cabin thermal indicator of the present invention, wherein the aircraft 10 includes a fuselage 12 and a wing 14, the wing including a wing leading edge 16, and the wing 14 houses an internal wing leading edge component 16a within a wing cabin housed within the wing 14.

[0044] According to an aspect of the invention, the self-powered aircraft cabin thermal indicator can be configured to be detachably attached to an aircraft component to indicate that at least one internal region of the aircraft cabin located near and / or adjacent to the thermal indicator, and a localized internal aircraft region where the thermal indicator temperature sensing side (e.g., the second side of the indicator body) extends into the cabin, has exceeded a selected threshold temperature. According to an aspect of the invention, the aircraft cabin can be, but does not need to be, a completely enclosed cabin into which the aircraft cabin thermal indicator extends. In an example of the invention, the aircraft cabin can be an aircraft wing leading-edge cabin capable of accommodating an aircraft bleed air duct, the bleed air duct including an aircraft bleed air duct connector positioned along the bleed air duct.

[0045] According to an aspect of the invention, when the ambient temperature in the cabin and / or a partial interior space of the aircraft exceeds a selected threshold temperature, the self-powered cabin thermal indicator of the invention can be operatively triggered to form an enabled power source (e.g., an enabled kinetic energy source) within the thermal indicator – equivalently referred to herein as a battery – wherein the enabled power source communicates with a visually detectable indicator (e.g., a light including a flashlight) that can be powered by the enabled power source, and wherein the visually detectable indicator is configured to emit a visually detectable signal that can be detected at an external location outside the aircraft.

[0046] According to aspects of the present invention, the self-powered aircraft cabin thermal indicator is configured to respond to changes in ambient temperature from a temperature maintained below a threshold temperature and / or within a range of the threshold temperature to a temperature above the threshold temperature and / or within a range of the threshold temperature. That is, the self-powered aircraft cabin thermal indicator can be configured to activate at a selected temperature above a selected threshold temperature. The self-powered aircraft cabin thermal indicator includes a force-related component, which can be, for example, a spring that, when the self-powered thermal indicator is maintained in an environment where the ambient temperature is below the threshold temperature, has a potential outward force while being held in a compressed state by a retainer. Below the threshold temperature, the retainer (equivalently referred to herein as a degradable retainer) has sufficient retaining force on the compressed spring, exceeding the potential outward force of the compressed spring; resulting in the spring being held in a compressed or "held" and / or "restrained" state.

[0047] When the self-powered aircraft cabin thermal indicator of this invention is subjected to and / or exposed to temperatures exceeding a selected threshold temperature, the degradable retainer, which may be made of a cryogenic alloy, begins to change state and / or otherwise sustains a significant reduction in the retaining force, allowing the retaining force to be overcome and otherwise exceeded by the potential outward force of the spring. When this occurs, the spring releases from the compressed or retained state and expands outward along its longitudinal axis, at which point the spring is able to direct (e.g., on the spring-positioned element adjacent to the compressed state) force from the resting initial element position to the spring-driven "driven" or activated element position.

[0048] In an example of the invention, during operation, a force ranging from about 10 lbf to about 30 lbf may be required to rupture the brittle battery electrolyte container housed within the thermal indicator. Therefore, the thermal indicator of the present invention includes a spring configured to deliver a similar force ranging from about 10 lbf to about 30 lbf to the container rupture element (e.g., a piston) in the spring-released state. As described herein, in order to hold the spring element in a compressed state when the aircraft cabin thermal indicator of the present invention is in an “inactive state,” and wherein a degradable retainer is solid and configured to hold the spring in a compressed or held state, the degradable retainer is configured to apply a holding force on the spring exceeding the outward spring release force of the spring.

[0049] In one example of the invention, the degradable retainer is made of and / or otherwise includes a "low-melting-point" material (equivalently referred to herein as a "low-temperature material"), which may be a low-melting-point metal, a low-melting-point alloy (equivalently referred to herein as a "low-temperature alloy"), a wax, and / or a material that will begin to undergo a phase change from a solid to a liquid or semi-solid phase at a selected threshold temperature and / or within a selected threshold temperature range. That is, according to aspects of the invention, when the thermal indicator of the invention is exposed to an environment at a temperature at least equal to the selected threshold temperature, the low-melting-point material will undergo a change in physical properties, at least in terms of its retaining capacity in the solid state, and the low-temperature material will "melt" into a liquid or semi-solid state (e.g., "semi-solid" is a state in which the material begins to "flow," etc.), wherein liquid and semi-solid are collectively referred to herein as "liquid."

[0050] In other words, according to aspects of the invention, when the low-melting-point material used to form the degradable retainer of the aircraft cabin thermal indicator of the invention is in solid form and the ambient temperature in the aircraft cabin to which the thermal indicator is exposed is below a threshold temperature (which may be, for example, below about 140℉), the degradable retainer maintains a retaining force in the solid state exceeding (e.g., the outward potential force of the spring may be impregnated with the low-melting-point material of the degradable retainer), and the degradable retainer maintains the spring in a compressed and / or "held" state. When the ambient temperature to which the thermal indicator is exposed rises to and / or exceeds (in one example, ranging from about 140℉ to about 200℉) the threshold temperature, the low-melting-point material used to form the degradable retainer changes from a solid phase to a liquid phase (e.g., a liquid "state") such that the retaining force of the low-melting-point material in a liquid (e.g., in a "non-solid" state) is lower than the outward potential force of the spring (and it is lower than the retaining force when the low-melting-point material is in a solid state), causing the spring to release from an initial compressed state to an expanded and released spring state.

[0051] As described herein, and according to aspects of the invention, the degradable retainer comprises a "low melting point" material (equivalently referred to herein as a "cryogenic material" and / or a "cryogenic alloy") that is in a solid phase below a selected threshold temperature, which in one example of the invention is about 200℉. In another example of the invention, the selected threshold temperature is a threshold temperature ranging from about 160℉ to about 240℉. In another example of the invention, the selected threshold is a temperature at which a fire generated by an electronic device can occur, and its range is from about 160℉ to about 280℉. In another example of the invention, the selected threshold temperature is an elevated temperature within an aircraft hydraulic compartment, and its range is from about 160℉ to about 280℉. In another example of the invention, the selected threshold temperature is a threshold temperature ranging from about 140℉ to about 165℉. In another example of the invention, the selected threshold for cargo storage compartments and / or aircraft cabin storage cabinets may be a temperature ranging from about 160℉ to about 170℉.

[0052] In other words, according to aspects of the invention, the aircraft cabin thermal indicator of the present invention can be selectively tuned or otherwise configured to provide thermal indication at a selected temperature and / or a selected temperature range, which can vary depending on the installation location of the thermal indicator and further depending on changes in or presence of unwanted temperature rises selected for monitoring in the aircraft area and / or aircraft cabin. According to aspects of the invention, the thermal indication properties of the thermal indicator can be selected to substantially match a threshold temperature to be monitored on the aircraft, which may include monitoring of aircraft cabins that may require overheat protection; wherein detection of early temperature rises can be highly beneficial. Aircraft cabins that may benefit from overheat protection may include, for example, fuel tanks, areas adjacent to fuel tanks, cabins containing hot air and / or bleed air ducts, cargo holds, passenger storage cabins, cabins containing electrical and / or hydraulic components, battery compartments, engine fan housings, wheel wells, etc.

