Patent Description:
An aircraft such as a passenger jet aircraft typically includes insulation blankets that line an interior of the aircraft's fuselage. The insulation blankets can be made of fiberglass or other materials and provide both acoustic and thermal insulation for the aircraft.

During travel at high altitudes, air within an aircraft (e.g., a passenger jet aircraft) can become high in humidity and a fuselage of the aircraft can become cold. The combination of humidity and cold can cause water from the air to condense and/or freeze to the fuselage. As the aircraft lowers its altitude, this water flows downward due to gravity, which can cause an accumulation of moisture on and in the insulation blankets, as well as in other areas of the aircraft. The accumulation of moisture on and in the insulation blankets can saturate the insulation blankets, thereby undesirably increasing weight of the aircraft and potentially creating an environment in which mold can form. In addition, the accumulation of moisture can potentially cause damage to areas of the aircraft near the insulation blankets or in other areas. For example, moisture that accumulates on metal areas can corrode those surfaces. As another example, moisture that accumulates on composite laminate areas can egress into the composite laminate and then, if the moisture becomes cold and freezes, the moisture can expand and cause delamination.

Existing systems for relieving the aircraft of moisture typically include using passive physical structures within the aircraft as dams for blocking moisture flow into certain areas of the aircraft and as channels for routing water to drain masts where the water can exit the aircraft. However, these existing systems can be inefficient, can sometimes add weight and complexity to the aircraft, and might not alleviate or prevent moisture buildup in the aircraft.

What is needed is an efficient, reliable system for moisture control in an aircraft.

In accordance with its abstract, <CIT> states ' An aircraft may include a fuselage, and a moisture accumulation prevention system that prevents moisture from accumulating on at least one structure within the fuselage. The moisture accumulation prevention system includes at least one ultrasonic element coupled to the structure(s). The ultrasonic element(s) operates at a frequency that prevents moisture particles from adhering to a surface of the structure(s).

The addition to the state of the art is set out in the claims.

The illustrative examples, however, as well as a preferred mode of use, further objectives and descriptions thereof, will best be understood by reference to the following detailed description of an illustrative example of the present disclosure when read in conjunction with the accompanying drawings, wherein:.

Disclosed examples will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all of the disclosed examples are shown. Indeed, several different examples may be described and should not be construed as limited to the examples set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete and will fully convey the scope of the disclosure to those skilled in the art.

By the terms "substantially," "about," and "proximate" used herein, it is meant that the recited characteristic, parameter, or value need not be achieved exactly, but that deviations or variations, including for example, tolerances, measurement error, measurement accuracy limitations and other factors known to skill in the art, may occur in amounts that do not preclude the effect the characteristic was intended to provide.

Unless otherwise specifically noted, elements depicted in the drawings are not necessarily drawn to scale.

<FIG> shows an aircraft <NUM>, according to an example implementation. The aircraft <NUM> includes a nose <NUM>, wings <NUM>, a fuselage <NUM>, and a tail <NUM>. <FIG> also illustrates a downward arrow <NUM> indicating an expected direction in which a force of gravity will pull objects, such as liquid water, onboard an aircraft <NUM> in a nominal operational profile.

<FIG> is a cross-sectional, schematic view of the aircraft <NUM> indicated by view arrows <NUM> in <FIG>, according to an example implementation. The fuselage <NUM> includes a floor <NUM>, a ceiling <NUM>, and an aesthetic fascia wall or an inner wall <NUM> that defines a cabin <NUM>, where the ceiling <NUM> and/or the inner wall <NUM> represents an interior wall of the aircraft <NUM> for purposes of this Description. The inner wall <NUM> is a lining that separates a main cabin, cockpit, and/or other areas within the aircraft <NUM> from an insulation blanket <NUM> and the fuselage <NUM>. The inner wall <NUM> can be made of plastic, glass-fiber, carbon fiber, glass-reinforced resin, other reinforced polymers, and/or other materials. The inner wall <NUM> can be designed to provide thermal and acoustic insulation as well.

Passengers in the aircraft <NUM> may congregate in seats <NUM> of the cabin <NUM> during flight. <FIG> illustrates that, inside of the fuselage <NUM> (e.g., in the cabin <NUM>), respiration and other sources of water cause a moisture <NUM> to enter or form in the air in the cabin <NUM>. For example, warm exhaled air includes the moisture <NUM> and rises upward through luggage compartments <NUM>. Some of this warm and moist air rises through the ceiling <NUM>. Furthermore, some warm air continues to rise upward through the insulation blanket <NUM> (or insulation blanket) into a space <NUM> between the insulation blanket <NUM> and an outer wall <NUM> of the aircraft <NUM>, also known as the aircraft skin.

