Abstract: A non-toxic corrosion resistant conversion coating for aluminum is formed by a process which includes subjecting the aluminum to an acidic aqueous solution containing potassium permanganate and cerous chloride, alone or in combination with strontium chloride. The corrosion resistance is improved by a subsequent treatment in an alkaline solution containing molybdate, nitrite and metasilicate ions. The corrosion resistant is further improved by treating the coated surface with an acholic solution containing glycidoxy(epoxy)polyfunctionalmethoxysilane, alone or in combination with phenyltrimethoxysilane. The coating thus produced is a mixture of oxides and hydroxides of cerium strontium and aluminum. These oxides and hydroxides may also be intermixed with molybdate silicate and nitrite ions. In the most corrosion resistant form the mixture further includes a silane overcoat.

Abstract: A non-toxic corrosion resistant conversion coating for aluminum is formed by a process which includes subjecting the aluminum to an acidic aqueous solution containing potassium permanganate and cerous chloride, alone or in combination with strontium chloride. The corrosion resistance is improved by a subsequent treatment in an alkaline solution containing molybdate, nitrite and metasilicate ions. The corrosion resistant is further improved by treating the coated surface with an acholic solution containing glycidoxy(epoxy)polyfunctionalmethoxysilane, alone or in combination with phenyltrimethoxysilane. The coating thus produced is a mixture of oxides and hydroxides of cerium strontium and aluminum. These oxides and hydroxides may also be intermixed with molybdate silicate and nitrite ions. In the most corrosion resistant form the mixture further includes a silane overcoat.

Abstract: A non-toxic corrosion resistant conversion coating process for aluminum and aluminum alloys which includes subjecting the aluminum to an aqueous solution containing hydrogen peroxide or cerous chloride, alone or in combination with strontium chloride. The corrosion resistance is improved by a subsequent treatment in an alkaline solution containing molybdate, nitrite and metasilicate ions. The corrosion resistant is further improved by treating the coated surface with an acholic solution containing glycidoxy(epoxy)polyfunctionalmethoxysilane, alone or in combination with phenyltrimethoxysilane. The coating thus produced is a mixture of oxides and hydroxides of cerium, strontium and aluminum. These oxides and hydroxides may also be intermixed with molybdate silicate and nitrite ions. In the most corrosion resistant form the mixture further includes a silane overcoat.

Abstract: A corrosion and crack growth inhibitor is disclosed, the inhibitor being relatively non-toxic as well as unreactive with curable elastomeric materials so as to form a coating composition for application to metal surfaces. The inhibitor comprises a curable polymer material, such as epoxy polyamide, and cerous molybdate in the amount of from about 1 to 15 percent by weight of the inhibitor.

Abstract: An ultrasonic liquid quantity measuring apparatus directs a collimated beam of ultrasonic energy from a transmitter transducer (14) through a conveyor (15) into the liquid (11) in a container (10) perpendicular to the top liquid surface. The ultrasonic beam travels with little loss through a tube (20) connected to the conveyor (15) until it reaches the top liquid surface. At this time the energy is reflected and detected with a receiver transducer (14). A microprocessor (34) measures the total signal round trip travel time representing the height of the liquid (11). Using several ultrasonic transducers (14) and knowing the size and shape of the container (10) the quantity of liquid (11) in the container (10) is accurately determined. A calibration (known reflected signal time) transducer (14a) is used to compensate for the change in propagation velocity due to temperature change in the liquid (11).

Abstract: There is disclosed and shown an automatic nut installation and torquing system (10) connected with an automatic fastener installation machine (11) whereby a threaded nut (21) is automatically conveyed in proper orientation from a supply source to a final installed position on a threaded fastener (34); the installed nut (21) being at a selectively predetermined final torque value that is selectively variably and controllable without regard to the torque output of the torque motor (48) so long as the desired installed torque value of the nut (21) does not exceed the maximum torque deliverable by the torque motor (48). The variability and controllability of installed torque is accomplishable without any recalibration or readjustment of torque motor (48) to change its torque output.

