Abstract: A system for measuring gamma-ray radial energy deposition is provided for use in conjunction with a semiconductor detector. The detector comprises two electrodes and a detector material, and defines a plurality of zones within the detecting material in parallel with the two electrodes. The detector produces a charge signal E(t) when a gamma-ray interacts with the detector. Digitizing means are provided for converting the charge signal E(t) into a digitized signal. A computational means receives the digitized signal and calculates in which of the plurality of zones the gamma-ray deposited energy when interacting with the detector. The computational means produces an output indicating the amount of energy deposited by the gamma-ray in each of the plurality of zones.

Abstract: A nozzle is adapted to receive an ultrasonic transducer. The nozzle includes a cylindrical plenum chamber. An annular passageway circumscribes the plenum chamber. A porous material forms the annular walls of the plenum chamber and separates the plenum chamber from the passageway. The plenum chamber fluidly communicates with the passageway through the porous material. The passageway fluidly communicates with a supply line that, in turn, fluidly communicates with a pump that supplies water. The plenum chamber has a circular exhaust orifice for the exhaust of water from the nozzle. The plenum chamber contains an unobstructed forming space to facilitate the forming of ultrasonic waves. The diameter of the plenum chamber divided by the diameter of the exhaust orifice is a quotient of at least three.

Abstract: A perforated sheet is diffusion bonded to a thin solid sheet. Each of the perforations of the perforated sheet is tapered, having a maximum diameter at the surface that is not bonded to the thin sheet and a smaller diameter at the surface that is bonded to the thin sheet. The bonded perforated sheet and thin sheet are included with other solid metallic sheets in a forming pack to be superplastically deformed into a structure. The bonded perforated sheet and thin sheet are placed on the top of the forming pack so that the thin sheet will face outwards after the structure is formed. After the superplastic deformation process is completed, the thin sheet is removed by machining to expose the perforated sheet and provide a structure for controlling laminar flow over the perforated sheet. The exposed surface of the perforated sheet includes the smaller diameter of each tapered perforation, while the inner-facing or blind surface of the sheet includes the maximum diameter.

Abstract: An aft facing step situated across the span of an airfoil. A chemical or thermal deicing or running wet anti-icing device is located in or on the airfoil upstream of the step, and causes water to run back towards the step. The step suddenly reduces the thickness of the airfoil chord section, which causes a disturbance in the boundary layer across the span of the airfoil downstream of the step. The aforementioned disturbance causes runback water to form droplets and be blown clear of the airfoil surface downstream of the step, thereby preventing ice from being formed on the airfoil surface downstream of the step.

Abstract: A forming die which includes a die cavity contains a forming blank composed of a metallic alloy having superplastic properties. The forming pressure in a pressurized space adjacent the forming blank is regulated by a pressure regulator. The volume of the die cavity is determined, as is the mass of gas initially contained in the die cavity at the beginning of the forming cycle. The total forming time is empirically determined. The average gas mass flow rate that will be exhausted from the die cavity is calculated by dividing the total mass of gas initially contained in the die cavity by the total forming time. A gas mass flow meter fluidly communicates with the die cavity and measures the mass flow rate of the gas displaced by the forming blank and exhausted from the die cavity. The gas mass flow meter is continuously monitored during the forming cycle or a gas mass flow rate signal is fed back to the pressure regulator.

Abstract: Two arms rotatably mounted in slideable abutment with an interior wall of a nozzle. The arms extend from a common axis of rotation, and each includes a bump having a crest running radially from the axis of rotation to the tip of the arm. Together with the opposing ceiling and adjacent sidewalls of the nozzle, the arms define the moveable throat of the nozzle. The ceiling of the nozzle opposite the arms is contoured so that rotation of the arms changes the area of the nozzle throat while changing the direction of fluid medium flowing through the nozzle. The arms are connected by a linkage which coordinates their movement. Coordinated rotation of the arms can simultaneously change the throat area of the nozzle and the direction of fluid flow, or change either the throat area or the direction of fluid flow while keeping the other constant.

