Abstract: A system and method for controlling air flow through a combustor swirler assembly that includes an inner swirler and an outer swirler. A bistable fluidic amplifier that includes an air inlet, a first air outlet, a second air outlet, and a control port is disposed upstream of the combustor swirler assembly. A flow of compressed is directed into the air inlet of the bistable fluidic amplifier and, based on the control air pressure at the control port, the flow of compressed air supplied to the air inlet is selectively directed to either the first air outlet or the second air outlet.

Abstract: A system and method for controlling air flow through a combustor swirler assembly that includes an inner swirler and an outer swirler. A bistable fluidic amplifier that includes an air inlet, a first air outlet, a second air outlet, and a control port is disposed upstream of the combustor swirler assembly. A flow of compressed is directed into the air inlet of the bistable fluidic amplifier and, based on the control air pressure at the control port, the flow of compressed air supplied to the air inlet is selectively directed to either the first air outlet or the second air outlet.

Abstract: A hot-gas thruster is actuated using a relatively small electric motor. The hot-gas thruster includes a pressure assisted pilot shaft to keep electric power demand to only a few hundred watts peak and only tens of watts on average, while exhibiting relatively fast response times.

Abstract: A gas control valve is configured to controllably supply propellant gas to a thruster so that the thruster may produce thrust over a relatively wide range, and so that the thruster exhibits relatively fine minimum impulse bit (MIB) performance. The gas control valve includes a pilot stage having a pilot valve, and a main stage having a main valve. The gas control valve responds to control signals supplied to the pilot stage and is configured such that for commands of relatively short duration, only the pilot valve responds. Conversely, for commands of relatively longer duration, the pilot valve and main valve both respond.

Abstract: A hot-gas thruster is actuated using a relatively small electric motor. The hot-gas thruster includes a pressure assisted pilot shaft to keep electric power demand to only a few hundred watts peak and only tens of watts on average, while exhibiting relatively fast response times.

Abstract: A gas thruster is configured to supply thrust over a relatively wide range, from a relatively low value to a relatively high thrust value, and exhibits relatively fine minimum impulse bit (MIB) performance. The gas thruster includes a thrust nozzle, a main stage, a main valve element, and a pilot valve. The gas thruster responds to thruster control signals supplied to the pilot valve and is configured such that for commands of relatively short duration, only the pilot valve responds and relatively low thrust is produced. Conversely, for command or relatively longer duration, the pilot valve and main valve element both respond and relatively higher thrust is produced.

Abstract: A gas control valve is configured to controllably supply propellant gas to a thruster so that the thruster may produce thrust over a relatively wide range, and so that the thruster exhibits relatively fine minimum impulse bit (MIB) performance. The gas control valve includes a pilot stage having a pilot valve, and a main stage having a main valve. The gas control valve responds to control signals supplied to the pilot stage and is configured such that for commands of relatively short duration, only the pilot valve responds. Conversely, for commands of relatively longer duration, the pilot valve and main valve both respond.

Abstract: A gas thruster is configured to supply thrust over a relatively wide range, from a relatively low value to a relatively high thrust value, and exhibits relatively fine minimum impulse bit (MIB) performance. The gas thruster includes a thrust nozzle, a main stage, a main valve element, and a pilot valve. The gas thruster responds to thruster control signals supplied to the pilot valve and is configured such that for commands of relatively short duration, only the pilot valve responds and relatively low thrust is produced. Conversely, for command or relatively longer duration, the pilot valve and main valve element both respond and relatively higher thrust is produced.

Abstract: A gas valve apparatus is provided. A primary valve includes a flapper nozzle valve and first and second outputs. A secondary valve includes a housing having first and second inputs coupled to the first and second outputs of the primary valve, first and second seats coupled to the first and second inputs, first and second nozzles coupled to the first and second seats, and a moveable element configured for alternatively sealing the first and second nozzles as the moving element comes into contact with the first and second seats.

Abstract: A force balanced butterfly proportional hot gas valve is configured to receive pressurized gas from a pressurized gas source and to selectively divert the pressurized gas to one or both of two outlet nozzles. The valve includes a primary inlet, a flow passage coupled to the primary inlet, a portion of the flow passage formed into a power jet structure, a diffuser, first and second outlet nozzles coupled to the flow passage, and a butterfly element disposed at least partially within the flow passage and moveable therein to selectively divert gas flow to the first, second or both first and second outlet nozzles simultaneously.

Abstract: A diverter valve includes a valve bore having a set of valve seats associated with each fluid outlet port. Each set of valve seats is at least partially separated from one another by a flow channel. The valve seat configuration increases the impact area for the valve element. As a result, the impact force upon seating against the valve seats is reduced. Moreover, by including flow channels between the sets of valve seats, the switching force and performance of the valve element is not adversely affected.

Abstract: A valve is disclosed for regulating the flow of a pressurized working fluid through a nozzle having a nozzle throat. In a preferred embodiment of the invention, the valve comprises a valve body defining a valve bore, a pressure inlet and a nozzle plenum. The nozzle plenum fluidly communicates with the nozzle throat. A valve seat is disposed between the pressure inlet and the nozzle plenum. A valve member is slidably disposed within the valve bore. The valve member comprises a first end disposed proximal the valve seat and a second end distal the valve seat. The first end comprises a valve face and the second end comprises first and second rear surfaces. The second rear surface is spaced apart from the first rear surface. The first rear surface cooperates with the valve bore to define a rear chamber. The second rear surface cooperates with the valve bore to define an actuation chamber, the volume of which is not a function of the valve member diameter.

Abstract: A pneumatic regulating valve that operates on high-temperature, high-pressure gases. This invention reduces the upstream pressure of a flow of gas, which can be as high as 10,000 psia, down to a level usable by downstream control valves, which may require controlled pressure input. The springs and seals of this invention are isolated from the high temperature and pressure of the upstream gas, thus enabling regulation of gas flows of up to 10,000 psia and 2,500.degree. F.

Abstract: A fluidic circuit (10) having two oscillators (22,24) which separately vent to a common volume (78) and receive pressurized fluid inputs along separate flow paths (54,56) is provided with filters (80) positioned both upstream and downstream from each oscillator. Each of the filters (80) is adapted to attenuate oscillator-induced noise and comprises a series combination of an inductive element (82), a capacitive element (84), and an inductive element (86).