Abstract: A probe (P) capable of sensing acoustic and hydrodynamic pressures in a heated flow field and an associated apparatus for acoustically exciting the heat flow (35), for positioning the probe (P) within the flow field and fro acquiring data. The probe (P) consists of a miniature microphone (10) mounted in an assembly which provides direct water cooling to the microphone body and which, by means of a bullet nosed extension (23, 24) with lateral ports (25), protects the microphone element (10) from direct impingement of the flow (35). Acoustic excitation of the flow (35) is introduced upstream of the nozzle (34) through a tube (37) from an externally mounted acoustic driver (36) which responds to the amplified output of a signal generator (38); the signal generator (38) and the amplifier (39) are adjusted to control the frequency and amplitude of the excitation. A traversing mechanism (32), capable of movement in three orthogonal directions is used to position the probe (P) within the flow (35).

Abstract: This invention relates to a flexible, rolling track assembly (12) that carries and keeps aligned various flexible conductors, as exemplied by electrical, coolant and hydraulic lines, extending between locations (13,14) associated with a machine (15) that is movable along guides or rails whereby the relative spacing between the locations (13,14) is constantly changing by increasing or decreasing as the machine (15) travels along the guides or rails; and more particularly, the invention concerns a structure arrangement (10,11) that functions as a self-erecting support for the track assembly (12) as the portion of the track assembly (12) to which the structure (10,11) is connected rolls upwardly to an elevated position, while vice-versa, the structure arrangement (10,11) functions as a self-retracting track assembly support as the portion of the track assembly (12) to which the structure is connected rolls downwardly to a retracted position.

Abstract: A sealant applicator assembly (20) for mounting to an automatic drilling and fastener installation machine to apply sealant to the tip or shank surfaces of varying grip-length fasteners (24,53) before "wet" installation of the fastener into a hole. The assembly includes a pair of valve members (32,35) controlling the flow of sealant into contact with the fastener shank: one valve member (32) being opened or actuated by physical engagement between the valve member and the fastener tip when the shank length of the fastener being installed is sufficient to engage the valve member; and a second valve member (35) being opened or actuated by engagement of means (52) on the fastener installation machine when the shank length of the fastener being installed is insufficient to permit physical engagement between the fastener tip and the first valve member.

Abstract: Aircraft wing fatigue life and weight are strongly influenced by maximum wing root bending moment. The object of the invention is to augment the wing root bending moment relief that can be provided by the deflection of aircraft ailerons (12) in the conventional manner, while reducing or eliminating aileron induced wing torsional loading. To accomplish this, a movable aerodynamic control surface (14) is mounted on the outboard side of a contoured boom (13) situated at each wingtip. The exact size and location of the control surfaces (14) are determined by the particular aircraft application. Control surface size is a function of the aircraft aileron size, and each control surface (14) is located ahead of the elastic axis (10') of the wing (10). In addition to providing load alleviation, asymmetric deflection of the wingtip control surfaces (14) creates an aircraft rolling moment that adds to that produced by aileron deflection.

Abstract: An apparatus and method is disclosed for the fabrication of cylindrical structures (26) by filament winding of resin impregnated filaments around a novel cylindrical mandrel assembly (10) whereby the mandrel assembly (10) and fabricated cylindrical structure (26) are easily separated after curing of the resin impregnated materials.The invention utilizes an inner, hollow cylindrical mandrel member (11) onto which a metal cable (12) is wound over afterwhich segmented outer mandrel sections (13) are connected to the inner mandrel member by fastener devices (20) installed from the inner side of the inner mandrel member (14). The resin impregnated filament is then wound over the outer mandrel segments (13) and cured in a conventional manner. After curing, the fasteners (20) are removed from the inner side of the inner mandrel (11), and the cable (12) is removed by pulling it from one end of the mandrel assembly (10).

Abstract: A hydraulic isolation valve (10) will not open if leaks are present in the associated utility subsystem (15). The continuity of the hydraulic fluid circuit actuates the valve (10) to the open position by an energized solenoid operated pilot valve (21) sending a small flow through a fuse (23) and one-way restrictor (24) to the utility function (15). If no leaks are present, the utility function (15) begins to actuate sending return flow through a two-way restrictor (31) and moving a continuity actuation piston (28) to push the shut off spool (16) to the open position so that full flow is admitted to actuate the utility function (15). If the continuity of the hydraulic circuit is broken by leaks, the return flow does not reach the continuity actuation piston and the shut off spool (16) remains in the shut off position, the fuse (23) closing to block further flow and then resetting by spring action when the solenoid operated pilot valve (21) is deenergized so that actuation may be attempted again, if desired.

