Abstract: In accordance with the present invention, there is provided portable fluid application and rinse apparatus for applying a first fluid and for rinsing with a second fluid. A first storage reservoir retains the first fluid and has an outlet. A first application conduit communicates with the outlet of the first storage reservoir. The first application conduit receives the first fluid from the outlet of the first storage reservoir and dispenses the first fluid therethrough. A first drain pan receives the first fluid. A second storage reservoir retains the second fluid and has an inlet and an outlet. A second application conduit communicates with the outlet of the second storage reservoir. The second application conduit receives the second fluid from the outlet of the second storage reservoir and dispenses the second fluid therethrough. A concentration measuring device measures the concentration of the second fluid.

Abstract: An isolation bag for isolating a casualty from a contaminated environment. The bag is preferably fabricated from a transparent, biochemically resistive material and is specifically designed and configured to be utilized in combination with a self-contained transportable life support system. The isolation bag is further provided with a plurality of tubular passages which are designed to be filled with air provided by the transportable life support system to thus cause the isolation bag to expand and form a semi-rigid structure. A multiplicity of apertures are formed upon the tubular passages in such a manner that enables refreshed air to pass therethrough which washes over the patient in a head-to-toe direction such that rapid removal of toxic and infectious residues is facilitated.

Abstract: A method of forming a breakage resistant, erosion resistant ceramic liner for a part comprising the steps of, forming a liner of a ceramic material containing pores; filling the pores with a pre-ceramic polymer resin; and, firing the liner saturated with a pre-ceramic polymer resin at a temperature and for a time which converts the resin into a ceramic within the pores. The liner can be mechanically attached, adhesively bonded or, a metal part can be cast onto the liner by placing the liner within the metal casting mold for the part as a sidewall or integral element thereof. The invention also includes method for producing parts and liners of fiber reinforced ceramic matrix composite by a resin transfer molding process or the like wherein fiber preforms are saturated with liquid pre-ceramic polymer resin. The preforms are then polymerized in a mold, the part removed from the mold, and then fired to transform the polymer to ceramic. The process can also be employed to form hollow parts such as manifolds.

Abstract: A power distribution system (12) is provided in radar apparatus to distribute power from a 270 VDC source (60) through an intermediate power converter (70) and very high frequency (VHF) regulator/modulator units (80). Bus conductors (71,74) interconnect the source, the intermediate power converter, and the VHF units. Capacitors (71, 76) are connected to the bus conductors on the input and output sides of the intermediate power converter. Each VHF unit supplies modulating pulses to RF amplifiers (82) of an AESA array of the radar apparatus.

Abstract: Apparatus for simulating aerodynamic heating and cooling on the outer surface of equipment externally mounted on an aircraft or missile as if airborne and exposed to an air stream. A first proximately spaced enclosure substantially uniformly conforms to the outer surface of the equipment and defines a low pressure chamber. A second enclosure envelops the first enclosure and defines a high pressure chamber. An adjustable flow producing mechanism directs flow of pressurized inlet air into the high pressure chamber. A temperature control mechanism selectively heats and cools the inlet air. Vents in the second enclosure exhaust the air from the low pressure chamber to the ambient region and a plurality of spaced orifices in the first enclosure direct jets of the pressurized air from the high pressure chamber into the low pressure chamber which vigorously impinge on the outer surface of the equipment.

Abstract: A tail fin assembly for a munition having a housing configured for attachment to the munition, at least one flight control surface, an actuator for effecting movement of the flight control surface(s), so as to facilitate guiding of the munition, and a guidance system for controlling the actuator mechanism. The guidance system has a global positioning system (GPS) receiver for effecting control of the actuator mechanism.

Abstract: A vehicle slot antenna system including a vehicle having generally interconnected metal parts, a window frame integral with the vehicle, and a connector having two electrically conductive conduits each extending to the window frame from an impedance matching module in communication with a radio signal generator and/or receiver. The window frame has first and second substantially parallel metal border members whose perimeters form a slot and wherein perimeter sites of a window can be retained, with the slot being functional as a slot antenna. Such functionality is achieved through having one conduit of the connector in communication with the first border member of the window frame and the other conduit thereof in communication with the second border member of the window frame. The vehicle functions as a contoured metal ground plane having sufficient metal-to-metal interconnections to enable window frame utility as a slot antenna.

