Abstract: A metering cargo fire inerting assembly is activated to supplement an initial release of fire extinguishing fluid into a cargo hold of an aircraft when a fire is detected during flight. The metering components of the fire inerting assembly control the temperature and pressure of the fire extinguishing fluid within a metering container. A heater element within the metering container controls temperature and pressure. A flow control metering orifice is immersed in a portion of the fire extinguishing fluid sealed by a hermetically sealed disc downstream of the metering orifice. A cutter with an internal fluid flow passageway can pierce the disc to release the fire extinguishing fluid under control of a timer attached to the metering container that can activate a pyrotechnic charge to drive the cutter for releasing the fire extinguishing fluid such as Halon 1301 to a discharge outlet for delivery to the cargo hold.

Abstract: A calibration and verification system and method for dynamically controlling sequential delivery of mixtures containing a fire suppression agent to detection locations to simulate an agent discharge during a flight operation of an aircraft and for allowing direct monitoring of the concentration amounts at the detection locations to adjust a testing operation accordingly. Each of the mixtures is prepared with a precise concentration amount of the agent. The system and method include a remote test sequence unit for determining an optimal testing time period during a flight operation to remotely control the discharge and monitoring of the agent. Prior to the optimal testing time period, an airflow at an altitude of the flight operation is drawn through each of a plurality of detectors to tare out the characteristics of a surrounding environment using a processor, thereby establishing a measurement baseline for each of the plurality of detectors.

Abstract: A calibration and verification system and method for dynamically controlling sequential delivery of mixtures containing a fire suppression agent to detection locations to simulate an agent discharge during a flight operation of an aircraft and for allowing direct monitoring of the concentration amounts at the detection locations to adjust a testing operation accordingly. Each of the mixtures is prepared with a precise concentration amount of the agent. The system and method include a remote test sequence unit for determining an optimal testing time period during a flight operation to remotely control the discharge and monitoring of the agent. Prior to the optimal testing time period, an airflow at an altitude of the flight operation is drawn through each of a plurality of detectors to tare out the characteristics of a surrounding environment using a processor, thereby establishing a measurement baseline for each of the plurality of detectors.

Abstract: An emergency oxygen system for aircraft passengers includes a hermetically welded sealed oxygen cylinder of stainless steel, a welded metal diaphragm sealing a discharge port and an extended hermetically sealed capillary tube for charging the cylinder with pressurized oxygen. A hollow piston cutter is driven to pierce the metal diaphragm as part of a first passageway delivering oxygen to the passenger. A second passageway delivers any leaking oxygen to a release port when the piston cutter is in position. A method of filling the cylinder includes welding to the cylinder a member having a metal diaphragm of a predetermined rupturable characteristic and using the open capillary tube to fill oxygen in the cylinder and subsequently crimping a portion of the capillary tube to provide a hermetic seal. A pressure gauge can be hermetically sealed to the bottom of the oxygen cylinder.

Abstract: A temperature compensated pressure switch (“TCPS”) with thermal lag compensation, trend indication, and forecast analysis. The TCPS has a first control unit, a pressure sensor connected to the first control unit outputting a first pressure data, a temperature sensor connected to the first control unit outputting a first temperature data, and a first storage unit connected to the first control unit storing: minimum and maximum pressure data corresponding to temperature data and rate of temperature change values. The first control unit can substitute a second temperature data, for the first temperature data for a period of time. The first control unit also outputs a first signal indicating the amount of material is acceptable when the first pressure data is above the minimum pressure data and outputs a second signal indicating the amount of material is unacceptable when the first pressure data is not above the minimum pressure data.

Abstract: An emergency oxygen system for aircraft passengers includes a hermetically welded sealed oxygen cylinder of stainless steel, a welded metal diaphragm sealing a discharge port and an extended hermetically sealed capillary tube for charging the cylinder with pressurized oxygen. A hollow piston cutter is driven to pierce the metal diaphragm as part of a first passageway delivering oxygen to the passenger. A second passageway delivers any leaking oxygen to a release port when the piston cutter is in position. A method of filling the cylinder includes welding to the cylinder a member having a metal diaphragm of a predetermined rupturable characteristic and using the open capillary tube to fill oxygen in the cylinder and subsequently crimping a portion of the capillary tube to provide a hermetic seal. A pressure gauge can be hermetically sealed to the bottom of the oxygen cylinder.

Abstract: A temperature compensated pressure switch (“TCPS”) with thermal lag compensation, trend indication, and forecast analysis. The TCPS has a first control unit, a pressure sensor connected to the first control unit outputting a first pressure data, a temperature sensor connected to the first control unit outputting a first temperature data, and a first storage unit connected to the first control unit storing: minimum and maximum pressure data corresponding to temperature data and rate of temperature change values. The first control unit can substitute a second temperature data, for the first temperature data for a period of time. The first control unit also outputs a first signal indicating the amount of material is acceptable when the first pressure data is above the minimum pressure data and outputs a second signal indicating the amount of material is unacceptable when the first pressure data is not above the minimum pressure data.

Abstract: A solid state temperature compensated annunciator is disclosed. The solid state temperature compensated annunciator includes a pressure sensor for measuring a pressure of the fillant within a vessel and a temperature sensor for measuring the temperature of the fillant within the vessel. The solid state temperature compensated annunciator determines a pressure that the vessel would have if the vessel were filled with a predetermined amount of fillant, and compares the measured pressure to the determined pressure. If the measured pressure is below the determined pressure, a warning signal is issued.

Abstract: A pressure gauge assembly for aircraft tires and the like having a helical coil bourdon tube sensor capable of indicating a pressure differential between a monitored source of pressure and a calibrated reference source of pressure. The reference pressure is applied to one surface of the bourdon tube coils while the monitored pressure is applied to the other surface of the coils. The resultant movement is a linear indication of any pressure differential. A valve assembly can be provided with the pressure gauge assembly to permit fluidic access to the monitored pressure. If the volume of the monitored pressure is variable such as an aircraft tire, the secondary source of calibrated pressure can be provided with a predetermined pressure relative to the normal tire pressure to compensate for any volumetric changes in the tire during operation. In an alternative embodiment, the bourdon tube can be used to monitor the pressure in a fire extinguisher for indicating any leaks.

Abstract: A temperature compensated pressure indicator adapted to be mounted within a pressure container includes a reservoir housing and housing member welded together to form a secondary pressure chamber. A bellows member is hermetically mounted within the secondary pressure chamber and communicates with the exterior pressure of the container. Mounted on the bellows member is a movable magnetic member adapted to slide on a hollow guide post as a result of any pressure differentials. A reed switch assembly is held stationary in the guide post by a pair of band springs. The switch assembly is electrically connected to a source of power and an external indicator such as a light. When the bellows member moves the magnetic member close to the switch assembly due to a pressure differential, the magnetic field closes the switch assembly to activate the light. The indicator is substantially non-responsive to wide variations in the ambient temperature.