WO2015172857A1

WO2015172857A1 - Power and data distribution module and method for power and data distribution in an airborne vehicle

Info

Publication number: WO2015172857A1
Application number: PCT/EP2014/075920
Authority: WO
Inventors: Klaus-Udo Freitag; Palit YENER
Original assignee: Airbus Operations GmbH
Current assignee: Airbus Operations GmbH
Priority date: 2014-05-15
Filing date: 2014-11-28
Publication date: 2015-11-19
Anticipated expiration: 2016-11-15
Also published as: US11018521B2; US20170063151A1; EP2945244B1; EP2945244A1

Abstract

A power and data distribution module (10), particularly in an aircraft or spacecraft, comprising a plurality of power supply input interfaces (11), a data bus interface (12), a plurality of power output interfaces (26-29, 40), a plurality of voltage distribution modules (19, 20) coupled between the power supply input interfaces and the power output interfaces, a load shedding module (17) receiving load shedding information via data communication over one or more of the plurality of power supply lines (P1-P3), and a data concentrator (31) receiving redundant load shedding information via data communication over a data bus (D1) and transmitting the redundant load shedding information to the load shedding module, wherein the load shedding module sheds one or more electrical loads connected to the plurality of power output interfaces depending on the received load shedding and the redundant load shedding information.

Description

Power and data distribution module and

method for power and data distribution in an airborne vehicle

TECHNICAL FIELD

The present invention relates to a power and data distribution module, particularly for use in aircraft or spacecraft, a power and data distribution network of an airborne vehicle, an airborne vehicle comprising a power and data distribution network and a method for power and data distribution in an airborne vehicle. The invention may be particularly useful for any type of vehicle where for reasons of security multiple electrical routes are desired, for example waterborne vehicles such as ships or submarines, groundborne vehicles such as trucks, busses or trains, and spaceships, starships, space stations or satellites.

TECHNICAL BACKGROUND

Every new aircraft is primarily designed to satisfy the customer's needs. The design should support manufacturing needs and constraints, allowing fast ramp-ups and high load production. On the other hand, cost efficiency, simplicity of operation along with flexibility in terms of customization should be considered in the design phase.

In contemporary power distribution networks of aircraft, power switching activities are performed mostly in electronic power distribution centers. This means that different load systems and different sheddable loads within the aircraft each need a separate power line from the power source up to the installed power consumer. Such network topology requires many different electrical routings and wirings within the aircraft. Moreover, conventional data communication systems within aircraft are usually individually routed for each different consumer or circuit.

The document US 2009/0167076 Al discloses a system and a method for distribution of electric power inside an aircraft. The system includes at least two systems distributing electric power from at least one power source to electric loads of the aircraft via electric and/or electronic protection/switching components, the components being configurable and commandable by dedicated electronics. Each electric distribution system includes command electronics in which a configuration file is downloaded allocating an installation status to each of the protection/switching components.

The document US 6,664,656 B2 discloses a data collection network and electrical power distribution network designed to reduce airplane wire weight and to allow nearly complete wiring design and installation of wiring and equipment in the major structural sections of the airplane.

The document US 2013/0169036 Al discloses an aircraft power distribution network comprising first and second galvanically isolated power bus bars, and first and second remote data concentrators (RDCs), each RDC having an input/output interface (I/O) and a power supply, the first RDC power supply being connected to the first power bus bar, the second RDC power supply being connected to the second power bus bar, an input/output device being connected to the I/O of the first RDC and to the I/O of the second RDC, each RDC being adapted to supply electrical power to the input/output device through its respective I/O, wherein each RDC includes a switch for isolating the input/output device, and the switches being operatively coupled such that electrical power cannot be supplied to the input/output device by both RDCs simultaneously. The document CN 1204879 A discloses a power distribution arrangement, especially in an aircraft, includes plural power sources, a power line having plural power supply strands connected to the power sources, plural power consumer groups each including plural power consuming devices, and branch lines respectively connecting the power line with the power consumer groups. A respective allocation unit selectively interconnects the power consuming devices of each group with selected individual branch line strands of the branch lines. A status unit acquires information regarding the respective operating status of the power sources and the power line strands, and conveys corresponding information regarding a power failure on any power line strand to a central power control unit, which correspondingly transmits control commands over a control bus to the respective allocation units. In response to the control commands, each allocation unit automatically disconnects power consuming devices from any power line strand that has failed and reconnects the devices to another power line strand that is still operating properly.