Abstract: Conductive and/or chemically absorptive ceramic fibers are woven with optional non-conductive/non-absorptive ceramic fibers to create a fiber reinforcement which is impregnated with a ceramic-material-producing (pre-ceramic polymer) binder and heated to create the ceramic honeycomb with controlled ohmic loss and/or chemical absorption properties. The desired properties of the honeycomb material can be provided by the conductive and/absorptive ceramic fibers alone or in combination with non-fibrous or fibrous conductive and/or absorptive ceramic material provided by the binder, typically a preceramic polymer which may or may not contain dispersed ceramic materials; after the honeycomb is formed, the non-fibrous or fibrous conductive and/or absorptive ceramic material is interspersed throughout the honeycomb. By heating the impregnated fiber reinforcement in the absence of oxygen, carbon from any carbon-containing materials within the binder remain as a part of the honeycomb material.

Abstract: An air intake system disposable in an air vehicle turbo engine housing disposed in an exterior airflow for selectively reducing external engine boundary layer separation drag and external engine friction drag on the engine housing comprising an air inlet member for receiving engine intake air disposable within the engine housing. The air intake system further comprising a first air exit port disposed in fluid communication with the air inlet member, adapted to direct intake air from the air inlet member and to direct intake air substantially in the direction of exterior airflow, to reduce external engine boundary layer separation drag. The air intake system further comprising a second air exit port disposed in fluid communication with the air inlet member, adapted to direct intake air from the air inlet member and to direct intake air substantially in a direction perpendicular to the exterior airflow, to reduce external engine friction drag.

Abstract: Spin-polarized xenon gas is provided in medical-grade purity for use as a contrast medium in MRI studies by use of collision-induced transfer of spin energy to the xenon gas from laser-pumped spin-polarized Rb gas. The Rb gas is provided by thermally vaporizing solid Rb at low pressure in a container having an inside surface coated with a siliconizing agent and exposed to the Rb gas. The combined xenon and Rb gases are separated after transfer of the spin energy in order to provide a sufficient purity of the xenon gas by use of a cryogenic separation process. The Rb gas is removed from the xenon gas and is returned cryogenically to a solid stated to an acceptable level of purity for the xenon gas. The gas may be analyzed optically to measure the remaining Rb concentration.

Abstract: The present invention is a wingtip vortex device for induced drag reduction and vortex cancellation. The wingtip vortex device is an aerodynamic drag reduction system installed at the wingtips of an aircraft. The wingtip vortex device comprises an impeller located ahead of the wingtip chord, a wind turbine device located behind the wingtip chord, and an intermediate gear device for coupling the impeller with the wind turbine and/or for generating power. Thus, the wingtip vortex device is self-contained as the impeller is powered by the vortex-driven turbine. As a result, induced drag is reduced without requiring an external power source such as the aircraft propulsion system.

Abstract: A system for facilitating the enhanced aerodynamic control of an aircraft having a fuselage including a forebody defining a frontal portion adapted to create a primary vortex under certain flight conditions and a rear portion. The control system comprises a contour discontinuity which is formed between the frontal and rear portions of the forebody. The contour discontinuity is sized and configured to create a secondary vortex under certain flight conditions. In addition to the contour discontinuity, the control system comprises a pressurized fluid injecting device which is disposed within the forebody of the fuselage adjacent the contour discontinuity. The pressurized fluid injecting device is used to selectively manipulate the secondary vortex to control the flight performance characteristics of the aircraft.

Abstract: The present invention is a dowel-adhesive method for repairing ceramic matrix composites. The dowel adhesive method embodied in the present invention incorporates both adhesive and mechanical bonding of a patch to a damaged CMC surface area. The damaged area is first identified and then pre-processed. Next, a CMC patch plug is produced and adhesively and mechanically bonded to the pre-processed area. Mechanical bonding is accomplished with dowel pins and corresponding dowel pin holes in the patch plug and the panel. The dowel pins anchor the CMC patch plug to the panel. Adhesive bonding is accomplished by placing a ceramic adhesive between the patch plug and the panel. Also, the dowel pins are adhesively bonded within the dowel pin holes of the plug and the panel. The ceramic adhesive is set by a low temperature cure (if required) and a high temperature firing.