Referring again to <FIG>, as the outer wall <NUM> is cooled by outside air at high altitude during flight, the temperature of the outer wall <NUM> eventually decreases to a temperature below a freezing temperature of water. This cooling causes the moisture <NUM> (e.g., water) to condense out of the air in the space <NUM> and freeze onto an interior surface of the outer wall <NUM> as ice <NUM>. As the aircraft <NUM> changes to a lower altitude and/or commences descent for landing and the temperature increases, the ice <NUM> begins to melt causing water droplets <NUM> to travel through the space <NUM> towards a bottom <NUM> of the fuselage <NUM>, drawn by gravitational force as shown by the downward arrow <NUM>. Some water droplets <NUM> enter gaps in the insulation blanket <NUM>, particularly where structural members <NUM> pass through apertures within the insulation blanket <NUM>, and drip into the cabin <NUM>, sometimes on passengers. Further, some water droplets <NUM> collect in the insulation blanket <NUM> as well. The moisture cycle of water cooling, freezing, and then melting can creates issues of liquid management for the aircraft <NUM>.

A size of the space <NUM> has been exaggerated somewhat in <FIG> in order to more clearly show the details of the structure. The structural members <NUM> are often used for attaching aircraft components <NUM>, such as the luggage compartments <NUM>, the ceiling <NUM>, ducting, equipment, and racks, as examples. For simplicity, common aircraft load bearing components such as stringers and/or frame members are not shown, but it should be understood that in some aspects, the structural members <NUM> attach various aircraft components to stringers and/or frame members, and not directly to the outer wall <NUM> of the aircraft <NUM>.

Thus, the structural members <NUM> can include frames, stringers, and/or other mechanical elements (e.g., longerons, spars, beams, trusses) that are fastened (e.g., with bolts, rivets, pins, or other fasteners), bonded (e.g., with an adhesive), welded, or otherwise attached to the inner wall <NUM> and outer wall <NUM>. The structural members <NUM> can be made of metallic material (e.g., aluminum) and/or non-metallic material (e.g., composite material). At least some of the structural members <NUM> can also be load-bearing. Additionally, at least some of the structural members <NUM> can be interconnected - namely, fastened, bonded, welded, or otherwise attached to each other. Further, at least some of the structural members <NUM> can include notches through which the water droplets <NUM> can flow. (These notches are shown below in <FIG>).

Within examples, a moisture control system and method for controlling moisture in the aircraft <NUM> are described that can increase reliability and efficiency of removing moisture, while reducing weight and complexity from existing aircraft drainage systems. Existing systems add weight to the aircraft with additional structures and are more passive in nature in that they heavily rely on gravity to bring moisture to drain masts or other areas where the moisture can exit the aircraft. In contrast, the disclosed systems and methods involve arranging cathodes and anodes inside the aircraft <NUM> such that, when a voltage is applied across the cathodes and anodes, moisture is drawn out and away from the insulation blanket <NUM>, toward an interior surface of the outer wall <NUM> of the fuselage <NUM>. Additionally, the applied voltage keeps moisture away from the insulation blanket <NUM> and drives moisture along a drainage path <NUM> toward a drainage port <NUM>. As such, the disclosed systems and methods can efficiently promote drainage of moisture in the aircraft <NUM> without adding much weight to the aircraft, and can also efficiently and proactively prevent moisture from accumulating on and in the insulation blanket <NUM>.

<FIG> illustrates a portion of the fuselage <NUM> as shown in <FIG>, according to an example implementation. The fuselage <NUM> includes the inner wall <NUM>, the outer wall <NUM>, and the <NUM> structural members (shown in <FIG>) coupled between the inner wall <NUM> and the outer wall <NUM>. As shown in <FIG>, the structural members <NUM> form the drainage path <NUM> terminating at the drainage port <NUM>. The insulation blanket <NUM> is positioned between the inner wall <NUM> and the outer wall <NUM>.

