Aircraft section and aircraft

Abstract

The present disclosure relates to an aircraft section (10) and an aircraft (1) having a fixture (50) and a water supply line (110) with a heating element (120) as anti-freezing protection in a space overlapping with a frame (3) of the aircraft.

Description

aircraft sections and aircraft Technical Field

[0001] This disclosure generally relates to an aircraft segment and an aircraft having a water supply line with antifreeze protection. In particular, this disclosure relates to an aircraft segment and an aircraft having fixed facilities and a water supply line with heating elements, wherein the water supply line is installed in a space near the frame of the main structure of the aircraft, which is at risk of freezing. Background Technology

[0002] Conventional water supply systems in aircraft are typically installed using gravity-fed drainage. This complicates the routing and installation of water pipes and conduits. To prevent these pipes and conduits from freezing, an additional electro-icing protection system can be provided, which must be laid out in the same manner as the water pipes, further complicating the installation process.

[0003] Additional water supply systems include flexible hoses with a smaller diameter that operate at higher pressures. Due to their smaller diameter, the hoses can be pneumatically drained, making installation routes less complex and easier to install in aircraft.

[0004] However, even flexible hoses can be deployed in areas of the aircraft at risk of freezing, whether during flight operations or during the ground phase when the aircraft is in a cold environment. Summary of the Invention

[0005] Therefore, one object of this disclosure is to provide an improved water supply system, particularly a water supply system with improved operational availability and reduced risk of damage due to freezing.

[0006] This objective is achieved by the invention as defined in the independent claims. Preferred embodiments are defined in the dependent claims.

[0007] According to a first aspect of this disclosure, an aircraft segment is provided, comprising at least one frame arranged in the circumferential direction of the aircraft segment; at least one cabin floor connected to the frame; a fixture having a water consumer; and a water supply line fluidly connected to and configured to supply water to the water consumer. For example, such a fixture may be a toilet, a kitchen, a partition wall or the like having a water dispenser or similar water consumer.

[0008] The water supply lines are installed in the space that overlaps with the frame (at the time of observation) in the longitudinal direction of the aircraft segment. The aircraft segment also includes a heating element configured to heat the water supply lines in the space overlapping with the frame.

[0009] In other words, the water supply lines are at least partially located in the space or block near the outer skin of the aircraft segment, which is typically fitted to the aircraft fuselage frame. This block near the outer skin is at risk of freezing during flight or in a freezing environment on the ground. Heating elements are located only in this block. Therefore, the water supply lines can be located in an area of ​​the aircraft segment where they do not obstruct the installation or arrangement of other components. Simultaneously, because the heating elements are located in the segment (or one or more segments) at risk of freezing, damage to the water supply lines can be prevented.

[0010] As an example only, installing the water supply line in the space that overlaps with the frame in the longitudinal direction allows the water supply line to be "hidden" in the structure of the aircraft, i.e., in the frame block.

[0011] In this variant, water supply lines can be installed in the space beneath the cabin floor, and heating elements can be further configured to heat a portion of the water supply lines located in the space beneath the cabin floor. Specifically, because the cabin floor is fitted to or near the frame structure, the space beneath the cabin floor is also at risk of freezing, at least a portion of which is at risk of freezing. However, heating elements can be installed throughout the entire area at risk of freezing, covering some spaces between the frames and, for example, between floor beams.

[0012] It should be noted that "below the cabin floor" should be understood to include the space defined by the beams supporting the cabin floor, and not necessarily the space beneath these beams. Therefore, "below the cabin floor" should be understood to include any space beneath the actual floor panels (e.g., space positioned on top of beams). In any case, the cargo hold area may not have water supply lines for cargo, as water supply lines are not located in spaces dedicated to cargo and other goods. Therefore, water supply lines can be "hidden" within the cargo hold floor.

[0013] It should be understood that water supply lines with heating elements can be installed in any other area at risk of freezing.

[0014] In this variant, the water supply line can be a conventional water line made of stainless steel or titanium, such as a line with a diameter between ½ inch and ¾ inch (i.e., 1.27 cm to 1.905 cm). This conventional water line can be used in a water supply system operating at pressures optimized for one or more water consumers.