SUMMARY OF THE DISCLOSURE

One object of the invention is thus to provide solutions for decentralized power shedding that take into consideration the different power needs of different electrical

loads/consumers.

This object is achieved by a power and data distribution module having the features of claim 1, a power and data distribution network of an airborne vehicle having the features of claim 9, an airborne vehicle having the features of claim 12, and a method for power and data distribution in an airborne vehicle having the features of claim 13.

A first aspect of the disclosure pertains to a power and data distribution module, particularly in an aircraft or spacecraft, comprising a plurality of first power supply interfaces, each configured to be connected to a plurality of power supply lines, a data bus interface configured to be connected to a data bus, a plurality of power output interfaces, each configured to be connected to one or more electrical loads and to supply electrical power from one of the first power supply interfaces to the connected electrical loads, a plurality of voltage distribution modules coupled between the plurality of first power supply interfaces and the plurality of power output interfaces and configured to provide AC or DC voltage via the power output interfaces, a load shedding module configured to receive load shedding information via data communication over one or more of the plurality of power supply lines, and a data concentrator configured to receive redundant load shedding information via data communication over the data bus and to transmit the redundant load shedding information to the load shedding module, wherein the load shedding module is further configured to shed one or more electrical loads connected to the plurality of power output interfaces depending on the received load shedding information and the received redundant load shedding information.

According to a second aspect of the disclosure, a power and data distribution network comprises a plurality of PADD modules according to the first aspect of the disclosure, at least one electrical power distribution center coupled to the plurality of PADD modules via one or more of the first power supply interfaces, and a data communication director coupled the plurality of PADD modules via the data bus interface.

According to a third aspect of the disclosure, a method for power and data distribution in an airborne vehicle comprises generating electrical power in at least one electrical power distribution center, distributing the generated electrical power via one or more power supply lines to a plurality of PADD modules, receiving load shedding information at the plurality of PADD modules via data communication over one or more of the plurality of power supply lines, receiving redundant load shedding information at the plurality of PADD modules via data communication over a data bus, transmitting the redundant load shedding information in the plurality of PADD modules to the load shedding module, and shedding one or more electrical loads connected to power output interfaces of the PADD modules depending on the received load shedding information and the received redundant load shedding information. According to a fourth aspect of the disclosure, an airborne vehicle comprises a power and data distribution network in line with the second aspect of the disclosure.

Key to the present invention is the development of a common power and data infrastructure of cabin power and data distribution for all cabin and cargo essential and non-essential modules and systems. The power and data distribution modules of the present disclosure may be employed as decentralised platforms for data and electrical power distribution for all linked cabin and cargo equipment, modules and systems.

It will advantageously serve as selective electrical load shedding, voltage transforming, overvoltage and overcurrent protection and switching-on-demand device. Additionally, the power and data distribution modules of the present disclosure operate as data transformers and/or transmission providers as well as functional hosts to all functions within cabin and cargo areas of an airborne vehicle.

The power and data distribution network of the present disclosure takes into account additional requirements based on particular risks, such as engine bursts or hydraulic accumulator bursts, without requiring different redundant routings for each relevant different system, such as oxygen distribution, smoke detection and emergency lighting. It relies on a universal data bus concept with combined data over power, wireless, optical data transmission and wirebound data communication in one unit.

The power and data distribution network of the present disclosure advantageously allows for elimination of power supply line wiring, communication via a high speed data bus and reduction of interface connectors. Moreover, the power and data distribution network of the present disclosure provides decentralised shedding functionality of selective loads, load groups or single consumers that are advantageously communicated redundantly via data over power (DOP), wireless data transmission and/or high speed cabin data bus electrical or optical in the aircraft cabin, thereby increasing safety and reliability of the whole network. The installation efforts of wirings, routes, connector interfaces, brackets for wiring installations and different data bus communication are reduced while only route segregation between high voltage AC power supply lines and hot busses that cannot be powered or shut down as other normal busses is necessary, thus leading to minimized installation weight and reduced troubleshooting action and troubleshooting time while maintaining the same or higher reliability of the overall network.

