Abstract: A flush inlet and inlet air passage for supersonic aircraft including provisions for efficiently decelerating a supersonic airstream entering the inlet and converting such airstream to subsonic airflow within the inlet air passage prior to introduction into the aircraft's jet propulsion engine.

Abstract: A log handling device for biased, adjustable circumferential envelopment of a log during a splitting operation to maintain the general conformation thereof as the same is reduced to a plurality of split elements and provide an ability to grasp the log, whether whole or split, is disclosed herein.

Abstract: An output matrix adapted to receive an L+R signal component (made up of the sum of L and R stereo components) and an L-R signal component, and to combine these in a manner to produce a separate L output and a separate R output, with certain modifications to the outputs. The higher frequency portion of the L-R signal is passed through a detector which, in turn, causes a leading edge amplifier to transmit to the matrix only those signal portions where there is a relatively abrupt change of amplitude, these being the signal portions which contain the main stereo information which gives the directional information. Also, the L+R signal component, in addition to being transmitted directly to the matrix, is directed through time delay means to produce a time delayed L+R signal component that is also transmitted to the matrix, so as to provide what are called "ambient" to the output of the matrix.

Abstract: A deployable inlet for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the air inlet located in the leading edge of the vertical stabilizer at such times as the center boost engine is shut down and non-operative, thus minimizing drag. More particularly, an inlet construction for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations; and/or (iii), under certain emergency operating conditions; and, wherein the air inlet for such center boost engine is located at the root leading edge of the aircraft's vertical stabilizer.

Abstract: A cartridge having a housing removably mounted in a cleaning cassette. The housing has a first pivotal connecting member to pivotally engage a matching connecting means in the structure, and a second connecting member adapted to engage second connecting means in the structure to prevent rotation of the housing. There is a fixed pad mounting member in the housing and a second pad mounting head movably mounted on spring arm.

Abstract: A cassette housing having a reciprocating wiper arm which comprises a front end cleaning section, a rear portion pivotally mounted to the housing, and an intermediate spring portion. The spring portion comprises three relatively rigid link sections joined to one another by two relatively flexible elbow sections, with the link sections extending generally laterally in a general "Z" configuration.

Abstract: A connector for joining structural components which may be subjected to bending, shear, tensional and/or torsional forces at the joint is comprised of a fixture member spanning the joint between the structural components for coupling the same along a longitudinal connector axis generally normal to the joint, socket members disposed within each of the components to be joined and through which the fixture member passes, the sockets defining a shear pocket configured to receive a resilient shear cushion. The fixture member is preferably a compressive fixture member and includes resilient compression cushion members disposed intermediate the length thereof outwardly proximate the shear pocket and inwardly proximate adjustable compression members for establishing a compressive force across the joint. A bending cushion may be disposed at the joint between the structural components.

Abstract: A shake resaw machine for converting a generally rectilinear wooden blank into a pair of oppositely tapered shingles, each having a tip and a butt end, is comprised of a support table hingedly disposed for cooperative engagement with a saw for lateral movement with respect to a longitudinal feed axis along which the wooden blank progresses during a resaw sequence through the saw, including a first tip-cutting stage, an intermediate diagonal-cutting stage, and a second tip-cutting stage, a table control member for moving the support table at a predetermined rate in a lateral path relative to the feed axis during the resaw sequence, first and second blank guide members having variable lateral stiffness, one of each disposed on either side of the feed axis forwardly proximate a saw blade location thereon, for cooperatively routing the blank along a variable, predetermined resaw path, and first and second guide control members for regulating, respectively, the lateral stiffness of the first and second guide membe

Abstract: An apparatus for dry placer mining to concentrate recoverable metallic constituents, such as gold or silver, from a dry gravel mix containing same is comprised of a frame for supporting and guiding an endless belt along a path including an upwardly inclined segment for receiving gravel particulate; an endless belt including a woven mesh belt member, a plurality of riffle members disposed in spaced parallel relationship within the intertices of the mesh member, and a composite fabric member disposed in face-to-face contact with the bottom surface of the mesh member; and a fluidizing member for passing a fluidizing gas upwardly through the endless belt along the inclined segment for fluidizing the gravel particulate and for establishing an electrostatic charge proximate the riffle members. The composite fabric member is specially constructed to permit a proper airflow for fluidizing the particulate and for assisting in the establishment of an electrostatic potential proximate the riffle members.

Abstract: An improved jet engine two dimensional, asymmetric afterburner nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its low profile configuration, simplicity of construction, and lack of interference with, or excessive intrusion into, the wing spar structural space within the airfoil; yet, which permits minimization of the included angle between the wing chord reference plane and the visual line-of-sight from the airfoil trailing edge into the jet engine nozzle while in its cruise position. More specifically, the present invention pertains to a simplified two dimensional, asymmetric convergent or CD nozzle construction, and an actuating mechanism therefore, which avoids the necessity to devote critical wing spar structural space to pneumatic load or pressure balance chambers, and wherein the nozzle may be shifted to a dry nozzle position--i.e.

