Abstract: A fire suppression agent includes a fluid medium, vermiculite particles suspended in the fluid medium, and a colorant additive proximate at least a subset of the vermiculite particles. The fire suppression agent is capable of suppressing a fire comprising a combustible metal material.

Abstract: A covered chamberless particulate detector includes a chamberless detector configured to produce a signal when particulate sensing events occur; one or more optical emitters disposed on the chamberless detector, configured to emit one or more emitting cones of light; one or more optical sensors disposed on the chamberless detector, defining one or more receiving cones; and a protective cover on the chamberless detector defining an inside region and an outside region. Each of the one or more optical sensors is configured to detect occurrence of particulate sensing events. The protective cover includes a material having one or more optical properties of transmission, reflection, and absorption; and at least of these optical properties has a bandwidth.

Abstract: A clamp fixture includes a hub extending between a first end and a second end. A first leg extends in a first direction from the first end of the hub, and a second leg extends in the first direction from the second end of the hub. At least a portion of the first leg curves away from the second leg, and at least a portion of the second leg curves away from the first leg. The clamp fixture also includes a loop with a first half and a second half. The first half includes a first jaw extending from the hub. The second half includes a flange and a second jaw extending from the flange. A fastener connects the flange to the hub such that the first jaw and the second jaw join to close the loop.

Abstract: A system for monitoring smoke and/or temperature of an electronic device includes a fiber harness having at least one fiber optic cable terminating at a node. The node is located to measure one or more conditions at the electronic device, and a control system operably connected to the fiber harness. The control system includes a light source configured to transmit light through the fiber harness, a light sensitive device configured to receive scattered light associated with the node, and a control unit configured to analyze the scattered light to determine at least one of a presence and magnitude of the one or more conditions at the node of one or more conditions at the electronic device, wherein the control unit is further configured to transmit a signal in response to the one or more conditions, wherein the one or more conditions are one or more of smoke, fire, and temperature.

Abstract: Disclosed is a computer-implemented method for maintenance planning for an aircraft. The method includes retrieving, via a processor, a data transmission comprising a plurality of component faults from an aircraft processor while the aircraft is in flight. The processor executes, using a prediction engine, a predictive fault list based on the component faults. The predictive fault list includes a plurality of weighted predictions of authentic component faults and nuisance component faults. The processor prioritizes the weighted predictions of authentic component faults, and generates a maintenance checklist prioritized based on the weighted prediction of authentic component faults. The processor then outputs the prioritized maintenance checklist on an operatively connected maintenance planning device.

Abstract: A system configured to a plurality of zones of an aircraft includes first and second connectors are in optical communication, an optical fiber, a first interrogator, and a controller. The optical fiber extends between the first and second connectors and includes a first timing fiber Bragg grating disposed in the optical fiber at a reference location of the optical fiber. The first interrogator is connected to the optical fiber and is configured to provide a first optical signal to the optical fiber and to receive a first timing signal from the optical fiber. The first timing fiber Bragg grating is configured to provide the first timing signal with information related to the first timing fiber Bragg grating from the first interrogator. The controller is operatively connected to the first interrogator and is configured to determine the reference location of the optical fiber.

Abstract: Overheat and fire detection for aircraft systems includes at least one temperature sensing fiber optic cable. The at least one fiber optic cable is comprised of a plurality of modular fiber optic cables. The plurality of modular fiber optic cables includes at least one sensing and one non-sensing section. Portions of the at least one temperature sensing fiber optic cable can be removed and replace with separate modular fiber optic cables.

Abstract: A fire suppression nozzle includes a body including a cylindrical portion having a first end and a second end and a conical portion connected to the second end of the cylindrical portion, a main channel extending through the cylindrical portion, a flow deflector connected to the body, and a flow foil ring positioned adjacent the flow deflector and the conical portion of the body. The flow deflector includes a top portion in alignment with the main channel, an annular flange extending out of a side of the flow deflector, and a conical base extending out of the side of the flow deflector at an angle.

Abstract: Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.

Abstract: A method of operating safety mechanism includes extending a safety pin to block a poppet from opening a flow path from a pressure vessel in the event of the pressure vessel being unmounted from a bracket or in the event of the bracket being unmounted from a support structure. The method includes retracting the safety pin to allow free movement of the poppet for opening the flow path only in the event of the pressure vessel being mounted to the bracket and the bracket being mounted to a support structure.

Abstract: A valve assembly includes a valve with a valve body and chamber. A poppet with a stem and piston is slidably engaged inside the valve body. A poppet release mechanism is included for releasing the poppet from a closed position. A mechanism cover is attached to the valve body. A safety mechanism with a pin, spring, and lever is included for preventing the poppet from moving into a fully open position. A first end of the pin extends into the chamber into a pathway of the poppet and a second end of the pin extends into the valve body of the valve. The spring is positioned between and in contact with the pin and the mechanism cover to bias the pin toward the poppet. A first end of the lever is pivotably attached to the pin and a second end of the lever extends out from the valve body.

