A pyrotechnic egress system for a structure may comprise an explosive cord, an outer sheath disposed about the explosive cord, and a stress concentrator coupled to the outer sheath. The stress concentrator may comprise a triangular cross section. The stress concentrator may include a standoff structure.

A pyrotechnic egress system for a structure may comprise an explosive cord, an outer sheath disposed about the explosive cord, and a stress concentrator coupled to the outer sheath. The stress concentrator may comprise a triangular cross section. The stress concentrator may include a standoff structure.

An aircraft safety apparatus removably disposed on at least a portion of an aircraft, the aircraft safety apparatus including a parachute canister, including a main body to store at least one item therein, and at least one parachute disposed within at least a portion of the main body to reduce a rate of descent of the aircraft in response to extraction from the main body, and a rocket canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a combustible gas, and a gas canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a non-combustible gas.

This invention provides an integrated pilot autonomous ejection system with skydiving safety/training which combines sensors, hardware and software technologies to improve pilot training and safety. It offers pilots state-of-the-art cost-effective Virtual Reality Skydiving and flight simulations which prepares pilots on skydiving after ejections and for the dangers of Vertigo and G-LOC which can result in a crash in seconds. Related flight data including cameras which constantly monitors pilots can be used for debriefings/accident investigations which can be done in minutes. The goal is to improve pilot safety during the transition to fully autonomous fleets of fighter jets which have better warrior capabilities.

This invention provides an integrated pilot autonomous ejection system with skydiving safety/training which combines sensors, hardware and software technologies to improve pilot training and safety. It offers pilots state-of-the-art cost-effective Virtual Reality Skydiving and flight simulations which prepares pilots on skydiving after ejections and for the dangers of Vertigo and G-LOC which can result in a crash in seconds. Related flight data including cameras which constantly monitors pilots can be used for debriefings/accident investigations which can be done in minutes. The goal is to improve pilot safety during the transition to fully autonomous fleets of fighter jets which have better warrior capabilities.

The present disclosure provides a high explosive firing mechanism. The high explosive firing mechanism may comprise a housing comprising a firing pin tube having a primer inlet. The high explosive firing mechanism may further comprise a firing pin disposed within the firing pin tube, the firing pin comprising a nub. The nub may partially extend into the primer inlet.

An assembly for arming/disarming a slide of an airplane door according to the invention comprises a system with two releasable connection mechanisms (2) linked with the door (1) and a cabin floor of the airplane, each mechanism (2) comprising a releasable connector (21b) secured to the door (1), extending at right angles to the floor on each side of a door bottom, and an anchor fitting (22b) fixed to the cabin floor. Each connector (21b) is equipped with an elastic centering element (70) and a locking/unlocking grab (25b) on the corresponding anchor fitting (22b), the connectors (21b) being linked by a girt bar (5). Each grab (25b) being rotationally mobile, one of the grabs (25b) is driven by a single command (5; 25b) which drives the other grab in rotation via the girt bar (5).

An assembly for arming/disarming a slide of an airplane door according to the invention comprises a system with two releasable connection mechanisms (2) linked with the door (1) and a cabin floor of the airplane, each mechanism (2) comprising a releasable connector (21b) secured to the door (1), extending at right angles to the floor on each side of a door bottom, and an anchor fitting (22b) fixed to the cabin floor. Each connector (21b) is equipped with an elastic centering element (70) and a locking/unlocking grab (25b) on the corresponding anchor fitting (22b), the connectors (21b) being linked by a girt bar (5). Each grab (25b) being rotationally mobile, one of the grabs (25b) is driven by a single command (5; 25b) which drives the other grab in rotation via the girt bar (5).

An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.

The present disclosure relates to an aircraft comprising a passenger module, and also a method of protecting a passenger on an aircraft. The passenger module is configured to be ejected through a skin of the aircraft in response to an ejection command. The ejection command may be given in response to a fatal condition to the aircraft being detected or manually indicated.