Abstract: A conventional crutch having a ground engaging blunted tip member adapted to frictionally engage a finished ground surface. A second ground engaging member having a sharp tip adapted to be stuck into an icy surface is fixedly attached to and spaced from the crutch member. In one position, with the crutch assembly slanting downwardly and outwardly from the person, the point of the second member is above the ground surface. However, by rotating the crutch assembly 180 degrees from the first position, the point of the second member comes into ground engagement to firmly engage an icy surface. The blunted tip is compressible and the sharp tip is disposed slightly above the bottom of the compressible blunted tip when the crutch is disposed vertically with no weight applied thereto.

Abstract: A nacelle mounted by a pylon above and forwardly of a wing. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle and pylon have a critical surface region which is a lower side surface portion of the nacelle and the contiguous pylon surface adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle and pylon are shaped to be in alignment with a plurality of airfoil stream lines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent stream lines and correspond more closely to the engine structure contour.

Abstract: A nacelle mounted directly to and above a wing so as to extend forwardly therefrom. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle has a critical surface region which is a side surface portion of the nacelle adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface area that is within the critical zone. The critical contour region of the nacelle is shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.

Abstract: A nacelle mounted by a pylon below and forwardly of a wing. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle and pylon have a critical surface region which is an upper side surface portion of the nacelle and the contiguous pylon surface adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle and pylon are shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.

Abstract: An improved pressure balanced nonaxisymmetric high aspect ratio afterburner convergent nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its simplicity of construction, ease and reliability of operation, and improved simplified sealing characteristics; yet, which permits substantial reduction of the included angle between the wing chord reference plane WCRP and the visual line-of-sight from the airfoil trailing edge into the jet engine nozzle while in its cruise position. More specifically, the present invention pertains to a simplified pressure balanced nonaxisymmetric high aspect ratio afterburner convergent nozzle construction which permits of simplified, highly effective sealing arrangements and wherein when the nozzle is shifted to a dry nozzle position--i.e., the cruise position--the trailing edge line-of-sight into the nozzle is maintained at a minimum angle, preferably on the order of from about 5.degree. to about 10.degree.

Abstract: A nacelle mounted directly to and below a wing so as to extend forwardly therefrom. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle has a critical surface region which is a side surface portion of the nacelle adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle is shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.

Abstract: A supersonic two spool turbojet engine capable not only of developing sufficient power to accelerate up to supersonic cruise and maintain efficient operation at supersonic cruise, but also arranged to cruise at subsonic velocities with a relatively low specific fuel consumption. The engine is provided with a variable bypass passageway downstream of the compressor. Flow into the bypass passageway is controlled so that during low power setting the bypass passageway is closed so that all the gaseous flow is directed through the turbine. During higher power settings, the bypass passageway is opened to the extent that a selected portion of the gaseous flow is directed through the bypass passageway to bypass the first stage of the turbine section so that the corrected flow to the first turbine stage remains substantially constant for high and low power setting of the engine.

Abstract: A method for chemically milling an etchable workpiece by exposure thereof to an etchant in order to mill selected etchant-active areas and thereby form a plurality of raised die elements separated and bounded by a plurality of recessed cavities, which method is comprised of the steps of initially, partially etching the workpiece to form recessed die element precursors separated and bounded by recessed cavities, depositing a film of an etchant-resistant composition on the workpiece in at least selected ones of the recessed cavities, filling those selected cavities with an etchant-resistant filler and then subsequently processing the workpiece. In a highly preferred embodiment, the method comprises depositing a thin film of gold on the workpiece, removing the gold film from selected areas where active etching is to occur, and then filling the recessed cavities with an epoxy filler.

Abstract: A compact, cam operated, counterbalance system (30) is provided for the torque tube assembly (25) associated with a moveable hinged structural member (20) of the type hingedly connected to a fixed structural member and adapted to pivot about an inclined hinge axis in which the counterbalance system includes: (i) a cylindrical cam (31) surrounding a torque tube (38) and defining an axially presented continuous cylindrical cam surface (32) formed by a plurality of axially presented curved ramps (32a, 32b); (ii) cam follower means (34, 35, 36) mounted concentrically about the torque tube (38); (iii) a compression spring (42) mounted concentrically about the torque tube (38) for continuously biasing one of the cylindrical cam (31) or the cam follower means (34, 35, 36) axially towards the other; (iv) one of the cylindrical cam (31) and the cam follower means (34, 35, 36) being rigidly mounted on the fixed structural member (22); (v) the other of the cylindrical cam (31) and the cam follower means (34, 35, 36) bei

Abstract: In an aircraft having a pair of engines mounted forwardly of the wing and discharging jet exhaust over the wing for augmented lift, a trailing edge flap is positioned directly behind each of the engines. Each flap has a stowed position for the cruise mode, a rearwardly and downwardly extending position for maximum deflection of the jet exhaust downwardly for STOL operation, and various intermediate positions. The upper aerodynamic surface of each flap is curved in a manner that the radius of curvature increases along the chord length of the flap from the forward knee of the flap to the trailing edge of the flap. Each flap is moved from its stowed position, through intermediate positions to its fully deployed position in a manner that the upper aerodynamic surface of each flap forms a smooth and continuous extension of the fixed rear portion of the upper aerodynamic surface of the wing.