The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles.

The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles.

A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

A system and method for controlling hypersonic boundary layer transition for a hypersonic flight vehicle are disclosed. The reduction or elimination of hot streaks that naturally occurs in the boundary layer transition process during hypersonic flight is achieved by utilizing various techniques. One such technique utilizes roughness elements to counteract streak development. The techniques for reducing or eliminating the streaks are tailored such that the nonlinear stages of transition are profoundly altered. This results in significant drag reduction, and consequently an increase in range of the vehicle, and also a reduction of the weight penalty due to the Thermal Protection Systems (TPS) as less protective material would be required, thus allowing for an increased payload and/or range of the vehicle.

A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators.

A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators.

A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.

An aircraft, an aircraft wing structure and a method are provided in order to address lift and drag, such as by increasing lift and reducing drag. In the context of an aircraft wing structure, the aircraft wing structure includes a wing extending outboard from a fuselage of an aircraft. The wing also extends from a leading edge to a trailing edge. The aircraft wing structure also includes one or more actuators carried by the wing and causing fluid to be directed through one or more respective orifices defined by the wing so as to alter flow over a lower surface of the wing. The one or more orifices that are defined by the wing are closer to the leading edge than to the trailing edge. Thus, the fluid introduced through the one or more orifices may increase lift and reduce drag of the associated aircraft.

A fixed wing drone comprises an air channel embedded therein. The air channel has an upstream an air inlet. A microcontroller mounted within the drone is configured to control navigation of the drone. An air scoop having a section positioned adjacent the inlet to the air channel is adjustable between a first position to capture and divert air into the inlet and thereby to air channel and a second position to block air flow into the air inlet. The air scoop is positioned to divert air flow into the air channel and to the gas sensor during forward flight of the drone. In one embodiment, the fixed wing drone comprises an aircraft having a fuselage and at least two wings. In another embodiment, the fixed wing drone has a flying wing construction, that is, is a tailless design.