Method and system for automatically testing cabin electrical consumers of an aircraft cabin

Abstract

A method for automatically testing cabin electrical appliances of an aircraft cabin, the method comprising: operating at least one cabin electrical appliance in a predetermined operating mode via a test controller; detecting a power consumption curve of the at least one cabin electrical appliance in the activated operating mode via a power controller of a power distribution system of the aircraft cabin, wherein the power controller regulates the power consumption of the at least one cabin electrical appliance within the power distribution system; transmitting the detected power consumption curve to the test controller; and comparing the detected power consumption curve with the reference curve for the activated operating mode of the at least one cabin electrical appliance via the test controller to test the functionality of the at least one cabin electrical appliance.

Description

Technical Field

[0001] This invention relates to a method and system for automatically testing cabin electrical components of an aircraft cabin. Background Technology

[0002] The cabin of an aircraft, especially a passenger aircraft cabin, typically includes a digital cabin management system (CMS). This system controls the electrical equipment and functions within the cabin and regulates the inputs and outputs of certain cabin parameters to passengers and crew. Its functions may include, in particular, cabin lighting, cabin communications (e.g., cockpit / cabin announcements), entertainment systems, visual and / or acoustic signals (e.g., emergency signals, no-smoking / seatbelt signs, door closing displays, etc.), cabin monitoring systems or cabin sensors (e.g., temperature sensors, smoke detectors, or cameras), and various other cabin functions, some of which may have safety-related significance. A typical cabin management system for this purpose also includes a central computer, multiple flight attendant panels, and a data network for data transmission within the cabin.

[0003] Here, the electrical equipment in the cabin is typically powered by an Electric Power Distribution System (EPDS), see, for example, EP 1 973 018 B1. For this purpose, such an EPDS may include one or more power controllers and / or power distribution boxes (PDBs) that regulate the power consumption of cabin appliances within the EPDS. For example, the EPDS may be designed to continuously monitor the power supply to cabin electronics. To this end, the EPDS can be connected to the cabin management system via a data network. The cabin management system may in turn have electronic switching units for activating (deactivating) individual cabin appliances or groups of cabin appliances.

[0004] In the automated testing of electronic components in the cabin, i.e., in the automated testing of cabin hardware, it is sometimes proposed to equip the cabin with suitable sensors to test the functionality of various cabin components. For example, by installing multiple light sensors in the cabin, such as brightness and / or ambient light sensors, cameras, etc., the functionality of the lighting system can be tested. However, this approach incurs certain installation and cost expenses because additional cables and data lines need to be laid in addition to these sensors. Summary of the Invention

[0005] Against this backdrop, the present invention aims to find a solution that is as simple as possible for the automated testing of cabin electrical equipment.

[0006] According to the present invention, this objective is achieved by a method for automatically testing cabin electrical components of an aircraft cabin, a system for automatically testing cabin electrical components of an aircraft cabin, and an aircraft having said system.

[0007] Accordingly, a method for automatically testing cabin electrical appliances of an aircraft cabin is proposed. The method includes: operating at least one cabin electrical appliance in a predetermined operating mode via a test controller; detecting the power consumption curve of the at least one cabin electrical appliance in the activated operating mode via a power controller of the aircraft cabin's power distribution system, wherein the power controller adjusts the power consumption of the at least one cabin electrical appliance within the power distribution system; transmitting the detected power consumption curve to the test controller; and comparing the detected power consumption curve with a reference curve of the activated operating mode of the at least one cabin electrical appliance via the test controller to test the functionality of the at least one cabin electrical appliance.

[0008] Furthermore, a system for automatically testing cabin electrical appliances of an aircraft cabin is proposed. The system includes at least one cabin electrical appliance; a power distribution system for supplying power to the at least one cabin electrical appliance, wherein the power distribution system includes a power controller designed to regulate the power consumption of the at least one cabin electrical appliance within the power distribution system and to detect the power consumption curve of the at least one cabin electrical appliance; and a test controller communicatively connected to the power controller and designed to: operate the at least one cabin electrical appliance in a predetermined operating mode, and compare the power consumption curve of the at least one cabin electrical appliance detected by the power controller and transmitted to the test controller in the activated operating mode with a reference curve for the activated operating mode, in order to test the functionality of the at least one cabin electrical appliance.

[0009] Furthermore, the present invention also proposes an aircraft having a system according to the present invention.