Abstract: A valve assembly includes a valve with a valve body and chamber. A poppet with a stem and piston is slidably engaged inside the valve body. A poppet release mechanism is included for releasing the poppet from a closed position. A mechanism cover is attached to the valve body. A safety mechanism with a pin, spring, and lever is included for preventing the poppet from moving into a fully open position. A first end of the pin extends into the chamber into a pathway of the poppet and a second end of the pin extends into the valve body of the valve. The spring is positioned between and in contact with the pin and the mechanism cover to bias the pin toward the poppet. A first end of the lever is pivotably attached to the pin and a second end of the lever extends out from the valve body.

Abstract: A thermal sensor for an aircraft includes a first electrode, a second electrode, a support layer disposed between the first electrode and the second electrode, and a state changing material is configured to disposed within the support layer, wherein the state changing material transitions between a non-conductive state to a conductive state at a threshold temperature to electrically connect the first and second electrodes.

Abstract: A system includes a turbo pump configured to convert a tank compressed gas or an engine compressed gas into at least one of electrical power, hydraulic power, or pneumatic power. The system also includes a storage tank configured to store the tank compressed gas. The system also includes a bleed line configured to port the engine compressed gas from the gas turbine engine to the turbo pump. The system also includes a propellant selector valve having an off position in which the turbo pump is prevented from receiving either the tank compressed gas or the engine compressed gas, a tank position in which the tank compressed gas from the storage tank is ported through the propellant selector valve to the turbo pump, and an engine position in which the engine compressed gas from the bleed line is ported through the propellant selector valve to the turbo pump.

Abstract: An advance pneumatic detector to indicate pressure changes in an environment includes a switch, a pressure tube, an endcap, a piston, and a magnet. The pressure tube is connected to the switch. The endcap is disposed on an end of the pressure tube opposite from the switch. The piston is disposed within and forms a seal against the pressure tube. The piston is slidably engaged with the pressure tube. The magnet is slidably attached to and surrounds a portion of the pressure tube. The magnet is configured to control the positioning of the piston within the pressure tube.

Abstract: A system includes a turbo pump to convert compressed gas into power, a storage tank to store the compressed gas, and a fire suppression control valve having a closed position in which the compressed gas is prevented from flowing to the cargo compartment and an open position in which the compressed gas is ported to the cargo compartment to suppress a fire. The system also includes a pump control valve having a closed position in which the compressed gas is prevented from flowing to the turbo pump and an open position in which the compressed gas is ported to the turbo pump to cause the turbo pump to convert the compressed gas into the power. The system also includes an OBIGGS to convert bleed air from a gas turbine engine into an inert gas to provide low rate discharge (LRD) fire suppression to the cargo compartment.

Abstract: Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.

Abstract: A system includes a turbo pump configured to convert a tank compressed gas or an engine compressed gas into at least one of electrical power, hydraulic power, or pneumatic power. The system also includes a storage tank configured to store the tank compressed gas. The system also includes a bleed line configured to port the engine compressed gas from the gas turbine engine to the turbo pump. The system also includes a propellant selector valve having an off position in which the turbo pump is prevented from receiving either the tank compressed gas or the engine compressed gas, a tank position in which the tank compressed gas from the storage tank is ported through the propellant selector valve to the turbo pump, and an engine position in which the engine compressed gas from the bleed line is ported through the propellant selector valve to the turbo pump.

Abstract: A system includes a turbo pump that converts a compressed gas into power, and a storage tank configured to store the compressed gas. The system also includes a fire suppression control valve configured to be coupled between the storage tank and a cargo compartment of the aircraft and having a closed position in which the compressed gas is prevented from flowing to the cargo compartment and an open position in which the compressed gas flows to the cargo compartment to suppress a fire. The system also includes a pump control valve configured to be coupled between the turbo pump and the storage tank and having a closed position in which the compressed gas is prevented from flowing to the turbo pump and an open position in which the compressed gas flows to the turbo pump to cause the turbo pump to convert the compressed gas into the power.

Abstract: A fire extinguisher vessel includes a hollow body made of stainless steel, a fill port attached to a first end of the body, a discharge outlet attached to a second end of the body, a mechanical attachment lug attached to the body between the first end of the body and the second end of the body, a pressure switch attached to the body between the mechanical attachment lug and the discharge outlet, and a wrap covering the body. The wrap is flush with the fill port, the discharge outlet, the mechanical attachment lug, and the pressure switch.