Abstract: A solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cross sectional flow area. Controlling the effective cross sectional flow area of the nozzle throat in turn controls combustion chamber pressure, thus the burn rate of the propellant in the combustion chamber, and thus the thrust generated thereby.

Abstract: The feeder passages (22) in the aircap (20) of an air spray gun (10) arc slots which are significantly wider than the horn exit holes (24). This construction makes centerline offset much more forgiving by providing a consistent intersection of the passages. The feeder passages (22) are also deeper in that they extent past the intersection point (26) again making them more forgiving of irregularities. Sealing and seating of the nozzle (18) to the fluid inlet (16) have also been improved over the prior art. In the instant invention, o-rings (28) seal the nozzle (18) to the fluid inlet (16) and allow the shoulder (18b) of the nozzle (18) to seat squarely on the spray housing (14) controlling angularity.

Abstract: A retractable thrust vector control system (10) for a rocket motor (26) that can generate an exhaust plume comprises at least one control vane (12) connectable to an attitude control assembly (20) that rotates the vane (12) about a control axis (44). The system also includes a retraction mechanism (14) for withdrawing the control vane (12) along the control axis (44) from an extended position at least partially within a path of a rocket exhaust plume and a retracted position substantially out of a path of a rocket exhaust plume.

Abstract: A shroud for an aircraft engine exhaust plume, the shroud being formed of a flexible material secured at one end to the exhaust nozzle and selectively extendable downstream with the exhaust plume so as to surround and shroud it, thereby to reduce infrared/radar/noise emissions from the aircraft engine.

Abstract: A method and device for adding special substances to the gaseous outflow of the jet engine in order to create a “virtual wall” of increased pressure zone behind the jet engine nozzle which can serve as a support for the jet engine gas outflow to push against, thus increasing the thrust power of the jet engine. This increase in acceleration power results in the accelerated movement of the jet engine equipped vehicle or higher fuel efficiency. A device that adds the special substances to the gaseous outflow is proposed. Characteristics of the special substances, which if added into the jet engine gaseous outflow may create a “virtual wall” of increased pressure zone behind the jet engine, are proposed.

Abstract: A cowl for a turbomachine nozzle, the cowl having a plurality of repeated patterns disposed circumferentially at a trailing edge, each pattern being asymmetrical about a midplane of the pattern containing a longitudinal axis of the cowl, and each pattern having a first portion inclined radially towards the inside of the cowl and a second portion inclined radially towards the outside of the cowl.

Abstract: A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled vehicle, including aircraft and watercraft.

Abstract: A device for controlling fluid flow. The device includes an arc generator coupled to electrodes. The electrodes are placed adjacent a fluid flowpath such that upon being energized by the arc generator, an arc filament plasma adjacent the electrodes is formed. In turn, this plasma forms a localized high temperature, high pressure perturbation in the adjacent fluid flowpath. The perturbations can be arranged to produce vortices, such as streamwise vortices, in the flowing fluid to control mixing and noise in such flows. The electrodes can further be arranged within a conduit configured to contain the flowing fluid such that when energized in a particular frequency and sequence, can excite flow instabilities in the flowing fluid. The placement of the electrodes is such that they are unobtrusive relative to the fluid flowpath being controlled.

Abstract: A device for reducing the jet noise of a turbomachine, the turbomachine having a longitudinal axis and a substantially cylindrical nozzle extending along the longitudinal axis of the turbomachine, having a downstream end for mixing the flows of gas inside and outside the nozzle, the device comprising a plurality of corrugations disposed to extend the downstream end of the nozzle, and a plurality of notches disposed between pairs of successive corrugations in the plurality of corrugations, and the plurality of corrugations and the plurality of notches are symmetrical relative to at least one axis perpendicular to the longitudinal axis of the turbomachine so as to generate a dual counter-rotating effect between the gas flows.

Abstract: The present invention is directed to a device for splitting a propelled aerosol cloud. The device utilizes a curved spray chamber and a thermal technique to divert any desired portion of the aerosol to waste. The remainder of the aerosol is made available to an ELSD or similar instrument for analysis.

