The present disclosure provides an arm catcher system for an aircraft ejection seat. The arm catcher system may comprise a first support member configured to rotate in a first direction to be deployed in response to an ejection event and a first persistent locking mechanism coupled to the first support member, wherein the first persistent locking mechanism is configured to allow the support member to rotate in the first direction and configured to prevent the first support member from rotating in a second direction opposite the first direction.

A universal sequencer for an ejection seat may comprise a connector defining a plurality of pin receptacles. A controller may be electrically coupled to the connector. A tangible, non-transitory may be memory configured to communicate with the controller. The tangible, non-transitory memory has instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations, which may comprise determining an ejection seat or aircraft model and determining an ejection sequence based on the ejection seat or aircraft model determination.

A seat configured to support an occupant may include a urine-based power generator and an adjustable cushion. The urine-based power generator includes a urine accumulation reservoir configured to receive urine from the occupant, and the urine-based power generator is configured to provide power to the adjustable cushion. The seat may be an ejection seat, and the urine-based power generator and the adjustable cushion may be mounted to the seat such that the urine-based power generator and the adjustable cushion are configured to be ejected with the ejection seat.

An adjustable leg restraint for an ejection seat may be configured to translate between an extended state and a nonextended state. The adjustable leg restraint may include a leg located proximate a side panel of the ejection seat. An extension flange may be coupled to the leg guard. The extension flange may be configured to translate the leg guard relative to the side panel of the ejection seat.

An ejection seat for an aircraft is disclosed. In various embodiments, the ejection seat includes a seat frame; and a moveable headrest attached to the seat frame, the moveable headrest including a first piercer assembly configured for fracturing a canopy.

An inclining aircraft ejection seat assembly includes a curved ejection rail and an ejection seat having a guide disposed on a side of the ejection seat configured to travel along an arcuate path in mating alignment with the curved ejection rail and change a configuration of the ejection seat from a reclining position to an inclining position prior to ejection.

A chute-deployment-seat-release system for an ejection seat may be configured to deploy a parachute from the ejection seat and release an occupant restraint of the ejection seat. The chute-deployment-seat-release system may comprise an auto-deployment assembly, including a first power supply, and a manual deployment assembly, including a second power supply and a handle. The first power supply may be configured to activate in response to expulsion of the ejection seat from an aircraft. The second power supply may be configured to activate in response to an actuation of the handle.

In one embodiment, an apparatus includes a collapsible workstation assembly to be used in a temporarily-mounted control system of an aircraft. The collapsible workstation assembly is mounted to a floor of the aircraft via one or more mounting plates and one or more adaptive floor plates. The collapsible workstation assembly includes a number of modules for display and user controls. Each of the modules are connected via hinges and hinge locks to be moved between a deployed position for use and a stowed position when not in use. The collapsible workstation assembly is further connected to an observer chair assembly and a temporary door plug.

In one embodiment, an apparatus includes a collapsible workstation assembly to be used in a temporarily-mounted control system of an aircraft. The collapsible workstation assembly is mounted to a floor of the aircraft via one or more mounting plates and one or more adaptive floor plates. The collapsible workstation assembly includes a number of modules for display and user controls. Each of the modules are connected via hinges and hinge locks to be moved between a deployed position for use and a stowed position when not in use. The collapsible workstation assembly is further connected to an observer chair assembly and a temporary door plug.

A method is disclosed herein. The method includes receiving, by a processor, a first acceleration data from an accelerometer, calculating, by the processor, a change in velocity based on the first acceleration data, the change in velocity being calculated over a first period of time, and adjusting, by the processor, a timing sequence based on the change in velocity.