[0015] In a variation, the water supply line can be a flexible hose made of plastic material; by way of example only, the hose can be made of multiple layers of fabric, which may further comprise plastic material. This flexible hose can have a small diameter, i.e., less than ½ inch (<1.27 cm), for example, between 6 mm and 12 mm. The flexible hose can be used in water supply systems operating at pressures higher than those required by one or more water consumers, such as systems operating between 2.7 bar and 50 bar.

[0016] Flexible hoses also allow for compensation for any tolerances, such as assembly tolerances, because water supply lines can be installed at different radii, or can be bent, pulled, pushed, etc. within the installation space.

[0017] Furthermore, this flexible hose allows for the flexible installation of water consumers within the aircraft during final assembly and during modifications or alterations to the cockpit layout. The flexible hose allows for the installation of water supply lines (with heating elements) with lengths corresponding to the maximum length required for the water consumer at the furthest point from a given installation space. Due to the hose's flexibility, it can be installed in a straight line to reach the water consumer at the maximum distance, as well as in any other water line layout to conceal the water consumer relative to a water consumer closer to the installation space. As just one example, the length of the flexible hose can be selected to reach any fixture within a section of the aircraft along its longitudinal direction, where a fixture with a water consumer can be flexibly installed.

[0018] Alternatively, flexible hoses of varying lengths can be provided, allowing for replacement with hoses of different lengths during final assembly of the aircraft and during modifications or alterations to the cockpit layout, ensuring that the optimal length of the water supply line is always available.

[0019] It should be understood that this different installation method may also involve heating elements and / or heated water hoses.

[0020] In this variant, the heating element may be a heated water supply hose fluidly connected to the water supply line and arranged in a space overlapping with the frame, and optionally further arranged in a space below the cabin floor. In other words, the heated water supply hose can replace a conventional water supply hose or line without a heating element. Therefore, while the heating element may be an add-on to a conventional water supply hose, in this variant, the water supply hose may have an integrated heating element.

[0021] In a variant implementation, the heating element can be an electric heating element with an electrical connector. Therefore, power can be easily supplied to the heating element by connecting the electrical connector to a power supply source.

[0022] In a variant implementation, the aircraft section may also include a power supply line configured to provide electrical power to the stationary facility, wherein the electrical connectors of the heating element are electrically connected to the power supply source. Therefore, the power required by the heating element can be simply provided from an existing power source (i.e., the power supply line for the stationary facility).

[0023] In this variant, the electrical connectors are located within the fixed installation. This facilitates the installation and assembly of the water supply and heating elements, as the electrical connectors are readily accessible at the ends of the water supply lines within the fixed installation, i.e., where the water supply lines connect to the water consumer and the power supply source for the fixed installation is already present. No work may be performed under the cabin floor, particularly in the cargo hold area within the triangular region between the frame and the cabin floor, which is typically used for supply lines and connections.

[0024] In a variant implementation, the aircraft section may further include at least one main water line, wherein a water supply line is fluidly connected to the main water line. Such a main water line may have a larger diameter than, but is not limited to, the water supply line used for fixed installations. In other words, the two water lines may have the same diameter, allowing the use of the same water supply hose.

[0025] In this variant, the main water line can be installed in the space beneath the cockpit floor. Specifically, the main water line can extend beneath the actual floor panels, such as in the space between floor beams. For example, the floor beams may include through-holes through which the main water line extends. By way of example only, the main water line can be installed along the longitudinal direction of the aircraft, for example, along the entire aircraft (or nearly the entire aircraft, since the nose and tail sections may not require water supply).

[0026] In a modified version, the aircraft section may also include a temperature sensor arranged in the space overlapping with the frame, and preferably adjacent to the water supply lines. This allows for monitoring of temperatures in areas at risk of freezing.

[0027] In a variant implementation, the aircraft section may also include a controller configured to control the operation of the heating element. For example, the controller may be configured to activate the heating element, i.e., to warm or heat the water supply line, when there is a risk of freezing in the water supply line.