[0010] This invention is based on the idea of ​​automatically testing cabin electrical equipment using the power controller of the existing power distribution system for the cabin. To this end, the invention follows a scheme where the power consumption or power consumption curves of individual cabin power supplies or groups of power supplies are used, to some extent, as sensors. The power consumption curves are detected and compared with a predetermined, desired reference curve. If the detected power consumption curve is sufficiently consistent with the corresponding reference curve, the tested cabin power supply or group of power supplies is considered to be functionally normal. However, if the detected power consumption curve deviates significantly from the reference curve, a functional deficiency of one or more cabin power supplies is identified. Therefore, as a result, additional sensors for automated testing and the necessary wiring can be eliminated. Thus, the system is significantly simpler and ultimately more robust to potential sources of error (e.g., sensor failure and / or missing sensors, defective and / or inaccurately calibrated or configured sensors, etc.). More specifically, a practical testing method or system is provided by which cabin condition testing can be performed without large-scale and expensive testing.

[0011] For example, a lighting system can be tested by operating one or more light sources or lamps and evaluating their power consumption. If the actual power consumption deviates from the curve expected when fully functional, it can be concluded that the lighting system or a component of the system is functionally deficient.

[0012] On the one hand, the method according to the invention can be operated entirely within the aircraft cabin. For this purpose, for example, a test controller can be specifically installed within the cabin. However, on the other hand, the method can also be performed, for example, to some extent, by test personnel located outside the aircraft cabin via remote diagnostics. For this purpose, cabin power supplies and power controllers can be accessed from outside the cabin, for example, by the test controller.

[0013] Advantageous configurations and improvements are derived below and from the description of the accompanying drawings.

[0014] According to an improved approach, multiple cabin power supplies can be tested together as a group of power supplies. Therefore, in this improved approach, instead of testing individual cabin power supplies separately, the common power consumption curve of the group formed by multiple power supplies is tested. Here, the common power consumption curve is compared correspondingly with an expected or predetermined reference curve for that group. This allows for quick and easy acquisition of results regarding the basic state of a group of power supplies without the need for costly individual testing of each cabin power supply.

[0015] According to an improved approach, a reference curve for the activated operating mode of a power supply group is determined from reference curves for the operating modes of individual cabin power supplies. For example, a power supply group may consist of multiple cabin power supplies, each operating in a specific operating mode. The common operating mode of the cabin power supplies within the power supply group can now be defined as a combination of the operations of the individual cabin power supplies. If the reference curves for the individual operating modes of the cabin power supplies are known, the reference curve for the common operation can be calculated from them, where appropriate. For example, a power supply group may consist of four identical cabin power supplies, where the power consumption curve of the power supply group can be generated by simply summing the power consumption curves of the individual cabin power supplies.

[0016] According to an improved version, in the event of a functional deficiency in the power supply group, the method further includes individually testing the functionality of the cabin power supply subgroups of the power supply group. Therefore, if a functional deficiency is demonstrated in the testing of the power supply group, the functionality of different subgroups of the power supply group or subsets of cabin power supplies can be tested sequentially.

[0017] According to an improved approach, individual tests can be repeated until at least one malfunctioning cabin electrical appliance is identified. Once a fault or functional deficiency is identified in a group of appliances, progressively smaller groups of cabin electrical appliances can be tested repeatedly until a single remaining group or set of remaining cabin electrical appliances is identified as malfunctioning.

[0018] According to an improved approach, multiple cabin electrical appliances can be divided into at least two appliance zones. Cabin electrical appliances in one of these zones can be tested jointly, while a power controller disables the power supply to the appliances in the other zone. This improved approach is particularly useful for identifying incorrect wiring or connections in individual cabin electrical appliances. In one example, the system comprises four identical cabin electrical appliances, each paired and divided into two distinct appliance zones, such as two separate cabin zones, for example, a forward zone and a rear zone. Assuming all four appliances are fully functional, however, one appliance in each appliance zone may be confused with an appliance in the other zone in its connection; for example, an appliance from the forward zone may be incorrectly connected in the rear zone, and conversely, one appliance in the rear zone may be connected to the forward zone. Joint testing of all four appliances may now only indicate that the group is fully functional. However, if the power supply to the cabin appliances in one of these two power-consuming areas (e.g., the aft area) is disabled, testing of the cabin appliances in the other power-consuming area (i.e., the forward area in the example above) shows that this group of cabin appliances is malfunctioning. In other words, one of the two cabin appliances is not receiving power due to an incorrect connection (this appliance is connected to the electrically disabled power-consuming area; in this example, the aft area), causing the power consumption curve to not correspond to the expected reference curve for two fully functional cabin appliances.

