Abstract: The present invention relates to porous mat gas fired radiant burner panels utilizing improved reverberatory screens. The purpose of these screens is to boost the overall radiant output of the burner relative to a burner using no screen and the same fuel-air flow rates. In one embodiment, the reverberatory screen is fabricated from ceramic composite material, which can withstand higher operating temperatures than its metallic equivalent. In another embodiment the reverberatory screen is corrugated. The corrugations add stiffness which helps to resist creep and thermally induced distortions due to temperature or thermal expansion coefficient differences. As an added benefit, it has been unexpectedly discovered that the corrugations further increase the radiant efficiency of the burner. In a preferred embodiment, the reverberatory screen is both corrugated and made from ceramic composite material.

Abstract: A fluid powered rotary actuator (10) having a stator (13) and a rotor (15) journalled with limited rotary motion within the stator includes at least one arcuate chamber defined between the rotor and stator and has an angularly movable vane (16) fixed to the rotor. There is a seal member (21, 23) at the vane for slidingly sealing a cylindrical sidewall surface of the stator thereby subdividing the arcuate chamber into two variable volume subchambers (25, 29; 27, 31). Pressurized fluid is ported selectively to one of the subchambers while a fluid egress path for fluid from the other of the subchambers allows the rotor to move angularly within the stator. There is a fail-safe aperture (22) in the cylindrical stator surface in a region traversed by the seal member and for conveying fluid from a selected one of the subchambers, as determined by the position of the vane, and a fail safe valve (24) coupled to and normally blocking the egress of fluid from a subchamber through the aperture (22).

Abstract: An optic position sensor provides a data encoding method which improves the resolution capability of the sensing system. The data pattern of the sensor comprises a series of data signals having a start bit, digital data bits, an analog bit region (12) and a stop bit. The digital data bits may be a Manchester Encoded, Gray Coded data signal pattern. The analog data bit region (12) comprises a vernier track (10) which will produce a signal peak that moves linearly with position. The detection of the position of the vernier track (10) or bit relative to its range or region (12) provides a measurement of the percent of travel that has occurred within and between the discernible resolution of the digital data bits of the data signal, to provide resolution capability of approximately one part in sixteen thousand.

Abstract: This invention describes the infiltration methods used to incorporate ceramic additives in carbon/carbon brake disc preforms. Aqueous vacuum infiltration techniques were employed. Both methods were effective in achieving homogeneous dispersion of ceramic additives throughout brake disc thickness. Heat treatment processes were developed to convert oxide additives to more refractory phases. Both temperature and N.sub.2 overpressure were precisely controlled during conversion. By using the additives, infiltration routes, and heat treatment schedules, brake disc friction material performance properties such as friction coefficient, friction coefficient stability, and brake disc wear rate are improved. The disclosed carbon/carbon brake discs can be used in aerospace, automotive and other friction material applications.

Abstract: The integrated aircraft wheel, brake and axle comprises a hollow wheel and brake axle (16, 116) having longitudinal splines (17, 117) about its outer periphery, the longitudinal splines (17, 117) engaging splines (62, 162) of a piston housing (60, 160) to effect a non-rotatable connection therebetween. In one embodiment, the piston housing (60) is connected by way of a spline sleeve (70) with a backing plate (80). A wheel (45) is rotatably mounted upon an end of the brake axle (16) and includes a drum drive (52) which extends axially to a drum drive end (52A) having at its inner diameter a bearing assembly (55, 56) between the drum drive end (52A) and an outer diameter of the piston housing (60). In another embodiment, the drum drive (152) may include a thrust flange (151) engaging a rotor disc backing plate (192A).

Abstract: A drive key (10) for an aircraft wheel comprises a hardened and tempered steel member (10) having improved wear and corrosion resistance. The steel member (10) is coated selectively with a tungsten carbide-cobalt coating (22) to provide wear resistance at side portions (18) where the drive key (10) is engaged by portions of an aircraft brake, and the entire steel member (10) including the tungsten carbide-cobalt coating can be plated with electroless nickel to provide improved corrosion resistance.

Abstract: A convertible aircraft brake assembly (10, 60, 77, 78, 83, 85, 96, 120, 130) designed as original equipment to have heat sinks comprising a steel heat sink (20, 70, 80, 90, 91, 100, 110, 122) aircraft brake assembly and a carbon--carbon composite heat sink (40) aircraft brake assembly. When the aircraft brake assembly is converted from one type of heat sink to the other, the conversion is accomplished with minimal changes in component parts. The conversion can be accomplished without any changes in the piston housing (14), torque tube (12), and wheel (30) because the heat sinks include therein respective components which enable each heat sink to be utilized with the commonly used piston housing (14), torque tube (12), and wheel (30).