The fuselage <NUM> includes a moisture control system <NUM>, which includes an anode <NUM> coupled to the insulation blanket <NUM> that is positioned between the inner wall <NUM> and the outer wall <NUM> of the fuselage <NUM>, a cathode <NUM> coupled to an interior surface <NUM> of the outer wall <NUM>, and a power control unit <NUM> coupled to the anode <NUM> and the cathode <NUM> to apply voltage across the anode <NUM> and the cathode <NUM>. When the voltage is applied across the anode <NUM> and the cathode <NUM>, moisture is drawn away from the anode <NUM> and toward the cathode <NUM> on the interior surface <NUM> of the outer wall <NUM> and guided along the drainage path <NUM> provided via the structural members <NUM> disposed between the inner wall <NUM> and the outer wall <NUM> toward the drainage port <NUM>.

The inner wall <NUM> is a surface of the fuselage <NUM> that is located in an interior of the aircraft <NUM> and is opposite the outer wall <NUM> of the fuselage <NUM>. Like the fuselage <NUM>, the inner wall <NUM> can be made of aluminum, an aluminum-lithium alloy, a composite laminate, and/or other metallic or non-metallic materials.

The insulation blanket <NUM> is positioned between the inner wall <NUM> and the outer wall <NUM>, and the insulation blanket <NUM> includes an exterior face <NUM> positioned adjacent to the outer wall <NUM> and an interior face <NUM> opposite the exterior face <NUM>. In <FIG>, the anode <NUM> is shown coupled to the interior face <NUM> of the insulation blanket <NUM>, and when the voltage is applied, the moisture accumulated on and in the insulation blanket <NUM> is drawn out and away from the insulation blanket <NUM> towards the cathode <NUM>. In other examples, however, the anode <NUM> may be coupled to the exterior face <NUM> of the insulation blanket <NUM>.

The insulation blanket <NUM> is made of fiberglass, polyetherketoneketon, polyetheretherketone, ethylene chlorotrifluoroethylene, aramid paper, and/or other materials and is designed to acoustically and thermally insulate an interior of the aircraft <NUM> from noise and temperature outside the aircraft. The insulation blanket <NUM> can be fastened, adhered, or otherwise attached to the inner wall <NUM>, the outer wall <NUM>, and/or to the structural members <NUM>, thus securing the insulation blanket <NUM> in place. For example, pins can penetrate the insulation blanket <NUM> to attach the insulation blanket <NUM> to the outer wall <NUM>, and stainless steel spring clips can clamp around the structural members <NUM> to attach the insulation blanket <NUM> to the structural members <NUM>. Holes formed by the pins penetrating the insulation blanket <NUM> can be sealed with felt washers and tape. Other examples are possible as well. The insulation blanket <NUM> can be one of multiple insulation blankets attached throughout the fuselage <NUM>.

The exterior face <NUM> and the interior face <NUM> can be made of the same material as an interior of the insulation blanket <NUM> or a different material. For example, the exterior face <NUM> and the interior face <NUM> can be made of a polymer film (e.g., mylar film), and a portion of the insulation blanket <NUM> between the exterior face <NUM> and the interior face <NUM> can be made of fiberglass. In other words, the exterior face <NUM> and the interior face <NUM> can be configured to hold the fiberglass or other insulating material inside the insulation blanket <NUM>. Other examples are possible as well.

The anode <NUM> is a positively charged electrode made of a conductive material, such as copper, graphite, and/or aluminum. The anode <NUM> can take the form of a single wire, multiple interconnected wires (e.g., a mesh of wires, or wires arranged in another type of pattern), one or more strips of tape, a sheet, film, and/or other structure that is capable of being fastened, adhered, or otherwise attached to the insulation blanket <NUM>. The anode <NUM> can have approximately the same dimensions as the insulation blanket <NUM> or can have different dimensions.

The cathode <NUM> is a negatively charged electrode made of a conductive material, such as copper, graphite, and/or aluminum. The cathode <NUM> can take the form of a single wire, multiple interconnected wires (e.g., a mesh of wires, or wires arranged in another type of pattern), one or more strips of tape, a sheet, film, and/or other structure that is capable of being fastened, adhered, or otherwise attached to the interior surface <NUM> of the outer wall <NUM>.

