Abstract: This invention provides an improved aircraft wheel rim wherein a demountable tire bead flange has an annular chamfer within the outboard end of the flange bore, and a split lockring which cooperates to maintain the flange on the wheel rim body has an outer surface chamfer which matches the flange bore chamfer, the angle of the flange bore and lockring surface chamfers being determined by the coefficient of friction of the material comprising the wheel rim assembly such that a compressive wedge-locking load force exists at the chamfer joint as may be imposed by inflation of a rim-mounted tire.
Abstract: This invention provides provides a separable nosecap for the forward end of a homing torpedo, the nosecap and torpedo comprising a missile that is launched into the atmosphere for a ballistic trajectory to a distant underwater target. The nosecap comprises a nosecap shell having a volume of rigid cushioning foam material within its interior space defining a cavity into which is mounted a pneumatic apparatus including a flexible inflatable sleeve for forcefully disengaging the nosecap from the torpedo after the missile has entered the water environment. The inflatable sleeve engages the forward end of the torpedo and, upon inflation and axial extension, the sleeve disengages the nosecap from its mounting to the torpedo such that a homing mechanism of the torpedo may guide it to the intended target.
Abstract: The invention provides an integral brake disk comprised of two brake disks each having a disk thickness of one-half the design required disk thickness and these two disks are clamped together in planar face-to-face orientation by fasteners to form the integral brake disk. The integral brake disk has an inboard-facing brake wear surface provided by a wear surface of a first of the combined brake disks and an outboard-facing brake wear surface provided by the second of the combined brake disks. The integral brake disk is put into braking service for a first period after which refurbishment is required. The integral brake disk is refurbished by declamping the two disks and grinding the worn wear surfaces to planar specification. The two disks are recombined at the ground planar surfaces and reclamped to form a new integral brake disk.
Abstract: This invention generally relates to aircraft countermeasures and more particularly to an infrared decoy flare which operates in a substantially aerodynamic configuration and effectively shields aerodynamic cooling associated with its operation when ejected into the adjacent windstream of a tactical aircraft. The decoy provides an enhanced infrared signature to IR and heat-seeking threats to effectively decoy them away from the protected aircraft.
Abstract: A device which is deployable in the ocean environment to defeat an active torpedo comprises a mesh net structure constructed of a plurality of flat ribbons oriented in a particular geometric orientation with uniform spacings between adjacent ribbons, the ribbons being comprised of synthetic materials and more particularly of SPECTRA yarns in combination with yarns taken from the group comprising nylon, polyester, aramid, and KEVLAR. The net structure has stitched interconnections of the ribbons and a diameter of at least ten feet and exhibits a packing density of about 45 lbs/ft.sup.3 and a substantial neutral buoyancy in salt water.
Abstract: An electro-expulsive boot comprises two peripherally-interconnected and juxtaposed elastomeric members and an electrically-conductive element helically and/or spirally wound between the two members and embedded in the elastomeric material which comprises the members and an electrical current pulse applied to the conductive element generates a force in one member which opposes a force generated in the other member and the members are expulsively separated by the existence of the current pulse.
Abstract: This invention provides brake clamping and declamping in response to a position feedback controlled brake actuator in which an electric torque motor drives a rotating member of a reciprocating drive mechanism to axially move another member into out of engagement with a brake pressure plate of a multi-disk brake assembly. A microprocessor controller receives electric signals indicative of (i) a pilot's command for braking, (ii) a command for brake release and antiskid braking, (iii) the position of the torque motor rotor at any instant, and (iv) the initiation of brake clamping of the multi-disk brake. The controller generates a feedback control signal to the torque motor which adjusts the motor rotor position, in revolutions, to increase or decrease brake clamping in accordance with the pilot signal and to effect brake release in accordance with an overriding antiskid signal.
Abstract: A support bracket has a base member adapted for attachment to a particular measuring tool and a vertical member extends from the base member and it has a horizontal slot within its top edge which mounts a tape rule by way of the tape rule spring clip. The tape rule is oriented on the support bracket such that measurements may be made along a common baseline with reference to the measuring tool and a workpiece to be measured while, at the same time, measurements may also be made along a ruler edge of the measuring tool which is positioned at an angle with respect to the common baseline.
Abstract: The invention is directed to a method of increasing and/or extending the operational service life of an aircraft brake disk stack by selectively limiting the number of brake assemblies which comprise the aircraft landing gear configuration and which are put into operation during the time the aircraft is on the ground and subject to taxi-snub braking cycles while also providing that all of the brake assemblies of the total available on the aircraft are operational during landing of the aircraft.
Abstract: An aircraft windshield transparency includes a base frame defining an opening into which an inboard-positioned transparency is mounted with at least one outboard-positioned transparency and an interlayer between the two transparencies. The interlayer exhibits a stronger adhesion to the outboard transparency than to the inboard transparency. The peripheries of the outboard transparency and interlayer carry a means which functions to expose a groove penetrating to the surface of the inboard transparency such that the outboard transparency and interlayer may be removed and the inboard transparency thereafter functions as the primary windshield transparency of the aircraft.
Abstract: An optical fiber pressure sensor in a double polarimetric configuration comprises a first polarimetric circuit including an optical fiber sensing coil in a planar, substantially circuitous orientation between two flat plates to provide an optical signal indicative of a pressure within a fluid medium, the circuit including light detection and signal demodulation means to provide an output signal indicative of the pressure; and a second polarimetric circuit intercoupled to the first circuit through an optical coupler, the second circuit providing a source of light which is divided by the coupler between the two circuits and the second circuit includes optical and electronic circuit means to provide a feedback signal to stabilize the operation of the source of light. The pressure sensor is configured and packaged to enhance its sensitivity to pressure while substantially immunizing it against changes in temperature.
