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.

An ejectable flight data recorder for robust retention of flight data and aiding in locating an aircraft after an emergency situation comprises: a buoyant housing comprising an internal cavity, a door for access to at least a portion of the internal cavity, and an aerodynamic outer shape having a longitudinal axis; an energy-dissipating nose cone for reducing an impact load on the housing when the flight data recorder impacts a water surface; a nonvolatile memory configured to store flight data; a position sensor for detecting a geographic position of the flight data recorder; a radio transmitter; an antenna electrically coupled to the radio transmitter; a sustainable power system; and a hydrophone for acoustically tracking a sinking trajectory of the aircraft in a body of water.

A short term, autonomous, electrical power supply system, particularly an emergency short term, autonomous, electrical power supply system. Said system comprises an actuator with an electrical motor (14), an electrical generator (15) for driving said electrical motor (14) of said actuator, a turbine (13) in driving engagement with said electrical generator (15), an generator (7) of combustible, fluidic energy, a fluid line (10) from said generator (7) to said turbine (13), a control unit (5), and an igniter (9) arranged inside said generator (7) and controlled by said control unit (5).

A short term, autonomous, electrical power supply system, particularly an emergency short term, autonomous, electrical power supply system. Said system comprises an actuator with an electrical motor (14), an electrical generator (15) for driving said electrical motor (14) of said actuator, a turbine (13) in driving engagement with said electrical generator (15), an generator (7) of combustible, fluidic energy, a fluid line (10) from said generator (7) to said turbine (13), a control unit (5), and an igniter (9) arranged inside said generator (7) and controlled by said control unit (5).

An emergency opening device of an aircraft door including a tubular actuating member (2); a resilient compression device; a retaining member for retaining the tubular actuating member (2), having a retaining wire (12) which, when the tubular actuating member (2) is in the retracted position, is held taut between a first attachment (14, 17) and a second attachment (16, 18); a release device which includes a cutting member (22) for transversely cutting the retaining wire (12).

An emergency opening device of an aircraft door including a tubular actuating member (2); a resilient compression device; a retaining member for retaining the tubular actuating member (2), having a retaining wire (12) which, when the tubular actuating member (2) is in the retracted position, is held taut between a first attachment (14, 17) and a second attachment (16, 18); a release device which includes a cutting member (22) for transversely cutting the retaining wire (12).

Aspects of this disclosure relate to a removable fuselage expansion window assembly, comprising: a window panel; an outer window frame; a window bracket configured to secure the window panel to the outer window frame; an inner window frame with an indented rim that is aligned with the window bracket; and a latch assembly located below the indented rim of the inner window frame between the outer window frame and the inner window frame. The latch assembly includes one or more retainers to hold a bottom portion of the removable fuselage expansion window assembly within a rectangular frame formed by vertical and horizontal beams in an outer wall of an aircraft, wherein the latch assembly includes a lever that releases the removable fuselage expansion window assembly by disengaging the one or more retainers from the rectangular frame when the lever is pulled.

Aspects of this disclosure relate to a removable fuselage expansion window assembly, comprising: a window panel; an outer window frame; a window bracket configured to secure the window panel to the outer window frame; an inner window frame with an indented rim that is aligned with the window bracket; and a latch assembly located below the indented rim of the inner window frame between the outer window frame and the inner window frame. The latch assembly includes one or more retainers to hold a bottom portion of the removable fuselage expansion window assembly within a rectangular frame formed by vertical and horizontal beams in an outer wall of an aircraft, wherein the latch assembly includes a lever that releases the removable fuselage expansion window assembly by disengaging the one or more retainers from the rectangular frame when the lever is pulled.

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.