According to the claims, the outer wall <NUM> of the fuselage <NUM> includes an electrically conductive material. The interior surface <NUM> of the outer wall <NUM> is made of a conductive material, the cathode <NUM> being attached to the interior surface <NUM> causes the interior surface <NUM> to act as a cathode as well. Thus, the cathode <NUM> used can be made smaller if the interior surface <NUM> is made of a conductive material. For example, the cathode <NUM> can be partitioned into a plurality of discrete cathodes positioned along the drainage path <NUM> (e.g., segments of conducting tape). This can also be useful in a situation in which some of the discrete cathodes become unattached from the interior surface <NUM>, since the remaining cathode(s) could still be used to provide conductivity needed for applying the voltage.

In an alternative not according to the claims, if the interior surface <NUM> is made of a non-conductive material, it can be desirable to have the cathode <NUM> be larger, such as a single, continuous cathode strip positioned along the drainage path <NUM> (e.g., an elongated strip of conducting tape). Other examples are possible as well.

The power control unit <NUM> includes a voltage source of direct current (DC) and/or alternating current (AC) electricity and is coupled to the anode <NUM> and the cathode <NUM> to deliver electricity and apply the voltage across the anode <NUM> and the cathode <NUM>. The power control unit <NUM> can deliver the electricity in a continuous manner or as individual pulses. The voltage applied across the anode <NUM> and the cathode <NUM> can vary and can fall within a larger range (e.g., <NUM> to <NUM> Volts (V)) or a smaller range (e.g., <NUM> to <NUM> V). Other voltages are possible. In some examples, the power control unit <NUM> can include hardware and/or software that enables the power control unit <NUM> to receive a signal that triggers the power control unit <NUM> to deliver electricity. For example, the moisture control system <NUM> may further include a moisture sensor <NUM> configured to detect presence of the moisture between the inner wall <NUM> and the outer wall <NUM>, as well as the moisture accumulating in the insulation blanket <NUM>, and the power control unit <NUM> is coupled to the moisture sensor <NUM> and is further configured to apply the voltage in response to the moisture sensor <NUM> detecting that the moisture exceeds a predefined moisture level (e.g., approximately <NUM> millimeters of the moisture). The power control unit <NUM> can receive the signal from the moisture sensor <NUM> and responsively apply the voltage across the anode <NUM> and the cathode <NUM>. Additionally or alternatively, the power control unit <NUM> can receive the signal from a computing device within the aircraft <NUM> (e.g., a flight control system operated either autonomously or by a pilot or crew member of the aircraft <NUM>), and responsively apply the voltage across the anode <NUM> and the cathode <NUM>. Other examples are possible as well.

The power control unit <NUM> can make the determination that the moisture exceeds the predefined moisture level on its own after receiving the signal from the moisture sensor <NUM> (or via an instruction in the signal from the moisture sensor <NUM>), and responsively apply the voltage. The power control unit <NUM> can discontinue applying the voltage as soon as the moisture falls below the predefined moisture level. In other examples, the power control unit <NUM> can be configured to continuously provide electricity, or pulses of electricity, in an autonomous manner, without being triggered to do so.

The moisture sensor <NUM> is a physical electronic device having circuitry configured to emit electromagnetic signals for detecting and measuring liquid (e.g., the moisture) that directly contacts and/or is proximate to the moisture sensor <NUM>. The moisture sensor <NUM> is configured to monitor buildup of the moisture between the inner wall <NUM> and the insulation blanket <NUM>, between the outer wall <NUM> and the insulation blanket <NUM>, as well as the moisture accumulating in the insulation blanket <NUM>. In particular, the moisture sensor <NUM> can be configured to transmit, to the power control unit <NUM> or to another computing device, a signal representing a level (e.g., an amount, measured in millimeters) of the moisture that is contacting the moisture sensor <NUM> and/or that is proximate to the moisture sensor <NUM>.

Furthermore, the moisture sensor <NUM> can be wireless or operated by a wired connection, and can optionally include a battery. The moisture sensor <NUM> can be rigid or flexible and can vary in size, such as millimeters in width, height, and/or length. Further, the moisture sensor <NUM> can include an adhesive backing or other means for attaching the moisture sensor <NUM> to various metallic and/or non-metallic surfaces within the aircraft <NUM>. <FIG> does not illustrate where the moisture sensor <NUM> is attached within the aircraft <NUM>, but it should be understood that the moisture sensor <NUM> can be included at various locations where the moisture is present. For example, the moisture sensor <NUM> can be attached to the exterior face <NUM>, to the interior face <NUM>, to the inner wall <NUM>, and/or within the insulation blanket <NUM> (i.e., in a batting of the insulation blanket <NUM>, positioned between the exterior face <NUM> and the interior face <NUM>).