According to an embodiment of the power and data distribution module, the power and data distribution module may comprise a wireless transceiver coupled to the data concentrator, wherein the data concentrator is configured to receive redundant load shedding information via wireless data communication over the wireless transceiver.

According to a further embodiment of the power and data distribution module, the power and data distribution module may comprise a secondary power supply interface configured to be connected to other PADD modules, and a solid state power controller coupled to the secondary power supply interface, wherein the load shedding module is further configured to control the solid state power controller depending on the received load shedding information and the received redundant load shedding information.

According to a further embodiment of the power and data distribution module, the power and data distribution module may comprise a plurality of circuit breaking devices coupled between the power output interfaces and the voltage distribution modules, and a shedding control unit coupled to the load shedding module, the shedding control unit being configured to selectively activate or deactivate the circuit breaking devices depending on the received load shedding information and the received redundant load shedding information. According to a further embodiment of the power and data distribution module, the first power supply interfaces may be configured to receive high-voltage AC power and low- voltage DC power.

According to a further embodiment of the power and data distribution module, the secondary power supply interface may be configured to receive hot battery DC power.

According to a further embodiment of the power and data distribution module, the data bus interface may be configured to receive high speed cabin data.

According to a further embodiment of the power and data distribution module, the power and data distribution module may comprise an electrical energy storage device coupled to at least one of the plurality of power output interfaces and configured to temporarily store electrical energy to provide to one or more electrical loads coupled to the at least one of the plurality of power output interfaces.

According to a further embodiment of the power and data distribution module, the power and data distribution module may be an aircraft galley module or an aircraft lavatory module.

According to an embodiment of the power and data distribution network, the power and data distribution network may comprise a plurality of electrical energy supplies, and a plurality of electrical circuit breakers coupled to the plurality of electrical energy supplies and configured to selectively decouple the plurality of electrical energy supplies from the output of the electrical power distribution center.

According to a further embodiment of the power and data distribution network, the power and data distribution network may comprise an electrical network management controller configured to control the plurality of electrical circuit breakers. BRIEF DESCRIPTION OF THE DRAWINGS

The invention will be explained in greater detail with reference to exemplary embodiments depicted in the drawings as appended.

The accompanying drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this specification. The drawings illustrate the embodiments of the present invention and together with the description serve to explain the principles of the invention. Other embodiments of the present invention and many of the intended advantages of the present invention will be readily appreciated as they become better understood by reference to the following detailed description. The elements of the drawings are not necessarily to scale relative to each other. Like reference numerals designate corresponding similar parts.

Fig. 1 schematically illustrates a power and data distribution network in an airborne vehicle according to an embodiment.

Fig. 2 schematically illustrates an electrical power distribution center for the power and data distribution network of Fig. 1.

Fig. 3 schematically illustrates an exemplary power and data distribution module according to another embodiment.

Fig. 4 schematically illustrates a further exemplary power and data distribution module according to another embodiment.

Fig. 5 schematically illustrates an airborne vehicle having a power and data distribution network according to another embodiment. Fig. 6 schematically illustrates a method for power and data distribution in an airborne vehicle according to another embodiment.

DETAILED DESCRIPTION OF EMBODIMENTS

Although specific embodiments have been illustrated and described herein, it will be appreciated by those of ordinary skill in the art that a variety of alternate and/or equivalent implementations may be substituted for the specific embodiments shown and described without departing from the scope of the present invention. Generally, this application is intended to cover any adaptations or variations of the specific embodiments discussed herein.

Fig. 1 shows a schematic illustration of a power and data distribution (PADD) network 100. The PADD network 100 may generally be employed in an airborne vehicle such as an aircraft or spacecraft. The PADD network 100 may also be employed in other vehicles such as ships, submarines, trucks, trains, space stations or satellites. Fig. 5 shows a schematic illustration of an exemplary aircraft 200 employing a PADD network, for example a PADD network 100 as shown and explained in conjunction with Figs. 1 to 4.