[0028] As an example only, the controller can operate on a time-based basis. For instance, the controller may activate the heating element during a flight phase or depending on a switch or a signal from the aircraft controls indicating that the aircraft is in a cold environment. For example, crew members or cockpit occupants may turn on the heating element via the controller to avoid any damage to the water supply lines.

[0029] In a variant implementation, the controller can also be configured to control the operation of the heating element based on temperature signals received from a temperature sensor. This enables automatic freeze prevention control.

[0030] In a variant, the controller can also be configured to monitor the operation of the heating element. Therefore, in the event that the heating element is not operating, a warning signal can be output despite the risk of freezing in the water supply lines. This warning signal could, for example, be received at a more general monitoring or surveillance system on the aircraft, making individuals aware of the heating element's malfunction.

[0031] In addition, the controller can be configured, for example, to test the heating element before the aircraft takes flight, or something similar.

[0032] In a variant implementation, the aircraft section may also include a thermostat configured to activate a heating element based on a preset temperature. By way of example only, the thermostat may be preset to 0°C, 1°C, or 2°C (or any value within the range of 0°C and 5°C), and the heating element is activated if an airflow reaches a temperature below this. For example, the thermostat may include an electrical switch that closes at the preset temperature.

[0033] In this variant, the heating element is configured to heat the water supply line to a temperature above the freezing point. Therefore, in normal conditions, the heating element can be configured to heat the water supply line to a temperature above 0°C. By way of example only, the heating element can be configured to heat the water supply line to a temperature between 1°C and 10°C, preferably between 2°C and 10°C, and most preferably between 4°C and 8°C, such as 4°C or 5°C. This is sufficient to prevent the water supply line from freezing to avoid any damage, while the water itself is not heated, allowing the heating element to operate in an energy-efficient manner.

[0034] In this variant, the aircraft segment may include multiple fixed installations, each with at least one water consumer. The water supply line may also be installed in a manner that connects one fixed installation to an adjacent fixed installation, wherein heating elements can heat multiple segments of the water supply line in the space overlapping with the frame. For example, the water supply line may branch in the first fixed installation and / or in the space overlapping with the frame, such that one branch connects to the water consumer of the first fixed installation, and another branch is installed into or connected to a second fixed installation. Therefore, the water supply line may include additional segments (branches) arranged in blocks at risk of freezing. All these segments (branches) can be heated by heating elements.

[0035] This allows multiple fixed installations to be connected to the water supply line without requiring any changes or adjustments to the remaining aircraft installations, such as the aircraft's internal components.

[0036] According to the second aspect, in order to better understand this disclosure, the aircraft includes at least one aircraft segment according to the first aspect or one or more variations thereof.

[0037] In a variant, the aircraft may include several aircraft sections, each of which has one or more water supply lines that connect one or more fixed facilities to a main water line that extends through the aircraft in the longitudinal direction.

[0038] This disclosure is not limited to the aspects and variations in the form and order described. In particular, the description of aspects and variations should not be construed as a specific restrictive grouping of features. It should be understood that this disclosure also covers combinations of aspects and variations. Thus, each variation or optional feature can be combined with any other aspect, variation, optional feature, or even combination thereof. Attached Figure Description

[0039] In the following description, the present disclosure will be further described with reference to exemplary embodiments illustrated in the accompanying drawings, wherein:

[0040] Figure 1 schematically illustrates a side view of an aircraft including a water supply system and several aircraft sections;

[0041] Figure 2 schematically illustrates a cross-section of an aircraft section with a water supply;

[0042] Figure 3 schematically illustrates a plan view of an aircraft section with a water supply; and

[0043] Figure 4 schematically illustrates a plan view of an aircraft section with several fixed facilities. Detailed Implementation

[0044] In the following description, specific details are set forth for purposes of explanation and not limitation, in order to provide a thorough understanding of this disclosure. It will be apparent to those skilled in the art that this disclosure may be practiced in other embodiments that depart from these specific details.

