Abstract: A fuel metering system includes a metering valve having a first inlet fluidly coupled to a source of fluid at a first pressure, a second inlet, a first outlet and a second outlet. The metering valve includes a slot, and a valve body movable to control an amount of fluid supplied to the first and second outlet. The fuel metering system includes a servo valve fluidly coupled to the second inlet and to a second source of fluid at a second pressure. The servo valve is in fluid communication with the second inlet and a body of the servo valve is movable to supply a fluid to move the valve body. The slot is configured to variably restrict the flow of the fluid through the second outlet to balance a force applied by a biasing member. The fuel metering system includes a fixed flow restriction downstream of the second outlet.

Abstract: A fuel metering system includes a metering valve having a first inlet fluidly coupled to a source of fluid at a first pressure, a second inlet, a first outlet and a second outlet. The metering valve includes a slot, and a valve body movable to control an amount of fluid supplied to the first and second outlet. The fuel metering system includes a servo valve fluidly coupled to the second inlet and to a second source of fluid at a second pressure. The servo valve is in fluid communication with the second inlet and a body of the servo valve is movable to supply a fluid to move the valve body. The slot is configured to variably restrict the flow of the fluid through the second outlet to balance a force applied by a biasing member. The fuel metering system includes a fixed flow restriction downstream of the second outlet.

Abstract: Embodiments of a combined overspeed and fuel stream selector system are provided. In an embodiment, the assembly includes a conduit network, a Discharge Select Valve (DSV), and a shutoff valve. The DSV is fluidly coupled to a primary fuel inlet, a secondary fuel inlet, and a primary fuel outlet included in the conduit network. The shutoff valve is fluidly coupled between the primary fuel inlet and the primary fuel outlet. In a standard operation mode, the shutoff valve is maintained in an open position, while fuel received at the primary fuel inlet is directed through the shutoff valve, through the DSV, and to the primary fuel inlet. Conversely, in a backup operation mode, the shutoff valve is closed to block fuel flow from the primary fuel inlet to the primary fuel outlet, while the DSV directs fuel flow received at the secondary fuel inlet to the primary fuel outlet.

Abstract: Embodiments of a combined overspeed and fuel stream selector system are provided. In an embodiment, the assembly includes a conduit network, a Discharge Select Valve (DSV), and a shutoff valve. The DSV is fluidly coupled to a primary fuel inlet, a secondary fuel inlet, and a primary fuel outlet included in the conduit network. The shutoff valve is fluidly coupled between the primary fuel inlet and the primary fuel outlet. In a standard operation mode, the shutoff valve is maintained in an open position, while fuel received at the primary fuel inlet is directed through the shutoff valve, through the DSV, and to the primary fuel inlet. Conversely, in a backup operation mode, the shutoff valve is closed to block fuel flow from the primary fuel inlet to the primary fuel outlet, while the DSV directs fuel flow received at the secondary fuel inlet to the primary fuel outlet.

Abstract: A gas turbine engine fuel supply system includes a primary gear pump and a secondary gear pump. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The supercharger pump is preferably activated only during high demand conditions as an additional energy conservation measure.

Abstract: A heat transfer device for installation in a system having a heat generating element within the system away from which heat is to be transferred is described. The heat transfer device includes a heat pipe having a first portion, a second portion, and a working fluid contained within the heat pipe for transferring heat from the first portion to the second portion. The first portion is disposed in proximity with the heat generating element. The second portion is coupled to the first portion. At least part of the second portion is disposed outside the system to dissipate heat from the heat generating element and the second portion may be variably extended outside the system.

Abstract: A projectile cartridge for a hybrid capillary variable velocity electric launcher comprising a launcher and breech/barrel assembly as well as a projectile and a pulsed power supply for supplying adjustable amounts of electric energy to permit variable projectile velocity. The projectile cartridge also includes at least an anode and cathode section, a fuse wire, a capillary liner, and the projectile, which may include both a slug and a sabot jacket. A hybridization medium is included with restraining mechanisms.

Abstract: A gas turbine engine fuel supply system includes a primary gear pump, a secondary gear pump, and a pump bypass valve. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The pump bypass valve is configured to regulate fuel pressure at the primary gear pump outlet to one of a plurality of preset differential pressures above one of a plurality of fuel load pressures and prevents reverse pressurization of the gear pumps.

Abstract: A method and apparatus comprising a layer of material having a decorative graphic and an electrically conductive material in the layer of material. The layer of material is configured to be attached to a surface of an aircraft. The electrically conductive material is configured to cause a current from an atmospheric electrostatic discharge contacting the layer of material to spread out in a desired amount within the layer of material.

Abstract: A gas turbine engine fuel supply system includes a primary gear pump, a secondary gear pump, and a pump bypass valve. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The pump bypass valve is configured to regulate fuel pressure at the primary gear pump outlet to one of a plurality of preset differential pressures above one of a plurality of fuel load pressures and prevents reverse pressurization of the gear pumps.

