Abstract: An output device and/or an output device assembly configured to be initiated in response to different types of input. The disclosed output device may be generally configured so as to be able to receive different types of input in order to produce an output. For example, the two different types of input may be mechanical force and fluid pressure, and thus the disclosed output device may be able to receive either form of input and convert either input into the desired/predetermined output.

Abstract: A method for removing a gas from a propellant composition includes providing an uncured propellant composition comprising a bonding agent, energetic particles, and a polymeric binder, and flowing an inert gas through the uncured propellant composition to remove an evolved gas from the uncured propellant composition.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon for controlling deployment of aircraft escape and ejection seat subsystems. The instructions, in response to execution by a first sequencer, cause the first sequencer to perform operations which may comprise receiving a power input, determining a seat location and a seat identity of a first ejection seat in which the first sequencer is installed, determining an ejection mode, sending a first deploy command to an escape path clearance subsystem, determining a deployment sequence for a seat rocket catapult subsystem and a plurality of ejection seat subsystems of the first ejection seat based on the seat location, the seat identity, and the ejection mode, sending a second deploy command to the seat rocket catapult subsystem, and sending a series of third deploy commands to the plurality of ejection seat subsystems.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon for controlling deployment of aircraft escape and ejection seat subsystems. The instructions, in response to execution by a first sequencer, cause the first sequencer to perform operations which may comprise receiving a power input, determining a seat location and a seat identity of a first ejection seat in which the first sequencer is installed, determining an ejection mode, sending a first deploy command to an escape path clearance subsystem, determining a deployment sequence for a seat rocket catapult subsystem and a plurality of ejection seat subsystems of the first ejection seat based on the seat location, the seat identity, and the ejection mode, sending a second deploy command to the seat rocket catapult subsystem, and sending a series of third deploy commands to the plurality of ejection seat subsystems.

Abstract: A spring damper system for a pyrotechnic time delay may comprise: a piston; a firing pin; a hydraulic chamber, a portion of the piston disposed in the hydraulic chamber; and a first spring configured to compress in response to a time delay sequence being initiated, the piston configured to translate axially in the first axial direction in response to the first spring returning axially towards a neutral state, the first engagement end and the second engagement end configured to release in response to exiting the channel, and the firing pin configured to translate in the second axial direction in response to a second spring returning towards a second neutral state.

Abstract: A damper system for a pyrotechnic time delay may comprise: a firing pin; a moveable housing defining a chamber therein; a fixed piston comprising a piston head disposed in the chamber, a first rod extending from the piston head axially outward of the moveable housing, and a second rod configured to fixedly couple to a housing; a first spring extending axially from the moveable housing to the firing pin; and a second spring extending axially from the moveable housing to the firing pin.

Abstract: A spring damper system for a pyrotechnic time delay may comprise: a piston; a firing pin; a hydraulic chamber, a portion of the piston disposed in the hydraulic chamber; and a first spring configured to compress in response to a time delay sequence being initiated, the piston configured to translate axially in the first axial direction in response to the first spring returning axially towards a neutral state, the first engagement end and the second engagement end configured to release in response to exiting the channel, and the firing pin configured to translate in the second axial direction in response to a second spring returning towards a second neutral state.

Abstract: A method for generating electric power for a rocket system includes burning a primary solid propellant grain to create a primary high pressure gas for providing thrust to the rocket, opening a first valve to divert a portion of the high pressure gas to an auxiliary solid propellant grain for igniting the auxiliary solid propellant grain, wherein the auxiliary solid propellant grain is disposed in a housing separate from the primary solid propellant grain, and burning the auxiliary solid propellant grain to create an auxiliary high pressure gas for turning a turbine. The method further includes driving a generator with the turbine and generating an electric power with the generator.

Abstract: An output device and/or an output device assembly configured to be initiated in response to different types of input. The disclosed output device may be generally configured so as to be able to receive different types of input in order to produce an output. For example, the two different types of input may be mechanical force and fluid pressure, and thus the disclosed output device may be able to receive either form of input and convert either input into the desired/predetermined output.

