Plaisir, France
Plaisir, France

Zodiac Aerospace is a French corporation that, as of May 2012, specializes in the production and development of on-board systems, safety systems and cabin interiors. The company is a world leader in aerospace equipment and systems for commercial, regional and business aircraft, as well as helicopters and space applications. The Zodiac Aerospace Group applies a strategy built on internal and external growth in niche markets that offer a high technology content, generate significant after-sales support business and have the potential to establish the Group as a world leader. The Marine Segment was separated from the Group in September 2007 to become Zodiac Marine & Pool. Wikipedia.


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Patent
Zodiac Aerospace | Date: 2016-08-01

A system for controlling electrical power supply of an aircraft includes at least two control boards and at least two switching members. Each switching member is connected to each control board. Each control board includes a processor. Each processor is configured to determine a command for switching states of switch contacts of each switching member and to determine information relating to validity of each switching command. Each switching member includes a transmitter to determine a command to be transmitted to a detector to detect parallelization, a power actuator configured to transmit a power signal to the switch contacts depending on the command received from the detector, and switch contacts configured to selectively open or close an electrical power supply line. The command is selected from the switching commands and the information relating to the validity of each switching command.


Grant
Agency: European Commission | Branch: FP7 | Program: CP-IP | Phase: AAT.2012.3.5-2. | Award Amount: 30.50M | Year: 2013

Outstanding safety level of air transport is partly due to the two pilots standard. However situations where difficult flight conditions, system failures or cockpit crew incapacitation lead to peak workload conditions.The amount of information and actions to process may then exceed the crew capacity. Systems alleviating crew workload would improve safety. ACROSS Advanced Cockpit for Reduction of StreSs and workload - will develop new applications and HMI in a cockpit concept for all crew duties from gate to gate. Human factors, safety and certification will drive this approach. The new system will balance the crew capacity and the demand on crew resource. ACROSS workload gains will be assessed by pilots and experts. A Crew Monitoring environment will monitor physiological and behavioural parameters to assess workload and stress levels of pilots. A new indicator will consolidate flight situation and aircraft status into an indicator of the need for crew resource. If this need becomes higher than available crew resource, cockpit applications and systems will adapt to the new situation : a) Decision support: cockpit interfaces will adapt to focus crew on needed actions, b) Prioritisation: non-critical applications/information will be muted in favor of critical elements, c) Progressive automation: crew actions not directly relevant with the situation will be automated, d) Decision sharing: in case of persistent crisis situation, an automatic information link with the ground will be established to further assist the crew. In extreme situation where both pilots are incapacitated, further steps will be: a) Full automation: measures to maintain the aircraft on a safe trajectory, then reroute to nearest airport and autoland. b) Decision handling: mechanisms allowing ground crew to remotely fly the aircraft. ACROSS groups a large team of key European stakeholders. They are committed to deliver innovation in the field of air transport safety.


Grant
Agency: European Commission | Branch: FP7 | Program: JTI-CP-FCH | Phase: SP1-JTI-FCH.2012.1.6 | Award Amount: 10.52M | Year: 2013

In order to meet the increasing pressure to reduce fuel consumption and greenhouse gas emissions, airlines are seeking alternative sources to power non-propulsive aircraft systems. The next generation of aircraft is heavily investigating the use of non-fossil fuel to generate electrical power for non-essential applications (NEA). Hydrogen fuel cells are actively being pursued as the most promising means of providing this power. Fuel cells also have the added benefits of no pollution, better efficiency than conventional systems, silent operating mode and low maintenance. The by-products from the fuel cells (heat, water and oxygen depleted air) will also have a positive impact on the global aircraft efficiency when they are harnessed and reused within the aircraft system. The HYCARUS project will design a generic PEM fuel cell system compatible of two NEA, then develop, test and demonstrate it against TRL6 . A secondary electrical power generation model for a business executive jet will be run. The application will be tested with the fuel cell system and the storage system under flying conditions. Furthermore, investigations will be made to understand how to capture and reuse the by-products. The HYCARUS project will extend the work already completed in the automotive sector, particularly for safety codes and standards, and develop these for use in airborne installation and applications. Improvements in terms of efficiency, reliability, performance, weight /volume ratio, safety, cost and lifetime under flight conditions at altitude and under low ambient temperatures (mainly in the air) will also be examined. The HYCARUS project also aims to foster a better and stronger cooperation between all the agents of the sector: Aeronautics equipment and systems manufacturers, aircraft manufacturers, system integrators and fuel cell technology suppliers.


