Goodrich Corporation

Ami Industries, Inc.

Luis G Interiano

John Hampton

Jerry A Lambert

Kassidy L Carson

Steve Andrew Holstine

Jeff Benjamin

Matthew D Salois

Kevin Mueller

Matthew Campbell

James Tulloch

Leo P Leighton

Matthew Salois

Ejection seat systems include an ejection seat and a propellant assembly mounted to the ejection seat. A nozzle assembly having an adjustable nozzle is moveably attached to the ejection seat and configured to receive propellant exhaust from the propellant assembly and exhaust through the adjustable nozzle. A first linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a first direction and a second linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a second direction. The second direction includes a directional component that is normal to the first direction. A control module is configured to control operation of the first linear electric actuator and the second linear electric actuator.

Electronically actuated rocket catapult system for ejection seats

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.

Dual input actuator for an output device

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.

Multi-seat escape system and ejection seat sequencer

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.

Time delay systems, methods, and devices

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.

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).

Thermally initiated variable venting system for rocket motor

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.

Methods and systems for an explosive cord

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&#xb0; C. per hour over at least twenty hours.

Detonation transfer assembly

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.

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Galt, CA, United States of America

Luis G Interiano