A vertical-tailless aircraft includes a body, a main wing, and a negative pressure generating portion. The body extends in a direction along an aircraft axis and includes a front body and a rear body. The main wing is provided on a side surface of the body. The negative pressure generating portion is provided at the rear body and is configured to generate negative pressure on the side surface of the rear body in a case that the vertical-tailless aircraft sideslips.

An airborne docking method is provided for an unmanned aerial vehicle. The airborne docking method includes securing an unmanned aerial vehicle (UAV) to a host aircraft via a docking assembly having a base coupled to the host aircraft, a tug device, and a cable connecting the tug device to the base, the tug device being engaged with the base, and the UAV being engaged to the tug device. The tug device is deployed from the base and the cable is extended therebetween to distance the tug device from the base. The UAV is then disengaged from the tug device.

An airborne docking method is provided for an unmanned aerial vehicle. The airborne docking method includes securing an unmanned aerial vehicle (UAV) to a host aircraft via a docking assembly having a base coupled to the host aircraft, a tug device, and a cable connecting the tug device to the base, the tug device being engaged with the base, and the UAV being engaged to the tug device. The tug device is deployed from the base and the cable is extended therebetween to distance the tug device from the base. The UAV is then disengaged from the tug device.

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

Aspects of the disclosure are directed to a toolset configured to fabricate a component of an aircraft, the toolset comprising: a mold base configured to seat at least one mandrel, a mold lid configured to be coupled to the mold base, and at least one driver block that is integral with the mold lid and projects from an interior surface of the mold lid.

A tethered uni-rotor network of satellite vehicles combines fixed-wing and rotorcraft designs. A central hub with multiple tethers to satellite vehicles radiates outward in a hub-and-spoke arrangement. Satellites have lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The system operates in a persistent state of rotation, driven by satellite propulsion units. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite vehicle and the central hub. As the system rotates, centrifugal forces pull each satellite vehicle outwards, which keeps each tether taught. The tethers are attached at innermost portions of each lifting surface; the energy storage mass is located at the outermost portion; the tension alleviates bending moment common to fixed-wing aircraft, reducing the weight within the structural members, utilize higher aspect ratio wings to reduce induced drag, and thin-thickness high-camber airfoil profiles achieve higher lift-to-drag ratios yield a more aerodynamically efficient aircraft.

A tethered uni-rotor network of satellite vehicles combines fixed-wing and rotorcraft designs. A central hub with multiple tethers to satellite vehicles radiates outward in a hub-and-spoke arrangement. Satellites have lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The system operates in a persistent state of rotation, driven by satellite propulsion units. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite vehicle and the central hub. As the system rotates, centrifugal forces pull each satellite vehicle outwards, which keeps each tether taught. The tethers are attached at innermost portions of each lifting surface; the energy storage mass is located at the outermost portion; the tension alleviates bending moment common to fixed-wing aircraft, reducing the weight within the structural members, utilize higher aspect ratio wings to reduce induced drag, and thin-thickness high-camber airfoil profiles achieve higher lift-to-drag ratios yield a more aerodynamically efficient aircraft.

An actuator of an aircraft includes at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20). Each destructible portion of each destructible bearing surface is mounted to be removable with respect to the stop as to be able to be replaced.

An actuator of an aircraft includes at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20). Each destructible portion of each destructible bearing surface is mounted to be removable with respect to the stop as to be able to be replaced.