[0045] Figure 1 schematically illustrates a partially cut-away side view of the aircraft 1. Inside the aircraft 1, a water supply system 200 and several aircraft sections 10 are schematically shown. The water supply system 200 includes a central water tank 210 and at least one main water line 250. For example, as illustrated in Figure 1, a first main water line 250 extends to the front of the aircraft, while a second main water line 250 extends towards the rear (tail) of the aircraft. It should be understood that the number of main water lines 250 depends on the location of the central water tank 210 and the location of the aircraft sections 10 requiring water supply.

[0046] Each aircraft segment 10 includes at least one fixed facility 50 having at least one water consumer 130. In other words, this disclosure is not limited to a specific number of fixed facilities 50 for each aircraft segment 10, nor is it limited to a specific number of fixed facilities 50 and / or water consumers 130 for each aircraft segment 10.

[0047] Although Figure 1 illustrates a fixture 50 as a partition component, it should be understood that fixture 50 can have any shape and size. By way of example only, while kitchens and toilets typically have a three-dimensional body including a specific internal volume, partition walls or brackets or fittings, such as those for water dispensers or water purifiers (not shown), have a substantially two-dimensional body, such as a wall or column.

[0048] One or more water consumers 130 are connected to the main water line 250 via water supply lines 110. For clarity in Figure 1, only some water supply lines 110 are marked with reference numerals. It should be understood that multiple water consumers 130 may be connected to branches of water supply lines 110 (not shown) (i.e., one or more water supply lines 110 branching from another water supply line 110), wherein the root water supply line 110 is fluidly connected to the main water line 250.

[0049] Water consumer 130 may be a (non-pressurized) buffer tank, water dispenser, toilet, faucet, coffee machine, beverage machine, or several such devices. Therefore, the water consumer 130 illustrated is generally a device or group of devices associated with a fixed facility 50 that requires a water supply.

[0050] Figure 2 schematically illustrates a cross-section of an aircraft segment 10 with a water supply. The aircraft segment 10 includes at least one frame 3 arranged along the circumferential direction of both the aircraft segment 10 and the aircraft 1. A cockpit floor 5, or at least one segment of a cockpit floor 5, is also provided within the aircraft segment 10. Therefore, the aircraft segment 10 does not necessarily cover the entire frame 3, nor is it limited to any specific portion of the frame 3.

[0051] Water supply line 110 is installed in the space beneath the cockpit floor 5. It should be understood that the space beneath the cockpit floor 5 includes any area below the floor panel (the upper surface of the cockpit floor 5 illustrated in Figure 2). Therefore, the space beneath the cockpit floor 5 should be understood to include the space between floor beams, which can be understood as beams extending in the cross-sectional direction (Y-axis) of the aircraft 1 (in the drawing plane of Figure 2) and extending from the top surface of the cockpit floor 5 to the bottom surface of the cockpit floor 5 (illustrated as the lower line of the cockpit floor 5 in Figure 2).

[0052] Water supply line 110 can be fluidly connected to main water line 250, which can also be located below cabin floor 5. By way of example only and as illustrated in Figure 2, main water line 250 can be located below floor panel and can extend through an opening in floor beam (not explicitly shown).

[0053] In any case, a water supply line 110, which is fluidly connected to and branches off from the main water line 250, fluidly connects the main water line 250 to a water consumer 130 located in or at the fixed facility 50. The water supply line 110 is also installed in a space that overlaps with one or more frames 3 in the longitudinal direction (X-axis) of the aircraft segment 10.

[0054] Figure 2 illustrates area 20, which is at risk of freezing because it is close to the outer skin of aircraft 1 (not explicitly shown). As an example only, the space below cabin floor 5 (i.e., the area near or within the cargo hold area) may have a higher risk of freezing than the space within the fixed structure (i.e., the area within the cabin area). This is because the cabin area is normally heated, while the cargo hold area may not be consistently heated. For example, during loading / unloading of cargo and baggage, the cargo door (not shown) may be opened, while the cabin area is heated for passengers. Therefore, in cold environments, the cargo hold area may be much colder than the cabin area.

