A vertical take-off and landing aircraft that includes a fuselage which has a nose end, a tail end, and a plurality of seats disposed in an interior of the aircraft with vertical takeoff and conventional aircraft ability. 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 the pair of front wings includes an adjustably mounted turbine which includes a statically mounted fan pod, a duct rotatably connected to the fan pod, and an adjustable nozzle rotatably connected to the duct. The adjustable nozzle is adjusted to a variety of configurations ranging between a vertical position and a horizontal position via the duct.

A thrust vector controller includes an airflow guiding member, a connecting member, a first driving device, and a second driving device. The airflow guiding member is adjacent to an air exhaust opening. The airflow guiding member includes a main body, a first driving portion, a second driving portion, and a connecting portion. Airflow passes through the main body and is guided by the main body. The first driving portion, the second driving portion, and the connecting portion are connected to the main body. The connecting member is movably connected to the connecting portion and an exhaust propulsion device. The main body is movably connected to the exhaust propulsion device through the connecting portion and the connecting member. The first driving device is connected to the first driving portion and drives the first driving portion to move the airflow guiding member toward a first direction.

A system for enhancing the thrust produced by an aircraft propulsion element having a propulsion fluid outlet includes a shroud element having an inlet, an outlet and a diffusing section positioned between the shroud element inlet and shroud element outlet. The shroud element is coupled to the aircraft such that the diffusing section is positioned directly downstream of the propulsion fluid outlet. At least one actuator is operable to rotate the shroud element about a first transverse axis of the shroud element and a second transverse axis of the shroud element.

A nozzle having a movable diverging section, the nozzle including a stationary throat forming a ball joint and a diverging section having a top portion that is movably mounted around the throat; an annular lubrication chamber being interposed between the stationary throat and the top portion of the diverging section, the annular lubrication chamber containing a grease seal; an annular throttling element arranged between the stationary throat and the diverging section downstream from the annular lubrication chamber, the annular throttling element being made of refractory material; and an annular thermal protection element arranged between the stationary throat and the diverging section downstream from the annular lubrication chamber and upstream from the annular throttling element, the annular thermal protection element closing the lubrication chamber in its bottom portion.

A variable geometry exhaust nozzle arrangement includes a plurality of hingable exhaust petals defining a perimeter of an exhaust duct and an annular ring slidably engagable against a radially outer surface of each petal. The annular ring is coupled to a plurality of circumferentially spaced actuator arrangements, each including first and second circumferentially spaced parallel actuator arms pivotably coupled to the annular ring at a first end and to a slide arrangement at a second end. Each slide arrangement is mounted for linear sliding movement relative to the annular ring, such that sliding movement of each slide arrangement causes pivoting of the first and second actuator arms to thereby translate the annular ring in one or both of a longitudinal direction and a lateral direction.

A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.

A vertical take-off and landing aircraft that includes a fuselage which has a nose end, a tail end, and a plurality of seats disposed in an interior of the aircraft with vertical takeoff and conventional aircraft ability. 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 the pair of front wings includes an adjustably mounted turbine which includes a statically mounted fan pod, a duct rotatably connected to the fan pod, and an adjustable nozzle rotatably connected to the duct. The adjustable nozzle is adjusted to a variety of configurations ranging between a vertical position and a horizontal position via the duct.

An aircraft with at least one engine that generates a hot air flow in operation of the aircraft, wherein at least one hot air exhaust is provided for exhausting the generated hot air flow, the at least one hot air exhaust comprising at least one first exhaust section that is mounted in a rotatable manner to at least one second exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided that is adapted for applying a turning moment to the at least one second exhaust section in operation of the aircraft in order to displace a longitudinal axis of the at least one second exhaust section with respect to a longitudinal axis of the at least one first exhaust section by a predetermined displacement angle.

A variable area nozzle assembly includes a fixed nozzle structure, a translating sleeve, a plurality of nozzle segments, and a plurality of segment hoop locking assemblies. The translating sleeve is movably mounted to the fixed nozzle structure. The translating sleeve is translatable along the nozzle axis within the fixed nozzle structure between and to a first axial position and a second axial position. The plurality of nozzle segments form a variable area nozzle extending circumferentially about the nozzle axis. Each nozzle segment of the plurality of nozzle segments is pivotably mounted to the translating sleeve. The plurality of nozzle segments includes a first nozzle segment and a second nozzle segment. The plurality of segment hoop locking assemblies include a first segment hoop locking assembly. The first segment hoop locking assembly includes a hoop crank. With the translating sleeve in the first axial position or the second axial position, the hoop crank restricts circumferential movement of the first nozzle segment relative to the second nozzle segment.

A vertical take-off and landing aircraft that includes a fuselage which has a nose end, a tail end, and a plurality of seats disposed in an interior of the aircraft with vertical takeoff and conventional aircraft ability. 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 the pair of front wings includes an adjustably mounted turbine which includes a statically mounted fan pod, a duct rotatably connected to the fan pod, and an adjustable nozzle rotatably connected to the duct. The adjustable nozzle is adjusted to a variety of configurations ranging between a vertical position and a horizontal position via the duct.