A propulsion device includes a propulsion body and a diversion assembly. The propulsion body includes a propulsion system and a housing accommodating the propulsion system. The housing has an air-intake opening and an air-discharge opening respectively on two opposite sides of the propulsion system. The diversion assembly includes first and second diversion annular sheets. The first diversion annular sheet is disposed outside the air-discharge opening of the housing and having a surrounding center. The first diversion annular sheet is swung relative to the air discharge opening by a first axis passing through the surrounding center. The second diversion annular sheet is disposed outside the air-discharge opening of the housing and concentrically disposed with the first diversion annular sheet. The second diversion annular sheet is swung relative to the air-discharge opening by a second axis passing through the surrounding center, and first axis intersects the second axis.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A vertical take-off and landing aircraft is provided. The aircraft comprises a fuselage which has a nose end, a tail end, and a plurality of seats disposed in the interior. A pair of rear wings extend outwardly from opposing sides of the fuselage between a cockpit and the tail end, and a pair of front wings extend outwardly from opposing sides of the fuselage between the cockpit and the nose end. Each of the pair of rear wings and front wings includes an adjustably mounted turbine which comprises a statically mounted fan pod, a duct rotatably connected to the fan pod, and an adjustable nozzle rotatably connected to the duct. The nozzle can be adjusted to a variety of configurations ranging between a vertical position and a horizontal position via the duct. The adjustably mounted turbine enables the aircraft to adjust thrust through vectors ranging between horizontal and vertical.

A vehicle includes a main body and at least one wing coupled to the main body. A source of compressed fluid is coupled to the main body. The vehicle further includes first and second thrusters, each said first and second thruster having an intake structure and each said first and second thruster in fluid communication with the source. The first thruster is coupled to the main body and the second thruster is coupled to the at least one wing. The first and second thrusters are positioned, when in a first configuration, such that at least a portion of a boundary layer produced due to motion of the vehicle is ingested by the intake structures of the first and second thrusters. The vehicle further includes a system for selectively providing the compressed fluid to the first and second thrusters.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

Rotating detonation engines are provided with various improvements pertaining to performance and reliability. Improvements pertain to, for example, a fluidic valve/premixing chamber, injection/swirl, flow control and turning, ignition, and cooling.

A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.