Abstract: A turbine engine exhaust diffuser assembly having a tuneable exhaust velocity profile is disclosed. The assembly includes structure that generates a desired, tunable velocity profile within working fluid exiting the exhaust diffuser assembly. The exhaust assembly includes an concentric boundary sleeves that extend along a central axis and form an exhaust flowpath between them. A flow deflecting member disposed within the flowpath longitudinally divides the flowpath into a first region and a second region. The first region is characterized by a first predetermined velocity profile, and the second region is characterized by a second predetermined velocity profile. The second velocity profile is determined by at least one pre-selected dimension of the flow deflecting member. Methods of maximizing HRSG energy extraction capacity and extending HRSG lifespan are also disclosed.

Abstract: A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled vehicle, including aircraft and watercraft.

Abstract: A turbine engine nozzle assembly has an upstream flap and a downstream flap pivotally coupled thereto for relative rotation about a hinge axis. An actuator linkage is coupled to the downstream flap along a forward portion thereof for actuating the upstream flaps and downstream flaps between a number of throat area conditions while permitting mode changes.

Abstract: An injection lance for injecting a fluid over a predefined target area within a system includes a support block with an inlet side and an outlet side. A plurality of channels are disposed non-parallel with respect to each other within the support block and extend between the inlet and outlet sides of the support block so as to receive fluid at the inlet side and deliver fluid through the support block for injection from the outlet side of the support block over the target area. At least two channels extend from the inlet side toward the outlet side in a direction away from a central axis of the support block, where the central axis intersects the outlet side. The target area includes a plurality of consecutively aligned sectors, and the channels are oriented within the support block so that a central axis of a fluid stream injected from each channel over the target area is centered between longitudinal boundaries defined by a respective sector.

Abstract: An exhaust nozzle assembly for a gas turbine engine, the assembly comprises a main axis, an inner nozzle, an outer nozzle, a translatable centre-body and an actuator for translating the centre-body between a forward position and a rearward position. The centre-body is disposed radially inwardly of the inner nozzle thereby partly defining an inner duct for a core engine gas flow, an outer duct for a bypass gas flow is defined by the inner nozzle and the outer nozzle. The outer nozzle extends downstream of the inner nozzle and with the centre-body defines a final mixing duct having a final exhaust exit area. When the centre-body is in the forward position the final exhaust exit area is at a maximum area, and when the centre-body is in a rearward position the final exhaust exit area is at a minimum area.

Abstract: A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an internal wall of the jet engine including a divergent trailing edge on the wall that generates conditions of a separation of the primary jet close to an existence limit value and a primary jet controller that enables control of passage of the primary jet from a separated state to a reattached state, and vice versa.

Abstract: An apparatus for reducing gas turbine engine noise, such as noise generated by an aircraft gas turbine engine, comprises at least one and preferably a plurality of gas injectors for injecting gas such as high pressure engine bleed air, diverted core air, air obtained from a pressurized storage container or air obtained from a synthetic jet actuator into the area proximate to one or more engine nozzle portions, thereby disrupting the noise-generating gas streams generated by the engine exhaust and the travel of the airplane through the air. The apparatus is particularly useful for reducing engine noise during the takeoff period of aircraft flight.

Abstract: A thrust vector control system for a plug nozzle rocket engine for propelling and maneuvering a vehicle is disclosed. The plug nozzle rocket engine includes a housing having a nozzle throat, a plug disposed within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat, and a thrust diverter moveably disposed relative to the housing to define an asymmetric pressure distribution along the plug for thrust-vectoring. In one embodiment, the thrust diverter is normally biased to a non-thrust-vectoring position, but is moveable in a plane substantially perpendicular to an axis extending longitudinally through the plug.

Abstract: A thrust control valve includes a nozzle having a gas supply chamber, a gas jetting chamber and a connecting passage therebetween. The nozzle has an upstream inner surface defining the gas supply chamber and a downstream inner surface defining the gas jetting chamber. The valve also includes a plug axially movably inserted into the gas supply chamber, the connecting passage and the gas jetting chamber. The plug has an upstream outer surface facing the upstream inner surface to define an upstream passage and a downstream outer surface facing the downstream inner surface to define a downstream passage. The plug can control thrust by simultaneously changing sectional areas of the upstream and downstream passages by an axial movement of the plug.