A connection between the moisture sensor <NUM> and the power control unit <NUM> can be a wired interface (i.e., a physical connection, such as by way of a cable or other electrical medium through which current can flow), or a wireless interface.

In operation, the power control unit <NUM> applies the voltage across the anode <NUM> and the cathode <NUM>, which causes the water droplets <NUM> and moisture to be ionized and drawn toward the cathode <NUM>. Thus, applying the voltage causes the moisture to be drawn away from the insulation blanket <NUM> and toward the interior surface <NUM> where the cathode <NUM> is attached. In addition, because the cathode <NUM> is attached to the interior surface <NUM> proximate to the drainage path <NUM>, the voltage, as well as gravity, keeps the moisture on the interior surface <NUM> and causes the moisture to be guided along the drainage path <NUM> toward the drainage port <NUM>. Furthermore, because the anode <NUM> is attached to the exterior face <NUM>, applying the voltage causes the moisture that is saturating the insulation blanket <NUM> to be drawn out of the insulation blanket <NUM> and toward the interior surface <NUM>.

The drainage path <NUM> includes a physical area proximate to, on, or through the structural members <NUM> where the moisture flows before reaching the drainage port <NUM>. That is, as the moisture flows downward toward the drainage port <NUM>, the moisture physically contacts the interior surface <NUM> proximate to the structural members <NUM> and/or the structural members <NUM> themselves. The drainage path <NUM> can also be formed at least in part by ridges on, or grooves in, the interior surface <NUM> and/or ridges on, or grooves in, the structural members <NUM>. For example, during a portion of the drainage path <NUM>, the moisture might flow between two ridges formed in the interior surface <NUM>. Other examples are possible as well.

The drainage port <NUM> is a physical pathway (e.g., tubes, pipes, inlet(s), outlet(s), and/or other structures) disposed in the fuselage <NUM> and through which the moisture can flow to exit the aircraft <NUM>. The drainage port <NUM> can extend from the interior surface <NUM>, through the fuselage <NUM>, to an exterior of the fuselage <NUM>. In some examples, flow of the moisture through the drainage port <NUM> can be controlled by a drain valve (not shown) within the drainage port <NUM>. The drain valve might be closed when the fuselage <NUM> is pressurized, thus preventing the moisture from exiting the aircraft <NUM>, and opened when the aircraft <NUM> is not pressurized (e.g., when the aircraft <NUM> is on a runway or Tarmac), thus allowing the moisture to exit the aircraft <NUM>. The drainage port <NUM> can thus be configured to open automatically when the fuselage <NUM> is non-pressurized. Although the drainage port <NUM> is shown in <FIG> as being on the bottom <NUM> of the fuselage <NUM>, the drainage port <NUM> can be at other locations on the fuselage <NUM> in other examples.

As a result, the moisture control system <NUM> can advantageously help alleviate an accumulation of the moisture in the insulation blanket <NUM>, on the insulation blanket <NUM> (e.g., on the exterior face <NUM>), and on the interior surface <NUM>. The moisture control system <NUM> can also cause the moisture to reach the drainage port <NUM> faster than in existing systems. Additionally, the moisture control system <NUM> can advantageously prevent further moisture accumulation in the above-noted areas in a proactive manner. Further, the moisture control system <NUM> advantageously leverages the structural members <NUM> that form the fuselage <NUM>, rather than requiring additional drainage structures that might add weight to the aircraft <NUM> as in existing systems.

The moisture control system <NUM> can be usefully implemented throughout the aircraft <NUM>, such as in particular areas of the aircraft <NUM> that might be prone to more moisture accumulation than others. For example, areas surrounding doors or hatchways in the aircraft <NUM> might experience more airflow, and thus more moisture, than other areas in the aircraft <NUM>. Thus, the moisture control system <NUM> can be particularly useful when applied in the areas surrounding the doors or hatchways, since the moisture control system <NUM> can efficiently remove moisture from these areas as well as help prevent additional moisture from accumulating.

<FIG> shows an example of the interior surface <NUM>, the structural members <NUM> (shown as frames <NUM> interconnected with stringers <NUM>), the drainage path <NUM>, and the anode <NUM> and the cathode <NUM>, according to an example implementation. The frames <NUM> and the stringers <NUM> include notches <NUM> through which the moisture flows as the moisture is guided along the drainage path <NUM>.

