KIDDE TECHNOLOGIES, INC.

Apparatus and associated methods relate to galvanically isolating one or more sensors from a controller. Power and control signals are provided to an isolation system via RF electromagnetic waves transmitted from the controller to the isolation system via a dielectric waveguide. The received RF electromagnetic waves are converted into an RF electrical signal and then the RF electrical signal is separated into power and control signal components. The RF power signal component is rectified and regulated so as to provide power to the isolation system. A sensor interrogator is electrically connected to one or more sensors so as to receive sense signals therefrom. The sensor interrogator generates a data signal indicative of one or more physical metrics of a potentially hazardous environment in which the one or more sensors are situated. The data signal is converted to RF electromagnetic waves, which are transmitted, via the dielectric waveguide, to the controller.

Disclosed is a heat sensor cable having: a conductor defining a conductor first end and a conductor body extending by a first longitudinal span from the conductor first end to a conductor second end; a coil that is non-conductive and includes a coil first end and a coil body extending by a second longitudinal span from the coil first end to a coil second end, wherein the coil surrounds the conductor from the conductor first end to the conductor second end; an outer sheath that is conductive and includes an outer sheath first end and an outer sheath body extending by a third longitudinal span from the outer sheath first end to an outer sheath second end, wherein the outer sheath surrounds the coil from the conductor first end to the conductor second end; and an eutectic salt that is disbursed between the conductor and the outer sheath.

Aircraft fire and overheat detection systems are described. The systems include a support bracket configured to secure the system to a component of an aircraft. A terminal assembly is fixedly connected to the support bracket and includes a connection assembly and a connection cable. A sensing element is electrically connected to the terminal assembly and arranged to detect at least one of fire and heat associated with the component of the aircraft. A protective sleeve is arranged about the connection assembly and connection cable. The sleeve has a lug portion at a first end with a sealing protrusion extending radially inward, a first wire portion, and a second wire portion, with progressively smaller diameters for each portion.

An apparatus for locating a measurand anomaly, such as a hot-spot, along an optical waveguide is provided comprising: an optical waveguide, a light source configured to transmit pulsed light along the waveguide, and a first and second set of sensors provided along the waveguide. Each sensor is configured to reflect a portion of light propagating along the waveguide at a respective sensor wavelength corresponding to a measurand. The first set of sensors provides one or more groups of sensors configured to detect a measurand anomaly within that group. The second set comprises a plurality of sensors each separated from the adjacent sensor of that set by a distance along the waveguide greater than half the distance travelled by the light along the waveguide during the pulse duration. A plurality of sensors of the first set is provided between each adjacent sensor of the second set. The apparatus further comprises a detector configured to monitor the light reflected by the sensors, and a control system configured to control the light source and the detector to both locate at least the group containing a measurand anomaly and to monitor the measurand using the second set.

A linear detector element includes an outer sheath having a first end and a second end, one or more shape memory responsive elements within the outer sheath and between the first end and the second end and first and second conductive wires passing through at least a portion of the outer sheath and through the one or more shape memory responsive elements. The one more shape memory responsive elements include a shape memory actuator surrounding the first and second conductive wires and that has an expanded size and a contracted size and that is sized and arranged such that when the shape memory actuator is in the contracted state the first and second conductive wires contact one another and when the shape memory actuator is in the expanded state the first and second conductive wires do not contact one another.

Aircraft fire and overheat detection systems are described. The systems include a support bracket configured to secure the system to a component of an aircraft. A terminal assembly is fixedly connected to the support bracket and includes a connection assembly and a connection cable. A sensing element is electrically connected to the terminal assembly and arranged to detect at least one of fire and heat associated with the component of the aircraft. A protective sleeve is arranged about the connection assembly and connection cable. The sleeve has a lug portion at a first end with a sealing protrusion extending radially inward, a first wire portion, and a second wire portion, with progressively smaller diameters for each portion.

A sensing assembly comprising includes one or more sensing elements formed as a tube. The sensing assembly also includes one or more clamps to secure the one or more sensing elements. Each of the one or more clamps includes a recess in which each of the one or more sensing elements is seated.

A smoke and temperature detection system includes a plurality of fiber optic cables terminating in a plurality of nodes positioned to monitor a fire or smoke condition at one or more protected spaces, and a temperature detection fiber optic cable having a plurality of fiber Bragg gratings arrayed along the temperature detection fiber optic cable. A control system is operably connected to the plurality of fiber optic cables and to the temperature detection fiber optic cable. The control system includes a first light sensitive device configured to receive a scattered light signal from the plurality of fiber optic cables, and a second light sensitive device configured to receive a reflected light signal from the fiber Bragg gratings. The control system is configured to detect a temperature at the fiber Bragg gratings based on one or more properties of the reflected light signal received at the second light sensitive device.

A sleeving apparatus includes a worm gear. The worm gear has a plurality of threads, the worm gear receptive of a bead between adjacent threads of the plurality of threads. A plurality of flexible diaphragms are positioned along the worm gear. Each diaphragm of the plurality of diaphragms is configured to position a wire in alignment with a central bead opening of the bead. With rotation of the worm gear about a worm gear axis, the bead advances onto the wire with the wire passing into the central bead opening. The plurality of diaphragms are configured to allow passage of the bead through each diaphragm of the plurality of diaphragms.

A thermal sensor and a method of making a thermal sensor is disclosed. The thermal sensor includes a first electrode, a second electrode, and a composition between the first and second electrodes. The composition includes solid particles of a state-changing material that transitions at a threshold temperature between solid and liquid states having different electrical conductivities.