[0019] According to an improved approach, at least one cabin power supply can be tested using its corresponding reference curve for multiple different operating modes. For example, the different functionalities of a cabin power supply or a group of cabin power supplies can be tested. In a specific example, a lighting system consisting of multiple light sources or lamps is tested, where different lighting conditions are detected, such as in terms of color, brightness, and luminous intensity.

[0020] According to one improvement, at least one cabin electrical appliance may include components derived from: cabin lighting systems, communication systems, entertainment systems, cabin sensors, sanitation equipment, service systems, and / or seating systems.

[0021] The above configurations and improvements can be combined with each other arbitrarily where meaningful. Other possible configurations, improvements, and implementations of the invention include combinations of features not explicitly mentioned in the preceding or subsequent descriptions of the invention with reference to embodiments. Furthermore, those skilled in the art can add individual aspects as improvements or additions to the corresponding basic forms of the invention. Attached Figure Description

[0022] The invention will now be described in detail with the aid of embodiments shown in the illustrative drawings. In the drawings:

[0023] Figure 1 A schematic diagram of a system for automatically testing cabin electrical components of an aircraft cabin according to an embodiment of the present invention is shown.

[0024] Figure 2 Showing the use of Figure 1 A schematic flowchart of one method of the system;

[0025] Figure 3 A schematic diagram of a system according to another embodiment of the present invention is shown; and

[0026] Figure 4 Showing has Figure 1 Or a schematic side view of the aircraft in system 3.

[0027] The accompanying drawings should provide a further understanding of embodiments of the invention. They illustrate embodiments and serve to explain the principles and concepts of the invention in conjunction with the specification. Many other embodiments and advantages described above will become apparent from viewing the drawings. Elements in the drawings are not necessarily shown to scale relative to each other.

[0028] In the accompanying drawings, identical, functionally identical, and operationally identical elements, features, and components are correspondingly given the same reference numerals unless otherwise described in detail. Detailed Implementation

[0029] Figure 1 A schematic diagram of a system 10 for cabin power supplies 1 of a cabin 11 of an automated test aircraft 100, according to an embodiment of the present invention, is shown. Such an aircraft 100 can, for example, be... Figure 4 The passenger aircraft is shown as an example.

[0030] System 1 includes a cabin power consumer 1 or a power consumer group 13 consisting of multiple cabin power consumers 1. System 1 further includes a power distribution system 4 for supplying power to the at least one cabin power consumer 1. The power distribution system 4 includes a power controller 3 designed to regulate the electrical power consumption of the at least one cabin power consumer 1 within the power distribution system 4. For this purpose, the power controller 3 is electrically connected to the at least one cabin power consumer 1 via one or more wires 7. For example, the power controller 3 may be a distribution box (PDB) of an EPDS. Furthermore, the cabin 11 has a cabin management system 12 (CMS) designed to operate the at least one cabin power consumer 1. For this purpose, the CMS 12 may, for example, include a solid state power controller (SSPC) or other electronic switching elements (not shown), through which individual cabin power consumers 1 or groups of cabin power consumers 1 can be operated (deactivated).

[0031] System 10 also includes a test controller 2, which is communicatively connected to the power controller 3 and connected to the CMS 12 (see [link]). Figure 1 (Middle arrow). The test controller 2 is designed to operate the at least one cabin power consumer 1 in a predetermined operating mode via the CMS 12. Furthermore, the power controller 3 is designed to detect the power consumption curve of the at least one cabin power consumer 1 and transmit it to the test controller 2. The test controller 2 is configured to compare the transmitted power consumption curve with a predetermined reference curve for the activated operating mode to test the functionality of the at least one cabin power consumer 1. In the case of testing power consumer group 13, the corresponding reference curve for the activated operating mode of power consumer group 13 can be determined from the reference curve for the operating mode of the individual cabin power consumer 1. It is further proposed that the at least one cabin power consumer 1 be tested for multiple different operating modes using their respective corresponding reference curves.