The cathode <NUM> is shown in <FIG> as a continuous cathode strip positioned along a vertical portion of the drainage path <NUM> - namely, along a portion of the drainage path <NUM> formed by the frames <NUM>. In operation, the voltage can be applied, which causes the moisture to flow along the drainage path <NUM> both downward and diagonally as denoted by the arrows shown in <FIG>, thereby advantageously guiding the moisture toward the drainage port <NUM> as described above.

<FIG> shows another perspective view of an example of the drainage port <NUM>, the interior surface <NUM>, the structural members <NUM>, and the drainage path <NUM>, according to an example implementation. In <FIG>, the drainage port <NUM> is shown as a plurality of drainage ports disposed at various locations on the interior surface <NUM>. Further, the structural members <NUM> are embodied as various interconnected frames and stringers, examples of which are denoted in <FIG>. The dotted arrows shown in <FIG> represent the drainage path <NUM> along which the moisture can flow and can be guided toward the plurality of drainage ports using the moisture control system <NUM> described herein. Although the cathode is not explicitly shown, the cathode could be attached to the interior surface <NUM> proximate to the structural members <NUM> at one or more locations proximate to the arrows representing the drainage path <NUM>.

<FIG> show further views of examples of the drainage path <NUM>, according to example implementations. In <FIG>, the drainage path <NUM> is shown to be horizontal and vertical to follow a path created by the structural members <NUM>. In this example, cathodes can be positioned along the structural members <NUM> to guide the moisture in the drainage path <NUM> as shown. In <FIG>, the drainage path <NUM> is shown as vertically downward along the structural members <NUM> in which notches <NUM> are included at positions in the frames <NUM> and the stringers <NUM> to enable the moisture to flow downward. <FIG> illustrates an example of a door or hatch, which opens and closes, and thus, the drainage path <NUM> in a downward direction may be more efficient.

<FIG> illustrates an end and side views of the fuselage <NUM> with examples of the drainage path <NUM>, according to an example implementation. In the end view, the drainage paths <NUM> are shown by arrows, and illustrate that moisture can flow downward along a curved portion of the outer wall <NUM> of the fuselage <NUM>. Further, the side views along lines A-A and B-B illustrate that the moisture can flow in a forward direction as well toward the drainage port <NUM>.

<FIG> illustrates another perspective view of a portion of the fuselage <NUM> illustrating example locations of the drainage port <NUM>. In <FIG>, the fuselage <NUM> is shown with multiple drainage ports positioned along a center and the bottom <NUM> of the fuselage <NUM>.

<FIG> illustrates a detailed view of an example of the drainage port <NUM>. The drainage port <NUM> can include an internal valve, as described above, which remains closed when pressurized and open when non-pressurized, for example.

<FIG> shows a flowchart of an example of a method <NUM> for controlling moisture in the aircraft <NUM>, according to an example implementation. Method <NUM> shown in <FIG> presents an example of a method that could be used with the moisture control system <NUM> described herein. Method <NUM> may include one or more operations, functions, or actions as illustrated by one or more of blocks <NUM>-<NUM>.

At block <NUM>, the method <NUM> includes coupling the anode <NUM> to the insulation blanket <NUM> that is positioned between the inner wall <NUM> and the outer wall <NUM> of the fuselage <NUM>. At block <NUM>, the method <NUM> includes coupling the cathode <NUM> to the interior surface <NUM> of the outer wall <NUM>. At block <NUM>, the method <NUM> includes causing the power control unit <NUM> to apply voltage across the anode <NUM> and the cathode <NUM>, thereby drawing moisture away from the anode <NUM> and toward the cathode <NUM> on the interior surface <NUM> of the outer wall <NUM> and guiding the moisture along the drainage path <NUM> provided via the structural members <NUM> disposed between the inner wall <NUM> and the outer wall <NUM> toward the drainage port <NUM>.

<FIG> shows a flowchart of an example method for use in performing the coupling as shown in block <NUM>, according to an example implementation. In particular, the flowchart in <FIG> relates to an example implementation in which the insulation blanket <NUM> includes the exterior face <NUM> positioned adjacent to the interior surface <NUM> and the interior face <NUM> opposite the exterior face <NUM>. At block <NUM>, functions include coupling the anode <NUM> to the interior face <NUM> of the insulation blanket <NUM>, and whereby when the power control unit <NUM> is applying the voltage, the moisture accumulated on and in the insulation blanket <NUM> is drawn out and away from the insulation blanket <NUM> towards the cathode <NUM>.