[0053] A further aspect of the invention considers detecting a threshold temperature reached in the aircraft cabin that may prove to be a system anomaly or system interruption caused by anticipated system malfunction. Detection may include, for example, detecting heat leakage from a ducted pathway (e.g., at a junction area of ​​the ducted pathway), which includes, for example, an air duct located at the leading edge of the wing within the wing cabin.

[0054] Low-melting-point materials may include metals, metal alloys, or other low-melting-point materials (e.g., wax), and may include at least one of the following: bismuth-containing compounds, lead-containing compounds, tin-containing compounds, indium-containing compounds, thallium-containing compounds, gallium-containing compounds, Loss metal, Shilosifer, Wood's alloy, Field metal, Shilolu 136, Shilolu 117, gallium, and combinations thereof. Low-melting-point materials may also include at least one of the following: wax-containing compounds and other non-metallic compounds, and combinations thereof. In one example of the invention, the degradable retainer includes a low-melting-point material with a melting point range from about 140℉ to about 165℉.

[0055] According to an aspect of the invention, at a threshold temperature and when the degradable retainer changes from a solid phase to a liquid phase, a compression spring into which the degradable retainer material can be embedded is released, and the spring is released from a compressed state to an expanded state along its longitudinal axis. A mechanical force is applied to a movable element (e.g., a piston) to cause the brittle container (equivalently referred to herein as a "brittle reservoir," "brittle battery electrolyte reservoir," or "brittle battery electrolyte container") containing the liquid battery electrolyte to rupture. The liquid battery electrolyte is released from the ruptured brittle container, and the electrolyte is driven by the piston into the battery compartment such that the presence of the battery electrolyte in the battery compartment forms a battery capable of delivering current (e.g., charge) to an indicator element, which may be a visually detectable indicator (equivalently referred to as a "visually detectable signal transmission device"), which may be an illumination device and may be, for example, a light-emitting diode (LED). Current from the activated battery travels along the circuit established by the activated battery to activate the lighting equipment, which emits a visually detectable beam of light (which may be a beam of light from a flashing lighting equipment) and provides a visual indication of a temperature exceeding a selected threshold temperature present in the thermal indicator area.

[0056] Figure 2 and Figure 3 This is a cross-sectional side view of the aircraft cabin thermal indicator 20 of the present invention. The aircraft cabin thermal indicator 20 is fixedly and detachably attached to and extends through the aircraft component substrate 18 in a suitable position. The aircraft component substrate 18 has an outer surface 18a and an inner surface 18b. Figure 2 and Figure 3 The same thermal indicator 20 is depicted, but the internal components of thermal indicator 20 are from... Figure 2 The compression or clamping state shown is towards Figure 3 The indicated expansion or "release" state moves and moves to that expansion or "release" state.

[0057] like Figure 2 As shown, the aircraft component substrate 18 can be Figure 2 The aircraft component shown is wing 14. Figure 2 As shown, the self-powered aircraft cabin thermal indicator of the present invention includes an indicator body 22 having an indicator body interior 22a and an indicator body exterior 22b. The indicator body 22 also includes an indicator body wall 24, which is defined by a first side 24a (equivalently referred to herein as the “inner and / or internal surface of the indicator body wall”) and a second side 24b (equivalently referred to herein as the “outer and / or external surface of the inner body wall”) and otherwise extends from and between the first side 24a and the second side 24b.

[0058] The indicator body 22 also includes a first end 26 of the indicator body that is substantially flush with the outer surface 18a of the aircraft component. The indicator body 22 also includes an indicator body length "l" extending from the first end 26 to a second end 28. The indicator body 22 also includes a second end 28 of the indicator body, which extends a selected distance "d" away from the inner surface 18b of the aircraft component and can extend into the aircraft cabin. Figure 2 As shown, the second end 28 of the indicator body also includes a second end base 29 of the indicator body. According to aspects of the invention, the first end 26 of the indicator body is equivalently referred to herein as the indicator “indicator end”, and the second end 28 of the indicator body is equivalently referred to herein as the indicator “temperature sensing end” and / or “sensing end”.

[0059] In an example of the present invention ( Figure 2 In (not shown), the first end 26 of the indicator body may extend slightly beyond the outer surface 18a of the aircraft component. In another example of the invention ( Figure 2 (Not shown in the image) The first end 26 of the indicator body can be embedded at a selected distance in the outer surface 18a of the aircraft component.

[0060] like Figure 2 As further shown, the first end 26 of the indicator body may also include an indicator body first end through hole 26a defined by an indicator body first end through hole wall 26b. The first end 26 of the indicator body also includes an indicator body first end thread 26c, which is configured to physically engage with a size-matching thread (e.g., a size-fitting thread) in the aircraft component substrate 18, for example, to securely and releasably (and detachably) engage the aircraft cabin thermal indicator 20 at a selected location in the aircraft component substrate 18.

[0061] like Figure 2As shown, the self-powered aircraft cabin thermal indicator 20 comprises three sections: 1) a battery compartment 30, defined by and otherwise positioned adjacent to the first end 26 of the indicator body and the battery compartment base 30a; 2) a first chamber 25a of the indicator body, defined by and otherwise positioned adjacent to the first end 26 of the indicator body and the first side 38a of the piston base 38 of the piston 36 and located therebetween; and 3) a second chamber 25b of the indicator body, defined by the second side 38b of the piston base 38 of the piston 36 and the second end base 29 of the indicator body at the second end 28 of the indicator body and located therebetween. The battery compartment 30 is located in... Figure 2 The image shows a battery compartment base 30a, which includes multiple battery panels 32 and a battery compartment base 30a, and the battery compartment base 30a includes a battery compartment base through hole 30b.

[0062] like Figure 2 As further shown, the first chamber 25a of the indicator body includes and is otherwise configured to contain a brittle container 34 in an unbroken state, the brittle container 34 showing that it contains a certain amount of battery electrolyte 34a, the battery electrolyte 34a being encapsulated within the brittle container 34 in an unbroken state. Figure 2 An internal piston 36 (referred to herein as "piston 36") is also shown, which further includes a piston base 38, and the piston base includes a first side 38a of the piston base facing into the first chamber 25a of the indicator body and otherwise forming its boundary "wall". The piston base 38 also includes a second side 38b of the piston base facing into the second chamber 25b of the indicator body and otherwise forming its boundary "wall". Figure 2 As shown, the first chamber of the indicator body can be defined and / or limited by the battery compartment base 30a, the first side of the indicator body wall 24a, and the first side of the piston base 38a. The piston 36 also includes a piston rod 39 having a first end 39a in close contact with an illumination device 40, which may be a light-emitting diode (LED) with a light lens 40a. The piston rod 39 also includes a second end 39b, which may be attached to or integral with the piston base 38 at the first side of the piston base 38a.