Abstract: A method and system for phased array radar antenna calibration to be made in flight employs a synthesized initial transmission signal having a notch in the main direction of beam. This has the effect of returning reflected receiver signals that are main lobe clutter free, but contain clutter returned solely from the sidelobe radiation. The received clutter data is processed to yield a set of coefficients that, when combined with subsequent radar signal return resulting from a signal having a main lobe, provides a return signal that is free from aircraft induced distortions and misalignments that can result in sidelobe induced false alarms. All data processing is conducted in the time domain rather than the frequency domain, thus, avoiding Doppler frequency foldover problems due to ambiguities from signals received at multiple aspect angles.

Abstract: A DC power converter is disclosed for converting an input voltage to a final output voltage that is higher than the input voltage. The power converter includes an input terminal for receiving the input voltage and a final output terminal. A boost converter generates an intermediate voltage that is higher than the input voltage and lower than the final output voltage. The boost converter includes an inductor having a primary winding that has a first end connected to the input terminal, a switch for selectively connecting the second end of the first winding to ground, a first diode connected between the second end of the first winding and an intermediate node, and a first output capacitor connected between the intermediate node and ground. The boost converter produces at the first output capacitor an intermediate voltage higher than the input voltage. The step up converter described further includes a second winding on the inductor, a first end of which is connected to receive the intermediate voltage.

Abstract: A system for fastening aircraft assemblies is disclosed. The system comprises a first wing clip (10) having an anchor plate (12) with at least one ear (20) for affixing to a first assembly (16); a second wing clip (11) having an anchor plate (14) and at least one ear (20) for affixing to a second assembly (18); and a fastener (44) for joining the first wing clip (10) to the second wing clip (11).

Abstract: An extended reaction acoustic liner for use in jet engine noise mitigation has a substantially non-porous outer layer, a honeycomb core disposed in laminar juxtaposition to the outer layer, and a porous inner layer in laminar juxtaposition to the honeycomb core such that the honeycomb core is sandwiched between the outer layer and the inner layer. The honeycomb core comprises a plurality of cell walls defining a plurality of cells. Some of the cells are in fluid communication with one another via the openings formed in the cell walls. The openings in the cell walls cause viscous acoustic losses, resulting in acoustic energy dissipation and enhanced noise attenuation.

Abstract: The present invention is embodied in a reconfigurable gantry tool and a reconfigurable tool system. The reconfigurable tool includes a platform, a reconfigurable holding mechanism, a gantry frame, a multi-axis numerically controlled robotic tool, a multi-movement control device coupled to the mobile multi-axis tool, and a rotatable and translatable sine plate. The reconfigurable gantry tool system comprises a plurality of reconfigurable gantry tools strategically coupled to one another to form a non-matrix assembly line. Other tooling systems can be coupled to and/or within the reconfigurable gantry tool system for performing additional operations.

Abstract: In a method of detecting ice on surfaces of an aircraft, a surface of an aircraft is scanned with laser light operating at different wavelength regions in a manner whereby the surface scatters the laser light. Laser light scattered from the surface is detected. Radiation outside the wavelength bands of interest is removed prior to detection. The detected, filtered, scattered laser light is processed to reconstruct images of the surface, thereby indicating areas of ice and water on the surface. The processing takes into account the directions of scanned continuous wattage laser beams relative to the surface, laser beam geometry factors due to changing distance between the laser beams and the surface while scanning, relative signal levels, normalizations and returns from other detectors. The material of the windows of the aircraft blocks the laser beam and any stray laser light. Also, the windows of the aircraft could be treated to block the laser beam and the laser light.

Abstract: A device for measuring electromagnetic radiation absorption of a test surface includes an electromagnetic transceiver, an x-y axis positioning mechanism, and a z axis positioning mechanism. The x-y axis positioning mechanism facilitates mapping of electromagnetic radiation absorption at different locations upon the test surface and the z axis positioning mechanism enhances the accuracy of electromagnetic radiation measurements by facilitating phase matching of electromagnetic radiation transmitted by the electromagnetic transceiver with electromagnetic radiation received thereby.