The present invention provides a system of using compressed air as force source, comprising: compressed air jet engines, which use high/ultra-high pressure compressed air as a jet working medium, a compressed air production/supply device to economically, environmentally and quantitatively produce, store and supply the high/ultra-high pressure compressed air, and a controller. The compressed air jet engines are equipped on an airplane, rocket, submarine, train, or other moving carrier for aviation, aerospace, navigation and/or ground travel, comprising an air tank and air engines for generating power. The air engines comprise a main air engine for generating thrust, and a plurality of auxiliary air engines for reducing the air (or seawater) resistance and the sliding friction with air (or seawater) during the carrier movement to facilitate the speed-rising and energy-saving, and for improving the lift force of airplane wings to facilitate airplane short-range or vertical take-off/landing, etc.

A system and method for controlling boundary layer transition for a high-speed vehicle are disclosed. The method includes determining a location of onset of boundary-layer transition that naturally develops during high-speed flight of the high-speed vehicle, and providing a pair of flow control strips at a surface/wall/skin of the high-speed vehicle such that the boundary-layer transition is delayed or prevented during high-speed flight of the high-speed vehicle. The delayed or prevented locations of the transition result in a change in the high-speed boundary layer during the high-speed flight of the high-speed vehicle. The change in the high-speed boundary layer transition affects skin friction drag, aero-thermodynamic heating, and pressure fluctuations in the boundary layer of the high-speed vehicle.

A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit.

Systems and method for active control of stationary vortices for aerodynamic structures are disclosed herein. In one embodiment, a method for active control of vortices over a solid surface includes: generating vortices proximate to the solid surface; sensing locations of vortices by printed skin sensors; and maintaining the vortices in their fixed spanwise positions with respect to the solid surface by actuation of printed skin actuators.

An unmanned aerial vehicle according to the present invention may comprise: a rotor-blade for providing thrust according to generation of main stream; and a safety guard disposed to surround the rotor-blade. The safety guard may comprise: a guide member which is disposed coaxially with the rotor-blade while having a gap between the guard member and the end of the rotor-blade, so as to stabilize, when the rotor-blade rotates, a flow field suctioned by a negative pressure, and stably boost a discharge flow when the pressure is changed to a positive pressure; and a diffuser which is disposed coaxially with and radially spaced apart from the guide member, and generates a secondary flow toward the main stream to increase a flow rate.

An automated flying transport vehicle that capitalizes on the strengths and complexities of a fixed and rotary winged aircraft. The air transport vehicle comprises a body aerodynamically designed to generate lift and a plurality of rotors that can generate lift as well as forward thrust from which a fixed wing portion of the air transport vehicle will begin to generate additional lift allowing for a sustained flight.

In one embodiment, systems and methods include to fluid transfer hinge used to transfer fluid from one surface to another. The fluid transfer hinge comprises a first housing. The fluid transfer hinge further comprises a second housing, wherein the first housing is coupled to the second housing, wherein the first housing is rotatable about the second housing along a central axis of the fluid transfer hinge. The fluid transfer hinge further comprises a fluid inlet, wherein the fluid inlet is disposed about at least a portion of the thickness of the first housing. The fluid transfer hinge further comprises a fluid outlet, wherein the fluid outlet is disposed about at least a portion of the thickness of the second housing.

A device for a variable and adaptable diverterless bump engine inlet of an aircraft comprises a flexible inlet, a mechanism to change the shape of the flexible inlet, and a processing unit to control the mechanism. The flexible inlet of the device includes a plurality of edges attached partly to a fuselage skin and partly to an engine inlet duct. With this device, the shape of the flexible inlet can be controlled according to the flight conditions, and hence the engine air intake will perform more efficient at all speeds while fulfilling requirements for less radar visibility.

An aeroseal comprises a substantially straight portion having a first engagement end and a second engagement end opposite the first engagement end. The aeroseal also comprises a first engagement extension extending transversely from the first engagement end of the substantially straight portion and having a distal end. The aeroseal further comprises a second engagement extension extending transversely from the second engagement end of the substantially straight portion and having a distal end. The aeroseal also comprises a substantially curved portion interconnecting the distal end of the first engagement extension and the distal end of the second engagement extension to form an acute angle between the first and second engagement extensions and facing away from the substantially straight portion.

A plasma plate is used to minimize drag of a fluid flow over an exposed surface. The plasma plate includes a series of plasma actuators positioned on the surface. Each plasma actuator is made of a dielectric separating a first electrode exposed to a fluid flow and a second electrode separated from the fluid flow under the dielectric. A pulsed direct current power supply provides a first voltage to the first electrode and a second voltage to the second electrode. The series of plasma actuators is operably connected to a bus which distribute powers and is positioned to minimize flow disturbances. The plasma actuators are arranged into a series of linear rows such that a velocity component is imparted to the fluid flow.