Grant
Agency: European Commission | Branch: H2020 | Program: CS2-IA | Phase: JTI-CS2-2014-CFP01-FRC-02-06 | Award Amount: 3.93M | Year: 2016

The VOLT Consortium will develop an innovative high voltage network (using 270 VDC) inspired by a Clean Sky architecture. This new architecture requires an innovative battery solution that will provide mainly pre-flight and starting power to the rotorcraft The objective of VOLT is to demonstrate their ability to: Propose to the aeronautical industry an innovative battery concept for a High Voltage Network battery (HVNB) using an array of commercial available off-the-shelf battery cells with smart controllers rather than a single massive specific cell thus providing a far more reliable approach than classic solutions Design, develop and manufacture a battery prototype (TRL6) and charger according to the technical, physical, and stringent environment requirements as defined in the call text Perform the necessary stringent battery testing required before being qualified for flight testing and provide a monitoring and troubleshooting software easily used by unqualified operators Prepare in parallel to the above mentioned research work performed in this project, the necessary pre-industrialization work to be able to meet future production demands of the VOLT battery.


A configurable control panel for an aircraft cockpit includes a set of universal control modules each comprising at least one screen including at least one manually manipulable control key. Each of the control modules further includes at least one master control module, and at least one universal slave module associated with the master module, and including a screen and at least one control key. The at least one master module is configured to control the screen and the at least one control key of the at least one universal slave module.


A Light Emitting Diode (LED) light for an aircraft includes a hollow cylindrical body, a plurality of LEDs mounted in the hollow body, and at least one reflector to receive light beams emitted by the LEDs and configured to direct the light beams in a lighting direction of the LED light. The LEDs are mounted on a cylindrical support and disposed radially in the cylindrical body, and the cylindrical support has a polygonal contour.


A Hall-effect universal control button for a man-machine interface includes a base adapted for mounting on the interface, and a plurality of manually actuable and interchangeable control modules. Each control module is mountable on the base and includes a bipolar magnet. The base includes at least one sensor to detect a magnetic field of the magnet.


Connection system arranged in a rack, for connecting at least one protection board (13a, 13b) of an electrical distribution system of an aircraft with a primary power supply, to at least one powered device (8a, 8b) and to a motherboard arranged in the rack. The connection system includes at least one modular connector on each protection board and, for each protection board capable of being inserted in the rack, at least one additional modular connector attached at least partly on the rack and at least one additional connector connected to the motherboard.


Supply system for electronic boards of an electrical distribution system comprising at least two protection boards (2a, 2b) each able to control the supply of at least one protected pathway (3a, 3b) on the basis of a power line (4a, 4b), characterized by the fact that each protection board (2a, 2b) comprises at least one voltage converter (13a, 13b) able to provide an internal supply voltage of the protection board on the basis of a supply voltage, the voltage converter (13a) of a first protection board (2a) being connected to at least one second protection board (2b) so as to be able to provide the internal supply of the second protection board (2b) in case of failure of the voltage converter (13b) of the second protection board (2b).


Patent
Zodiac Aerospace | Date: 2015-08-14

Electrical distribution system for an aircraft comprising at least one electrical supply path comprising at least one power unit capable of opening or closing the connection between at least one electrical energy source and at least one device of the aircraft. The system comprises protection cards (2b, 2n) each comprising at least two microcontrollers each capable of sending a command to each power unit of the electrical supply paths protected by each protection card and, among the set of microcontrollers of the protection cards, at least two microcontrollers are provided with a communication and computation function with all of the microcontrollers of the protection cards (2b, 2n).

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