Abstract: A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust.

Abstract: A target type thrust reverser is provided for reversing the thrust of jet engines, particularly on aircraft. The thrust reverser preferably has a plurality of doors that occupy a stowed position about the nozzle of the jet engine until deployed. In the stowed position, the doors are out of the exhaust stream of the jet engine. The doors are mounted to pivot joints on the rear portions of the doors. To deploy the thrust reverser, actuators connected to the pivot joints cause the pivot joints to translate linearly aft, and link rods attached to the forward portions of the doors cause the doors to pivot about the sliding pivot joints. In this manner, the distance between the doors and the engine exhaust nozzle is minimized during deployment, which enables significant weight savings due to reduced loads and fewer parts. A novel lock is also provided for simultaneously locking the thrust reverser doors and the actuators.

Abstract: A nozzle includes a sideways split and aftwardly swept nozzle ramp extends between a fixed lower nozzle wall and a pivotal upper nozzle wall pivotally connected to an aft end of the nozzle and operable to vary a throat area of a throat of the nozzle. The upper and lower nozzle walls and the ramp extend transversely between first and second nozzle sidewalls. A sideways pivotable ramp structure pivotally connected to the lower nozzle wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls. Right hand and left hand upper ramp sections of the nozzle ramp may be connected to right hand and left hand upper nozzle wall sections respectively of the upper nozzle wall which are pivotally connected to right and left handed triangular side walls of the aft end.

Abstract: An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member positioned intermediate adjacent ones of the flaps. The bridge member includes a bridge bracket and a sealing element joined to the bridge bracket. The sealing element has an upper surface. The bridge bracket has a lower surface which diverges from the upper surface of the sealing element. In a preferred embodiment of the present invention, the bridge bracket has a shape which allows variable slot size depending on nozzle throat jet area.

Abstract: An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for controlling exhaust flow discharged therethrough. An arcuate unison bar surrounds the duct adjacent to the frame and includes circumferentially spaced apart cam followers engaging corresponding cams affixed to the flaps. An actuator is joined to the bar for selective rotation thereof between opposite first and second directions to pivot open and closed the flaps atop the apertures.

Abstract: Disclosed is a means for reducing jet engine exhaust noise wherein mixing is enhanced between adjacent exhaust flows and between exhaust flow and free-stream flow. Also disclosed is a means for improving the thrust of jet engines and for reducing the noise and drag of aircraft. The device is a segmented, triangular or trapezoidal shaped, curved extension to a nozzle's sleeve or surface trailing edge that results in a serrated trailing edge. The extensions enhance the natural free mixing of the adjacent flows and therefore reduce the acoustic energy associated with the velocity differences between the streams in which they are imbedded. The novel structure forces adjacent flows to penetrate into one another to a greater depth than that achieved with free mixing and results in a more uniform flow in a shorter stream wise distance. As a result of the enhanced mixing, drag on flow surfaces that are downstream of the devices and are scrubbed by the flows adjacent to the devices can be reduced.

Abstract: A vectorable nozzle includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls. The upper and lower fixed walls and the fixed ramp extend transversely between first and second fixed sidewalls. An outer nozzle wall is spaced apart from the upper and lower fixed walls and extends transversely between first and second fixed sidewalls. A nozzle flowpath is defined between the upper and lower fixed walls and the outer nozzle wall and the first and second fixed sidewalls. A sideways pivotable ramp structure pivotally connected to the lower fixed wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls.

Abstract: A nozzle system includes a multiple of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of a gas path. Each divergent flap includes a multiple of cooling channels with respective intakes and outlets. As the nozzle transitions between positions, the divergent flap seals move relative a divergent flap longitudinal axis to modulate the cooling airflow which enters the separate intakes.

