Abstract: A flexible coupling mechanism may be used to suspend a structural component, such as a propulsion pod, from a support member, such as a strut of a hydrofoil watercraft. The flexible coupling mechanism may include multiple vibration isolating mounts configured to extend through the support member to suspend the structural component. The vibration isolating mounts may include a plurality of elastomeric bushings configured to prevent direct contact between a component rigidly coupled to the support member and a component rigidly coupled to the structural component. The elastomeric bushings may include a tapered outer profile configured to provide a nonlinear force feedback profile in response to rotation of the support member relative to the structural component.

Abstract: A rocket motor has a nozzle that is reconfigurable by erosion or ablation of the material around the throat of the nozzle. The nozzle throat has layers of materials with different erosion characteristics, with the erosion occurring so as to achieve the desired nozzle characteristics (configurations) during different parts of the fuel burn. The nozzle throat includes relatively-high-erosion material layers and relatively-low-erosion material layers, with some layers of the throat resisting erosion, while other of the layers erode or ablate relatively quickly. The relatively-low-erosion material layers may act as thermal barriers to fix the throat at relatively stable geometry for long periods of time, such as during most of the burn of different fuel segments, with the relatively-high-erosion material layers allowing rapid transition of the throat from one geometry to the next. The layers may be made by resin transfer molding (RTM).

Abstract: A thruster has an additively-manufactured housing that includes an integrally-formed nozzle with a burst disk in it. The housing is part of a casing that surrounds and encloses a propellant that is burned to produce pressurized gases that burst the burst disk and produce thrust. The thruster may be placed in a receptacle that defines a recess for receiving the thruster. The receptacle also may be additively manufactured. The thruster and the recess both may be cylindrical, with the housing being closely fit with the cylindrical walls of the receptacle. This may allow some of the structural loads on the housing, such as loads produced by the combustion of the propellant, to be transferred to the adjoining walls of the receptacle. This enables the housing to have less structural strength than if it were to have to contain the pressure from the propellant all on its own.

Abstract: A core compartment aft vent is disclosed. The core compartment aft vent may include a flexible core engine cowl surrounding a core engine case. A plurality of circumferentially spaced bumpers may be disposed within the aft vent and in operative contact with the flexible core engine cowl.

Abstract: An exhaust includes a wall that has a first composite material having a first coefficient of thermal expansion and a second composite material having a second coefficient of the thermal expansion that is less than the first coefficient of thermal expansion.

Abstract: A nozzle is provided that can be used as part of an aircraft engine. In one form the nozzle includes an inner cowl and an outer cowl. The inner cowl can be actuated to a variety of positions. The outer cowl is piggybacked on the inner cowl and is initially retained in first position relative to the inner cowl with an outer cowl actuator. The outer cowl actuator can be commanded to release the outer cowl so that the outer cowl can be moved to a second position relative to the inner cowl. In one form the outer cowl actuator is an explosive bolt and a spring is provided to urge the outer cowl to the second position.

Abstract: A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.

Abstract: An exhaust nozzle for a gas turbine engine according to an exemplary aspect of the present invention includes: an outer cowl; a cowl interface ring attached to the outer cowl; an acoustic nozzle; an acoustic nozzle interface ring attached to the acoustic nozzle, the acoustic nozzle interface ring attachable to the cowl interface ring; and a removable nozzle section attachable to the acoustic nozzle interface ring and the cowl interface ring.

Abstract: A cured ablative composite assembly comprises a housing enclosing a pair of ablative composite sub-assemblies joined by a film adhesive. The cured ablative composite assembly is made by surface treating both ablative composite sub-assemblies in preparation for joining; coupling one ablative composite sub-assembly to another ablative composite sub-assembly with a film adhesive and enclosing the uncured ablative composite assembly within a housing; and depositing the combination of the housing and uncured ablative composite assembly in a ventilated oven with a load applied to the combination housing and uncured ablative composite assembly. The film adhesive is cured providing a portion of a hot gas valve suitable for use in tactical missiles. The film adhesive does not erode at the high temperatures (5000° F.) encountered in hot gas rocket exhausts, thereby providing a seal that offers high strength, pressure-tight joints.

