A wing apparatus and aircraft are described providing greater maneuverability and efficiency for vertical takeoff and landing vehicles. Use of a fowler flap is shown in combination with a sliding panel. The sliding panel can nest within a wing similar to a fowler flap. During vertical maneuvers the sliding panel can be moved forward and on top of the wing. This can alleviate download during vertical maneuvers while minimizing drag as forward flight begins.

A wing apparatus and aircraft are described providing greater maneuverability and efficiency for vertical takeoff and landing vehicles. Use of a fowler flap is shown in combination with a sliding panel. The sliding panel can nest within a wing similar to a fowler flap. During vertical maneuvers the sliding panel can be moved forward and on top of the wing. This can alleviate download during vertical maneuvers while minimizing drag as forward flight begins.

A wing system includes an aerodynamic wing structure which is stowable. The wing structure which can be rolled up and/or folded, including at least one pressure-tight tubular pressure chamber which is made of a flexible material and extends preferably along the wingspan of the wing structure. A tear-resistant outer skin fabric encases the wing structure. The pressure chamber of the wing structure can be filled with a fluid, and the wing system includes a high-pressure pump system. The fluid is kept in the pressure chamber under high pressure, such as over 50 bar, over 100 bar, or over 150 bar. A transport device is for use as an aircraft for traveling in the air and as a vehicle for traveling on land. The transport device includes the wing system, with the wing system being attached preferably to the upper face of the transport device.

A wing system includes an aerodynamic wing structure which is stowable. The wing structure which can be rolled up and/or folded, including at least one pressure-tight tubular pressure chamber which is made of a flexible material and extends preferably along the wingspan of the wing structure. A tear-resistant outer skin fabric encases the wing structure. The pressure chamber of the wing structure can be filled with a fluid, and the wing system includes a high-pressure pump system. The fluid is kept in the pressure chamber under high pressure, such as over 50 bar, over 100 bar, or over 150 bar. A transport device is for use as an aircraft for traveling in the air and as a vehicle for traveling on land. The transport device includes the wing system, with the wing system being attached preferably to the upper face of the transport device.

A system and a method include a flight control surface, an actuator configured to control motion of the flight control surface, and a brake configured to engage at least a portion of the flight control surface in response to the flight control surface disengaging from the actuator. The brake arrests unrestrained motion of the flight control surface when the brake engages the at least a portion of the flight control surface.

Methods, systems, and assemblies for controlling flight control surfaces of an aircraft wing are described. The method comprises displacing a first trailing edge of a first flight control surface towards a contact surface of a second flight control surface; determining a mechanical stiffness of the first flight control surface as defined by a ratio of ΔF/ΔX as the first flight control surface is displaced, where ΔF is a difference in force F applied to at least two different positions X1 and X2 of the first flight control surface at times T1 and T2, and ΔX is a difference in position X2−X1; and achieving full contact between the first trailing edge and the second leading edge when a known full contact mechanical stiffness is reached.

A multirotor drone comprises a main body and an air channel embedded within the main body having an air inlet on the surface of the main body, multiple propellers that induce an air flow toward the air inlet and into the air channel, a microcontroller positioned and configured to control navigation of the drone by actuation of the plurality of propellers, an air scoop having a section positioned at the outer surface of the main body adjacent to the air inlet which is adjustable so as to capture and divert air into the air inlet and air channel or to block air flow into the air inlet, and a gas sensor positioned within the air channel. The air scoop is positioned to capture air flow from at least one of the plurality of propellers into the air channel and to the gas sensor.

An aerodynamic aircraft component includes a fixed aerodynamic part, which has a first contact surface, and a movable aerodynamic part, which has a second contact surface and is mounted to the fixed aerodynamic part for movement relative to the fixed aerodynamic part between a first position, in which the first and second contact surfaces are spaced apart, and a second position, in which the second contact surface contacts the first contact surface. The fixed aerodynamic part includes one of a magnet device and a piece of magnetic material and the movable aerodynamic part includes the other of the magnet device and the piece of magnetic material. The magnet device and the piece of magnetic material are arranged such that a magnetic force between the magnet device and the piece of magnetic material urges the second contact surface in contact with the first contact surface.

Methods, apparatus, systems and articles of manufacture are disclosed for overheat prevention of anti-ice systems for aircraft. An example aircraft includes a wing, a slat movably coupled to the wing, the slat having a compartment to receive heated bleed air, the slat including a panel, an opening formed in the panel, a door in the opening of the panel of the slat, an edge of the door hingeably coupled to the panel, the door movable between a closed position and an open position, and a latch coupled to the panel, the latch to hold the door in the closed position, the latch constructed of a thermally sensitive material such that when a temperature inside of the compartment reaches a threshold temperature, the latch releases the door to enable the door to move to the open position to vent the heated bleed air from the compartment.

Methods, apparatus, systems and articles of manufacture are disclosed for overheat prevention of anti-ice systems for aircraft. An example aircraft includes a wing, a slat movably coupled to the wing, the slat having a compartment to receive heated bleed air, the slat including a panel, an opening formed in the panel, a door in the opening of the panel of the slat, an edge of the door hingeably coupled to the panel, the door movable between a closed position and an open position, and a latch coupled to the panel, the latch to hold the door in the closed position, the latch constructed of a thermally sensitive material such that when a temperature inside of the compartment reaches a threshold temperature, the latch releases the door to enable the door to move to the open position to vent the heated bleed air from the compartment.