[0063] like Figure 2 As shown, the second chamber 25b of the indicator body includes a spring 42, which has a first end 42a that is positioned adjacent to the second side 38b of the piston base. The spring 42 also includes a second end 42b that is positioned adjacent to the second end base 29 of the indicator body. Figure 2Also shown is a degradable retainer 44, which is embedded in the spring 42 or otherwise presented on the spring 42 as a "coating," "deposit," "impregnation coating," etc., so that the solid degradable retainer has a stable form sufficient to overcome the outward force of the spring 42. That is, according to the invention, the spring 42, in a compressed state, is held in the compressed state and the spring maintains a potential outward force, while the spring is embedded in the degradable retainer 44, at which point the degradable retainer 44 is in a solidified (e.g., "solid") state. Figure 2 In the compressed spring state shown, the second chamber 25b of the indicator body can be defined and / or limited by the material forming the degradable retainer 44, the second side 38b of the piston base, and the second end base 29 of the indicator body.

[0064] According to the present invention, and as described herein, the degradable retainer 44 is made of and otherwise includes a selected “low melting point” material that will begin to change state from a first state as a substantially solid (e.g., substantially “solid phase”) having a first retaining force to a second state as at least one of a liquid and a semi-solid state and having a second retaining force less than the first retaining force in the liquid state—e.g., a “gelled” state (collectively referred to herein as “liquid” and / or “liquid phase”), the second retaining force also being less than the potential outward force of a compression spring that is successfully held (e.g., “held” by a solid retainer) in a compressed state when the degradable retainer is in the solid phase.

[0065] therefore, Figure 2 The invention's self-powered aircraft cabin thermal indicator is shown in an "inactive" configuration when the ambient temperature is below a threshold temperature (e.g., when the spring remains compressed and the force applied to the brittle container is insufficient to break the brittle container (and release its contents)). The "inactive" configuration of the thermal indicator means that the thermal indicator battery has not yet been formed in the thermal indicator.

[0066] and Figure 2 Different, and according to aspects of the present invention, Figure 3 The diagram shows a self-powered aircraft cabin thermal indicator 20 in an enabled configuration in the presence of elevated temperatures above a selected threshold temperature (e.g., temperatures greater than / above a lower initial ambient temperature). The thermal indicator's "enabled" configuration means that a thermal indicator battery has been formed within the thermal indicator to power it.

[0067] like Figure 3 As shown, when a temperature rise equal to or above the selected threshold temperature is sensed (indicated by the presence of heat source 46, which can cause the temperature rise and may be in the form of a flame, etc.), the heat indicator 20 (from...) Figure 2The inactive indicator state shown is "enabled" to the enabled indicator state, the degradable retainer 44 now changes from solid to liquid, and the spring is released from... Figure 2 The compressed spring shown is released. Figure 3 In the enabled indicator state shown, as the potential outward force of spring 42 is along the longitudinal axis of the spring (in Figure 3 (Displayed as "upward" force) and applies the resulting, less constrained, and / or unconstrained outward actual force to piston 36. (As shown in the image) Figure 3 As shown, the area of ​​the second chamber 25b of the indicator body expands to fill and otherwise enlarges, thereby substantially completely occupying the area of ​​the first chamber 25a of the previous indicator body, the area of ​​the first chamber 25a of the previous indicator body existing in the thermal indicator in the "inactive" state of the thermal indicator. Figure 2 The indicator body shown has a first chamber 25a, while... Figure 3 (Not present in the text).

[0068] During operation, and when the thermal indicator 20 is exposed to a temperature above the selected threshold temperature, a force from the release spring 42 is transmitted to the piston 36, forcing the piston 36 into the first chamber 25a of the indicator body. The force is sufficient to compress the brittle container 44 between the piston base 38 and the battery compartment base 30a, and sufficient to cause the brittle container 34 to rupture. The rupture of the brittle container 34 releases the battery electrolyte 34a from the now-ruptured brittle container 34 (which may be, for example, an ampoule—such as a thin-walled glass ampoule). As the liquid electrolyte 34a is released from the now-ruptured brittle container 34, the electrolyte is driven from the reduced area of ​​the first chamber of the indicator body and through the opening 30b in the battery compartment base 30a into the battery compartment 30.

[0069] like Figure 2 and Figure 3 As shown, the O-ring 38c is circumferentially positioned around the piston base 38 to form a seal between the piston base 38 and a first side of the indicator body wall (e.g., the “inner surface” of the indicator body wall). This seal is essentially leak-proof while also facilitating, and not otherwise hindering, the relative movement of the piston in response to the force of the spring 42 (e.g., a force sufficient to break the brittle container and release the battery electrolyte from the brittle container into the battery). In addition to preventing unwanted electrolyte leakage into the second chamber of the indicator body, the O-ring 38c is made of a resilient and robust material (e.g., silicone, rubber, etc.) and has a selected Young's modulus and other O-ring material properties (e.g., physical and chemical properties, etc.) to maintain the electrolyte in place within the battery compartment 30.

[0070] like Figure 3As shown, the piston base 38, located close to the battery compartment base 30a, further seals the battery compartment base through an opening 30b. The electrolyte 34a (referred to herein as "battery electrolyte") of maximum usable volume is transferred from the broken, brittle container 34 (containing the electrolyte) into the battery compartment 30 to react with the battery plates 32 and form a working cell 33 that is now active and / or "enabled". The working cell 33 is configured to generate current along the battery lead 33a, thereby enabling the lighting device 40 and emitting a beam 41 from the lighting device 40 (which may be, for example, an LED) in an operational (and / or "active" and / or "enabled") thermal indicator state.

[0071] like Figure 3 As further shown, similar to the sealing function of the piston base O-ring 38c, the piston rod O-ring 38d is located at the first end of the indicator body, passing through the opening wall 26b, and is configured to contact the exposed piston rod 39. The piston rod O-ring 38d is also configured and positioned to form a substantially leak-proof seal, thereby facilitating the retention of the battery electrolyte in the battery 33 and within the battery compartment 30. Like the piston base O-ring 38c, the piston rod O-ring 38d may be made of a resilient and robust material and / or may otherwise include resilient and robust materials (e.g., silicone, rubber, etc.), which may have a selected Young's modulus and other O-ring material properties (e.g., physical and chemical properties, etc.) to maintain the electrolyte in place within the battery compartment 30.

[0072] Figure 4A and Figure 4B Further aspects of the invention are illustrated, including the self-powered aircraft cabin thermal indicator 20 of the invention, which may further include one or more integrated heat transfer elements to further improve the efficiency and sensitivity of the thermal indicator of the invention by concentrating and storing the effects and influences of temperature rises occurring near the thermal indicator—according to one example of the invention.

