Airbus Deutschland Gmbh

Airbus Operations Gmbh

Airbus Societe Par Actions Simplifiees

Lars Rowold

Bodo Wisch

Mikael Stavaeus

Wolfgang Suess

Olaf Von Wieding

Carsten Kohlmeier-Beckmann

Bruno Alquier

Stefan Ebeling

Michael Pope

Jan Peter

Carsten Kohlmeier Beckmann

Juergen Riekehof-Boehmer

The invention relates to a monitoring system for monitoring a state of a door lock mechanism of a door or of a closure of a storage space of a means of transportation, comprising a generator and a sensor/actuator. The generator produces electrical energy from vibration energy, and the sensor detects the state of the door lock mechanism. The sensor uses the kinetic energy that is produced by the actuation of the door lock to generate an electrical signal, which is then transmitted to a microcontroller.

Wireless self-sufficient monitoring system for a door lock mechanism

An energy buffer device supplies energy to a consumer in an aircraft, and an electrical system for an aircraft. In one example, the device includes an energy feed device, an energy storage device and an energy supply device. The energy supply device may have line with a larger cross-sectional area than a corresponding line of the energy feed device. With the use of an energy buffer device, power may be switched on only for a short period of time. In addition, in case of a voltage breakdown in an on-board network, energy may be stored in an energy storage device. Supply of energy may thus occur over a short time at correspondingly high power, without placing a load on an on-board network or a generator.

Energy buffer device for an aircraft

A landmark information system in an aircraft, by which landmark information system data relating to informing, instructing and entertaining passengers may be visually presented. An aircraft equipped with a landmark information system is also provided. The landmark information system comprises an aircraft window with at least one pane and a control unit. The at least one pane is coated with a translucent display that is coupled to the control unit, which, for the purpose of presenting information, is equipped to supply electrical current in a targeted manner to the display. Furthermore, the landmark information system comprises a landmark determination device which may provide geographic data relating to landmarks, for presentation on the translucent display.

Landmark information system for an aircraft

This device is provided for a luggage compartment designed to be placed overhead. The compartment comprises a mobile part () between an open position and a closed position and a mechanism for acting on said mobile part () to promote its closing. Said mobile part () presents an opening () designed for introducing and retrieving luggage as well as a lower exterior surface (). The control device comprises detection means reacting when pressure is exerted on a predetermined zone of the lower exterior surface () of the mobile part () as well as for sending a control signal to the mechanism acting on the mobile part () to close the part when pressure is exerted on said detection means. The detection means are disposed at the lower exterior surface () of the mobile part ().

Luggage compartment actuation

A detection unit for integration in a luggage compartment of an airplane, having a capacitive sensor with an active layer, wherein the capacitive sensor is adapted to detect a first event triggered by a user, wherein the detection unit is adapted to transmit a first control signal to a control mechanism, wherein the first control signal corresponds to the first event and wherein the active layer comprises carbon fiber electrically isolated from a surrounding compartment structure.

An electric window dimming device for reducing the light transmission of a window for an aircraft. The electric window dimming device comprises a capacitance. The electric window dimming device is adapted for being connected to the capacitance and to a primary energy source that provides energy. If the primary energy source fails, the capacitance supplies energy for electric window dimming device.

Power supply for an electric window dimming device

A window unit for an aircraft with which individual lighting scenarios can be produced. In addition, an aircraft is equipped with at least one window unit. The window unit includes a window pane, which is coated with an electrically actuatable shading device for reducing incidental light entering through the window page. In addition, the window unit includes a control unit for operating the shading device as well as a lighting device for producing a light effect in the region of the window unit. In this connection, the control unit has an interface via which the control unit is connected to a network system of the aircraft for operation of the shading device. Likewise, the lighting device is coupled with the control unit, so that the lighting device can be operated with the network system of the aircraft via the interface of the control unit.

Window unit for an aircraft with shading and lighting functions

An emergency lighting arrangement preferably includes plural emergency light units connected to an on-board power supply network of an aircraft, and plural emergency current sources that each include at least one capacitor. Each emergency light unit includes an emergency light emitting element and a control unit that automatically connects the capacitor of the emergency current source to the emergency light emitting element upon the failure of the on-board power supply network. Preferably, the emergency current source including the capacitor is integrated into the emergency light unit. The emergency light unit may further include normal operation light emitting elements selectively connected by the control unit to the on-board power supply network. The control unit switches between normal operation of the normal light emitting elements and charging of the capacitor, and emergency operation in which the capacitor discharges through the emergency light emitting element.

Emergency lighting arrangement with decentralized emergency power supply for an aircraft

The application concerns a lifting device for a luggage compartment in an aircraft, wherein the luggage compartment can be moved between an open and closed position, and the lifting device includes a power generation element that exerts a lifting force on the luggage compartment. The application also concerns an aircraft with a lifting device for a luggage compartment. The power generation element is an electrical power generation element, and the lifting device has a rechargeable energy accumulator to store energy for operation of the electrical power generation element.

Lifting device for a luggage compartment in an aircraft, as well as aircraft with a lifting device for a luggage compartment

A guidance system guides a driver to drive a service vehicle, such as a baggage loading vehicle, into a prescribed parking position adjacent to an aircraft without colliding with the aircraft. The guidance system includes at least two indicator markers, preferably marker lights, arranged spaced apart from one another on the aircraft. The two markers present a prescribed visual pattern, e.g. an alignment of the two markers, along a line of sight defining a safe approach path. If the driver steers along this safe approach path so that he sees the prescribed visual pattern of the markers, then a collision between the vehicle and the aircraft will be avoided. Alternatively, a projector projects a light pattern such as a projected boundary marker line onto the ground surface adjacent to the aircraft to mark a safe collision-free approach path.

Growing community of inventors

Wiefelstede, Germany

Lars Rowold