Abstract: A plate projecting in an aft direction from the blunt trailing edge of a wing. The plate extends across the span of the trailing edge, and may be either planar or curved in the spanwise direction. The plate is canted to form an acute depression angle with respect to a collinear extension of the chord line of each chordwise cross section of the wing. The depression angle may vary across the span of the trailing edge. The height location of the plate relative to the trailing edge thickness may also vary in a spanwise direction. The length of the plate may be anywhere from 0.5 to 2.0 times the thickness of the trailing edge.

Abstract: A valve is comprised of two parallel passageways running transversely through a cylindrical valve shaft. Several valves are spaced axially in the valve shaft. The valve shaft axially rotates in the upper portion of an internal combustion engine. Each of the valves is positioned adjacent an engine cylinder. Rotation of the valve shaft causes the passageways to allow fluid communication between an engine cylinder and, alternatively, intake and exhaust ports, thereby performing the valving function for that engine cylinder. Two parallel valve shafts are used so that each cylinder is serviced by two valves. The parallel valve shafts and the engine crankshaft are connected to a timing chain assembly which coordinates the rotation of the valves with the translational motion of the engine pistons. A retractable throttle valve is located in the intake port for each valve and controls the amount of the fuel and air mixture flowing through the valve and into the engine cylinder being serviced by that valve.

Abstract: An apparatus and method for controlling the superplastic forming process by measuring and controlling the gas mass flow rate of the gas displacing the blank being formed.

Abstract: An aerodynamic fairing seal for use on a variable incident airfoil which protrudes through a structural opening in an aircraft such that the fairing covers the opening as the airfoil is moved during flight. In the preferred embodiment on a T-tail configuration aircraft which utilizes a vertical stabilizer that supports a variable incident horizontal stabilizer at its uppermost section, a cover plate is attached to the upper surface of the horizontal stabilizer support structure such that it moves with the horizontal stabilizer. In addition, the cover plate is mounted internally to and adjacent to the structural opening in the vertical stabilizer through which the horizontal stabilizer protrudes. The cover plate is composed of two panels, an upper end and a lower panel, connected by a hinge and a torsion spring. A means is provided to hold the panels adjacent the structural opening when the horizontal stabilizer is in its lowermost position.

Abstract: Tapered disc rotatably mounted in the exhaust duct of a propulsion system. The disc can be rotated about an axis normal to the yaw plane. A disc bump projects from both the upper and lower surfaces of the disc, and extends diametrically across it. When fluid is flowing through the exhaust duct, the bump, together with the opposing surfaces of the exhaust duct, chokes the flow and causes a sonic plane to be formed at the bump. The supersonic flow downstream of the disc bump remains approximately normal to the bump for angles of rotation of up to 20.degree. from normality between the bump and the upstream flow. Rotation of the disc thus causes deflection or turning of the fluid flow. The resultant thrust vectoring enables the yaw of the propulsion system and, therefore, a vehicle containing the propulsion system, to be controlled.

Abstract: A cutting insert having four symmetrically located cutting edges is mounted on a cutting insert holder, which is in turn mounted on a rotary driver. One of the cutting edges projects out from the cutting insert holder. The rotary driver rotates the projecting cutting edge along a circular path. A tube end to be finished is held in contact with projecting cutting edge being colinear with the centerline of the tube. A plurality of cutting insert holders each has a cutting insert mounted thereon with the respective projecting cutting edges being located at varying distances from the axis of rotation. The design of the cutting edges also varies. Tube ends having different radii, wall thicknesses, cross section, or chamfers are finished by successively mounting on the rotary driver the cutting insert holders having projecting cutting edges located the required distances from the axis of rotation and having the appropriate designs.

Abstract: Barrel casing attached to the housing of a hand-held drill. A retractable guide arm is cantilevered from one end of the barrel casing. The cantilevered end of the guide arm has a passageway for the drill bit, and thereby guides it. A rate limiter is attached to the other end of the barrel casing and in axial alignment with it. On the inside of the barrel casing, the rate limiter is connected to the guide arm by abutment.