[0073] Figure 4A This is a cross-sectional side view of the aircraft cabin thermal indicator 20 of the present invention, which is fixedly and detachably attached to and extends through the aircraft component substrate 18 in a suitable position, the aircraft component substrate 18 having an outer surface 18a and an inner surface 18b. Figure 4A It shows Figure 2 A self-powered aircraft cabin thermal indicator 20 of the type shown and including similar component elements with similar designations. Figure 4AThe thermal indicator 20 is shown to also include an integrated heat transfer element in the form of a heat-conducting tube 50, which is positioned and otherwise integrated within (and can be securely attached thereto) the second chamber 25b of the indicator body of the thermal indicator 20. The heat-conducting tube 50 includes a first end 50a extending into the second chamber 25b of the indicator body and positioned such that the outer periphery of the heat-conducting tube wall 54 is positioned abutting and / or substantially adjacent to the degradable retainer 44. In one example of the invention, the heat-conducting tube 50 is in direct contact with the degradable retainer 44. The second end 50b of the heat-conducting tube is shown in… Figure 4A In the middle, the selection distance extends from the second chamber 25b of the indicator body and exceeds the base 29 of the second end of the indicator body. For example... Figure 4A As shown, the heat guide tube 50 may also include a "hot air" outlet 66 located at the first end 50a of the heat guide tube, the "hot air" outlet 66 being able to further guide, circulate and otherwise distribute heat to the degradable retainer 44.

[0074] Figure 4B Showing Figure 4A The type shown can be incorporated into Figure 4A A perspective view of a section of the heat guide tube 50 in the shown heat indicator 20. Or as... Figure 4B As shown, the heat-conducting tube 50 may be of a generally cylindrical shape, with its outer periphery dimensionally set such that the heat-conducting tube can substantially "fill" or otherwise substantially occupy the available area present within the second cavity of the indicator body. The outer surface of the edge of the tube fin 52 extends outward from the outer surface of the heat-conducting tube wall 54 of the heat-conducting tube 50 (forming the outer periphery of the heat-conducting tube 50), thereby directly contacting the degradable retainer 44, which comprises a cryogenic material used to manufacture the degradable retainer element. According to an aspect of the invention, the outer edge of the tube fin 52 is equivalently referred to herein as the outer periphery of the heat-conducting tube wall. A further aspect of the invention also contemplates incorporating a heat-conducting tube excluding the tube fin 52, wherein the heat-conducting tube wall is located very close to and adjacent to the degradable retainer. In another example of the invention, the outer periphery of the heat-conducting tube wall is positioned to directly contact the degradable retainer (e.g., in the absence of the tube fin 52).

[0075] like Figure 4A and Figure 4B As shown, the heat guide tube 50 can be "hollowed out" to further include a heat guide tube central path 56 extending longitudinally along the length of the heat guide tube 50, and the heat guide tube central path 56 is defined by the inner surface of the heat guide tube inner wall 54.

[0076] like Figure 4A and Figure 4BAs further shown, the tube fins 52 extend outward a selected distance from the inner wall 54 of the heat guide tube, wherein the tube fins 52 are configured to facilitate heat radiation, which can be absorbed by the heat guide tube 50 (e.g., by the heat guide tube of a heat indicator in an aircraft cabin) and then directed and / or “radiated” to the degradable retainer 44 located within the second chamber 25b of the indicator body of the heat indicator 20. Figure 4A As shown, the second end 50b of the heat-conducting conduit extends from the base 29 of the second end of the heat indicator body to enhance the collection of heat that may exist and otherwise be generated outside and near the heat indicator 20 and outside and near the second end 50b of the heat-conducting conduit (e.g., heat that may accumulate in the aircraft cabin, where the second end of the indicator body may extend into the aircraft cabin, thereby exposing the second end of the heat indicator to the aircraft cabin environment and the temperatures present within the aircraft cabin environment). The heat-conducting conduit of the present invention may be made of a material with high heat transfer capacity, which may include metals and metal alloys, and includes, for example, copper, copper alloys, and combinations thereof.

[0077] According to an aspect of the invention, the power source for operating the self-powered aircraft compartment thermal indicator activated by the invention resides only within the thermal indicator, and in a battery formed by combining battery electrolyte released from a broken, brittle container with a battery panel within the thermal indicator's battery compartment, which resides within the thermal indicator as needed and in the presence of a threshold temperature. According to an aspect of the invention, the type of battery formed in the thermal indicator of the invention can be a fuze battery.

[0078] When activated and operated, and depending on the intensity of the light beam(s) emitted from the illumination equipment, the self-powered aircraft cabin thermal indicator of the present invention is configured to deliver a visually detectable signal at least to personnel located at or very close to a thermal detector immediately outside the monitored aircraft cabin. That is, the thermal indicator of the present invention provides significant advantages to ground personnel when monitoring potentially overheated aircraft cabins, as the visual indication of an overheated cabin is visible to ground personnel both on the ground and outside the aircraft during non-flight periods, and when personnel may not be in the cockpit and have no access to the flight control panels within the cockpit. According to one example of the invention, the flash of light emitted by the illumination equipment of the thermal indicator of the present invention, powered by the self-powered aircraft cabin thermal indicator of the present invention, can visually indicate and warn personnel of the presence of excessively high temperatures (e.g., temperatures exceeding a selected temperature threshold), and can visually communicate to ground personnel (e.g., who can view the visual indication and are warned via a visual “temperature alarm”) the excessively high temperatures experienced and otherwise being subjected to by the internal cabin within the aircraft and the area immediately adjacent to the flashing thermal indicator within the internal cabin that require attention.

[0079] Therefore, the self-powered aircraft cabin thermal indicator of the present invention, configured to convey thermal information at the location of a potential thermal event, is distinctly different from typical aircraft thermal detector systems. Typical aircraft thermal detector systems are connected in series and connected or otherwise communicate with a large number of wiring leading to the aircraft power supply and to each other. They also require associated hardware, software, mechanical linkages and mountings, processors, readers, control panels, and other centralized system components that relay the sensed thermal information to a centrally located location within the aircraft (e.g., the cockpit panel). This significantly increases the cost and weight of the aircraft, which in turn increases the operating costs and otherwise adversely affects the aircraft's flight range, increases fuel consumption, and reduces available passenger seating capacity.

[0080] According to an aspect of the invention, once activated, the activated self-powered aircraft cabin thermal indicator cannot be returned to an inactive state—once the degradable retainer degrades and releases the spring, the spring is then allowed to exert a force on the piston that causes the brittle container holding the battery electrolyte to break. According to a further aspect of the invention, the thermal indicator is detachably fixed and positioned in the aircraft structure such that the activated thermal indicator can be removed from the aircraft structure and replaced with another "inactive" thermal indicator.

[0081] Figure 4C This is a box diagram outlining a system for indicating and determining the presence of a temperature exceeding a threshold temperature within an area of ​​the aircraft's interior located near the external location of the aircraft. According to aspects of the invention, and as... Figure 4C As shown, system 58 includes aircraft 10, aircraft 10 also includes aircraft component substrate 18, and aircraft component substrate 18 also includes a self-powered aircraft cabin thermal indicator 20 of the type described herein.

[0082] Figure 5A and Figure 5B A test method (e.g., inspection and / or quality control scheme method) according to an aspect of the invention is shown for testing the force load / release / activation of the thermal indicator of the invention. Figure 5A And to test the satisfactory operation and / or functional function of the lighting fixture components of the thermal indicator in situ and during installation and / or during storage in stock. Figure 5B This includes when the thermal indicator battery is inactive.

