An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

A deployable aircraft flotation system. The deployable aircraft flotation system includes a pair of flotation members. The pair of flotation members are positioned on opposing sides of a bottom surface of an aircraft body. Each flotation member of the pair of flotation members has an inner layer that is made of a first buoyant material, an outer layer that is made of a second buoyant material, and a middle layer between the inner layer and the outer layer that is made of a rigid material. The flotation members can be moved from a stowed position, where they are stored in housings, to a deployed position, where they emerge and are positioned on the bottom of the plane.

An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship.

An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship.

An aircraft having an airframe that extends longitudinally along an anteroposterior plane. A buoyancy system is provided with at least one pair of two floats arranged transversely on opposite sides of said anteroposterior plane. Each float is movable in elevation from a bottom position to a top position. For each float, the buoyancy system includes a blocking system for blocking each float by default in the bottom position, and for acting under a predetermined condition to block the floats present on one of the sides only of the aircraft in the top position.

An aircraft having an airframe that extends longitudinally along an anteroposterior plane. A buoyancy system is provided with at least one pair of two floats arranged transversely on opposite sides of said anteroposterior plane. Each float is movable in elevation from a bottom position to a top position. For each float, the buoyancy system includes a blocking system for blocking each float by default in the bottom position, and for acting under a predetermined condition to block the floats present on one of the sides only of the aircraft in the top position.

An aircraft includes a fuselage having a front, a center, and a rear section. A first mounting member is coupled to the front section. A second mounting member is coupled to the rear section. A first and a second wing are coupled to the center section. A plurality of power generator systems are included and coupled to the first or second mounting member. Each power generator system includes a power source, a first and a second propeller. The power source is configured to drive the first and second propeller. The first and second propeller have an axis of rotation, and are pivotable between a first and a second position. An amphibious landing gear system is coupled to an underside of the fuselage and has a flap and a bladder. The bladder is located under the flap, configured to inflate and deflate, and sized to provide buoyancy for the aircraft.

An aircraft includes a fuselage having a front, a center, and a rear section. A first mounting member is coupled to the front section. A second mounting member is coupled to the rear section. A first and a second wing are coupled to the center section. A plurality of power generator systems are included and coupled to the first or second mounting member. Each power generator system includes a power source, a first and a second propeller. The power source is configured to drive the first and second propeller. The first and second propeller have an axis of rotation, and are pivotable between a first and a second position. An amphibious landing gear system is coupled to an underside of the fuselage and has a flap and a bladder. The bladder is located under the flap, configured to inflate and deflate, and sized to provide buoyancy for the aircraft.

A compound helicopter with braced wings in joined-wing configuration, a fuselage that extends from a front fuselage section to a rear fuselage section, and an emergency floatation system with main floatation balloons and lateral floatation balloons, wherein the main floatation balloons comprise at least one front floatation balloon that is arranged in the front fuselage section 4a and at least one rear floatation balloon that is arranged in the rear fuselage section, and wherein the lateral floatation balloons comprise at least one first lateral floatation balloon that is arranged close to an interconnection region of the first braced wing and at least one second lateral floatation balloon that is arranged close to an interconnection region of the second braced wing.