Abstract: The present invention provides hydrochlorofluorocarbons having 3 to 5 carbons atoms, 1 to 2 chlorine atoms, and an OH rate constant from about 8 to about 25 cm.sup.3 /molecule/sec.times.10.sup.-14. The hydrochlorofluorocarbons are useful as solvents and blowing agents.

Abstract: A process for analyzing a spectral signal generated by a birefringent element and transmitted to an array. An output spectral signal emanating from the array is converted from an analog to a digital signal to establish a reference wave form which has a dominant frequency after the birefringent element is exposed to a known temperature. Thereafter, a current wave form is generated from the output spectral signal emanating from the array. A phase and frequency relationship is obtained by cross correlating the current wave form and the reference wave form. The dominant frequency for the phase and frequency relationship is obtained by Fast Fourier Transformation. Thereafter, the dominant frequency for the phase and frequency relationship of the current wave form is compared with the dominant frequency for the reference wave form to determine a temperature range.

Abstract: Magnesium base metal alloy sheet is produced by rolling the rolling stock extruded or forged from a billet at a temperature ranging from 200.degree. C. to 300.degree. C. The billet is consolidated from rapidly solidified magnesium based alloy powder that consists essentially of the formula Mg.sub.bal Al.sub.a Zn.sub.b X.sub.c, wherein X is at least one element selected from the group consisting of manganese, cerium, neodymium, praseodymium, and yttrium, "a" ranges from about 0 to 15 atom percent, "b" ranges from about 0 to 4 atom percent, "c" ranges from about 0.2 to 3 atom percent, the balance being magnesium and incidental impurities, with the proviso that the sum of aluminum and zinc present ranges from about 2 to 15 atom percent. The alloy has a uniform microstructure comprised of fine grain size ranging from 0.2-1.0 .mu.m together with precipitates of magnesium and aluminum containing intermetallic phases of a size less than 0.1 .mu.m.

Abstract: A method of restoring a damaged surface of a substrate to a functional condition through a filler material consisting essentially of tungsten disulfide epoxy resin having a 10:1 ratio. The filler material is cured after being applied to the damaged surface by uniformly raising the temperature to a cure temperature of the epoxy to allow any volatiles to evaporate without the creation of voids in the surface such that the resulting porosity prevents corrosion of the substrate when exposed to aromatic fuels at temperatures of 350 degrees F.

Abstract: A pneumatically dithered ring laser gyroscope features providing an oscillatory motion directly to a segment of the excited gas which serves as the laser photon source. Alternately switching ionizing potential between two cathodes in appropriately designed cavities establishes desired oscillatory gas velocities to effect emitted frequencies within the gyro, thereby permitting the detection of rotational rates below the "lock-in" rate of the undithered gyro.

Abstract: A power management system for turbine engines includes a plurality of switches, each allowing for engine speed and engine torque to be controlled together. The switches correspond to various modes of operation of the turbine engine. When a switch is selected, a mode signal is supplied to a FADEC which, in response, issues speed and torque commands to an associated engine. The FADEC includes function generators that issue the torque commands as a function of outside ambient conditions. The torque commands are continuously updated for changing ambient conditions. Further, takeoff torque can be corrected for heating conditions. The power management system can also provide torque commands as a linear function of power lever angle.

Abstract: The aircraft brake vibration damper (30, 60) comprises a mesh material (30, 60) located at axially extending spaced-apart side walls (22) of a spline (12) of a torque tube (10) so that the mesh material (30, 60) is located between the spline (12) and a metal cover cap (20, 50) for the spline (12). The mesh material (60) can extend about the torque tube (10) and splines (12) and completely over a top surface (17) of each spline (12). The mesh material (80) can be located in a cavity (75) of heat shield segments (70) located between the splines (12). The mesh material (30, 60, 80) may be a knit or woven damping material (30, 60, 80) that dampens vibrations during brake operation.

Abstract: An improved protective layer for ceramic insulating bodies includes a composite having a refractory fiber in a matrix of a black glass ceramic having the empirical formula SiCxOy where x ranges from about 0.5 to about 2.0, preferably 0.9 to 1.6 and y ranges from about 0.5 to 3 0, preferably 0.7 to 1.8. The black glass ceramic is derived from cyclosiloxane monomers containing a vinyl group attached to silicon and/or a hydride-silicon group. The protective layer is formed by laying up plies of a prepreg on the insulating body following by pressing, curing and pyrolyzing said prepreg to form said protective layer.

Abstract: A manifold (10) for holding a generally cylindrically shaped gas generator (12), the gas generator including inflation ports (26a, b) through which inflation gas exits to inflate an air bag, the manifold being a hollow extruded structure (14) having a cylindrical middle portion (16) and first (32) and second (34) ends, the middle portion formed having a diameter section slightly larger than the diameter of the gas generator, a diameter of the first end being smaller relative to the diameter of the middle portion to provide an interference fit with a mating portion of the gas generator upon insertion of the gas generator; the middle portion further having two opposingly positioned outwardly flared portions (18a, b), the flared portions in cooperation with walls of the gas generator, defining open chambers to receive inflation gas from the gas generator, the flared portions each including at least an exit port (44a, d, 46a) to direct inflation gas out of the manifold.