Abstract: A gas turbine engine fuel supply system includes a primary gear pump and a secondary gear pump. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The supercharger pump is preferably activated only during high demand conditions as an additional energy conservation measure.

Abstract: A flow divider assembly includes a dividing valve and a balancing valve. The dividing valve includes a dividing cavity configured to receive a flow of fuel and a piston device arranged within the dividing cavity and selectively positioned to divide the flow of fuel in the dividing cavity into the first dividing valve port and the second dividing valve port. The balancing valve is fluidly coupled to the dividing valve and configured to receive the first portion and the second portion of the flow. The balancing valve includes a balancing cavity and a balancing device arranged within the balancing cavity and selectively positioned to direct the first portion of the flow into the first balancing cavity port at a third pressure and the second portion of the flow into the second balancing cavity port at a fourth pressure such that the first pressure is approximately equal to the second pressure.

Abstract: Heat transfer devices are described. In one example, a heat transfer device for installation in a system having a heat generating element within the system away from which heat is to be transferred is described. The heat transfer device includes a heat pipe having a first portion, a second portion, and a working fluid contained within the heat pipe for transferring heat from the first portion to the second portion. The first portion is disposed in proximity with the heat generating element. The second portion is coupled to the first portion. At least part of the second portion is disposed outside the system to dissipate heat from the heat generating element and the second portion may be variably extended outside the system.

Abstract: A method and apparatus comprising a layer of material having a decorative graphic and an electrically conductive material in the layer of material. The layer of material is configured to be attached to a surface of an aircraft. The electrically conductive material is configured to cause a current from an atmospheric electrostatic discharge contacting the layer of material to spread out in a desired amount within the layer of material.

Abstract: A flow divider assembly includes a dividing valve and a balancing valve. The dividing valve includes a dividing cavity configured to receive a flow of fuel and a piston device arranged within the dividing cavity and selectively positioned to divide the flow of fuel in the dividing cavity into the first dividing valve port and the second dividing valve port. The balancing valve is fluidly coupled to the dividing valve and configured to receive the first portion and the second portion of the flow. The balancing valve includes a balancing cavity and a balancing device arranged within the balancing cavity and selectively positioned to direct the first portion of the flow into the first balancing cavity port at a third pressure and the second portion of the flow into the second balancing cavity port at a fourth pressure such that the first pressure is approximately equal to the second pressure.

Abstract: Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

Abstract: A composite heat shield includes a ceramic composite heat shield body comprising a pair of generally spaced-apart heat shield side panels, a heat shield bottom panel extending between the heat shield side panels and having a heat exposure surface, a heat shield top panel extending between the heat shield side panels in spaced-apart relationship with respect to the heat shield bottom panel and having at least one heat shield surface and at least one heat shield cavity defined between the heat shield bottom panel and the heat shield top panel.

Abstract: Heat exchanger systems and associated systems and methods for cooling aircraft starters/generators are disclosed. A system in accordance with one embodiment includes a first fluid flow path for a first fluid, a second fluid flow path for a second fluid, and a third fluid flow path for a third fluid. The first and second flow paths are positioned proximate to the third flow path to transfer heat between the third fluid and both the first and second fluids. The third flow path is configured to allow a transfer of heat between the second and third fluids at a first transfer rate when the first fluid carries heat at a first rate, and at a second transfer rate different than the first transfer rate when the first fluid does not carry heat, or carries heat at a second rate less than the first rate. Accordingly, when the heat to be rejected by one fluid is decreased, the heat transfer rate for the remaining fluid can be increased.

Abstract: A Joint Combined Aircrew Systems Tester (JCAST) that can be used to test aircrew integrated life support equipment currently authorized for use by aircrew members of the Air Force, Navy and Army. The JCAST will be capable of Chemical/Biological seal testing of all the Joint Service Aircrew Mask (JSAM) variants including the Type 2 JSAM for high performance aircraft. Like traditional Testers, the JCAST is capable of Performance and Fit Testing of masks at pressure levels, including COMBAT EDGE (Combined Advanced Technology Enhanced Design “G” Ensemble), consistent with aircraft supply levels. The JCAST provides an apparatus and technique for accurately measuring a leak rate for an elastic body such as a chemical mask at 0.5 sccm at 6 IWG. The JCAST is portable and light weight while providing novel leak testing using pressure decay.

Abstract: A composite heat shield includes a ceramic composite heat shield body comprising a pair of generally spaced-apart heat shield side panels, a heat shield bottom panel extending between the heat shield side panels and having a heat exposure surface, a heat shield top panel extending between the heat shield side panels in spaced-apart relationship with respect to the heat shield bottom panel and having at least one heat shield surface and at least one heat shield cavity defined between the heat shield bottom panel and the heat shield top panel.