[0032] exist Figure 2 The diagram schematically illustrates the corresponding test method M. Method M includes operating the at least one cabin electrical appliance 1 in a predetermined operating mode via test controller 2 under M1. Method M further includes detecting the power consumption curve of the at least one cabin electrical appliance 1 in the activated operating mode via power controller 3 of power distribution system 4 under M2. Method M further includes transmitting the detected power consumption curve to test controller 2 under M3 and comparing the detected power consumption curve with a reference curve for the activated operating mode of the at least one cabin electrical appliance 1 via test controller 2 under M4, in order to test the functionality of the at least one cabin electrical appliance 1.

[0033] If the detected power consumption curve matches the reference curve, then the cabin power consumer 1 or power consumer group 13 is classified as functionally normal. Figure 2 (Ref. 6 in the attached figure). Therefore, the general functionality of a group of naval power consumers 1 can be inferred very quickly without the need for additional sensors with corresponding wiring. Here, the power consumption curve of the power consumer group 13 or the naval power consumer 1 is used to some extent as the “footprint” of the component.

[0034] Conversely, if the power consumption curve does not adequately correspond to the reference curve, then power consumption group 13 or at least one cabin power consumption 1 is initially classified as substantially malfunctioning. In this case, with power consumption group 13 exhibiting functional deficiencies, method M can then proceed with individual testing of the functionality of the cabin power consumption 1 subgroup of power consumption group 13 under method M5. This process can be repeated (see [link to documentation]). Figure 2 (The arrow between M5 and M1) continues until at least one malfunctioning cabin electrical appliance 5 is identified. Therefore, the method M or system 10 shown not only enables practical testing of functionality but can also be used to locate faulty components.

[0035] Particular difficulties may arise if one or more of the naval power supplies 1 are incorrectly connected and / or wired within the naval compartment 11. Therefore, Figure 3 A system 10 according to another embodiment of the present invention is shown, which is substantially the same as Figure 1 and Figure 2 The system depicted is the same. However, exemplarily, in this variant, four identical cabin power devices 1 are explicitly provided, each individually powered by a power controller 3. For example, the cabin power device 1 could be a speaker connected to a digital-to-analog converter 8 via an analog data line 9a, which in turn is connected to a digital data line 9b, such as the data bus of a CMS 12. Two of the cabin power devices 1 are located in a first power device region 14a, for example, in the forward region of the cabin 11. The other two of the cabin power devices 1 are located in a second power device region 14b, for example, in the aft region of the cabin 11. However, in Figure 3In an exemplary embodiment, two central cabin power supplies 1 are incorrectly wired to CMS 12, such that both are located in incorrect power supply areas 14a, 14b in their connection to CMS 12 (see the routing of line 9a for these two central cabin power supplies 1). It is assumed that all four cabin power supplies 1 are fully functional. In this case, a common test of all four cabin power supplies 1 would correspondingly yield positive results, as their power consumption curves may not show any deviation from the expected reference curve. However, operating the cabin power supplies 1 via CMS 12 during operation may have undesirable consequences due to incorrect wiring. For example, attempting to operate a speaker in the forward area of ​​cabin 11 via CMS 12, i.e., in... Figure 3 The two upper cabin power supplies 1 may, due to incorrect wiring, only operate one of the two speakers in the forward area. Alternatively, one speaker in the rear area may also be switched on.

[0036] This problem can be solved by jointly testing the cabin power consumer 1 in one of the power consumer areas 14a and 14b (e.g., the upper power consumer area 14a, i.e., the forward area), while the power controller 3 disables the current supply to the cabin power consumer 1 in the other power consumer area 14b (i.e., the aft area). In this case, by detecting and comparing the power consumption curve of the cabin power consumer 1 in the upper power consumer area 14a, it can be concluded that one of the two cabin power consumers 1 is malfunctioning (i.e., the one located in the lower part of the two). In this regard, by disabling different power consumer areas 14a and 14b, it is possible to detect whether there is a faulty connection within the system 10, i.e., due to incorrect wiring, the individual cabin power consumers 1 are incorrectly assigned to the wrong power consumer areas 14a and 14b.

[0037] In the detailed description above, different features used to improve the rigor of the illustrations are summarized in one or more examples. However, it should be clear that the above description is merely illustrative and not restrictive. This description is intended to cover all alternatives, modifications, and equivalents of different features and embodiments. Many other examples will immediately and directly become apparent to those skilled in the art upon consulting the above description.

