The subject matter described herein relates to aircraft designs and more particularly to aircraft designs using tandem wings and a distributed propulsion system. The embodiments described enable synergies between aerodynamics, propulsion, structure, and stability/control. In one embodiment, the tandem wings include a first wing set and a second wing set, each having a wing span with a set of thrustors placed along the wing spans.

The subject matter described herein relates to aircraft designs and more particularly to aircraft designs using tandem wings and a distributed propulsion system. The embodiments described enable synergies between aerodynamics, propulsion, structure, and stability/control. In one embodiment, the tandem wings include a first wing set and a second wing set, each having a wing span with a set of thrustors placed along the wing spans.

In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.

In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.

A method and apparatus for controlling an airflow. The method draws air through a group of inlets. The group of inlets is located in a group of locations on the vehicle such that the group of inlets actively controls the airflow relative to an aircraft when drawing the air. The method compresses the air drawn by the group of inlets in a group of air compressor units located in an aircraft structure to form pressurized air. Further, the method sends the pressurized air through a group of exit ports in the aircraft structure. The pressurized air flowing out of the group of exit ports actively controls the airflow for an aircraft, enabling an improved performance of the aircraft.

A method and apparatus for controlling an airflow. The method draws air through a group of inlets. The group of inlets is located in a group of locations on the vehicle such that the group of inlets actively controls the airflow relative to an aircraft when drawing the air. The method compresses the air drawn by the group of inlets in a group of air compressor units located in an aircraft structure to form pressurized air. Further, the method sends the pressurized air through a group of exit ports in the aircraft structure. The pressurized air flowing out of the group of exit ports actively controls the airflow for an aircraft, enabling an improved performance of the aircraft.

There is provided an aerodynamic control apparatus for an air vehicle comprising a flap system including a first spanwise flap segment to be arranged on a first side of an air vehicle, a second spanwise flap segment to be arranged on the first side of the air vehicle, and a controller to actuate the first spanwise flap segment to a first flap deflection and the second spanwise flap segment to a second flap deflection, wherein the first spanwise flap segment at the first flap deflection and the second spanwise flap segment at the second flap deflection form a piecewise continuous trailing edge.

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 F/X as the first flight control surface is displaced, where F 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 X is a difference in position X2X1; and achieving full contact between the first trailing edge and the second leading edge when a known full contact mechanical stiffness is reached.

The present set of embodiments relate to systems, methods, and apparatuses for airfoil systems designed for aircraft or other craft. More specifically, the present disclosure includes various embodiments of airfoils that include fixed or adjustable louvers that allow the airfoil to adapt to various conditions including angle or attack and airspeed. Such airfoil systems increase the dynamic range or airfoils by maximizing lift or minimizing drag depending on the conditional requirements.

The present set of embodiments relate to systems, methods, and apparatuses for airfoil systems designed for aircraft or other craft. More specifically, the present disclosure includes various embodiments of airfoils that include fixed or adjustable louvers that allow the airfoil to adapt to various conditions including angle or attack and airspeed. Such airfoil systems increase the dynamic range or airfoils by maximizing lift or minimizing drag depending on the conditional requirements.