<FIG> shows a flowchart of another example method for use in performing the coupling as shown in block <NUM>, according to an example implementation. In particular, the flowchart in <FIG> relates to an example implementation in which the insulation blanket <NUM> includes the exterior face <NUM> positioned adjacent to the interior surface <NUM> and the interior face <NUM> opposite the exterior face <NUM>. At block <NUM>, functions include coupling the anode <NUM> to the exterior face <NUM>.

<FIG> shows a flowchart of another example method for use in performing the coupling as shown in block <NUM>, according to an example implementation. At block <NUM>, functions include coupling a continuous cathode strip positioned along the drainage path <NUM> to the interior surface <NUM> of the outer wall <NUM>.

<FIG> shows a flowchart of another example method for use with the method <NUM> of <FIG>, according to an example implementation. At block <NUM>, functions include detecting, by the moisture sensor <NUM>, presence of the moisture between the inner wall <NUM> and the outer wall <NUM>, as well as the moisture accumulating in the insulation blanket <NUM>. At block <NUM>, functions include causing the power control unit <NUM> to apply the voltage across the anode <NUM> and the cathode <NUM> in response to the moisture sensor <NUM> detecting that the moisture exceeds a predefined moisture level.

Devices or systems may be used or configured to perform logical functions presented in <FIG>. In some instances, components of the devices and/or systems may be configured to perform the functions such that the components are actually configured and structured (with hardware and/or software) to enable such performance. In other examples, components of the devices and/or systems may be arranged to be adapted to, capable of, or suited for performing the functions, such as when operated in a specific manner. Although blocks in <FIG>, are illustrated in a sequential order, these blocks may also be performed in parallel, and/or in a different order than those described herein. Also, the various blocks may be combined into fewer blocks, divided into additional blocks, and/or removed based upon the desired implementation.

It should be understood that for these and other processes and methods disclosed herein, flowcharts show functionality and operation of one possible implementation of present examples. In this regard, some blocks or portions of some blocks may represent a module, a segment, or a portion of program code, which includes one or more instructions executable by a processor for implementing specific logical functions or steps in the process. The program code may be stored on any type of computer readable medium or data storage, for example, such as a storage device including a disk or hard drive. Further, the program code can be encoded on a computer-readable storage media in a machine-readable format, or on other non-transitory media or articles of manufacture. The computer readable medium may include non-transitory computer readable medium or memory, for example, such as computer-readable media that stores data for short periods of time like register memory, processor cache and Random Access Memory (RAM). The computer readable medium may also include non-transitory media, such as secondary or persistent long term storage, like read only memory (ROM), optical or magnetic disks, compact-disc read only memory (CD-ROM), for example. The computer readable media may also be any other volatile or non-volatile storage systems. The computer readable medium may be considered a tangible computer readable storage medium, for example.

In addition, some blocks or portions of some blocks in <FIG> may represent circuitry that is wired to perform the specific logical functions in the process. Alternative implementations are included within the scope of the examples of the present disclosure in which functions may be executed out of order from that shown or discussed, including substantially concurrent or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art.

Using examples described herein, by passing a low voltage pulsating charge between positive and negative electrodes, water is ionized and drawn towards the negative electrodes that are placed on the fuselage skin. A pulsing, low-voltage current pushes positive ions toward the negative electrode charged area, dragging water molecules with them. A resulting flow is termed electro osmotic flow. Thus, electro-osmotic pulses (EOP) are beneficial to efficiently remove water from the fuselage skin and avoid drawbacks with existing systems in which passive dams and blockage areas are generally used to route water, with no action moving the water.

Further, the disclosure comprises the following embodiments, which are not encompassed by the wording of the claims, but are considered as useful for understanding the invention:
A moisture control system, comprising an anode coupled to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage; a cathode coupled to an interior surface of the outer wall; and a power control unit coupled to the anode and the cathode to apply voltage across the anode and the cathode, and when the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

The insulation blanket can include an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and wherein the anode can be coupled to the interior face of the insulation blanket, and when voltage is applied, the moisture accumulated on and in the insulation blanket is drawn out and away from the insulation blanket towards the cathode.