[0055] The aircraft section 10 also includes a heating element 120 configured to heat the water supply line 110 in the space overlapping with the frame 3. Therefore, the heating element 120 can be arranged only in the space overlapping with the frame 3. Alternatively, the heating element 120 can be arranged along the water supply line 110 intersecting the entire area 20 at risk of freezing. Thus, the heating element can be further configured to heat a portion of the water supply line arranged in the space below the cabin floor 5.

[0056] By way of example only, the area 20 at risk of freezing may have a cross-sectional range of 10 to 100 cm, preferably 10 to 60 cm, from the outer skin toward the center of the aircraft 1 (in the Y-axis direction).

[0057] While the heating element 120 may be a component supplementing the water supply line 110, it should be understood that the heating element 120 may also be a water supply hose fluidly connected to the water supply line 110 and (only) disposed in an area 20 at risk of freezing, and thus heated. Such a heated water supply hose 120 may have an integrated heating element. By way of example only, the heating element may be integrated into a plastic hose to directly heat the plastic hose, thereby forming a heated water supply hose.

[0058] The heating element 120 may be an electric heating element having an electrical connector 125. Instead of an electric heating element, the heating element 120 may be a fluid conduit through which a heated fluid (such as heated air or heated liquid) may be guided. Such a fluid conduit may be arranged adjacent to the water supply line 110 or may surround the water supply line 110.

[0059] In the case of an electric heating element, power can be supplied from a power supply line 25 configured to provide power to the fixture 50. This power supply line 25 can be any power line and / or data line extending through the aircraft 1. By way of example only, fixtures often require electrical power to operate lights, kitchen appliances, displays, or other electrical components. Therefore, fixture 50 is often already equipped with an electrical power supply or power line.

[0060] Therefore, the electrical connector 125 of the heating element 120 can be arranged in the fixture 50 so that it can be easily connected to any power line in the fixture 50. Alternatively, the power line will be installed in / through the fixture 50 to connect the electrical connector 125 to the power supply line 25 of the aircraft 1.

[0061] The aircraft segment 10 may also include a temperature sensor 160 disposed in the space overlapping with the frame 3. Referring additionally to Figure 3, which schematically illustrates a plan view of the aircraft segment 10 with a water supply, such as the aircraft segment 10 of Figure 2, the space between the frames 3 is close to the outer skin (not shown) of the aircraft 1. This area 20 is at risk of freezing. In Figure 3, area 20 is illustrated as a substantially rectangular region defined in the longitudinal direction (X-axis). However, it should be understood that area 20 is continuous in the longitudinal direction along the entire outer skin and frame 3 from the front to the tail of the aircraft 1.

[0062] In any case, temperature sensor 160 can be configured to measure the temperature in area 20, and in particular the temperature of water supply line 110 (or heated water supply hose 120) adjacent to this area 20. By way of example only, temperature sensor 160 can be attached to water supply line 110 (or heated water supply hose 120) to measure the temperature of the water supply line.

[0063] A controller 180 may be provided, configured to control the operation of the heating element 120. By way of example only, the controller 180 may be connected to a temperature sensor 160, allowing the controller 180 to analyze and / or react based on signals from the temperature sensor 160. The controller 180 may activate the heating element 120 when the temperature of the water supply line 110 drops below a threshold. By way of example only, an electrical connector 125 may be connected to the controller 180 or a switch controlled by the controller 180. Therefore, the heating element 120 can only be operated when the temperature is below the temperature threshold.

[0064] It should be understood that, instead of a separate controller 180, the temperature sensor 160 can be implemented as a temperature control switch connected to the electrical connector 125. Furthermore, a microcontroller (not shown) can be integrated into the water supply line 110 and / or the heating element 120. This microcontroller can be configured to control the start / stop of the heating element 120 and can also be configured to monitor the temperature of the water supply line 110 and the operation of the heating element 120. The microcontroller can also be configured to receive and transmit data to control the heating element 120 and provide information about the operation of the water supply line 110 and / or the heating element 120.

[0065] Figure 3 further schematically illustrates fittings 105, 115 (or fluid line connectors). Fittings 105, 115 can be used to connect water supply line 110 to the main water line 250 and to the heated water supply hose 120. Therefore, fitting 115 is redundant if the heating element 120 is added to the water supply line 110 in the area 20 at risk of freezing.