Abstract: A multi-disc brake comprises a piston housing (12) attached to a torque tube (16), a plurality of stator discs (18) engaging the torque tube (16) and a plurality of rotor discs (20) positioned about the torque tube (16) for engagement with a wheel. The torque tube (16) includes a flange (17) having a plurality of over-sized openings (31) with each opening (31) receiving therein a bushing (33, 55). A fastener (40) comprising a nut (44) and bolt (40) extends through each over-sized opening (31) and bushing (33, 55), and compresses a bearing plate (38, 48) against the bushing (33, 55) which is captured between the bearing plate (38, 48) and piston housing (12). The slightly over-sized openings (31) in the torque tube flange (17) allow tangential and radial slippage at the area where the torque tube flange (17) contacts the bearing plate (38, 48) during braking, so as to dampen vibrations which occur during braking. The bearing plate (48) may be segmented into arcuate segments (48a, 48b, 48c).

Abstract: A ceramic hot-gas candle filter having a porous support of filament-wound oxide ceramic yarn at least partially surrounded by a porous refractory oxide ceramic matrix, and a membrane layer on at least one surface thereof. The membrane layer may be on the outer surface, the inner surface, or both the outer and inner surface of the porous support. The membrane layer may be formed of an ordered arrangement of circularly wound, continuous filament oxide ceramic yarn, a ceramic filler material which is less permeable than the filament-wound support structure, or some combination of continuous filament and filler material. A particularly effective membrane layer features circularly wound filament with gaps intentionally placed between adjacent windings, and a filler material of ceramic particulates uniformly distributed throughout the gap region. The filter can withstand thermal cycling during backpulse cleaning and is resistant to chemical degradation at high temperatures.

Abstract: A device (10) for changing the focus and field of view of an optical device having an optical element (19, 21) which is movable grossly to change field of view and movable incrementally to change focus of the device (10) with either field of view includes an operator actuatable control system for varying incrementally the axial position of this optical element within each of the regions to focus the optical device in each field of view mode. The device (10) includes a control knob (31), a threaded shaft (33) coupled to the control knob (31), a pair of stop members (37, 39) engaging threadedly the threaded shaft, and a linkage (45, 53, 49, 63, 59, 55, 67, 69) for converting axial motion of a stop member along the threaded shaft to incremental movement of the movable optical element along the primary optical axis (29).

Abstract: A multi-disc brake (30,60) includes a piston housing (32,62) and attached torque tube (34,64) located about an axle (67,97). Axially adjacent the piston housing (32,62) is a brake actuator (40,70). In one embodiment, the piston housing (32) is located axially between an actuator member (59A) of the brake actuator (40) and a thrust sleeve (20) located about the axle sleeve (19) and abutting a wheel sleeve (16) engaging a wheel bearing assembly (12). In another embodiment, the actuator member (89A) can extend to engage a stationary portion (91) of the axle (97).

Abstract: A system (10) for controlling the quality of the cabin air in an aircraft of the type having a cabin air recirculating system (37, 43) which introduces selectable amounts of fresh outside air, an arrangement (25, 27) for venting controllable quantities of cabin air to the atmosphere, and a source of oxygen-rich air (49). The system (10) includes sensors for monitoring the partial pressure of carbon dioxide (15) in the cabin air, the partial pressure of oxygen (17) in the cabin air, the humidity (19) of the cabin air, and the total air pressure (21) of the cabin air, and an air quality controller (23). The air quality controller (23) includes at least four inputs, one input connected to each of the sensors, and at least two outputs, one output connected in controlling relationship to the source (49) of oxygen-rich air and another (47) connected in controlling relationship to the cabin air recirculating system.

Abstract: A control system (10) for a limited stall load actuator (60) comprises a servo pressure regulator (20), solenoid valve (40), relief valve (30) and a shuttle valve (50) connected with a piston actuator 60 such that when source pressure P1 is declining the servo pressure regulator (20) will open to permit more flow and maintain a minimum actuation force effected by the actuator (60), and should there occur a failure of the servo pressure regulator (20) that would permit high source pressure to be communicated to the control system (10), the relief valve (30) will operate to limit the amount of high pressure communicated to the control system (10) such that the actuator (60) will attain no greater than a predetermined maximum output force.