Abstract: A second stage external jet nozzle mixer (20) includes identically formed lobes which equal in number the lobes of the first stage internal mixer. The external mixer works with the internal mixer, and furthers the mixing of the jet engine internal bypass flow with the internal jet engine core flow. This mixing levels the disparate flow velocities attendant with the jet engine exhaust, reduces the peak velocities from the jet engine core and increases the lower bypass velocities of the jet engine internal bypass flow. The lobes include complex curvatures that greatly enhance mixing of the gases and ambient cooling air, and thereby reduce noise. At the lobe terminus, the lobe dimensional characteristics may be adjusted to thereby adjust the total terminus area to achieve a match to a jet engine to cause that jet engine to run at a determined RPM and noise level. Noise attenuation may also be adjusted by changing lobe dimensions.

Abstract: In a variable-section turbomachine nozzle, a plurality of flexible follower flaps are provided that are interposed between adjacent controlled flaps against which the follower flaps are held by fastener means, each follower flap comprising a plurality of independent transverse boxes mounted side by side in a support sheet, the boxes contacting one another via their longitudinal edges and being held in the support sheet via their lateral edges which are engaged in the longitudinal edges of the support sheet, which longitudinal edges define respective bearing zones for bearing against the adjacent controlled flaps.

Abstract: In a fluid pump and cartridge assembly, a cartridge includes a material inlet port, a material outlet port, and a feed screw. The feed screw delivers fluid to be dispensed from the fluid inlet to the outlet port. The fluid inlet is preferably elongated in a direction along a longitudinal axis of the feed screw to enhance consistency in material flow through the cartridge. The feed screw is preferably driven by a closed-loop servo motor to achieve high-performance dispensing resolution. The assembly is preferably compatible with fixed-z and floating-z cartridges. A optional vented dispense tip, in combination with the fluid pump, allows for repeatable deposit of fillet patterns while maintaining optimal consistency. A dispense controller allows for reverse-compatibility such that the fluid pump of the present invention can be mounted to, and controlled by, conventional pump position controllers.

Abstract: An infrared signature suppression system for reducing infrared radiation emitted by a vehicle. The system includes an elongate duct mounted on the vehicle having a hollow interior extending along an axial centerline between an upstream end and a downstream end for transporting exhaust gas emitted by the vehicle, and a baffle positioned in the hollow interior of the duct between the upstream end and the downstream end. At least a portion of at least one of the duct and the baffle includes an emissivity coating for reducing infrared radiation emitted by the vehicle.

Abstract: While commercial jet aircraft are capable of transporting large pay load economically, the same is not true for rockets. To solve this problem, a hybrid propulsion system is proposed for use in Horizontal Take-Off and Land (HOTOL) craft. The purpose is to maximized the use of ambient oxygen and minimize the use of cryogenic oxygen. At the core of the system is a jet engine whose after burner is modified to act as an evaporator. Liquid oxygen is pumped in, vaporized and ducted forward to the air intake through a gate. The gate is designed to control the mix of ambient oxygen and cryogenic oxygen going into the engine. It is also used as a hear shield to protect the engine from reentry temperatures.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, and coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine. In addition, the method also comprises coupling an infrared suppression system in flow communication with the engine exhaust nozzle for channeling exhaust gases discharged from said exhaust nozzle to facilitate suppressing an exhaust infrared signature of the core engine during operation, wherein the infrared suppression system includes an access door and a flow channel that is coupled to the access door such that the flow channel is movable with the access door from a closed position to an open position.

Abstract: A nozzle of a dishwasher reduces a space for installing a supplementary nozzle on a main nozzle by having first and second connectors coupled to be caught on each other between main and auxiliary nozzles. The nozzle assembly includes a main nozzle having a first coupling hole; an auxiliary nozzle, having a second coupling hole, for coupling with the main nozzle; a first interlocking device, having a first end, for coupling with the main nozzle at the first coupling hole, by being caught in the first coupling hole by the first end; and a second interlocking device, having a first end, for coupling with the auxiliary nozzle at the second coupling hole, by being caught in the second coupling hole by the first end and by having a second end to be caught on the first interlocking device.

Abstract: Force balance and moment balance associated with thrust of air and water craft equipped with thrust generators are preset in view of non-linear characteristics and dynamic characteristics of thrust generators. A performance index for minimizing thrusts generated by the thrust generators is defined. Using the balance as restricting condition, propeller thrusts of the thrust generators and rudder angles and changing speeds of rudders that minimize the performance index are calculated.