[0083] like Figure 5AAs shown, system 60, referred to herein equivalently as force gauge test system 60, is illustrated in the form of a test method for the thermal indicator of the present invention, used to determine the spring release force that the degradable retainer will release at a threshold temperature, and to test whether the spring will release as expected and apply a suitable force to the piston to cause the brittle battery electrolyte container to rupture when the thermal indicator is at or otherwise exposed to an elevated temperature indicating an increase above a selected threshold temperature. Figure 5A As shown, a force gauge 64 (referred to herein as force meter 64) may be positioned within a cap 62 to be adapted to the thermal indicator 20, wherein the force gauge is configured to assess and otherwise measure the release force or potential force of the spring 42. The force gauge 64 is positioned to communicate with a data acquisition device / processor 65 via data lead 64a, and a display 68 is configured to relay signals and information generated by the force gauge and interpreted by the processor via data line 67 (e.g., to observers, technicians, etc.).

[0084] According to the test scheme of the present invention for testing the operational force of the self-powered aircraft cabin thermal indicator 20, a test fixture is provided to support the thermal indicator and a data acquisition device 65 including a processor / computer is attached to the test fixture. Data acquisition software is run to record and display the data obtained through testing. A temperature sensor may be located near the thermal element of the thermal guide element to ensure that the thermal indicator is correctly calibrated and connected to the data acquisition device. Temperature changes are established by heating or cooling the sensor to verify the functional operation of the temperature sensor. A force gauge is placed in contact with the first end of the thermal indicator and further in contact with the first end of the piston rod at the illumination device (in the inactive state, and the force gauge is configured to remain substantially flush with the first end of the thermal indicator body). The force gauge is set to "zero" or otherwise calibrated according to the manufacturer's instructions. A heat source, which may be, for example, a hot air blower 46 (equivalently referred to as a "hot air gun"), is positioned to provide heat to the thermal indicator and the thermal indicator force test / verification system. Heat is applied to the thermal indicator's thermal guide tube, and the heat directed from the heat source is evenly distributed on the thermal indicator's thermal guide tube. Heating time is marked and recorded using a timing device (e.g., a stopwatch). When the temperature approaches and reaches the threshold temperature of the thermal indicator, the time is marked, and an internal spring releases the force generated, which is recorded on a force gauge. The maximum force applied to the force gauge during spring release is displayed on the system display and otherwise shown and recorded. Temperature versus spring release force over time can be recorded and plotted.

[0085] Figure 5BThis diagram illustrates an in-situ test of the self-powered aircraft thermal indicator 20 disclosed in this invention, which is mounted in a fixed and removable position within an aircraft component substrate 18. According to the test system 70, to assess the normal operating condition of the thermal indicator during, for example, routine maintenance and / or inspection of an aircraft component including the thermal indicator, the positive ("+") terminal of the battery 72 is placed in contact with the exposed pad of the thermal indicator via test lead 76, and the negative ("-") terminal of the battery 72 is placed in contact via test lead 74. When the current supplied by the battery 72 powers the thermal indicator, a flash at the illumination device 40 will indicate that the illumination device is functioning normally and confirm that the circuitry within the thermal indicator is active.

[0086] Figure 6 This is a representative cross-sectional side view of a section of the leading edge 16 of the aircraft wing 14. The leading edge 16 may be a base material 18 of the aircraft component described herein and may include the outer surface 18a of the aircraft component base material. Figure 6 The wing leading edge 16 shown also includes a wing leading edge nacelle 16a, and inside the nacelle 16a, there is also a wing leading edge air duct 16b having multiple wing leading edge air duct connectors 16c (e.g. Figure 7 (As shown). Figure 6 Also shown is the self-powered aircraft thermal indicator 20 of the present invention, detachably attached to an aircraft component substrate, wherein the first end of the indicator body is at least partially visible at the outer surface 18a of the aircraft component substrate 18, which is shown in the form of a wing leading edge component 16. That is, as Figure 6 As shown, the thermal indicator 20 is positioned such that the first end 26 of the "indication" indicator body is visible outside the outer surface 18a of the aircraft component substrate 18, while the second end 28 of the "temperature sensing" indicator body is located in and otherwise extends into the leading edge pod 16a of the aircraft wing and is positioned therein.

[0087] Figure 7 It is configured to be in Figure 6 A perspective view of a leading-edge component 16d of an aircraft wing, of the type shown, supporting a leading-edge bleed air duct 16b within a leading-edge nacelle 16a. The leading-edge bleed air duct 16b is configured to receive hot bleed air and guide it along a path that safely disperses it to an outlet (not shown). In the event that one or more of the plurality of hot bleed air duct joints 16c wear out due to use or otherwise leak hot bleed air from the duct (e.g., hot bleed air passing through the leading-edge bleed air duct 16b), the hot bleed air leaks out of the duct and enters and occupies the leading-edge nacelle 16a, thereby significantly increasing the temperature of the ambient air within the leading-edge nacelle 16a of the wing leading edge 16.

[0088] According to the present invention, and as Figure 6 As shown, in the event of a leak of warm / or hot bleed airflow 17 from the wing leading edge bleed air duct 16b, the second end 28 of the indicator body will be exposed to the increased temperature within the wing leading edge compartment 16a. If the temperature of the air within the wing leading edge compartment rises to a selected acceptable threshold temperature (e.g., ranging from about 140℉ to about 165℉), the self-powered aircraft compartment thermal indicator 20 will be activated when the degradable retainer releases an internal spring, thereby driving an internal piston into a position where the released spring force is sufficient to rupture the battery electrolyte container and release the battery electrolyte from the container, and an activated battery is formed in the indicator that powers an illumination device in the first end of the indicator, which is visible from the outside of the aircraft component displayed in the form of the wing leading edge 16 and otherwise visually detectable (e.g., visually detectable by ground personnel located outside and "outside" the aircraft). According to an aspect of the invention, during operation, and when such a warning or “visual alarm” (e.g., a flash) is issued from the activated thermal indicator 20, the person visually detecting the flash of the thermal indicator 20 will be aware of an undesirable temperature rise inside the cabin of the aircraft component housing the thermal indicator (e.g., in this case, the wing leading edge cabin 16a).

[0089] According to aspects of the invention, a self-powered aircraft thermal indicator can be detachably attached to an aircraft component, and visual indications of thermal events, servicing, inspection, rework, and replacement after a thermal event can be made, for example, by ground personnel outside the aircraft. Furthermore, after the thermal indicator is removed, an access point is provided for inspection of the aircraft compartment housing the thermal indicator, which allows for more efficient and cost-effective inspection of the aircraft compartment from the outside by ground personnel.