The PADD network 100 comprises one or more electrical power distribution centers (EPDCs) 50 that supply one or more power supply lines P with electrical power. The EPDCs 50 may comprise electrical power supply for a main network and/or electrical power supply for an emergency network as well as a ground power connector. In an airborne vehicle, two EPDCs 50 may be provided for the left hand and right hand generator sides. The EPDCs 50 ensure the reliable and high qualitative generation of electrical power, the segregation and management of the distribution of the generated electrical power as well as the controlling and monitoring of the electrical network. Alternatively or additionally, it may also be possible to employ other types of DC or AC power sources in the airborne vehicle for supplying the PADD network 100 with electrical power. For example, the airborne vehicle may be equipped with decentralized and locally arranged power sources such as fuel cells, photovoltaic modules or similar power sources.

Fig. 2 exemplarily shows an EPDC 50 as may be employed in the PADD network 100 of Fig. 1. The EPDC 50 may for example be an AC voltage EPDC 50 that comprises one or more electrical power supplies such as a variable frequency generator, a ram air turbine and/or an auxiliary generator. The electrical energy supplies, generally denoted as 51, 52, and 53, may operate under different normal and emergency conditions and supply electrical power for different needs. The electrical energy supplies 51, 52 and 53 may further be connected in supply groups that supply a common power line. Each of the electrical energy supplies 51, 52 and 53 or groups of electrical energy supplies may be equipped with a switch to selectively deactivate the power supply from the respective electrical energy supply 51, 52 or 53. The power lines may be coupled to a plurality of electrical circuit breakers in the respective separate power lines which are configured to selectively decouple the plurality of electrical energy supplies 51, 52, 53 from the output of the EPDC 50. This control may be effected by an electrical network management controller (ENMF) 55 which is configured to control the plurality of electrical circuit breakers 54.

The EPDC 50 may in particular be a 115VAC power supply essential (ESS) operation, Extended Range Operations for Two-Engine Aeroplanes (ETOPS) operation, and

emergency (EMER) condition cabin power (EEECP) cabin equipment which applies 115VAC output power over two times three single protected remote controlled circuit breaker power lines, one for each left hand and right hand system side of an airborne vehicle. Two different routes are provided to fulfil the particular risk requirements, such as engine burst, hydraulic accumulator burst and the like. The EEECP cabin equipment is configured to only switch the relevant power supply line, if all connected PADD modules 10 transmit the shedding status from all linked from the same system side under the relevant power supply condition. The ENMF 55 performs sheddings and reconfigures the PADD network 100 by

configuration of the aircraft power demand and generation. The sheddings may in particular be dependent on the percentage of load on the remaining generators. For example, with one main generator in flight, the main AC bus bars of the opposite side will not be supplied and the ENMF 55 will shed loads based on power condition.

The EPDC 50 may provide for 28 VDC power supply. For example, four batteries may be connected to the 28 VDC power supply network to support no-break power transfer (NBPT) functionality in order to supply standby DC power and provide electrical power on ground. Two out of four batteries may supply the emergency network with the charging and protection functionality being integrated in each of the batteries. The 28 VDC power supply may be provided on two normal power supply lines or power bus bars and on two emergency power supply lines or power bus bars. The DC power bus bars may normally be supplied from respective 230 VAC bus bars, with rectifiers/transformers transforming and distributing the 28 VDC DC power supply over the emergency power bus bars. However, it should be evident that other bus bars with other voltage values may be equally applicable as well.

Downstream of the output bus bars of the EPDC 50 one or more remote control circuit breaker units 56 may be connected in parallel which each comprise a remote control circuit breaker controller 58 (shedding information may be distributed via a data over power (DOP) from ENMF 55) coupled to a plurality of remote control circuit breakers 57. The system power operation will be controlled by the remote control circuit breaker controller 58 for all necessary electrical configurations. The remote control circuit breaker controller 58 manages the power supply for AC power loads usage by shedding and reconnecting the power supply lines selectively via the remote control circuit breakers 57, if enough power is available. The remote control circuit breaker controller 58 may monitor any cabin loads coupled downstream of the EPDC 50 and supplied with electrical power by the EPDC 50. Such cabin loads may include inter alia seat power supply systems, galleys, lavatory, commercial equipment fans, cabin air extraction fans, cabin lighting, ice protection control unit waste/water heating systems, floor panel heating systems and inflight entertainment systems.