Abstract: This invention provides a roller screw drive mechanism (60) driven by an electric torque motor (50) through a gear drive (58,58',58") associated with either the screw (64,94) or nut (62,92) member of the roller screw drive mechanism. Rotation of the gear drive (58, 58', 58") by the torque motor (50) effectively moves the other member of the roller screw drive mechanism into axial engagement with the brake pressure plate (32) for braking action in response to an electrical control signal fed to the torque motor. A plurality of torque motor driven roller screw drive mechanisms are mounted in a balanced arrangement about the axis of the wheel and brake assembly to effectively apply and release a brake pressure force on the brake pressure plate in response to an electrical control signal to the torque motors.
December 15, 1986
Date of Patent:
September 12, 1989
Opus Acquisition Corporation
Rick Morris, Moseley Douglas D., Gary M. Rimlinger, Thomas L. Soldat
Abstract: An assembly comprises drive key wearplates mounted in pairs to longitudinal side surfaces of each of a plurality of wheel key bosses and retaining members are fastened transversely across the top of a boss to engage both wearplates of the pair. A heatshield is positioned within the wheel bore between adjacent wheel key bosses and its opposite lateral edges engage respective wearplates in a manner such that it may not move either axially or radially within the bore.
Abstract: A method of fabricating a multilayer circuit board assembly capable of operating at microwave frequencies. Specifically, multilayer circuits such as complex beam forming networks and antennas having internal via holes may be fabricated in a single bonding cycle. This is accomplished by first preparing individual circuit boards (10) by pre-forming holes (18) through circuitry (14,16) etched on opposite sides of a substrate (12). The holes (18) are next selectively plated with a conductive layer (20) and then with a material (24) capable of forming a melted fusion bond and/or a solid-state fusion bond. Bonding film (56) is placed between each board-to-board interface of a multi-board assembly and the assembly of boards is subjected to a bonding cycle of heat and pressure wherein an integral unit is effected.
Abstract: A nosepiece for the forward end of a missile that is launched into the atmosphere for a ballistic trajectory and a water entry impact comprises a frangible base and a separable nosecap, the base having multiple segments of rigid foam defining an axial bore into the base and a volume of soft cellular foam within the bore to protect the forward end of the missile. The nosecap is in seated relationship within the bore opening on the tip end of the base during airborne flight and separates therefrom to expose the axial bore opening prior to water entry impact such that upon impact the base is fractured by the force of water entering the exposed bore and thus separated from the missile.
Abstract: An airborne spin dispensing apparatus (100,101) and method of dispensing a plurality of sub-units (60) such that the ground plane impact pattern of the plurality of sub-units substantially corresponds to a particular geometric ground target. An onboard microprocessor (24) which receives flight data (26) and a selected target data (28) also has a program store of sub-unit ejection sequences each of which corresponds to a particular target impact geometry. The microprocessor (24) selects an appropriate sub-unit ejection sequence in accordance with the flight and selected target data and effects a release of the sub-units (60) from the spinning apparatus such that their ground impact pattern substantially matches the geometry of the ground target.
January 27, 1987
Date of Patent:
June 14, 1988
Joseph C. Huber, Jr., Bellur L. Nagabhushan
Abstract: An airborne system (10) and method of dispensing a plurality of sub-units (22) such that the ground plane impact pattern of the plurality of sub-units (22) substantially corresponds to a particular geometric target area. An onboard control module (150) including a microprocessor (130) which receives flight data (138) and a selected target data (140) also has a program store of sub-unit ejection sequences (132) and a logic selection of sub-unit ejection velocities (134). The microprocessor (130) selects an appropriate sub-unit ejection sequence and individual sub-unit ejection velocity in accordance with the flight and selected target data and effects a release of the plurality of sub-units in a manner such that they disperse and impact in the pattern of the selected target.
Abstract: The invention herein relates to a computer organization capable of rapidly processing extremely large volumes of data. A staging memory is provided having a main stager portion consisting of a large number of memory banks which are accessed in parallel to receive, store, and transfer data words simultaneous with each other. Substager portions interconnect with the main stager portion to match input and output data formats with the data format of the main stager portion. An address generator is coded for accessing the data banks for receiving or transferring the appropriate words. Input and output permutation networks arrange the lineal order of data into and out of the memory banks.
Abstract: An aircraft-launched, ram-air inflatable, passive radar decoy (10) has a substantially cylindrically shaped body (12) having an open forward end (14) and a closed porous rearward end (16), the body comprised of a fabric reinforced composite having a high radar reflectivity coating on at least it interior surfaces (12i, 16i). A rod-shaped weight (22) is attached at the forward end (14) by way of shroud lines (20), the weight (22) providing the highest weight-to-drag-area ratio for the particular size body. The decoy (10) provides a high radar cross section and broad angle coverage to ground-based source of radar when it is ram-air inflated upon ejection by the aircraft into its adjacent windstream.
November 14, 1986
Date of Patent:
November 24, 1987
John J. Graham, Jr., Joseph C. Huber, Jr., John E. Neumann
Abstract: A torque tube (50) having a cylindrical body (50a) is characterized by a plurality of key surfaces (50k) which extend radially from the surface (50s) and extend longitudinally from an inboard end (50i) to terminate at an outboard end (50o) in a radius (R3) which defines a transition (50t) into a radially extending rib (50r). The cylindrical body portion between adjacent keys (50k) also extends at the outboard end (50o) into a flange (50f) which is continuous about the outboard end of the tube. The combination of radially extending ribs (50r) and flange (50f) define T-sections at the outboard end (50o) which provide the strength requirements of the torque tube in its intended service application.