Expandable decoy unmanned aerial vehicles (UAVs) are disclosed. A disclosed example decoy UAV includes an expandable body at least partially defining an exterior of the expandable decoy UAV, an expander to expand the expandable body to a desired footprint, and a propulsion device operatively coupled to the expandable body, the propulsion device to move the expandable decoy UAV.

A system that optimizes the shape or configuration of an aircraft to minimize ground overpressure shock strength while in supersonic flight over speed restricted terrain and to morph to an optimized configuration for drag minimization while over unrestricted terrain.

An in-flight impact protection system for aircraft. An aircraft having a panel, with a sensor disposed on the aircraft and adapted to transmit a signal and receive a reflection of the signal. A controller coupled to the sensor and adapted to receive the reflection from the sensor to determine whether an object is near the aircraft's panel. An inflation device, which includes a tube member, is coupled to the controller and positioned inside the aircraft, proximate the panel. After determining that the object is near the panel, the controller can activate the inflation device so that the tube member inflates, thereby buttressing at least a portion of the panel. The panel can be a windshield, fuselage member, or other suitable component.

An in-flight impact protection system for aircraft. An aircraft having a panel, with a sensor disposed on the aircraft and adapted to transmit a signal and receive a reflection of the signal. A controller coupled to the sensor and adapted to receive the reflection from the sensor to determine whether an object is near the aircraft's panel. An inflation device, which includes a tube member, is coupled to the controller and positioned inside the aircraft, proximate the panel. After determining that the object is near the panel, the controller can activate the inflation device so that the tube member inflates, thereby buttressing at least a portion of the panel. The panel can be a windshield, fuselage member, or other suitable component.

The invention relates to an aircraft having a supporting structure (12) and a shell (10) that can be filled with a gas and which is tensioned by the supporting structure (12). According to the invention, said supporting structure (12) comprises a plurality of rod or tube-shaped sections (24-30) which define a circular, oval or polygonal main clamping plane for the shell (10).

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.

A remote-controlled unmanned foldable aircraft comprises at least two motors that allow the aircraft to fly, and at least one support structure for supporting said motors; the support structure is flexible and inflatable such that the support structure can be folded and unfolded between a storage position and an operational position.

A remote-controlled unmanned foldable aircraft comprises at least two motors that allow the aircraft to fly, and at least one support structure for supporting said motors; the support structure is flexible and inflatable such that the support structure can be folded and unfolded between a storage position and an operational position.

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.