Abstract: According to various embodiments, a biomedically actuated occupant restraint system includes an occupant restraint system for a vehicle, the occupant restraint system having a locked position and an unlocked position. The biomedically actuated occupant restraint system further includes an occupant monitoring system operably connected to the occupant restraint system, the occupant monitoring system configured for monitoring a plurality of physiological conditions of an occupant of the vehicle. The occupant monitoring system includes a biometric sensor module including a plurality of physiological sensors configured for measuring a plurality of physiological conditions of the occupant and asserting a plurality of sensor signals, and a controller configured to receive the plurality of sensor signals and determine whether the occupant is incapacitated. The controller being configured to send a command to lock the occupant restraint system in response to determining the occupant is incapacitated.

Abstract: According to various embodiments, a biomedically actuated occupant restraint system includes an occupant restraint system for a vehicle, the occupant restraint system having a locked position and an unlocked position. The biomedically actuated occupant restraint system further includes an occupant monitoring system operably connected to the occupant restraint system, the occupant monitoring system configured for monitoring a plurality of physiological conditions of an occupant of the vehicle. The occupant monitoring system includes a biometric sensor module including a plurality of physiological sensors configured for measuring a plurality of physiological conditions of the occupant and asserting a plurality of sensor signals, and a controller configured to receive the plurality of sensor signals and determine whether the occupant is incapacitated. The controller being configured to send a command to lock the occupant restraint system in response to determining the occupant is incapacitated.

Abstract: A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes an input device configured to receive user input. The system further includes a controller coupled to the ejection system and to the input device and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the user input.

Abstract: A drogue bridle separation assembly may comprise a housing and a pyrotechnic fastener. The housing may define a riser channel and a fastener opening. The pyrotechnic fastener may be configured to extend through the fastener opening and the riser channel. The pyrotechnic fastener includes a charge configured to undergo an exothermic reaction in response to an electrical signal.

Abstract: An ejection handle separation system is disclosed herein. The ejection handle separation system includes an ejection seat handle, a rotatable component, a cable connected to the handle and coupled to the rotatable component, wherein the rotatable component rotates in response to pulling the ejection seat handle, and an anchor inserted into the rotatable component and configured to releasably connect the cable to the rotatable component.

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 recovery parachute assembly may comprise a container comprising an open base end, a parachute packed within the container, a plurality of riser lines and suspension lines packed within the container and proximate the open base end, a tray including a lip configured to receive the open base end of the parachute container, and a first standoff block coupled to the tray, wherein the first standoff block compresses at least one of the riser lines or suspension lines into the base end of the container and away from the tray, wherein the first standoff block defines a channel between the lip of the tray and the first standoff block, wherein the channel includes a plurality of drain holes formed along a distal edge of the tray.

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 system for controlling an aircraft in response to deployment of an ejection seat may comprise a seat controller located on the ejection seat and configured to output a signal in response to initiation of an ejection sequence. An aircraft controller may be configured to receive the signal from the seat controller. A tangible, non-transitory memory may be configured to communicate with the aircraft controller. The tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the aircraft controller, cause the aircraft controller to perform operations, which may comprise receiving the signal from the seat controller, receiving data signals from an operational data source, and sending command signals configured to control a component of the aircraft.

Abstract: A dual switch arm and mode select system for monitoring an ejection mode selection of an ejection system may include a controller. An ejection mode selector, a first arm switch assembly, a second arm switch assembly, and a display may be in communication with the controller. The controller may determine an ejection mode of the ejection system based on a signal received from the ejection mode selector. The controller may determine a position of the first arm switch assembly and a position of the second arm switch assembly. The controller may command the display to output at least one of a fault-free signal, a fault signal, or a warning signal based on the ejection mode and the positions of the first arm switch assembly and the second arm switch assembly.

Abstract: A cushion length adjusting system for use in an ejection seat of an aircraft may include a seat pan and first cushion length adjuster coupled to the seat pan. The cushion length adjuster may be hingedly or slidingly coupled to the seat pan. The cushion length adjuster may be configured to adjust a leg support length for greater ergonomics for a pilot of an aircraft.

Abstract: An ejection system may comprise an ejection seat and a rail assembly. A plurality of sliders may be coupled to the ejection seat. The rail assembly may include a rail defining a channel and a rail insert located in the channel. The rail insert may define an insert channel configured to receive the plurality of sliders.

Abstract: A drogue bridle separation assembly may comprise a housing and a pyrotechnic fastener. The housing may define a riser channel and a fastener opening. The pyrotechnic fastener may be configured to extend through the fastener opening and the riser channel. The pyrotechnic fastener includes a charge configured to undergo an exothermic reaction in response to an electrical signal.

Abstract: An ejection seat system is described. The ejection seat system includes a seat frame for supporting an aircraft occupant. The seat frame includes one or more of a ballast material or an auto-inflating unit. By the ballast material or the auto-inflating unit, the seat frame may be positively buoyant in saltwater or freshwater for improved recovery of the seat frame. The ballast material may include one or more of a gas or foam. The auto-inflating unit may include one or more of a pump or a gas cartridge. Such flotation means may be included within an internal void of one or more of a seat bucket or a seat back of the seat frame.

Abstract: An ejection system may comprise an ejection seat and a rail assembly. A plurality of sliders may be coupled to the ejection seat. The rail assembly may include a rail defining a channel and a rail insert located in the channel. The rail insert may define an insert channel configured to receive the plurality of sliders.

Abstract: A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes a sensor configured to detect user data corresponding to a user of the ejection system. The system further includes a controller coupled to the ejection system and to the sensor and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the user data detected by the sensor.

Abstract: A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes a sensor configured to detect weight data corresponding to a weight of a user of the ejection system. The system further includes a controller coupled to the ejection system and to the sensor and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the weight data.

Abstract: A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings and having a plurality of components. The system further includes a connector configured to connect to a component of the plurality of components and having a connector portion that includes information corresponding to a user of the ejection system. The system further includes a controller coupled to the ejection system and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the information corresponding to the user of the ejection system.

Abstract: An ejection seat for an aircraft is disclosed. In various embodiments, the ejection seat includes a base, a divergence rocket attached to the base, and a compensation rocket attached to the base.