Abstract: A drain valve assembly is mounted in the bottom of a fuel tank (10) to allow draining of condensate. The tank (10) is drained of fluid by the use of a tool (27) pushed upward against the piston (18) of the valve assembly separating it from its seat (15) in the valve housing (12) allowing liquid which has entered the housing (12) from the tank (10) through openings (16 ) to exit around the periphery of the unseated valve. If the valve assembly base is struck by lightning, a blast pressure occurs that can drive the poppet of a standard valve open allowing the electrical energy to enter the tank (10) causing a potential explosion. With the present valve assembly the pressure is allowed to pass through passage (20) in the piston (18) to apply a closing force on the surfaces (21, 22) and the inner end of the piston (18) which is greater than the opening force due to the area difference and the valve assembly remains closed.

Abstract: The object of the invention is to provide a coupling for fluid conveying ducts which has built in capability to allow for radial and/or angular misalignment of the ducts which it is coupling and also retain axial flexibility. Such coupling includes a pair of interconnectable coupling half assemblies each with eccentric openings (17) for passage of one of the tube ends (10) therethrough with their associated ends in spaced relation. These coupling half assemblies also may include abutting faces disposed in a plane (P) oblique to their longitudinal centerline (C). Relative adjustment of the eccentric openings (17) provides radial adjustment of the tubes (10) while relative adjustment of the coupling half assembly faces along the plane (P) provides angular adjustment of the tubes (10). Any combination of axial, radial, and/or angular misalignment of the tubes (10) within the dimensional envelope of the coupling can be accommodated by manipulation of the parts relative to each other.

Abstract: An adhesive is provided which comprises a thixotropic binder (24) containing metallic particles (23) of discrete size and specific density concentration. When used to bond faying surfaces (13 and 21/10 and 21) this adhesive is capable of conducting electrical currents on the order of 200,000 amps while withstanding structural loads on the order of 5000 psi. It has particular application in a highly volatile environment such as the skin panel (10) of an aircraft component housing an integral fuel tank (12). Lightning strike currents are thereby conducted in a controlled path (P) adjacent the exterior surfaces (S) of the component as defined by the parts (10, 13, 17 and 21) and arcing inside the fuel tank (12) is avoided.

Abstract: A door locking mechanism is formed by a pair of locking elements (19 and 20) carried by a bolt (18) on the door (12) and on the adjacent structure (10) respectively. The locking element (19) is movable into and out of engagement with the lock receptacle (20) by reciprocation of the bolt (18). Such movement is restricted and controlled by a rotary sleeve (23) having lands (22) which coact with and are complemental to mating lugs on the bolt (18) which assure and maintain the locked and unlocked condition of the door (12) through the locking elements (19 and 20). Actuators (15' and 31) are provided to rotate the sleeve and reciprocate the bolt (18) respectively in a selected sequence whereby door locking and unlocking is accomplished.

Abstract: Two airplanes (A and B) combine in aerial maneuvers to accomplish pick up, transport and delivery of a payload (10) from and to designated surface locations (11). The payload (10) is connected to, carried in the open by and disconnected from the ends of cables (15) extending from each airplane during the aerial maneuvers. Such airplane maneuvers include orbiting 180.degree. apart while banking at prescribed angles to effect substantially vertical lifting and lowering of the payload (10) relative to the pick up and delivery surfaces (11).

Abstract: An improved air/oil shock absorber (16) especially adapted for aircraft landing gears (11) is provided whereby the rate of strut (14) compression is programmed separately for the landing impact and for rollout after the landing. During the landing impact, increased tail clearance is achieved by temporarily delaying the last few inches of compression. After the aircraft rotates on to the nose landing gear, the shock absorber (16) slowly compresses to its static position where it then functions in a conventional manner. The shock absorber assembly (16) may be oriented in any position with respect to the aircraft (10) by virtue of two internal air/oil separator pistons (24 and 29).

Abstract: A hand held apparatus for automatically identifying a hybrid or monolithic integrated circuit or any standard circuit module having a known pin configuration (10) and an unknown identity. A plurality of test instructions (FIG. 6 ) for devices of known identity are stored in a test procedure memory (22) and sequentially provided (125) to the unit under test until the unit either passes a test thus revealing its identity (137) or fails all tests in the memory (145). The socket (10) is connected to a pair of peripheral chips (25a, 25b) having pin definable input/output ports (46, 65, 66) which are used selectively to treat any pin as input, output, or supply.