The physical architecture of the electrical distribution may consist of two distinct EPDCs 50 in a PADD network that may be located in the nose fuselage of the airborne vehicle. One of the EPDCs 50 may be a 28 VDC cabin power supply powered alternately under normal, essential and hot battery conditions. The other EPDC 50 may be a 115 VAC cabin power supply powered alternately under normal, essential, extended range operations for two- engine aeroplanes (ETOPS) and emergency conditions.

Cabin equipment devices which shall apply a 28 VDC output power supply from the EPDC 50 acting as top line switching device are able to operate under essential and emergency conditions. The top line switching device may only be activated in emergency mode, as long as no command of the ENMF 55 overrides the control signals for the linked top line switching device. 28 VDC emergency functions may include passenger address, cabin interphone, emergency lighting, evacuation systems and smoke detection systems.

The EPDC 50 acting as 115VAC power supply may supply power to operate essential and non-essential equipment under normal power supply conditions. In case of electrical essential condition, all non-essential loads will be shed, if the ENMF 55 sends an essential status configuration signal to the linked PADD modules 10. Similarly, the 115VAC power supply may supply power to operate some systems or equipment under ETOPS condition. In case of electrical ETOPS condition, all non-ETOPS loads will be shed, if the ENMF 55 sends an ETOPS status configuration signal to the linked PADD modules 10. Finally, the 115VAC power supply may supply power to operate some systems or equipment under emergency condition. In case of electrical emergency condition, all non-emergency loads will be shed, if the ENMF 55 sends an emergency status configuration signal to the linked PADD modules 10. Emergency functions for the cabin may inter alia include emergency lighting and oxygen containers. The PADD network 100 of Fig. 1 further includes a data communication director 60 that is coupled to the plurality of PADD modules 10 via a data bus D. The data bus D may be a high speed data bus, such as a CAN bus of Ethernet bus. The data bus D may be hardwired between the data communication director 60 to the respective PADD modules 10.

Additionally, redundant data transmission may be effected via a wireless data

communication system.

The data bus D may be used for data communication with regard to bidirectional shedding information to be shared among the remote control circuit breaker controller 58, the ENMF 55 and communication units of the PADD modules 10. Similarly, the wireless data communication may be used as full data backup in case of data corruption on the hardwired data bus D.

Additionally, data with regard to bidirectional shedding information may be distributed via a data over power (DOP) communication protocol. The bidirectional DOP information may include a healthy protocol, the shedding status of relevant shedding groups, for example detailed failure status, as well as the emergency status of major systems, for example the status of oxygen cabin decompression. By distributing shedding information via DOP protocols, the shedding information may be made available for decentralized shedding of loads within the PADD modules 10. Monitoring and command signals for shedding information may be transmitted bidirectionally and crossover bidirectionally from the ENMF 55 to the PADD modules 10 as well as 58 and vice versa.

Fig. 3 shows an exemplary illustration of a PADD module 10 that may be employed in a PADD network of an airborne vehicle, such as the PADD network 100 of Fig. 1. The PADD module 10 may comprise a plurality of first power supply interfaces 11, each configured to be connected to a plurality of power supply lines PI, P2 and P3. The power supply lines PI, P2 and P3 may for example be three phase power line of 115 VAC over which DOP shedding information may be distributed to the PADD module 10. The shedding information may for example be read out via a shedding transmission over power (STOP) interface of the PADD module 10.

The PADD module 10 may further comprise a data bus interface 12 configured to be connected to a data bus Dl, particularly a high speed data bus Dl. The PADD module 10 may be configured to supply electrical power from one of the first power supply interfaces 11 to electrical loads that are connected to a plurality of power output interfaces 26, 27, 28, 29 and 40 of the PADD module 10. To distribute the electrical power a plurality of voltage distribution modules 19, 20 may be coupled between the plurality of first power supply interfaces 11 and the plurality of power output interfaces 26, 27, 28, 29 and 40. The distribution modules 19, 20 may be configured to provide AC or DC voltage by respective AC/DC or DC/DC converters.