The insulation blanket may include an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and the anode can be coupled to the exterior face of the insulation blanket.

The cathode may include a continuous cathode strip positioned along the drainage path.

The cathode can be partitioned into a plurality of discrete cathodes positioned along the drainage path.

The structural members can include frames interconnected with stringers, and the frames and the stringers can include notches through which the moisture flows as the moisture is guided along the drainage path.

A moisture sensor configured to detect presence of the moisture can be arranged between the inner wall and the outer wall, as well as the moisture accumulating in the insulation blanket, and the power control unit can be further configured to apply the voltage in response to the moisture sensor detecting that the moisture exceeds a predefined moisture level.

The disclosure also comprises an aircraft comprising a fuselage comprising an inner wall, an outer wall, and structural members coupled between the inner wall and the outer wall, wherein the structural members form a drainage path terminating at a drainage port; an insulation blanket positioned between the inner wall and the outer wall; an anode coupled to the insulation blanket; a cathode coupled to an interior surface of the outer wall; and a power control unit coupled to the anode and the cathode to apply voltage across the anode and cathode, and when the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via the structural members toward the drainage port.

The structural members can include frames interconnected with stringers, and the frames and the stringers may include notches through which the moisture flows as the moisture is guided along the drainage path.

The outer wall of the fuselage may include an electrically conductive material.

The insulation blanket may include an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and the anode can be coupled to the interior face of the insulation blanket, and when voltage is applied, the moisture accumulated on and in the insulation blanket is drawn out and away from the insulation blanket towards the cathode.

The cathode can include a continuous cathode strip positioned along the drainage path.

The drainage port is closed when the fuselage is pressurized, and the drainage port opens automatically when the fuselage is non-pressurized.

A method for controlling moisture in an aircraft is also disclosed comprising coupling an anode to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage; coupling a cathode to an interior surface of the outer wall; and causing a power control unit to apply voltage across the anode and the cathode, thereby drawing moisture away from the anode and toward the cathode on the interior surface of the outer wall and guiding the moisture along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

The insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and coupling the anode to the insulation blanket of the aircraft can comprise coupling the anode to the interior face of the insulation blanket, and when the power control unit applies voltage, the moisture accumulated on and in the insulation blanket is drawn out and away from the insulation blanket towards the cathode.

The insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and coupling the anode to the insulation blanket can comprise coupling the anode to the exterior face.

Coupling the cathode to the interior surface of the outer wall can comprise coupling a continuous cathode strip positioned along the drainage path to the interior surface of the outer wall.

A moisture sensor can detect the presence of the moisture between the inner wall and the outer wall, as well as the moisture accumulating in the insulation blanket, wherein causing the power control unit to apply the voltage across the anode and the cathode comprises causing the power control unit to apply the voltage across the anode and the cathode in response to the moisture sensor detecting that the moisture exceeds a predefined moisture level.

Claim 1:
A moisture control system (<NUM>), comprising:
an anode (<NUM>) coupled to an insulation blanket (<NUM>) that is positioned between an inner wall (<NUM>) and an outer wall (<NUM>) of an aircraft fuselage (<NUM>);
a cathode (<NUM>) coupled to an interior surface (<NUM>) of the outer wall (<NUM>),
which interior surface (<NUM>) of the outer wall (<NUM>) of the aircraft fuselage (<NUM>) is made of a conductive material and which outer wall (<NUM>) of the aircraft fuselage (<NUM>) includes an electrically conductive material, whereby the cathode (<NUM>) coupled to the interior surface (<NUM>) of the outer wall (<NUM>) of the aircraft fuselage (<NUM>) causes the interior surface (<NUM>) of the outer wall (<NUM>) of the aircraft fuselage (<NUM>) to act as a cathode as well; and
a power control unit (<NUM>) coupled to the anode (<NUM>) and the cathode (<NUM>) to apply voltage across the anode (<NUM>) and the cathode (<NUM>), and when the voltage is applied across the anode (<NUM>) and the cathode (<NUM>), moisture is drawn away from the anode (<NUM>) and toward the cathode (<NUM>) on the interior surface (<NUM>) of the outer wall (<NUM>) and guided along a drainage path (<NUM>) provided via structural members (<NUM>) disposed between the inner wall (<NUM>) and the outer wall (<NUM>) toward a drainage port (<NUM>).