[0090] Furthermore, the "single-use" nature of the thermal indicator of this invention—which allows for easy replacement of detachably attached, self-powered aircraft thermal indicators—further facilitates the advantageous organization and, in other ways, greatly simplifies the maintenance of a stockpile of diverse thermal indicators for various locations on an aircraft, which can be installed in diverse aircraft components. Among these diverse thermal indicators of this invention, the diverse types have different "trigger" or threshold temperatures—which can be targeted and otherwise customized for specific uses and locations. That is, the thermal indicator "types" of this invention—each type having a diverse trigger threshold temperature—can be distinguished according to their intended location and, in other ways, categorized according to their final location destination on the aircraft to be activated at a diverse threshold temperature. For example, according to an aspect of the invention, thermal indicators with different activation threshold temperatures can be individually identified by easily identifiable markings, which may include, for example, “color coding” or other quickly identifiable features (to ensure that a particular thermal indicator is used correctly at a particular aircraft location according to the threshold temperature established for a particular aircraft component compartment), thereby facilitating and / or organizing the maintenance of an inventory of available and easily identifiable thermal indicators.

[0091] Figure 8 , Figure 9 and Figure 10 This is a flowchart outlining the method of the present invention. Figure 8This invention outlines a method 100 for detecting a threshold temperature in an internal region of an aircraft component outside an aircraft, the internal region of which may include an aircraft cabin located near the exterior of the aircraft. The method 100 includes positioning a self-powered aircraft cabin thermal indicator 20 within the aircraft component, wherein the aircraft component includes an outer surface (e.g., an external surface of the aircraft), and the outer surface of the aircraft component is positioned adjacent to the internal region of the aircraft component, which may include an aircraft cabin. The aircraft cabin thermal indicator 20 includes an indicator body 22, the indicator body 22 including an indicator body length (“l”). The indicator body also includes an indicator body interior 22a, an indicator body exterior 22b, a first end 26 (e.g., an indicating side), a second end 28 (e.g., a temperature sensing side), a base 29 of the second end, and an internal piston 36. The internal piston also includes a piston base 38, wherein the piston base includes a first side 38a and a second side 38b, and the internal piston also includes a piston rod 39, wherein the piston rod includes a first end 39a and a second end 39b, and the second end of the piston rod communicates at least with the first side 38a of the piston base. The indicator body also includes an indicator body wall 24, wherein the indicator body wall extends along the length of the indicator body from the first end 26 to the second end 28, and wherein the indicator body wall includes a second side (e.g., an "outer surface") 24b at the outer 22b of the indicator body and a first side (e.g., an "inner surface") 24a at the inner 22a of the indicator body. The indicator body also includes a battery compartment 30, which includes a plurality of battery panels, wherein the battery compartment includes a battery compartment base 30a, and wherein the battery compartment is defined by the battery compartment base 30a and the inner surface 24a of the indicator body wall. The indicator body also includes a first chamber 25a of the indicator body defined by the inner surface 24a of the indicator body wall, the first side 38a of the piston base, and the base 30a of the battery compartment, wherein the first chamber of the indicator body includes a brittle reservoir 34, and wherein the brittle reservoir contains a certain volume of battery electrolyte 34a. According to aspects of the invention, the brittle reservoir is equivalently referred to herein as a "brittle container".

[0092] The indicator body also includes a second chamber 25b defined by an inner surface 24a of the indicator body wall and a second side 38b of the piston base. The second chamber 25b includes a spring 42, comprising a first end 42a fixedly attached to the piston base 38, and a second end 42b adjacent to a second end base 29 of the indicator body. The second chamber also includes a degradable retainer 44 in communication with the spring 42. The degradable retainer is configured to hold the spring 42 in a compressed state within a first temperature range, and is configured to degrade at a threshold temperature within a second temperature range. The threshold temperature is within a second temperature range. The degradable retainer is further configured to hold the spring in a compressed state within the first temperature range, and to release the spring from the compressed state to an expanded state at the threshold temperature within the second temperature range, wherein the threshold temperature is higher than the first temperature range.

[0093] Method 100 further includes degrading the degradable retainer 104 in the presence of a cabin temperature exceeding a threshold temperature, releasing the spring from a compressed spring state 106 to an expanded spring state, conveying the piston from an initial piston position 108 to a piston deployment position, causing the brittle reservoir to fracture 110 to form a fractured brittle reservoir, releasing at least a portion of the predetermined volume of battery electrolyte from the fractured brittle reservoir 112, guiding at least a portion of the predetermined volume of battery electrolyte 114 into the battery compartment to form a battery, wherein the battery is configured to deliver the generated current, guiding 116 the first end of the piston rod through a first end through-hole of the indicator body to a selected distance beyond the outer surface of the aircraft component, and guiding the current from the battery 118 to a light emitting device to emit light from the light emitting device.

[0094] Figure 9 The present invention method 200 is summarized, which includes the method summarized in method 100 and Figure 8 The features shown in the figure and disclosed herein, wherein the method 200 of the invention further includes light emitted from an optical emitting device by visual detection 202 on the exterior of the aircraft, wherein the visual detection indicates the presence of at least a threshold temperature in the aircraft cabin located near or otherwise in direct communication with the aircraft cabin thermal indicator.

[0095] Figure 10 The present invention method 300 is summarized, comprising the methods summarized in methods 100 and 200 respectively and Figure 8 , Figure 9 The features shown in the figure and described herein include, wherein the method 300 of the invention further includes removably positioning 302 of a self-powered aircraft cabin thermal indicator in an aircraft component.

[0096] Figure 8 , Figure 9 and Figure 10 The methods of the invention summarized in the text and described herein can implement the methods described herein and at least in Figure 2 , Figure 3 , Figure 4A , Figure 4B , Figure 5A , Figure 5B and Figure 6 The invention is shown in the figure as a self-powered aircraft cabin thermal indicator.

[0097] Specifically, the present invention includes the following embodiments: Implementation method 1. A self-powered aircraft cabin thermal indicator (20), comprising: Indicator body (22), which includes an indicator body length, the indicator body comprising: Inside the indicator body (22a); External part of the indicator body (22b); First end of indicator body (26); The second end of the indicator body (28); The base of the second end of the indicator body (29); An internal piston (36) includes a piston base (38), the piston base includes a first side (38a) and a second side (38b) of the piston base, and the internal piston also includes a piston rod (39), the piston rod includes a first end (39a) and a second end (39b) of the piston rod, the first end of the piston rod is connected to a visually detectable signal transmission device (40), and the second end of the piston rod is connected to at least the first side (38a) of the piston base; The indicator body wall (24) extends from the first end (26) of the indicator body along the length of the indicator body to the second end (28) of the indicator body. The indicator body wall includes an outer surface (24b) of the indicator body wall outside the indicator body (22b) and an inner surface (24a) of the indicator body wall inside the indicator body (22a). A battery compartment (30) including a battery compartment base (30a) and the inner surface (24a) of the indicator body wall; The first chamber (25a) of the indicator body is defined by the inner surface (24a) of the indicator body wall, the first side (38a) of the piston base and the base (30a) of the battery compartment. The first chamber of the indicator body includes a brittle reservoir (34) that contains a certain volume of battery electrolyte (34a). A second chamber (25b) of the indicator body, defined by the inner surface (24a) of the indicator body wall and the second side (38b) of the piston base, includes a spring (42) comprising a first end (42a) fixedly attached to the piston base (38) and a second end (42b) positioned adjacent to the second end base (29) of the indicator body; and A degradable retainer (44), connected to the spring (42), is configured to hold the spring (42) in a compressed spring state within a first temperature range, and is configured to degrade at a threshold temperature within a second temperature range. The degradable retainer is also configured to hold the spring in a compressed spring state within the first temperature range, and to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range. The threshold temperature is higher than the first temperature range.