The PADD module 10 may further comprise a load shedding module 17 as central load controlling unit. The load shedding module 17 may for example be part of a primary power distribution module 16 within the PADD module 10. The load shedding module 17 may be configured to receive load shedding information via data communication over one or more of the plurality of power supply lines PI to P3, specifically via the DOP

communication protocol. At the same time, a data concentrator 31 of the PADD module may be configured to receive redundant load shedding information via data

communication over the data bus D. The redundant load shedding information may be shared with the load shedding module 17 within the PADD module. The data concentrator 31 may in particular be part of a data distribution module 30 of the PADD module 10.

The load shedding module 17 is configured to shed one or more electrical loads connected to the plurality of power output interfaces 26 to 29 and 40 depending on the received load shedding information and the received redundant load shedding information. To provide even more redundant load shedding information to the PADD module 10, the PADD module 10 may comprise a wireless transceiver 32 which is coupled to the data concentrator 31. The data concentrator 31 may be configured to receive further redundant load shedding information via wireless data communication 33 over the wireless transceiver 32, to share with the load shedding module 17.

Optionally, the PADD module 10 may comprise at least one secondary power supply interface 13 that is configured to be connected to EPDC 50 provide 28 VDC power supply (under normal, essential and hot battery conditions) or a PADD control unit. The at least one secondary power supply interface 13 may also be configured to receive battery power or fuel cell power. The secondary power supply interface 13 is secure via a solid state power controller 15 as part of a secondary power distribution module (SPDM) 14 coupled to the secondary power supply interface 13 that may be controlled by the load shedding module 17 depending on the various load shedding information.

The at least one secondary power supply interface 13 is generally connectable to centralized or decentralized power sources such as centralized or decentralized and locally arranged fuel cells in the airborne vehicle.

The PADD module 10 further comprises a plurality of circuit breaking devices 21, 22, 23, 24 and 39 that are coupled between respective ones of the power output interfaces 26 to 29 and 40 and the voltage distribution modules 19 and 20. A shedding control unit 18 under control of the load shedding module 17 may be configured to selectively activate or deactivate the circuit breaking devices 21 to 24 and 39 depending on the received load shedding information and the received redundant load shedding information.

The basic functionality of the PADD module 10 is power Distribution (AC and DC), voltage transformation, shedding based on ENMF and STOP control signals and data

communication via a linked high speed data bus and wireless data communication.

Moreover, the PADD module 10 may provide power overload protection for the connected electrical loads. All the different power supply categories are individually protected via circuit breaking devices 21 to 24 and 39 such as RCCBs or SSPCs. Those protection devices are monitored and controlled in real-time in order to realize local and global safety criticality. The monitoring and controlling information is redundantly communicated via DOP

communication protocol the high speed data bus as well as wireless data transmission, thereby enabling the system to recognize jamming attacks or disturbances of other transmitters reliably.

The PADD module 10 may be implemented as an aircraft lavatory module, including fault current detection for shower use case functions in order to protect passengers and maintenance personnel from high voltages. This may be realized via a module internal grounding and bonding network. The PADD module 10 may also be implemented in a galley module of an aircraft, being equipped with additional fault current detection for bar use case functions, in order to protect passengers, cabin crew and maintenance personnel from high voltages. This may be realized via a module internal grounding and bonding network.

Fig. 4 shows an illustration of an alternative implementation of a PADD module 10. The PADD module 10 of Fig. 4 may comprise a single data distribution module 30 which in turn includes a combined primary power and data distribution module 34 with a data concentrator 36 and a load shedding module 37. Moreover, the PADD module 10 may be connected with an electrical energy storage device 38 that is connected to one of the power supply outputs 29 of the PADD module 10. In order to save hot battery bus implementations the electrical energy storage device 38 may for example be a quantum super capacitor that may additionally and temporarily supply emergency lighting via the power supply output interface 29.