Abstract: A lock assembly for a thrust reverser system that prevents thrust reverser deployment when the thrust reversers are in the stowed position, but does not prevent thrust reverser movement, in either the deploy or stow directions, when the thrust reversers are out of the stowed position and the lock assembly is in the locked position.

Abstract: A thrust reverser for a jet engine of a mobile platform. The thrust reverser includes a hinge beam defining a first track and a latch beam defining a second track. The thrust reverser also includes at least one cascade support ring having an upper end portion and a lower end portion. A first fitting is disposed at the upper end portion of the cascade support ring. The first fitting includes an engagement portion slidably positioned within the first track. A second fitting is disposed at the lower end portion of the cascade support ring. The second fitting includes an engagement portion slidably positioned within the second track.

Abstract: A vectorable variable area nozzle is formed by a pair of parallel sidewalls, a pair of opposed clamshell elements arranged between the sidewalls and each able to rotate about an axis perpendicular to the sidewalls and a pair of flaps each pivotally lined to the downstream end of one of the clamshell elements. In use the thrust produced by the nozzle can be vectored by rotating the two clamshells about their respective axes.

Abstract: An aircraft having a propulsive power unit supported in a fuselage mounted configuration and including an engine and a nacelle structure housing the engine. The nacelle structure is provided with upper and lower displaceable nacelle portions, such as thrust reverser cowls and fan cowl doors which are displaceable between closed dispositions which they occupy during operational conditions of the aircraft and open dispositions which they take up to provide access to engine components. The upper and lower nacelle portions are so mounted as to be displaceable to their open and closed dispositions in movements in which one is assisted by gravitational force and the other is displaced against gravitational force. A force transfer mechanism is provided for transfer during opening and closing movements of the nacelle portions of gravitational force assisting displacement of one of the nacelle portions to assist in displacement of the other nacelle portion being displaced against gravitational force.

Abstract: An external jet nozzle mixer (20) includes identically formed lobes (48), equal in number those of the internal mixer (42). External mixer (20) works with internal mixer (42), further to mix the engine internal bypass flow with the internal jet engine core flow, to level the disparate exhaust flow velocities, to reduce the peak velocities from the jet engine core and increase the lower bypass velocities of the engine internal bypass flow, and thereby to reduce noise. The internal lobe contours act as lifting flutes, causing mixing of the primary hot and cold flows before exiting the nozzle. The external lobe contours act as venturi chutes, accelerating the cooler ambient air secondary flow. The lobes thus act collectively as an injector to force the cooler ambient secondary flow into the previously mixed primary flow as it exits the nozzle. Also obtained is an increased thrust efficiency and a consequently decreased fuel consumption and engine emissions.

Abstract: A target type thrust reverser is provided for reversing the thrust of jet engines, particularly on aircraft. The thrust reverser preferably has a plurality of doors that occupy a stowed position about the nozzle of the jet engine until deployed. In the stowed position, the doors are out of the exhaust stream of the jet engine. The doors are mounted to pivot joints on the rear portions of the doors. To deploy the thrust reverser, actuators connected to the pivot joints cause the pivot joints to translate linearly aft, and link rods attached to the forward portions of the doors cause the doors to pivot about the sliding pivot joints. In this manner, the distance between the doors and the engine exhaust nozzle is minimized during deployment, which enables significant weight savings due to reduced loads and fewer parts. A novel lock is also provided for simultaneously locking the thrust reverser doors and the actuators.

Abstract: A thrust reverser for a jet engine of a mobile platform. The thrust reverser includes a hinge beam defining a first track and a latch beam defining a second track. The thrust reverser also includes at least one cascade support ring having an upper end portion and a lower end portion. A first fitting is disposed at the upper end portion of the cascade support ring. The first fitting includes an engagement portion slidably positioned within the first track. A second fitting is disposed at the lower end portion of the cascade support ring. The second fitting includes an engagement portion slidably positioned within the second track.

Abstract: A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an internal wall of the jet engine including a divergent trailing edge on the wall that generates conditions of a separation of the primary jet close to an existence limit value and a primary jet controller that enables control of passage of the primary jet from a separated state to a reattached state, and vice versa.