[0038] These embodiments were selected and described in order to best demonstrate the principles upon which the invention is based and its practical applicability. Thus, those skilled in the art can optimally modify and use the invention and its various embodiments with reference to the intended uses. In this specification, the terms "comprising" and "having" are used as conceptualizations of the neutral language of the corresponding term "comprising." Furthermore, the use of the term "a" should, in principle, not exclude multiple features and components thus described.

[0039] List of reference numerals

[0040] 1. Cabin power supplies

[0041] 2 Test Controller

[0042] 3 Power Controller

[0043] 4. Power Distribution System

[0044] 5 Malfunctioning cabin power supplies

[0045] 6. Functionally operating cabin power supplies / power supply groups

[0046] 7. Electrical wires

[0047] 8. Digital-to-Analog Converter

[0048] 9a Analog Data Cable

[0049] 9B Digital Data Cable

[0050] 10 System

[0051] 11 Cabin

[0052] 12. Cabin Management System

[0053] 13 power consumption units

[0054] 14a, 14b Power Consumption Areas

[0055] 100 aircraft

[0056] M method

[0057] M1 Method Steps

[0058] M2 Method Steps

[0059] M3 Method Steps

[0060] M4 Method Steps

[0061] M5 Method Steps

Claims

1. A method (M) for automatically testing the cabin power supplies (1) of the cabin (11) of an aircraft (100), the method comprising: The test controller (2) enables at least one cabin power supply (1) to operate in a predetermined operating mode (M1). The power consumption curve of at least one cabin power consumer (1) in the activated operating mode is detected by the power controller (3) of the power distribution system (4) of the cabin (11) of the aircraft (100), wherein the power controller (3) regulates the power consumption of the at least one cabin power consumer (1) within the power distribution system (4). The detected power consumption curve is transmitted (M3) to the test controller (2); and The power consumption curve detected is compared (M4) with a reference curve for the activated operating mode of the at least one cabin power consumer (1) by the test controller (2) in order to test the functionality of the at least one cabin power consumer (1). The multiple cabin power supplies (1) are divided into at least two power supply zones, wherein the cabin power supplies (1) in one of the power supply zones (14a) are tested together, while the power controller (3) disables the power supply to the cabin power supplies (1) in the other power supply zone (14b), and wherein by disabling the different power supply zones, a faulty connection is detected in the system (10) of the cabin power supplies (1).

2. The method (M) according to claim 1, wherein a plurality of cabin power supplies (1) are tested together as a power supply group (13).

3. The method (M) according to claim 2, wherein a reference curve for the activated operating mode for the power supply group (13) is determined from a reference curve for the operating mode for the individual cabin power supply (1).

4. The method (M) according to claim 2 or 3, further comprising: In the event of a functional deficiency in the power consumption group (13), the functionality of the cabin power consumption (1) subgroup of the power consumption group (13) is tested separately (M5).

5. The method (M) of claim 4, wherein the individual tests (M5) are repeated until at least one malfunctioning cabin electrical appliance (5) is identified.

6. The method (M) according to any one of claims 1 to 5, wherein the at least one cabin power supply (1) is tested with a corresponding relevant reference curve for different operating modes.

7. The method (M) according to any one of claims 1 to 6, wherein the at least one cabin power supply (1) comprises components derived from: a cabin lighting system, a communication system, an entertainment system, cabin sensors, sanitation facilities, a service system, and a seating system.

8. A system (10) for cabin power supplies (1) of a cabin (11) of an automated test aircraft (100), the system comprising: At least one cabin power supply (1); A power distribution system (4) for the power supply of the at least one cabin appliance (1), wherein the power distribution system (4) includes a power controller (3) designed to regulate the power consumption of the at least one cabin appliance (1) within the power distribution system (4) and detect the power consumption curve of the at least one cabin appliance (1), wherein the plurality of cabin appliances (1) are divided into at least two appliance regions, wherein cabin appliances (1) in one of the appliance regions (14a) are tested together, while the power controller (3) disables the power supply of cabin appliances (1) in the other appliance region (14b), wherein by disabling different appliance regions, a faulty connection is detected within the system (10) of the cabin appliances (1); and Test controller (2), which is communicatively connected to power controller (3) and is designed to: enable at least one cabin power consumer (1) to operate in a predetermined operating mode, and compare the power consumption curve of the at least one cabin power consumer (1) detected by power controller (3) in the activated operating mode and transmitted to test controller (2) with a reference curve for the activated operating mode in order to test the functionality of the at least one cabin power consumer (1).

9. An aircraft (100) having the system (10) according to claim 8.

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