Fig. 6 exemplarily illustrates a method M for power and data distribution in an airborne vehicle such as the airborne vehicle 200 of Fig. 5, in particular using a PADD network 100 as illustrated in conjunction with Figs. 1 to 4. The method M may comprise at Ml generating electrical power in at least one electrical power distribution center 50 or any other suitable power source within the airborne vehicle. At M2, the generated electrical power may be distributed via one or more power supply lines to a plurality of PADD modules 10, which receive, at M3, load shedding information via data communication over one or more of the plurality of power supply lines. At the same time, at M4, redundant load shedding information may be received at the plurality of PADD modules 10 via data communication over a data bus. The redundant load shedding information may be transmitted in the plurality of PADD modules 10 to a load shedding module in the PADD modules 10 at M5. These load shedding modules may then, at M6, and shed one or more electrical loads connected to power output interfaces of the PADD modules 10 depending on the received load shedding information and the received redundant load shedding information.

In the foregoing detailed description, various features are grouped together in one or more examples or examples with the purpose of streamlining the disclosure. It is to be understood that the above description is intended to be illustrative, and not restrictive. It is intended to cover all alternatives, modifications and equivalents. Many other examples will be apparent to one skilled in the art upon reviewing the above specification.

The embodiments were chosen and described in order to best explain the principles of the invention and its practical applications, to thereby enable others skilled in the art to best utilize the invention and various embodiments with various modifications as are suited to the particular use contemplated. In the appended claims and throughout the specification, the terms "including" and "in which" are used as the plain-English equivalents of the respective terms "comprising" and "wherein," respectively. Furthermore, "a" or "one" does not exclude a plurality in the present case. List of reference numerals and signs

Power and data distribution module

Power supply interfaces

Data bus interface

Secondary power supply interface

Secondary power distribution module

Solid state power controller

Primary power distribution module

Load shedding module

Shedding control unit

DC voltage distribution module

AC voltage distribution module

Circuit breaking electronics

Shedding electronics

DC voltage output interface

AC voltage output interface

DC voltage output interface

Data distribution module

Data concentrator

Wireless transceiver

Wireless data transmission

Combined primary power and data distribution module

Data output interface

Data concentrator

Load shedding module 8 Electrical energy storage device

9 Circuit breaking electronics

0 AC voltage output interface

0 Electrical power distribution center

51 Electrical energy supply

52 Electrical energy supply

53 Electrical energy supply

54 Electrical circuit breaker

55 Electrical network management controller

56 Remote control circuit breaker unit

57 Remote control circuit breaker

58 Remote control circuit breaker controller

60 Data communication director

100 Power and data distribution network

200 Aircraft

C Cabin area

D Data bus

DI Data bus interface

Dl Data bus

M Method

Ml Method step

M2 Method step

M3 Method step

M4 Method step

M5 Method step

M6 Method step

P Power line

PI Power line

P2 Power line P3 Power line P4 Power line

Claims

1. Power and data distribution, PADD, module (10), comprising:

a plurality of first power supply interfaces (11), each configured to be connected to a plurality of power supply lines (P; PI; P2; P3);

a data bus interface (12) configured to be connected to a data bus (D; Dl);

a plurality of power output interfaces (26; 27; 28; 29; 40), each configured to be connected to one or more electrical loads and to supply electrical power from one of the first power supply interfaces (11) to the connected electrical loads;

a plurality of voltage distribution modules (19; 20) coupled between the plurality of first power supply interfaces (11) and the plurality of power output interfaces (26; 27; 28; 29; 40) and configured to provide AC or DC voltage via the power output interfaces (26; 27; 28; 29; 40);

a load shedding module (17; 37) configured to receive load shedding information via data communication over one or more of the plurality of power supply lines (P; PI; P2; P3); and

a data concentrator (31; 36) configured to receive redundant load shedding information via data communication over the data bus (D; Dl) and to transmit the redundant load shedding information to the load shedding module (17; 37), wherein the load shedding module (17; 37) is further configured to shed one or more electrical loads connected to the plurality of power output interfaces (26; 27; 28; 29; 40) depending on the received load shedding information and the received redundant load shedding information.