Abstract: A thrust reverser system that includes one or more power drive units operable to supply a drive force. The power drive unit includes a motor and at least two output sections, each operably coupled to transmit the drive force to the thrust reverser movable components. Each of the output sections is operable to decouple the motor from associated thrust reverser movable components upon a torque magnitude being reached in the output section. A deadband coupler is provided to couple the first and second output sections together a time period after the torque magnitude is reached in one of the output sections.

Abstract: A method for assembling a flap system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates extending a useful life of the exhaust nozzle. The method includes providing a flap basesheet having a width defined between a pair of side edges that are coupled together by a leading edge and a trailing edge, and including at least one stiffener that extends between the basesheet side edges and includes an intermediate portion that has a width that is smaller than that of the basesheet and is at least one of bonded to and formed integrally with the basesheet, and coupling the basesheet to the gas turbine engine with a backbone assembly.

Abstract: A pneumatic inhaler that is able to deliver a controlled burst or dose of aerosol from a reservoir of liquid medication. The inhaler is suitable for the aerosolization of liquid medication that is in solution or suspension form. The inhaler is also ideal for the delivery of unique and specialty liquid medications in short aerosol bursts because no additional formulation development is needed and has the further advantage of being able to deliver multiple medications, as mixed by the patient, doctor, or pharmacist, with a single burst at a repeatable output. Because medication and propellant are not mixed until aerosolization occurs, the inhaler is appropriate for more pharmaceutical agents than the current inhalers available and at a substantial cost savings.

Abstract: An exhaust flow nozzle for a jet engine having a plurality of flow altering components extending from a lip portion of a secondary exhaust nozzle that are movable between first and second positions. In the first position the flow altering components are disposed substantially parallel to an exhaust gas flow path and thereby do not produce drag or a reduction of thrust from the engine. In the second position the flow altering components bend or are deformed to project into the exhaust gas flow path exiting from the secondary exhaust nozzle. The flow altering components are comprised of a shape-memory alloy material which deforms in response to heat. One or more additional layers of material are bonded or otherwise coupled to the shape-memory alloy layer of each flow altering component to assist in returning the shape-memory alloy layer to its unheated shape.

Abstract: A nozzle where the sector into which noise reduction is sought (the direction of populated areas) has a moving lip, driven by actuators in an oscillatory, periodic or sinusoidal motion, around the mid position, to and from the axis, so as to cause the shear layer to become more irregular and turbulent, thus enhancing scattering effects on the sound of internal sources, including back reflection into the jet, widening the directivity pattern and spreading the acoustic energy into a broader spectrum, so as to reduce the acoustic energy transmitted in these sensitive directions; the nozzle lip may also be corrugated, undulated or have vortex generators, in the sector over which noise reduction is sought. In all other sectors, for which noise radiation is of no concern, even if enhanced, the nozzle lip is smooth and fixed, leading to a thin shear layer, across which sound is more easily, so that acoustic energy exits from the jet in these harmless directions.

Abstract: A backup locking system for a thrust reverser door comprises a catch pivotally mounted by a pivot pin to a fixed structure of the thrust reverser. A hook with a self-locking profile is provided at the free end of said catch for cooperation with a locking interface on the door in the event of failure of the normal locking systems. At its other end remote from said hook, the catch has a heel ending in a part-cylindrical surface which is concentric with said pivot pin. The catch is urged against the locking interface by a piston rod which presses against a front face of said heel under the force of a spring acting on a piston to which said piston rod is attached. When the rod is retracted, a double lever positively moves the catch toward a minimum opening angle, at which point the door can be opened. An unlocking spring causes the full opening of the catch to maximum open position when an opening lever is released.

Abstract: Force balance and moment balance associated with thrust of air and water craft equipped with thrust generators are preset in view of non-linear characteristics and dynamic characteristics of thrust generators. A performance index for minimizing thrusts generated by the thrust generators is defined. Using the balance as restricting condition, propeller thrusts of the thrust generators and rudder angles and changing speeds of rudders that minimize the performance index are calculated.