Abstract: A thermally initiated variable venting system may comprise a first linear shape charge (LSC) coupled to a first sensor and a second LSC coupled to a second sensor. An upper apex of the second LSC may be disposed within a lower apex of the first LSC. The output of the system may vary depending on whether the event is fast cook-off (FCO) or slow cook-off (SCO).

Abstract: Methods and systems for an explosive cord are disclosed. An explosive cord may comprise a tubing comprising an inner surface and an outer surface, a reactive material comprising hexanitrostilbene and/or boron potassium nitrate coupled to the inner surface of the tubing, and a hollow or solid core through the center of the explosive cord.

Abstract: A detonation transfer assembly is disclosed. A detonation transfer assembly may comprise an external casing comprising an input end and an output end axially opposite the input end, an explosive column spanning axially inside the external casing, a primary explosive disposed within the explosive column, and a secondary explosive disposed within the explosive column axially between the primary explosive and the output end. The primary explosive and/or the secondary explosive may comprise a thermally insensitive initiation material that resists at least one of detonation or thermal degradation in response to temperature increase rate of 3.3° C. per hour over at least twenty hours.

Abstract: A thermally initiated variable venting system may comprise a first linear shape charge (LSC) coupled to a first sensor and a second LSC coupled to a second sensor. An upper apex of the second LSC may be disposed within a lower apex of the first LSC. The output of the system may vary depending on whether the event is fast cook-off (FCO) or slow cook-off (SCO).

Abstract: Methods and systems for an explosive cord are disclosed. An explosive cord may comprise a tubing comprising an inner surface and an outer surface, a reactive material comprising hexanitrostilbene and/or boron potassium nitrate coupled to the inner surface of the tubing, and a hollow or solid core through the center of the explosive cord.

Abstract: A system for selecting an ejection mode on an aircraft may include an egress actuator, a ballistic signal system operatively connected to the egress actuator, and a processor operatively connected to the ballistic signal system and the egress actuator. The processor may be configured to receive, from an aircraft controller, a flight characteristic, and select, based on the flight characteristic, an ejection mode from two ejection modes. The processor may be further configured to receive a pilot egress command from the ballistic signal system, and transmit, to the egress actuator, a signal to actuate the ejection mode from the two ejection modes.

Abstract: Methods and systems for an explosive cord are disclosed. An explosive cord may comprise a tubing comprising an inner surface and an outer surface, a reactive material comprising hexanitrostilbene and/or boron potassium nitrate coupled to the inner surface of the tubing, and a hollow or solid core through the center of the explosive cord.

Abstract: A detonation transfer assembly is disclosed. A detonation transfer assembly may comprise an external casing comprising an input end and an output end axially opposite the input end, an explosive column spanning axially inside the external casing, a primary explosive disposed within the explosive column, and a secondary explosive disposed within the explosive column axially between the primary explosive and the output end. The primary explosive and/or the secondary explosive may comprise a thermally insensitive initiation material that resists at least one of detonation or thermal degradation in response to temperature increase rate of 3.3° C. per hour over at least twenty hours.

Abstract: Methods and systems for an explosive cord are disclosed. An explosive cord may comprise a tubing comprising an inner surface and an outer surface, a reactive material comprising hexanitrostilbene and/or boron potassium nitrate coupled to the inner surface of the tubing, and a hollow or solid core through the center of the explosive cord.

Abstract: A system for selecting an ejection mode on an aircraft may include an egress actuator, a ballistic signal system operatively connected to the egress actuator, and a processor operatively connected to the ballistic signal system and the egress actuator. The processor may be configured to receive, from an aircraft controller, a flight characteristic, and select, based on the flight characteristic, an ejection mode from two ejection modes. The processor may be further configured to receive a pilot egress command from the ballistic signal system, and transmit, to the egress actuator, a signal to actuate the ejection mode from the two ejection modes.

Abstract: Methods and systems for an explosive cord are disclosed. An explosive cord may comprise a tubing comprising an inner surface and an outer surface, a reactive material comprising hexanitrostilbene and/or boron potassium nitrate coupled to the inner surface of the tubing, and a hollow or solid core through the center of the explosive cord.