DE202015106938U1 - Detection system for determining the functionality of a plurality of system units in an aircraft - Google Patents

Abstract

Detection system (1) for determining the functionality of a plurality of system units (3) in an aircraft, the system units (3) each comprising a plurality of lamps (5), the system units (3) and the lamps (5) each having an integral configurable test device for verifying their respective operability, the test device each comprising a particular version of a configuration file, the lamps (5) each having an error-free status if undamaged and comprising the particular version of the configuration file, and wherein the system units (3) respectively have a fault - free status if all the lamps (5) of a system unit (3) have a faultless status, and wherein the status of the system units (3) can be communicated to a cabin management system (9) such that a comparison is made between the cabin management system (9) one provided in the cabin management system (9) envisaged versio n a configuration file and the particular version of the configuration file is feasible characterized in that a system unit (3) with a faulty status by the cabin management system (9) is controlled such that the lamps (5) of the system unit (3) with the faulty status in specific errors have a specific color.

Description

The present invention relates to a detection system for determining the functionality of a plurality of system units in an aircraft, in particular in a passenger aircraft, wherein the system units each comprise a plurality of lamps, the system units and the lamps each having an integral configurable test device for checking their respective operability the test device each comprises a particular version of a configuration file, the lamps each having an error-free status if undamaged and comprising the particular version of the configuration file, and the system units each having an error-free status if all lamps of a system unit have a healthy status and wherein the status of the system units can be communicated to a cabin management system in such a way that, through the cabin management system, a comparison is made between a cabin management system provided version of a configuration file and the specific version of the configuration file is feasible.

The invention further relates to a detection system for determining the functionality of a plurality of system units in an aircraft, the system units each comprising a plurality of lamps, the system units and the lamps each having an integral configurable test device for checking their respective operability, the test device each having a specific Version of a configuration file, wherein the lamps each have a faultless status, if they are undamaged and include the specific version of the configuration file, and wherein the status of the lamps is transmitted to a cabin management system such that the cabin management system, a comparison between a stored in the cabin management system provided version of a configuration file and the particular version of the configuration file is feasible.

In the present case, the term "configuration file" is to be understood as software that can be loaded onto devices, for example system units or lamps.

Furthermore, a lamp is present undamaged, if it is basically functional. In this case, the lamp was not damaged by external influences and it was not rendered incapable of aging or other internal processes in the lamp itself.

Such comparisons are known and are already used in the construction, maintenance or repair of an aircraft. However, many system units of an aircraft are in their intended configuration position poorly accessible or poorly visible, so that no unambiguous identification of system units with faulty status by the aircraft manufacturer or the maintenance or repair personnel is possible. This is the case, for example, for light units which are to be installed in such a way that they generate a certain lighting mood, but are invisible to the passenger's eye. In principle, however, due to the limited space available on board a passenger plane, all systems may be affected.

It is therefore an object of the present invention to provide a detection system that allows easier detection of system units with a faulty status by aircraft builders and maintenance or repair personnel.

To solve this problem, the device with the features of the claims 1 and 2. Advantageous embodiments are the subject of the respective subclaims.

According to the invention, a system unit with a faulty status can be controlled by means of the cabin management system in such a way that the lamps of the system unit have a specific color for specific errors. This may be a simple color code in which green glowing lights of a system unit means that the system unit has a faultless status while a red color indicates a faulty status. But it is also a more complex color possible.

Alternatively, a lamp with a faulty status can be controlled by the cabin management system in such a way that the lamp has a specific color for specific errors.

In a preferred embodiment, the coloring comprises a temporal sequence of colors. In this way, the search for a faulty system unit can be simplified with several adjacent system units with a hard to reach configuration position.

The system units are preferably designed to carry out a self-test to determine their status at the request of the cabin management system and to transmit the result of the self-test to the cabin management. This is possible through so-called built-in test equipment (BITE).

The lamps may also preferably be configured to carry out a self-test to determine their status by means of BITE at the request of the cabin management system and to transmit the result of the self-test to the cabin management.

The cabin management system and the system units are preferably connected to one another via a bidirectional data link. In this way, information such as the status of the light units at the request of the cabin management system can be exchanged weight-saving over a common data connection.

A system unit may each preferably comprise up to six lamps. But also a larger number of lamps is conceivable.

The system units are particularly preferably light units, since it is particularly advantageous for indirect cabin lighting to facilitate spatially resolved fault determination if no cabin lining has to be removed or light units have to be removed from the configuration position.

