Abstract: A heated floor panel for an airborne vehicle and an airborne vehicle having at least one heated floor panel are described. The floor panel includes a controller housing, a first heated panel configured to heat the floor panel, a panel connector arranged in a wall of the controller housing, at least one power line coupled between the panel connector and the first heated panel and configured to supply electric power, which is input to the panel connector, to the first heated panel, a switch connected in one of the power lines, and a microcontroller connected to the switch and configured to actuate the switch for interrupting the electric power supply to the first heated panel in case of an electric fault in the floor panel.

Abstract: A connection box for a system of an aircraft is provided, which includes a plurality of connection boxes, with a holder for holding a line connector for the supply of the system of the aircraft, wherein the system includes, in addition to this connection box, a further connection box with a holder for holding a line connector for the supply of the system of the aircraft. The connection box is configured to receive the further connection box in such a way that both connection boxes can be mounted under an opening in the floor of the aircraft so that both connection boxes are accessible from the opposite side of the floor through the opening in the floor.

Abstract: A connection box for a system of an aircraft is provided, which includes a plurality of connection boxes, with a holder for holding a line connector for the supply of the system of the aircraft, wherein the system includes, in addition to this connection box, a further connection box with a holder for holding a line connector for the supply of the system of the aircraft. The connection box is configured to receive the further connection box in such a way that both connection boxes can be mounted under an opening in the floor of the aircraft so that both connection boxes are accessible from the opposite side of the floor through the opening in the floor.

Abstract: A construction group of an aircraft for feeding a line to a connector section of the cabin module includes a flex zone for providing of at least one cabin module having a connector section for physical connection to a line of the aircraft. The flex zone is configured to receive different cabin modules and/or a cabin module at different positions. The construction group further includes a guide element for guiding the line to be connected to the connector section along the fuselage of the aircraft, and a support element extending along the flex zone for feeding the line from the guide element to the connector section, wherein during the receiving of the construction group in the aircraft, the longitudinal axis of the support element includes a component in direction of the attitudinal axis of the aircraft.

Abstract: A power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, a power management device coupled to the first power supply bus bar, at least one primary electrical equipment including a primary load being coupled in parallel to the power management device, and at least one secondary electrical equipment including a secondary load being coupled in parallel to the power management device. The power manager device is configured to supply electrical power to the at least one secondary electrical equipment, to supply electrical power to the at least one primary electrical equipment, and to deactivate the power supply to the at least one secondary electrical equipment, as long as the at least one primary electrical equipment is supplied with electrical power.

Abstract: An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment.

Abstract: A power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, a power management device coupled to the first power supply bus bar, at least one primary electrical equipment including a primary load being coupled in parallel to the power management device, and at least one secondary electrical equipment including a secondary load being coupled in parallel to the power management device. The power manager device is configured to supply electrical power to the at least one secondary electrical equipment, to supply electrical power to the at least one primary electrical equipment, and to deactivate the power supply to the at least one secondary electrical equipment, as long as the at least one primary electrical equipment is supplied with electrical power.

Abstract: An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment.

Abstract: A heated floor panel for an airborne vehicle and an airborne vehicle having at least one heated floor panel are described. The floor panel includes a controller housing, a first heated panel configured to heat the floor panel, a panel connector arranged in a wall of the controller housing, at least one power line coupled between the panel connector and the first heated panel and configured to supply electric power, which is input to the panel connector, to the first heated panel, a switch connected in one of the power lines, and a microcontroller connected to the switch and configured to actuate the switch for interrupting the electric power supply to the first heated panel in case of an electric fault in the floor panel.

Abstract: An overcurrent protection arrangement for aircraft to protect an electric element from an overcurrent, the overcurrent protection arrangement including an overcurrent protection device designed for detecting the overcurrent of a current through the electric element to be protected via the overcurrent protection device in such a way that the current through the element to be protected does not exceed an upper current limit.

Abstract: An overcurrent protection arrangement for aircraft that makes it possible to divert the overcurrent in case of a short-circuit in such a way that the current through an electric component to be protected does not exceed an upper current limit.