2. PADD module (10) according to claim 1, further comprising:

a wireless transceiver (32) coupled to the data concentrator (31; 36), wherein the data concentrator (31; 36) is configured to receive redundant load shedding information via wireless data communication (33) over the wireless transceiver (32).

3. PADD module (10) according to one of the claims 1 and 2, further comprising:

at least one secondary power supply interface (13) configured to be connected to other PADD modules (10); and

a solid state power controller (15) coupled to the secondary power supply interface (13),

wherein the load shedding module (17; 37) is further configured to control the solid state power controller (15) depending on the received load shedding information and the received redundant ioad shedding information.

4. PADD module (10) according to one of the claims 1 to 3, further comprising:

a plurality of circuit breaking devices (21; 22; 23; 24; 39) coupled between the power output interfaces (26; 27; 28; 29; 40) and the voltage distribution modules (19; 20); and

a shedding control unit (18) coupled to the load shedding module (17), the shedding control unit (18) being configured to selectively activate or deactivate the circuit breaking devices (21; 22; 23; 24; 39) depending on the received load shedding information and the received redundant load shedding information.

5. PADD module (10) according to claim 3, wherein the secondary power supply

interface (13) is configured to receive hot battery DC power, battery power or fuel cell power.

6. PADD module (10) according to one of the claims 4 and 5, wherein the at least one secondary power supply interface (13) is connectable to centralized or decentralized power sources.

7. PADD module (10) according to claim 6, wherein the at least one secondary power supply interface (13) is connectable to one or more decentralized fuel cells.

8. PADD module (10) according to one of the claims 1 to 7, wherein the data bus

interface (12) is configured to receive high speed cabin data.

9. PADD module (10) according to one of the claims 1 to 8, further comprising:

an electrical energy storage device (38) coupled to at least one of the plurality of power output interfaces (29) and configured to temporarily store electrical energy to provide to one or more electrical loads coupled to the at least one of the plurality of power output interfaces (29).

10. PADD module (10) according to one of the claims 1 to 9, wherein the PADD module (10) is an aircraft galley module an aircraft lavatory module or a decentralized aircraft module.

11. Power and data distribution, PADD, network (100), comprising:

a plurality of PADD modules (10) according to one of the claims 1 to 10;

at least one electrical power distribution center (50) coupled to the plurality of PADD modules (10) via one or more of the first power supply interfaces (11); and a data communication director (60) coupled to the plurality of PADD modules (10) via the data bus interface (12).

12. PADD network (100) according to claim 11, wherein the at least one electrical power distribution center (50) comprises:

a plurality of electrical energy supplies (51; 52; 53); and

a plurality of electrical circuit breakers (54) coupled to the plurality of electrical energy supplies (51; 52; 53) and configured to selectively decouple the plurality of electrical energy supplies (51; 52; 53) from the output of the electrical power distribution center (50) or other power sources such as a fuel cell.

13. PADD network (100) according to claim 12, further comprising:

an electrical network management controller configured to control the plurality of electrical circuit breakers (54).

14. Airborne vehicle (200), comprising a PADD network (100) according to one of the claims 11 to 13.

15. Method (M) for power and data distribution, PADD, in an airborne vehicle (200), the method (M) comprising:

generating (Ml) electrical power in at least one electrical power distribution center (50) or a decentralized power source in the airborne vehicle (200);

distributing (M2) the generated electrical power via one or more power supply lines (P; PI; P2; P3) to a plurality of PADD modules (10);

receiving (M3) load shedding information at the plurality of PADD modules (10) via data communication over one or more of the plurality of power supply lines (P; PI; P2; P3);

receiving (M4) redundant load shedding information at the plurality of PADD modules (10) via data communication over a data bus (D; Dl);

transmitting (M5) the redundant load shedding information in the plurality of PADD modules (10) to a load shedding module (17; 37) of the PADD modules (10); and shedding (M6) one or more electrical loads connected to power output interfaces (26; 27; 28; 29; 40) of the PADD modules (10) depending on the received load shedding information and the received redundant load shedding information.