Abstract: Nozzle contained within tubular housing. An annular manifold concentrically surrounds and abuts the outside of the housing. The manifold communicates with an external source of water. A cylindrical transducer is located within the housing. A hollow cone having an exit opening formed by a truncated vertex and an open base forms the front of the nozzle. The face of the transducer which emits ultrasonic waves is situated adjacent to the base of the cone. An annular passageway concentrically surrounds the transducer. The passageway runs axially towards the front of the nozzle before turning radially inward towards the nozzle's centerline. The axial section of the passageway communicates with the manifold through radial ports. The section of the passageway that turns inward communicates with the base of the cone, and also directs flow of water so that its confluence is on the emitting face of the transducer. The water subsequently flows out the exit opening in a steady state column.

Abstract: Avionics systems are cooled by circulating the heated air through an onboard closed loop system which includes a heat transfer envelope comprised of a liner and the fuselage of the flight vehicle. The liner keeps a constant, thermodynamically optimal passage height between the liner and the fuselage, and is contoured in order to maintain that optimal height between the liner and internal structural support members which abut the fuselage and pass through the heat transfer envelope. The liner is comprised of flexible interlocking liner sections, each of which is produced from the same mold using heat and flame resistant material and subsequently trimmed to precisely fit into its particular area. Each liner section has a convex ridge which fits over an internal structural support member to enclose the member within the heat exchange envelope. Each convex ridge has transverse flexible ribs which accept and removably grasp the support member, thereby removably attaching the liner section to the support member.

Abstract: A plurality of ultrasonic transducers mounted linearly on a belt that is contained and supported by a housing. The housing has wheels and handles mounted on its sides to allow an operator to grasp the apparatus and roll it across the surface of a test object along a line normal to the belt. The transducers are electrically connected to various devices which enable pulse echo testing to be performed on the test object and make the results immediately available as a picture either on paper or on a video monitor. The belt is moved laterally and cyclically back and forth as the apparatus is rolled longitudinally and the transducers are sequentially excited to emit ultrasonic waves, thus testing a swath having a width equal to the extremes of lateral motion of the line of transducers. A dynamic counterbalance swings 180.degree. out of phase with the cyclic motion of the belt, and serves to damp out the vibration generated by the belt's motion.

Abstract: Avionics systems are cooled by circulating the heated air through an onboard closed loop system which includes a heat transfer envelope comprised of a liner and the fuselage of the flight vehicle. The liner keeps a constant, thermodynamically optimal passage height between the liner and the fuselage, and is contoured in order to maintain that optimal height between the liner and internal structural support members which abut the fuselage and pass through the heat transfer envelope. The liner is comprised of flexible interlocking liner sections, each of which is produced from the same mold using heat and flame resistant material and subsequently trimmed to precisely fit into its particular area. Each liner section has a convex ridge which fits over an interal structural support member to enclose the member within the heat exchange envelope. Each convex ridge has transverse flexible ribs which accept and removably grasp the support member, thereby removably attaching the liner section to the support member.

Abstract: Gimbal comprised of four concentric cylindrical shells rotatively attached to each other by three pairs of bearings or flexures. The innermost shell is rigidly attached to a suspended instrument. The outermost shell is attached to a vehicle. Each of the three pairs of bearings are colinear and define three axes of rotation which intersect at a point. None of the three axes are coincidental with a line of sight emanating from the instrument, and two of them are nonorthogonal. The gimbal provides the instrument with freedom of rotation about any axis relative to the vehicle, including about the instrument's line of sight, without the line of sight being vignetted by a bearing or any other gimbal structure. The respective angles between the three axes of rotation are set to minimize the exposure of the gimbal to gimbal lock, as well as to minimize the onset of secondary disturbances that occur when gimbal lock is approached.

Abstract: Apparatus for sequencing the release of a missile from its launch apparatus, the unlocking of the missile's warhead fuze pre-launch safety lock, and the ignition of the missile's rocket motor. A cylindrical block having a radial passageway is situated between the warhead and the rocket motor of a missile. An actuator piston having a hollow cylindrical core slides within the passageway. One end of the actuator piston projects from the passageway and is engaged with the launch apparatus to prevent movement of the missile relative to the launch apparatus prior to launch. A source of pressurized gas communicates with the hollow core of the actuator piston through an opening in the actuator piston's projecting end. A notch in the side of the actuator piston is engaged with the warhead fuze pre-launch safety lock.