[0098] Implementation 2. The self-powered aircraft cabin thermal indicator according to Implementation 1, wherein the visually detectable signal transmission device (40) is at least one of an illumination device and a light-emitting diode.

[0099] Implementation 3. The self-powered aircraft cabin thermal indicator according to Implementation 1, wherein the battery cabin further includes a plurality of battery panels (32).

[0100] Embodiment 4. The self-powered aircraft cabin thermal indicator according to Embodiment 1, wherein the degradable retainer (44) comprises at least one of a cryogenic alloy and a wax, wherein the at least one of the cryogenic alloy and the wax, and the degradable retainer comprises a melting point ranging from about 140℉ to about 165℉.

[0101] Embodiment 5. The self-powered aircraft cabin thermal indicator according to Embodiment 4, wherein the cryogenic alloy comprises a cryogenic metal alloy comprising at least one of the following: bismuth, lead, tin, indium, cadmium, thallium, gallium, and combinations thereof, wherein the cryogenic alloy has a melting point ranging from about 140℉ to about 165℉.

[0102] Embodiment 6. The self-powered aircraft cabin thermal indicator according to Embodiment 5, wherein the cryogenic alloy comprises at least one of the following: Los metal, Shilosifer, Wood alloy, Field metal, Shilolu 136, Shilolu 117, gallium, and combinations thereof.

[0103] Embodiment 7. According to Embodiment 3, the self-powered aircraft cabin thermal indicator is configured in the presence of the electrolyte (34a) to form a battery (33) configured to deliver current.

[0104] Embodiment 8. The self-powered aircraft cabin thermal indicator according to Embodiment 7, wherein the battery is a fuze battery.

[0105] Implementation 9. The self-powered aircraft cabin thermal indicator according to Implementation 1 further includes a thermal guide tube (50), the thermal guide tube including a first end (50a), a second end (50b) and a thermal guide tube wall (54), the first end of the thermal guide tube being integrated into the second chamber of the indicator body, and the thermal guide tube wall being positioned adjacent to the degradable retainer.

[0106] Embodiment 10. Aircraft wing components (14) (16) (16a) (16b) (16c) including a self-powered aircraft cabin thermal indicator as described in Embodiment 1.

[0107] Embodiment 11. An aircraft (10) comprising a self-powered aircraft cabin thermal indicator as described in Embodiment 1.

[0108] Implementation 12. An aircraft cabin temperature indication system (58) for visually detecting temperatures above a threshold inside an aircraft cabin near the exterior of the aircraft, the aircraft cabin temperature indication system comprising: A self-powered aircraft cabin thermal indicator (20), which is detachably attached to aircraft components (14)(16)(16a)(16b)(16c), the self-powered aircraft cabin thermal indicator comprising: Indicator body (22), which includes an indicator body length (“l”), the indicator body comprising: Inside the indicator body (22a); External part of the indicator body (22b); The first end (26) of the indicator body is visible from the outside of the aircraft; The second end (28) of the indicator body is positioned inside the aircraft cabin and extends from the first end of the thermal indicator to a selected distance inside the aircraft cabin; The base of the second end of the indicator body (29); An internal piston (36) includes a piston base (38), the piston base includes a first side (38a) and a second side (38b) of the piston base, and the internal piston also includes a piston rod (39), the piston rod includes a first end (39a) and a second end (39b) of the piston rod, the second end of the piston rod being in communication with at least the first side (38a) of the piston base; The indicator body wall (24) extends from the first end (26) of the indicator body along the length of the indicator body to the second end (28) of the indicator body. The indicator body wall includes an outer surface (24b) of the indicator body wall outside the indicator body (22b) and an inner surface (24a) of the indicator body wall inside the indicator body (22a). A battery compartment (30) configured to house a battery (33) configured to deliver current along a circuit, the battery compartment including a plurality of battery panels (32), the battery compartment including a battery compartment base (30a), the battery compartment being defined by the battery compartment base (30a) and the inner surface (24a) of the indicator body wall; The first chamber (25a) of the indicator body is defined by the inner surface (24a) of the indicator body wall, the first side (38a) of the piston base and the base (30a) of the battery compartment. The first chamber of the indicator body includes a brittle reservoir (34) that contains a certain volume of battery electrolyte (34a). A second chamber (25b) of the indicator body, defined by the inner surface (24a) of the indicator body wall and the second side (38b) of the piston base, includes a spring (42) comprising a first end (42a) fixedly attached to the piston base (38) and a second end (42b) positioned adjacent to the second end base (29) of the indicator body; and A degradable retainer (44) is connected to the spring (42), the degradable retainer being configured to hold the spring (42) in a compressed spring state within a first temperature range, the degradable retainer (44) being configured to degrade at a threshold temperature within a second temperature range, the degradable retainer being further configured to hold the spring in a compressed spring state within the first temperature range, and the degradable retainer being further configured to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range; A visually detectable signal transmission device (40), located at the first end of the indicator body, communicates with the circuitry and is also configured to be visually detectable outside the aircraft; and The signal transmission device (40) is configured to be activated at and above the threshold temperature.

[0109] Embodiment 13. The aircraft cabin temperature indication system according to Embodiment 12, wherein the signal transmission device includes at least one of lighting equipment and light-emitting diodes.

[0110] Embodiment 14. The aircraft cabin temperature indication system according to Embodiment 12, wherein the signal transmission device is configured to emit a light beam in response to the second end of the indicator being exposed to a threshold temperature ranging from about 140℉ to about 165℉.

[0111] Embodiment 15. The aircraft cabin temperature indication system according to Embodiment 12, wherein the aircraft cabin thermal indicator is a detachable aircraft cabin thermal indicator.

[0112] Embodiment 16. The aircraft cabin temperature indication system according to Embodiment 12, wherein the battery is a fuze battery configured to be activated at the threshold temperature.

