A jettisonable emergency exit for a vehicle, comprising an outer peripheral edge that is adapted to be accommodated in an associated frame provided in a vehicle, wherein at least one emergency exit retention means and at least one emergency exit locking device are integrated into the outer peripheral edge, the at least one emergency exit retention means comprising at least one non-retractable pivot finger around which the jettisonable emergency exit is rotatable in an emergency mode, and the at least one emergency exit locking device comprising at least one locking hook that is adapted for locking the jettisonable emergency exit in an associated locking position in normal operation mode and for releasing the jettisonable emergency exit in an associated retracted position in the emergency mode.

An emergency exit assembly for an aircraft, including a window frame, a window assembly having an outer surface abutting the inner surface of the window frame around its perimeter, and retaining elements spaced around the perimeter of the window assembly. The retaining elements are each connected to the window frame and bias the window assembly toward and against the inner surface of the window frame. Each retaining element has a force-release portion so that the window assembly can be disengaged from the window frame through release of the force-release portion. The force-release portion may be a frangible portion breakable upon application of the pulling force. A cable with one or more handle(s) may be connected to the retaining elements to apply the pulling force. A method of accessing an emergency exit of an aircraft is also discussed.

An emergency exit assembly for an aircraft, including a window frame, a window assembly having an outer surface abutting the inner surface of the window frame around its perimeter, and retaining elements spaced around the perimeter of the window assembly. The retaining elements are each connected to the window frame and bias the window assembly toward and against the inner surface of the window frame. Each retaining element has a force-release portion so that the window assembly can be disengaged from the window frame through release of the force-release portion. The force-release portion may be a frangible portion breakable upon application of the pulling force. A cable with one or more handle(s) may be connected to the retaining elements to apply the pulling force. A method of accessing an emergency exit of an aircraft is also discussed.

Pyrotechnic devices and firing mechanisms for aircraft canopy jettison are disclosed herein. An example firing mechanism includes a housing defining a first bore, a second bore, and a channel between the first bore and the second bore, a primary charge disposed in the second bore, a closure disc between the second bore and the channel, and a firing pin assembly disposed in the first bore. The firing pin assembly includes a percussion primer and a firing pin piston including a piston body, a firing pin extending from the piston body, and a piercing pin extending from the piston body. In response to a firing signal, the firing pin piston is moved toward the primary charge such that the piercing pin punctures the closure disc and the firing pin engages the percussion primer to ignite the primary charge.

Pyrotechnic devices and firing mechanisms for aircraft canopy jettison are disclosed herein. An example firing mechanism includes a housing defining a first bore, a second bore, and a channel between the first bore and the second bore, a primary charge disposed in the second bore, a closure disc between the second bore and the channel, and a firing pin assembly disposed in the first bore. The firing pin assembly includes a percussion primer and a firing pin piston including a piston body, a firing pin extending from the piston body, and a piercing pin extending from the piston body. In response to a firing signal, the firing pin piston is moved toward the primary charge such that the piercing pin punctures the closure disc and the firing pin engages the percussion primer to ignite the primary charge.

An arm restraint assembly configured to pierce a canopy in response to expulsion of an ejection seat from a cockpit may comprise a primary arm configured to pivot relative to the ejection seat. A canopy piercer may be coupled to the primary arm. The primary arm may be configured to rotate to a fully-deployed position while located within the cockpit. An apex of the canopy piercer may be oriented toward the canopy, when the primary arm is in the fully-deployed position.

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.

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.

A propulsion assembly for an aircraft includes a housing having a gimbal coupled thereto that is operable to tilt about first and second axes. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades. The rotor assembly is rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector with a direction. The first axis of the gimbal is orthogonal to the second axis of the gimbal. Actuation of the gimbal tilts the propulsion system relative to the housing to change the rotational plane of the rotor assembly relative to the housing, thereby controlling the direction of the thrust vector within a thrust vector cone.

A propulsion assembly for an aircraft includes a housing having a gimbal coupled thereto that is operable to tilt about first and second axes. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades. The rotor assembly is rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector with a direction. The first axis of the gimbal is orthogonal to the second axis of the gimbal. Actuation of the gimbal tilts the propulsion system relative to the housing to change the rotational plane of the rotor assembly relative to the housing, thereby controlling the direction of the thrust vector within a thrust vector cone.