Abstract: A combustion system for a gas turbine engine provides a reaction limiting means for preventing the combustion process within the combustion chamber of the engine from proceeding towards completion by limiting the reaction rate or duration of the reaction process sufficiently such that a clean combustion gas is produced having substantially less carbon particles than for a combustor effective for essentially complete combustion. The invention also provides an efficient method of removing carbon deposits which do form by controlling the combustor shutdown technique in such a way as to cause the carbon to be oxidized. The preferred embodiment provides an aircraft emergency power unit having a high pressure air storage tank, an aviation fuel storage tank, and a combustor with a reaction limiting means which combusts pressurized air and aviation fuel in a fuel rich ratio to produce a motive combustion gas in a reaction limiting means.

Abstract: The ability of a packed bed of adsorbent to hold a gas is increased by employing at least two sizes of adsorbent particles having nominal diameters differing by at least 7/1. In a preferred embodiment, the capacity of a bed of carbon molecular sieve particles for adsorption of natural gas is significantly improved.

Abstract: A fluid pressure braking system for a vehicle equipped with a drive line retarder automatically reduces the braking pressure level communicated to the brakes controlling the driven wheels of the vehicle to adjust for the retardation effected by the retarder. The retarder is actuated automatically each time the brake is applied by calculating the appropriate retardation level as a function of the brake pressure being demanded by the vehicle operator and by the load carried by the vehicle.

Abstract: An assembly for an air bag (56) adapted to fit within an opening (22) in a panel in the vehicle interior such as an instrument panel. The assembly comprises a housing (44) including a first wall (100) and an opposite second wall (102), a flexible wall member (106) secured to the first wall (100) defining a space (132) therebetween to receive a hinge portion of the deployment door. One of the first wall (100) and flexible wall members (106) includes a plurality of depressions or first tabs (112) which extend into the space (132) to provide a mechanism to engage and lock the hinge portion of the deployment door in place. The second wall (102) includes at least one louver (122) forming a pocket (123) and a plurality of outwardly extending tabs (120) which provide a mechanism to engage and lock in place a tear seam portion of the deployment door.

Abstract: A compressor assembly includes a housing, and a rotatable impeller within the housing which includes a hub and blades extending from the hub. A ring circumscribes the leading edge of the blades, and cooperates with a groove in the housing to define a clearance therebetween which is larger than the clearance between the connecting edge of the blades and a corresponding conforming portion of the housing. This permits free flow of gas around the ring to enhance the operating range of the compressor wheel. The ring also stiffens the blades, permitting the thickness of the hub to be reduced, thereby further enhancing the operating range of the compressor wheel.

Abstract: A railroad interlocking control system utilizing a plurality of programmable controllers to regulate flow of train traffic through an interlocking track layout in which a number of track routes converge and overlap into a bottleneck area. Control of switch and signal devices in the bottleneck area is shared by multiple programmable controllers which may reduce redundancy requirements of prior art arrangements.

Abstract: An improved air conditioning system is provided for an aircraft, particularly with respect to providing an enhanced supply of fresh air to the aircraft cabin or cockpit. The system includes a dual inlet turbine driven at least in part by pressurized bleed air from an aircraft engine, wherein the turbine expands and cools the air preparatory to supply thereof as conditioned air to the aircraft cabin. During relatively low altitude operation, the bleed air flow is supplemented by compressed fresh air discharged from a turbine-driven compressor and supplied to the dual inlet turbine. At relatively higher altitude operation, this fresh air flow is bypassed around the turbine for addition to the bleed air flow at a downstream side of the turbine, and the entire nozzle area of the turbine is opened to the bleed air flow.

Abstract: The combination solenoid valve and shuttle valve (60, 160A-D, 260A-D) comprises a shuttle valve (50, 150) which is slidingly and sealingly received at or adjacent an end of the solenoid valve (40, 140). The shuttle valve (50, 150) includes a stepped interior opening (54, 154) which sealingly receives the end of the solenoid valve (40) or a valve part (140A), such that slidable movement of the shuttle valve (50) causes an insert (55, 55A, 155) within the interior opening (54, 154) to seat sealingly over either a solenoid insert seat (41C) or insert seat (141C) of the valve part (140A) in order to isolate pressure chambers (12A, 12B; 112A, 112B; 212A, 212B) of a master cylinder/hydraulic booster (12, 112, 212A, 212B) from a wheel brake (16, 116A-D, 216A-D).

Abstract: An aircraft is maintained at a constant glide slope and air speed by trimming delta torque commands provided by an autopilot. Delta torque commands that change by more than twenty percent are trimmed automatically to maintain the constant glide angle and to assist the pilot in maintaining air speed within .+-.5 knots on the approach glide slope.

Abstract: The accuracy of the performance of an inertial navigation system is validated by comparing data measured by a fourth gyro and accelerometer to an analytic equivalent constructed from measurements made by a primary gyro/accelerometer orthogonal triad.