A combination adaptive energy absorption and emergency flotation device for positioning beneath a plurality of seat pans of a seat assembly in an aircraft seating application. The device includes a plurality of fluidly coupled inflatable elastic bladders, at least one constrictor valve fluidly coupling at least two adjacent ones of the plurality of inflatable elastic bladders allowing fluid flow therethrough in response to predetermined pressure on the device from the plurality of seat pans, and a fluid supply source fluidly coupled to the plurality of inflatable elastic bladders for outputting a positive flow of fluid to the plurality of inflatable elastic bladders, wherein the adaptive energy absorption device is detached from the plurality of seat pans to allow removal from beneath the plurality of seat pans for use as an emergency flotation device.

A combination adaptive energy absorption and emergency flotation device for positioning beneath a plurality of seat pans of a seat assembly in an aircraft seating application. The device includes a plurality of fluidly coupled inflatable elastic bladders, at least one constrictor valve fluidly coupling at least two adjacent ones of the plurality of inflatable elastic bladders allowing fluid flow therethrough in response to predetermined pressure on the device from the plurality of seat pans, and a fluid supply source fluidly coupled to the plurality of inflatable elastic bladders for outputting a positive flow of fluid to the plurality of inflatable elastic bladders, wherein the adaptive energy absorption device is detached from the plurality of seat pans to allow removal from beneath the plurality of seat pans for use as an emergency flotation device.

The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft; and a first and/or second air bladder attached to a second end of the first and/or second boom, wherein the first and/or second air bladders are configured to inflate when an aircraft lands in the water, wherein deployment of the first and second boom and air bladder prevents aircraft rollover upon water landing; or a deployable keel affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.

A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

An aspirator air vent valve may include an air vent valve body coupled with an aspirator body and a pipe fitting. The air vent valve body may include an air vent valve air channel defined by an inner wall of the air vent valve body and disposed between the aspirator body and the pipe fitting. The aspirator air vent valve may further include a vent passage defined by a first vent wall and a second vent wall and disposed between an outer wall and the inner wall of the air vent valve body, wherein the vent passage is in fluid communication with the air vent valve air channel. The aspirator air vent valve may further include a plunger coupled with the air vent valve body.

An aspirator air vent valve may include an air vent valve body coupled with an aspirator body and a pipe fitting. The air vent valve body may include an air vent valve air channel defined by an inner wall of the air vent valve body and disposed between the aspirator body and the pipe fitting. The aspirator air vent valve may further include a vent passage defined by a first vent wall and a second vent wall and disposed between an outer wall and the inner wall of the air vent valve body, wherein the vent passage is in fluid communication with the air vent valve air channel. The aspirator air vent valve may further include a plunger coupled with the air vent valve body.

Provided is an inflatable wing for a rotary-wing aircraft capable of obtaining auxiliary lift by inflating the inflatable wing equipped on the fuselage when a main rotor is in non-powered rotation state by not providing power for rotating the main rotor due to causes such as an engine failure in a conventional type of rotary-wing aircraft having a single engine, thereby providing a safer emergency landing.