Abstract: An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the nozzle, thrust deflection then being achieved by swivelling the diverging portion so as to deflect the jet of combustion gas in contact with the inside wall of the diverging portion. The device includes a structure disposed inside the diverging portion in such a manner as to reduce the diverging nature of the flow section thereof and to increase the bearing area of pressure forces exerted by the jet on the diverging portion during swivelling thereof.

Abstract: A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material capable of maintaining structural integrity at a temperature up to about 5000° F. and is disposed at least partially in the throat section and has a flow path extending therethrough in fluid communication with the housing flow path. The throat retainer is constructed of material having insulating and ablative properties and is coupled between the housing and the insert and configured to retain the insert within the housing throat section.

Abstract: An afterburner includes an exhaust duct with a fixed area outer nozzle at an aft end thereof, and an ablative inner nozzle therein. The smaller inner nozzle is consumed during reheat operation to expose the larger outer nozzle for increased propulsion thrust.

Abstract: This disclosure relates to a method and an arrangement for preventing explosives such as rocket engines from exploding while subjected to an external fire in an ammunition bunker. The basic principle underlying the invention is that the casing surrounding the explosive includes a number of parts which are held together by mounting components made from a shape memory alloy, the properties of which are selected in such a manner that these mounting components no longer hold the various parts of the casing together if the surrounding temperature rises to approach the ignition temperature of the explosive in the rocket engine.

Abstract: The rocket motor nozzle assembly of this invention includes a throat insert and a carbon or silica protective eyelid. The throat insert has a carbon throat support and a refractory metal shell. The shell is positioned radially inside the throat support to cover the inner surface of the throat support. The protective eyelid covers a sufficient portion of the forward surface region of the shell and the underlying converging portion of the throat support to protect these components against particle impingement. The protective eyelid extends sufficiently far forward along the converging/diverging pathway to cover and protect the forward face or edge of the throat insert and prevent the combustion gases from passing under the throat insert and reaching the radially outer surfaces of the throat insert. However, the protective eyelid leaves the throat surface region of the shell exposed to the converging/diverging pathway.

Abstract: Methods and arrangements for tailoring rocket exhaust plume signatures of rocket exhaust systems are disclosed. The tailoring of the rocket exhaust plume signature is accomplished by providing and locating at least one structure having materials and/or additives that modify the radiant intensity pattern of the rocket exhaust plume upon ablation or melting into the rocket exhaust plume. The materials and/or additives can be manufactured or incorporated into preexisting ablative materials of the rocket exhaust system or be provided as stand-alone structures.

Abstract: A nozzle extension including flange elements of C/SiC is able to be manufactured relatively simply and provides sufficient physical properties. The carbon-fiber structure of the nozzle extension is wound, and a flange for fastening the nozzle extension to the nozzle outlet of the combustion chamber is integrated in the nozzle extension by a continuous fiber flow of the wound carbon-fiber structure. The foregoing may be intended for use in rocket propulsion units.

Abstract: A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable jet vane materials withstand the pressure and thermal loads associated with missile steering during the first few seconds of rocket boost until the missile attains sufficient speed to use conventional external aerodynamic control fins for steering control. Once control passes to the external fins, the jet vanes rapidly and uniformly dissolve in the exhaust stream. The dissolvable jet vane provides a lightweight, reliable means of removing steering jet vanes from the exhaust stream of a solid rocket motor nozzle.

Abstract: A method of making heat engine components, such as rocket nozzle throats, includes forming a body having at least one surface, wherein the body is made of a refractory metal, and compressing a ceramic powder between a die and the at least one surface of the body, with sufficient heat and pressure to densify and thus form a solid ceramic coating on the at least one surface of the body. Nozzle throats made according to the invention have bodies made of refractory metals, such as tantalum, and ceramic coatings on the inner surfaces of the annular bodies, wherein the ceramic coatings are made of ceramic materials such as tantalum carbides (TaC and Ta2C).

Abstract: A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible or retractable vanes inside of the nozzle. The vanes are removed from the rocket propelling thrust at rocket exit from the tube.

Abstract: To control the separation of a hot gas ejection jet within a rocket engine nozzle, the device comprises a jettisonable annular structure for placing around the outside wall of the nozzle at the gas outlet section thereof, which structure defines a radial extension around the nozzle so that in the presence of an outlet jet coming from the nozzle, it creates a low pressure zone in the vicinity of the bottom face of the device, thereby reducing jet separation inside the nozzle.