The present invention further relates to an aircraft with a cabin lighting according to the invention. Preferably, the aircraft is a passenger aircraft.

The invention will be explained below with reference to the drawing.

1 shows a schematic view of the detection system according to the invention 1 for determining the functionality of a plurality of system units 3 , As can be seen, the system units include 3 preferably each several lamps 5 , here are six per system unit 3 displayed. Here are the system units 3 and the lamps 5 each an integral configurable test device for checking their respective functionality.

As already described above, the lamps 5 each a healthy state if they are undamaged and have loaded a specific version of the configuration file.

The system units 3 in turn, each have a faultless status when all the lamps 5 a system unit 3 have a healthy status.

The current status of the system units 3 or alternatively the lamps 5 is via the bidirectional data link 7 to the cabin management system 9 transmittable. There is then a comparison between a cabin management system 9 deposited intended version of a configuration file and the particular loaded version of the configuration file is feasible.

In turn, the system units 3 or alternatively the lamps 5 to be configured on request of the cabin management system 9 perform a self-test to determine their status and the result of the self-test to the cabin management system 9 to convey.

Especially preferred are the system units 3 Light units.

The cabin management system 9 may be, for example, the Cabin Intercommunication Data System (CIDS). In the CIDS, cabin-related information is stored in a CIDS-internal database, the so-called CIDS Cabin Assignment Module (CAM). A central computer 11 enables communication between system units 3 and the cabin management system 9 ,

LIST OF REFERENCE NUMBERS

1

detection system

3

system unit

5

lamp

7

bidirectional data link

9

Cabin Management System

11

central computer

Claims (9)

Detection system ( 1 ) for determining the functionality of a plurality of system units ( 3 ) in an aircraft, the system units ( 3 ) several lamps ( 5 ), the system units ( 3 ) and the lamps ( 5 ) each have an integral configurable test device for checking their respective functionality, the test device each comprising a specific version of a configuration file, the lamps ( 5 ) each have a healthy state if undamaged and include the particular version of the configuration file, and where the system units ( 3 ) each have a faultless status when all the lamps ( 5 ) of a system unit ( 3 ) have a healthy status, and the status of the system units ( 3 ) to a cabin management system ( 9 ) is such that by the cabin management system ( 9 ) a comparison between a cabin management system ( 9 ) deposited provided version of a configuration file and the particular version of the configuration file is feasible characterized in that a system unit ( 3 ) with a faulty status by means of the cabin management system ( 9 ) is controllable such that the lamps ( 5 ) of the system unit ( 3 ) have a certain coloration with the erroneous status for specific errors. Detection system ( 1 ) for determining the functionality of a plurality of system units ( 3 ) in an aircraft, the system units ( 3 ) several lamps ( 5 ), the system units ( 3 ) and the lamps ( 5 ) each have an integral configurable test device for checking their respective functionality, the test device each comprising a specific version of a configuration file, the lamps ( 5 ) each have a healthy state if undamaged and include the particular version of the configuration file, and the status of the lamps ( 5 ) to a cabin management system ( 9 ) is such that by the cabin management system ( 9 ) a comparison between a cabin management system ( 9 ) deposited version of a configuration file and the particular version of the configuration file is feasible characterized in that a lamp ( 5 ) with a faulty status by means of the cabin management system ( 9 ) is controllable such that the lamp ( 5 ) has a specific color for specific errors. Detection system ( 1 ) according to claim 1 or 2, wherein the coloring comprises a temporal sequence of colors. Detection system ( 1 ) according to claim 1 or 3, wherein the system units ( 3 ) are designed, at the request of the cabin management system ( 9 ) to carry out a self-test to determine their status and to transmit the result of the self-test to the cabin management. Detection system ( 1 ) according to claim 2 or 3, wherein the lamps ( 5 ) are designed, at the request of the cabin management system ( 9 ) perform a self-test to determine their status and the result of the self-test to the cabin management system ( 9 ). Detection system ( 1 ) according to one of the preceding claims, wherein the cabin management system ( 9 ) and the system units ( 3 ) via a bidirectional data link ( 7 ) are connected. Detection system ( 1 ) according to one of the preceding claims, wherein a system unit ( 3 ) each up to six lamps ( 5 ). Detection system ( 1 ) according to one of the preceding claims, wherein the system units ( 3 ) Are light units. Aircraft with a detection system ( 1 ) according to one of the preceding claims.

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