Abstract: A noise cancellation system which balances the photocurrents derived by a measurement signal and a reference signal of a sensor. The invention has application in any measurement device which detects a small signal in combination with high noise content and further utilizes a reference signal.

Abstract: A piston shoe (10) of an axial piston pump or motor is crimped to an annular piston head (42) and has a flat shoe wear surface (12) that contacts a cam plate (22). A back flange (14) of the shoe (10) also wears against an auxilliary cam plate (24). In order for the piston shoe (10) to operate within a fuel environment, the piston shoe (10) must be corrosion resistant, compatible with fuel, and provide the desired wear resistance. The piston shoe (10) is made of a cold workable cobalt based alloy which is compatible with fuel and provides corrosion resistance. The wear surface (12) which bears against the cam plate (22) and the back flange (14) which bears against the auxilliary cam plate (24) are provided with a thermal diffusion boride treatment which provides the desired wear resistance. In order to restore sufficient ductility to flange (16) of the shoe (10) that will be cold worked, a solution treatment is performed at a temperature range of 2050.degree. to 2250.degree. F. in a non-oxidizing environment.

Abstract: A fuel system including a fuel pump for supplying fuel from a source through a variable orifice flow metering valve and then through a variable orifice pressurizing valve to an engine utilizes a determination of the pressurizing valve orifice area to ascertain the fuel flow through the pressurizing valve. The pressurizing valve includes a movable piston with a piston section movable linearly to open and close selectively an orifice. The pressurizing valve may take the form of a cylindrical cavity with the piston reciprocable therein. The cavity is provided with an Inlet port and at least one sidewall outlet port and the piston section slidable along the sidewall outlet port to increase and decrease selectively the effective size of the orifice. A transducer is coupled to the piston to provide an indication of piston position. A second piston section for opening and closing selectively a second orifice may be provided.

Abstract: Enhanced directional stability in an aircraft anti-skid braking system is achieved by using one common deceleration command (16) which is a selected one of left and right brake pedal deceleration commands (19, 119). The individual brake pedal deceleration commands (19, 119) are used to modify (34, 134) the common or selected deceleration command (16) and provide respective side wheel velocity commands to retain a differential braking capability (36, 136), and thereby avoid the potential for instability inherent when utilizing individual deceleration commands for the left and right wheel brakes of an aircraft.

Abstract: A multi-disc brake (80) includes a piston housing (102) and attached torque tube (94) located about an axle (87). Integrated within the piston housing (102) is a brake actuator (90). The piston housing (102) is located axially between an actuator member (98) of the brake actuator (90) and an axle sleeve (109) and radial portion 87a of the axle (87). Hydraulic actuation of the brake actuator (90) displaces axially the actuator member (98) against a stationary thrust sleeve (99) such that the piston housing (102) is compressed between the actuator member (98) and axle sleeve (109), thereby reducing torsional vibrational movement of the piston housing (102) and torque tube (94) about the axle (87).

Abstract: An aircraft brake assembly (10) comprises a torque tube (12) connected with a piston housing (14), and a heat sink (50) comprising friction material stator discs (22, 24, 26, 28, 30) connected non-rotatably with the torque tube (12) and friction material rotor discs (40) for connection with a wheel. The piston housing (14) includes a plurality of circumferentially spaced-apart pistons (16) for compressing the heat sink (50) during braking. Because of size limitations imposed upon the piston housing (14), fluid passages (23) in the piston housing (14) are offset or cross-drilled and terminate at piston housing bosses (15) located circumferentially between the pistons (16) and facing the pressure plate or adjacent friction material stator disc (30).

Abstract: A mechanical governor for use in a fuel management system having a fuel metering loop responsive to an electronic computer for supplying fuel to a combustion chamber of a turbine. The mechanical governor includes a cylindrical spinning spool valve assembly located in a bore which is responsive to an operational force derived from the rotation of the turbine. In a first mode of operation, communication of control pressure P.sub.c to an integrator valve assembly is inhibited by a first spring associated with the spool valve assembly while in a second mode of operation communication of an operational fluid pressure P.sub.x derived from the control pressure P.sub.c is communicated to the integrator valve assembly after an operational force corresponding to the rotation overcomes the first spring. In the first and second modes of operation, fuel is supplied to the combustion chamber as a function of a pressure differential across the fuel metering loop.