[0113] Implementation 17. A method (100) for indicating, from outside the aircraft, that the temperature inside an aircraft component compartment exceeds a threshold temperature, the method comprising: A cabin thermal indicator is positioned (102) within a cabin component, the cabin component including an outer surface of the cabin, the outer surface of the cabin being positioned adjacent to the cabin, the cabin thermal indicator comprising: Indicator body (22), which includes indicator body length (l), said indicator body includes: Inside the indicator body (22a); External part of the indicator body (22b); First end (26) of the indicator body (indicator side); The first end through hole (26a) of the indicator body; The second end of the indicator body (28); The base of the second end of the indicator body (29); An internal piston (36) includes a piston base (38), the piston base includes a first side (38a) and a second side (38b) of the piston base, the internal piston also includes a piston rod (39), the piston rod includes a first end (39a) and a second end (39b) of the piston rod, the second end of the piston rod is at least in communication with the first side (38a) of the piston base, and the first end of the piston rod includes a light emitting device (40). The indicator body wall (24) extends from the first end (26) of the indicator body along the length of the indicator body to the second end (28) of the indicator body and the base (29) of the second end of the indicator body. The indicator body wall includes the outer surface (24b) of the indicator body wall at the outside (22b) of the indicator body and the inner surface (24a) of the indicator body wall at the inside (22a) of the indicator body. A battery compartment (30) comprising a plurality of battery panels, the battery compartment including a battery compartment base (30a) defined by the battery compartment base (30a) and the inner surface (24a) of the indicator body wall; The first chamber (25a) of the indicator body is defined by the inner surface (24a) of the indicator body wall, the first side (38a) of the piston base and the base (30a) of the battery compartment. The first chamber of the indicator body includes a brittle reservoir (34) that contains a certain volume of battery electrolyte (34a). A second chamber (25b) of the indicator body, defined by the inner surface (24a) of the indicator body wall and the second side (38b) of the piston base, includes a spring (42) comprising a first end (42a) fixedly attached to the piston base (38) and a second end (42b) positioned adjacent to the second end base (29) of the indicator body; and A degradable retainer (44) is connected to the spring (42), the degradable retainer is configured to hold the spring (42) in a compressed spring state within a first temperature range, the degradable retainer (44) is configured to degrade at a threshold temperature within a second temperature range, the degradable retainer is also configured to release the spring from the compressed spring state in the first temperature range to an expanded spring state at the threshold temperature within the second temperature range, the threshold temperature being higher than the first temperature range; In the event of a cabin temperature exceeding the threshold temperature, the degradable retainer is degraded (104). Release the spring from the compressed spring state (106) to the expanded spring state; The piston is transported from its initial position (108) to its deployment position; The brittle reservoir is fractured (110) to form a fractured brittle reservoir; At least a portion of the battery electrolyte of a given volume is released from the ruptured brittle reservoir (112). At least a portion of the battery electrolyte of a given volume is directed (114) into the battery compartment to form a battery, the battery being configured to deliver the generated current; Guide (116) The first end of the piston rod passes through the through hole at the first end of the indicator body to a selected distance beyond the outer surface of the aircraft component; and Current is directed from the battery (118) to the light emitting device to emit light from the light emitting device.

[0114] Implementation 18. The method (200) according to implementation 17 further includes visually detecting light emitted from the light emitting device on the exterior of the aircraft (202).

[0115] Embodiment 19. The method (300) according to Embodiment 18 further includes detachably positioning (302) the aircraft cabin thermal indicator in the aircraft component.

[0116] Implementation 20. The method (200) according to Implementation 18, wherein visual detection of illumination light from the aircraft cabin thermal indicator on the exterior of the aircraft indicates that at least the threshold temperature within the aircraft components is present.

[0117] As used herein, the term "basically" means that a particular physical element, physical location, physical shape, orientation, etc., is almost completely or nearly completely realized. That is, for example, according to aspects of the invention, a "basically" completely enclosed compartment means a compartment that is nearly and / or almost completely and thoroughly enclosed.

[0118] Of course, various aspects of the invention can be practiced in ways other than those specifically set forth herein without departing from the essential features of this disclosure. All aspects of the invention are to be considered exemplary rather than restrictive in all respects, and all variations falling within the meaning and scope of the appended claims are intended to be encompassed therein.

Claims

1. A self-powered aircraft cabin thermal indicator (20), comprising: Indicator body (22), which includes an indicator body length, the indicator body comprising: Inside the indicator body (22a); External part of the indicator body (22b); First end of indicator body (26); The second end of the indicator body (28); The base of the second end of the indicator body (29); An internal piston (36) includes a piston base (38), the piston base includes a first side (38a) and a second side (38b) of the piston base, and the internal piston also includes a piston rod (39), the piston rod includes a first end (39a) and a second end (39b) of the piston rod, the first end of the piston rod is connected to a visually detectable signal transmission device (40), and the second end of the piston rod is connected to at least the first side (38a) of the piston base; The indicator body wall (24) extends from the first end (26) of the indicator body along the length of the indicator body to the second end (28) of the indicator body. The indicator body wall includes an outer surface (24b) of the indicator body wall outside the indicator body (22b) and an inner surface (24a) of the indicator body wall inside the indicator body (22a). A battery compartment (30) including a battery compartment base (30a) and the inner surface (24a) of the indicator body wall; The first chamber (25a) of the indicator body is defined by the inner surface (24a) of the indicator body wall, the first side (38a) of the piston base and the base (30a) of the battery compartment. The first chamber of the indicator body includes a brittle reservoir (34) that contains a certain volume of battery electrolyte (34a). A second chamber (25b) of the indicator body, defined by the inner surface (24a) of the indicator body wall and the second side (38b) of the piston base, includes a spring (42) comprising a first end (42a) fixedly attached to the piston base (38) and a second end (42b) positioned adjacent to the second end base (29) of the indicator body; and A degradable retainer (44), connected to the spring (42), is configured to hold the spring (42) in a compressed spring state within a first temperature range, and is configured to degrade at a threshold temperature within a second temperature range. The degradable retainer is also configured to hold the spring in a compressed spring state within the first temperature range, and to release the spring from the compressed spring state to an expanded spring state at the threshold temperature within the second temperature range. The threshold temperature is higher than the first temperature range.

2. The self-powered aircraft cabin thermal indicator according to claim 1, wherein the visually detectable signal transmission device (40) is at least one of an illumination device and a light-emitting diode.

3. The self-powered aircraft cabin thermal indicator according to claim 1, wherein the battery cabin further comprises a plurality of battery panels (32).

4. The self-powered aircraft cabin thermal indicator according to claim 1, wherein the degradable retainer (44) comprises at least one of a cryogenic alloy and a wax, wherein the at least one of the cryogenic alloy and the wax, and the degradable retainer comprises a melting point ranging from about 140℉ to about 165℉.

5. The self-powered aircraft cabin thermal indicator of claim 4, wherein the cryogenic alloy comprises a cryogenic metal alloy comprising at least one of the following: bismuth, lead, tin, indium, cadmium, thallium, gallium, and combinations thereof, wherein the cryogenic alloy has a melting point ranging from about 140℉ to about 165℉.

6. The self-powered aircraft cabin thermal indicator according to claim 5, wherein the cryogenic alloy comprises at least one of the following: Los Metal, Shilosifer, Wood alloy, Field Metal, Shilolu 136, Shilolu 117, gallium, and combinations thereof.

7. The self-powered aircraft cabin thermal indicator according to claim 3, wherein the battery panel (32) is configured in the presence of the electrolyte (34a) to form a battery (33) configured to deliver current.

8. The self-powered aircraft cabin thermal indicator according to claim 7, wherein the battery is a fuze battery.

9. The self-powered aircraft cabin thermal indicator according to claim 1, further comprising a thermal guide tube (50), the thermal guide tube comprising a first end (50a), a second end (50b) and a thermal guide tube wall (54), the first end of the thermal guide tube being integrated into the second chamber of the indicator body, and the thermal guide tube wall being positioned adjacent to the degradable retainer.

10. Aircraft wing components (14) (16) (16a) (16b) (16c) comprising a self-powered aircraft cabin thermal indicator as claimed in claim 1.

Images