An assembly is provided for an aircraft. This aircraft assembly includes a powerplant. The powerplant includes a gas turbine engine, an exhaust nozzle and a flowpath extending from the gas turbine engine to the exhaust nozzle. The exhaust nozzle is movable between a first position and a second position. The exhaust nozzle is configured to exhaust combustion products, received through the flowpath from the gas turbine engine, when the exhaust nozzle is in the first position. The exhaust nozzle is configured to block flow of the combustion products through the flowpath when the exhaust nozzle is in the second position.

A servo valve for an actuator is described. The servo valve comprises a housing and a sleeve provided within the housing having a plurality of metering holes for communication with a cavity within. The servo valve further comprising a metering rod provided with metering members on a central rod for metering flow into and out of the cavity through the metering holes. The metering members comprise annular elements which are located axially on the central rod by an interference fit. The position of the metering members can be adjusted through using heat to thermally expand the metering member relative to the central rod to release the hold of the friction fit, allowing the metering member to be repositioned by being slid along the central rod.

A servo valve for an actuator is described. The servo valve comprises a housing and a sleeve provided within the housing having a plurality of metering holes for communication with a cavity within. The servo valve further comprising a metering rod provided with metering members on a central rod for metering flow into and out of the cavity through the metering holes. The metering members comprise annular elements which are located axially on the central rod by an interference fit. The position of the metering members can be adjusted through using heat to thermally expand the metering member relative to the central rod to release the hold of the friction fit, allowing the metering member to be repositioned by being slid along the central rod.

A method for manufacturing a composite material part provided with a measuring sensor, the method including assembly of a first consolidated or unconsolidated preform of the part to be obtained with a second preform of a holding member, co-densification of the first and second preforms thus assembled in order to obtain the composite material part provided with the holding member, and positioning of at least one sensor of a physical or chemical parameter in a housing defined by the holding member.

A method for manufacturing a composite material part provided with a measuring sensor, the method including assembly of a first consolidated or unconsolidated preform of the part to be obtained with a second preform of a holding member, co-densification of the first and second preforms thus assembled in order to obtain the composite material part provided with the holding member, and positioning of at least one sensor of a physical or chemical parameter in a housing defined by the holding member.

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.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A deflector ring includes a generally annular body, and a plurality of static straightening vanes arranged interior to the body, the vanes dividing the body into a plurality of substantially equal sections. The vanes are configured to straighten a swirling flow of solid particles as they enter the annular body, and to divide the swirling flow into a plurality of straightened flows that are communicated to a turret positionable above the deflector ring.

A deflector ring includes a generally annular body, and a plurality of static straightening vanes arranged interior to the body, the vanes dividing the body into a plurality of substantially equal sections. The vanes are configured to straighten a swirling flow of solid particles as they enter the annular body, and to divide the swirling flow into a plurality of straightened flows that are communicated to a turret positionable above the deflector ring.

The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.