[0066] Figure 4 schematically illustrates a plan view of another exemplary aircraft section 10 with a water supply. It should be understood that the details and components illustrated in and described with respect to Figure 3 can also be adopted / installed in the aircraft section 10 illustrated in Figure 4, but may be omitted for clarity and brevity. The aircraft section 10 in Figure 4 also shows fixtures 50, specifically two fixtures 50 of the plurality of fixtures 50 that can be arranged in the aircraft 1, as exemplarily.

[0067] The water supply line 110 and heating element 120 allow for the space-saving installation of the water supply line 110 throughout the aircraft 1 without interfering with other facilities in the aircraft 1. Therefore, a branch 121 of the water supply line 110 / 120 can be provided between the two fixed facilities 50, instead of a separate water supply line 110 branching from the main water line 250 for the second fixed facility 50. In other words, although the right fixed facility in FIG4 is connected to the main water line 250 in the same manner as illustrated in FIG2 and FIG3, the last fixed facility in FIG4 (the right side in FIG4) is connected to the water supply line 110 / 120 of the first fixed facility 50.

[0068] The branch points of the water supply lines 110 / 120 can be located in the area 20 at risk of freezing. A heating element 120 or a heated hose can then be provided to this water supply line 110, which branches to a second fixed facility, specifically a water consumer 130 within the second fixed facility. As can be derived from Figures 2 and 4, the water supply to the fixed facility can be installed in the space overlapping with the frame 3, such that the water supply lines 110 / 120 are concealed and do not interfere with other components of the aircraft 1.

[0069] The advantages of the technology proposed herein will be fully understood from the foregoing description, and it will be apparent that various changes can be made to the form, construction, and arrangement of its exemplary aspects without departing from the scope of this disclosure or sacrificing all its advantageous effects. Because the technology proposed herein can be varied in many ways, it will be appreciated that this disclosure should be limited only by the scope of the appended claims.

Claims

1. An aircraft segment (10), said aircraft segment comprising: At least one frame (3) arranged in the circumferential direction of the aircraft section; at least one cockpit floor (5) connected to the frame (3); a fixture (50) having a water consumer (130); and a water supply line (110) fluidly connected to the water consumer (130) and configured to supply water to the water consumer, characterized in that the water supply line (110) is installed in a space overlapping the frame (3) in the longitudinal direction of the aircraft section, and the aircraft section further includes: a heating element (120) configured to heat the water supply line (110) in the space overlapping the frame (3).

2. The aircraft section (10) according to claim 1, wherein, The water supply line (110) is further installed in the space below the cabin floor (5), and the heating element (120) is further configured to heat a portion of the water supply line (110) located in the space below the cabin floor (5).

3. The aircraft section (10) according to claim 1 or 2, wherein, The heating element (120) is a heated water supply hose fluidly connected to the water supply line (110) and arranged in the space overlapping the frame (3), and preferably further arranged in the space below the cabin floor (5).

4. The aircraft section (10) according to any one of claims 1 to 3, wherein, The heating element (120) is an electric heating element having an electrical connector (125).

5. The aircraft segment (10) according to claim 4, further comprising: a power supply line (25) configured to provide electrical power to the fixed facility (50), wherein, The electrical connector (125) of the heating element (120) is electrically connected to the power supply source (25), wherein, preferably, the electrical connector (125) is arranged in the fixture (50).

6. The aircraft section (10) according to any one of claims 1 to 5, further comprising: at least one section of main water pipeline (250), wherein, The water supply line (110) is fluidly connected to the main water line (250).

7. The aircraft section (10) according to claim 6, wherein, The main water line (250) is installed in the space below the cabin floor (5).

8. The aircraft segment (10) according to any one of claims 1 to 7, further comprising: a temperature sensor (160) arranged in the space overlapping with the frame (3) and preferably adjacent to the water supply line (110); and / or a controller (180) configured to preferably control the operation of the heating element (120) based on a temperature signal received from the temperature sensor (160).

9. An aircraft (1), comprising: At least one aircraft section (10) according to any one of claims 1 to 8.

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