A panel comprising a heat providing layer is presented. The panel includes panel coupling means arranged for coupling the panel to adjacent panels. End panel grooves, at least partly extending between first and second opposite longitudinal sides of the panel, are arranged in the end panel coupling means of the panel. In order to provide heat, electrical end connectors are arranged in the end panel grooves of the panel. The electrical end connectors are arranged for being electrically connected to the heat providing layer of the panel, at least partly including an electrically conductive material, and at least partly protruding from the one or more end panel grooves, thereby providing an electrical connection between the heat providing layer of the panel and a corresponding heat providing layer of at least one adjacent panel coupled to the panel.

A radiant heating device for producing radiant heat in a passenger compartment of a motor vehicle includes a heating surface for emitting heat radiation, a heating element for providing heating power, a first temperature sensor for detecting a first temperature in a specific spot and for providing a corresponding first temperature indication, and a second temperature sensor for detecting a second temperature on the surface and for providing a corresponding second temperature indication. In order to detect a local over-heating of the heating surface, a difference between the two temperature indications is determined. In the event of a defect, a protective operating mode is then selected.

An operating method for an electric heater may include heating a fluid passing the electric heater to an outlet temperature by at least one heating element and operating the electric heater in one of a normal mode or a protection mode. In the normal mode, the at least one heating element may be supplied with at least one of a direct current and a direct voltage. In the protection mode, electrical power supplied to the at least one heating element may be regulated by pulse width modulation. The electric heater may be operated in the normal mode if a reference temperature is less than or equal to a critical temperature and in the protection mode if the reference temperature is greater than the critical temperature.

The disclosure relates to a covering system for a floor, a wall and/or a ceiling. The covering system includes a decorated side, a lower side opposite the decorated side and a plurality of interconnected covering elements. At least one conducting element is arranged between at least two of the covering elements in such a way that the at least one conducting element is at least partially visible on the decorated side. The at least one conducting element is configured to conduct a physical quantity, material or signals. The at least one conducting element includes an interface to a source or a consumer of the physical quantity, material or signals.

A panel comprising a heat providing layer is presented. The panel includes panel coupling means arranged for coupling the panel to adjacent panels. In order to provide heat, longitudinal grooves are arranged in the panel along the whole length of the panel. Electrical end connectors are arranged in the longitudinal grooves to protrude from at least one end side of the panel. The electrical end connectors are arranged for being electrically connected to the heat providing layer, and for being electrically connectable to at least one corresponding end connector of at least one adjacent panel, and for being at least partly resilient, thereby providing a connecting force F.sub.con being essentially perpendicular to the at least one of the first and the second end sides when the panel is coupled to at least one adjacent panel, and being directed towards at least one corresponding end connector of the at least one adjacent panel.

A heatable floor panel for an aircraft, with a supporting level, a heat-generating level and a heat-conducting level. The heat-generating level comprises a fiber composite layer with fibers and with a matrix surrounding the fibers. The fibers are at least partially formed as conducting fiber, and the conducting fibers are formed as carbon fibers with an electrically insulating coating. The conducting fibers integrated in the floor panel in order to conduct a heating current through them. Due to the electrically insulating coating of the conducting fibers, leakage currents are avoided. The carbon fibers serve not only as heating elements, but, at the same time, also as reinforcing fibers of the fiber composite layer or of the floor panel.

The present invention addresses the problem of providing a flooring material whereby it becomes possible to improve an anti-aging effect of an activity in various facilities. The present invention provides a flooring material containing a stone material, in which the stone material contains silicon dioxide in an amount of 67.0 to 80.0% by mass, inclusive, relative to the whole amount of the stone material.

A curtain wall includes one or more mullion profiles and one or more transom profiles and panels which are mounted in the mullion profiles and in the transom profiles by their edges. The one or more mullion profiles extend vertically and are provided with an undercut groove on two opposite sides which has an access opening. The grooves form a rebate in which the rim of a panel is mounted. The undercut groove has an elongate cross section which is provided, at the one or several of the transverse ends, with a rounded section and/or which is free from roundings with a radius of less than 2 millimeters at one or several of the transverse ends.

An aircraft heated floor panel includes a first face sheet, a second face sheet opposite the first face sheet, and core with an electrically conductive core portion. The electrically conductive core portion supports the first face sheet and the second face sheet, and is electrically insulated from the external environment to receive electrical power, resistively generate heat, and communicate heat to the first face sheet.

A heated floor panel assembly for aircraft includes an impact layer made from a 2-D or 3-D woven high temperature thermoplastic fiber matrix impregnated with a resin. The impact layer can further include woven metallic fibers. The assembly also includes a stack of structural layers, a heating layer, and a core layer for absorbing shear stress.