An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.

An inflatable panel comprising two flexible face sheets and a core located between the two flexible face sheets, and lateral joining members configured to be joined to an aircraft structure and coupled to the inflatable panel. The lateral joining members cover at least part of the linear contour of the two flexible face sheets and have a first part covering an edge portion adjacent to the contour of one of the face sheets and a second part covering an edge portion adjacent to the contour of the other face sheet.

An inflatable panel comprising two flexible face sheets and a core located between the two flexible face sheets, and lateral joining members configured to be joined to an aircraft structure and coupled to the inflatable panel. The lateral joining members cover at least part of the linear contour of the two flexible face sheets and have a first part covering an edge portion adjacent to the contour of one of the face sheets and a second part covering an edge portion adjacent to the contour of the other face sheet.

An aircraft comprising a fuselage defining a longitudinal axis and an interior compartment. Along the axis, in cross-section perpendicular to the axis, the compartment is enclosed by a floor, sidewall and ceiling structure. The aircraft further comprises an environmental control system comprising a conduit system through which a pressurized fluid is supplied, at least one first terminal disposed inside the compartment and in fluid communication with the conduit system, and a selectively inflatable and deflatable partition element. The partition element comprises at least one second terminal and is constructed such that it is inflatable from a deflated condition into an inflated condition by establishing a fluid communication between the second terminal and the first terminal. In the inflated condition the partition element completely closes the cross-section of the compartment, thereby dividing it into two portions, and in the deflated condition collapses and at least partially unblocks the cross section.

An aircraft comprising a fuselage defining a longitudinal axis and an interior compartment. Along the axis, in cross-section perpendicular to the axis, the compartment is enclosed by a floor, sidewall and ceiling structure. The aircraft further comprises an environmental control system comprising a conduit system through which a pressurized fluid is supplied, at least one first terminal disposed inside the compartment and in fluid communication with the conduit system, and a selectively inflatable and deflatable partition element. The partition element comprises at least one second terminal and is constructed such that it is inflatable from a deflated condition into an inflated condition by establishing a fluid communication between the second terminal and the first terminal. In the inflated condition the partition element completely closes the cross-section of the compartment, thereby dividing it into two portions, and in the deflated condition collapses and at least partially unblocks the cross section.

Systems and methods are provided by which a treatment fluid (e.g., a liquid corrosion inhibitor) may be applied onto the interior surfaces of an aircraft fuselage which employ an automated guided vehicle (AGV) comprising a carriage assembly and a robotic spray system carried by the carriage assembly supported by a support platform positioned laterally of an aircraft fuselage in alignment with the cabin door opening thereof. The AGV may thus be deployable through the cabin door opening of the fuselage to a deployed position within the interior of the fuselage so as to be moveable along a longitudinal axis of the fuselage to allow the robotic spray assembly to spray the treatment fluid onto interior surfaces of the fuselage. A sealing door assembly located rearwardly of the AGV which is moveable relative to a door opening in the fuselage may also be provided so as to sealingly close the door opening of the fuselage when the AGV is deployed within the interior of the fuselage.

An aerospace vehicle comprising an airplane or spacecraft, operatively coupled to an airship balloon containing lighter than air gas adapted to elevate the vehicle. A control system adapted to deflate the balloon upon reaching a specific altitude by directing the gas to a propulsion system and high pressure gas chambers for powering the vehicle at a greater speed or to a greater altitude. The balloon can be retracted into the vehicle to achieve a better aerodynamic shape and further re-inflated for decreasing the speed of the vehicle upon reaching a destination.

A pressure bulkhead for an aircraft comprising a fuselage. The pressure bulkhead comprises an inflatable element, suitable for being filled with air, which in turn comprises a cover which delimits an inner zone. The pressure bulkhead further comprises a seal suitable for providing an airtight seal between the cover and the fuselage of the aircraft.

A pressure bulkhead for an aircraft comprising a fuselage. The pressure bulkhead comprises an inflatable element, suitable for being filled with air, which in turn comprises a cover which delimits an inner zone. The pressure bulkhead further comprises a seal suitable for providing an airtight seal between the cover and the fuselage of the aircraft.

The present invention relates to an aerospace vehicle comprising an airplane or spacecraft, operatively coupled to an airship balloon containing lighter than air gas adapted to elevate the vehicle. A control system adapted to deflate the balloon upon reaching a predetermined altitude by directing the gas for powering the vehicle at greater speed. The balloon can be re-inflated for decreasing the speed of the vehicle upon reaching a destination and deflated in a controlled manner for landing the vehicle or disengaged from the vehicle upon transferring the gas from the balloon to a propulsion system of the vehicle.