A rocket catapult assembly for an ejection seat may comprise a motor assembly including a proximal end and a distal end, an outlet tube coupled to the distal end, and a valve coupled to the outlet tube. The valve may be configured to vary an operating pressure based on an occupant's weight. The valve may be in a closed configuration, on open configuration, or a partially open configuration during ejection of the ejection seat.

A rocket catapult assembly for an ejection seat may comprise a motor assembly including a proximal end and a distal end, an outlet tube coupled to the distal end, and a valve coupled to the outlet tube. The valve may be configured to vary an operating pressure based on an occupant's weight. The valve may be in a closed configuration, on open configuration, or a partially open configuration during ejection of the ejection seat.

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.

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.

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 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.

A canopy fragilization system for use in an aircraft ejection system may comprise: a sharp breaker disposed on a first side of an ejection seat, the sharp breaker configured to act as a primary breaker of a canopy of an aircraft; a blunt breaker disposed on a second side of the ejection seat, the blunt breaker configured to act as a secondary breaker of the canopy of the aircraft; and a deployable overhead protection assembly comprising a mitt extending forward of the sharp breaker and the blunt breaker when in a deployed position, a forward end of the mitt configured to act as a tertiary breaker of the canopy of the aircraft.

A canopy fragilization system for use in an aircraft ejection system may comprise: a sharp breaker disposed on a first side of an ejection seat, the sharp breaker configured to act as a primary breaker of a canopy of an aircraft; a blunt breaker disposed on a second side of the ejection seat, the blunt breaker configured to act as a secondary breaker of the canopy of the aircraft; and a deployable overhead protection assembly comprising a mitt extending forward of the sharp breaker and the blunt breaker when in a deployed position, a forward end of the mitt configured to act as a tertiary breaker of the canopy of the aircraft.

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.

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.