Abstract: A wire detector for semi-automatic wire stripper which responds to capacitance changes caused by sensing a capacitance object such as an exposed wire end and includes signal processing through an oscillator and amplifier circuit providing timer control for activating a relay driver circuit for an adjustable duration time period. The wire touch sensor circuit relay driver is then coupled through a mercury wetted relay which provides electrical isolation from external (switched) voltages to an air solenoid which when actuated allows the pneumatic mechanism of the wire stripper to cycle through its functions of wire stripping.

Abstract: A broadband high temperature radome includes a high density outer skin layer and a low density core layer made from a ceramic material selected from the group consisting of silicon nitride and barium-aluminum silicate. Silicon nitride is sintered, reaction-sintered or chemically vapor-deposited. The outer skin has a moderate dielectric constant of about 5.0 and the core layer has a low dielectric constant of about 1.8. Both dielectric constants do not sigificantly vary at temperatures up to 1500.degree. C. Low thermal expansion of the core and skin layers are matched by the thermal expansion of a base connector constructed in a laminated form of graphite/polyimide. The thickness of the core layer to the thickness of the skin layer is given by the ratio of about 15:1 where the skin layer thickness is about 0.030 inch. Polyimide resin is used for the high temperature adhesive to adhere the connector to the core and skin layers. The core layer is impregnated with a dielectric filler, if desired.

Abstract: A retainer has tabs which hold a pin and socket in good electrical contact until a separation force applied to the pin and socket exceeds a predetermined amount and breaks or bends the tabs, thereby ensuring a predictable separation of the pin and socket in response to large separation forces.

Abstract: The control system includes a schedule (54) which plots airspeed versus stabilizer angle for a trim condition. Following a pilot adjustment of the stabilizer angle to establish trim, the schedule (54) plots the trim airspeed to obtain a stabilizer angle value. A change in airspeed from trim is sensed by a sensor (52) and the schedule (54) plots the new airspeed on the same graph to obtain a new stabilizer angle value. The schedule (54) determines a change in stabilizer angle signal in the form of increments of movement of the stabilizer control actuator (28) to return the stabilizer (18) to a trim condition. A schedule (40) in the system also senses any change in the rate of change of altitude from trim and computes from this change a second signal in the form of increments of actuator movement. There is an algebraic summation of these two signals and a stabilizer angle feedback signal to produce a command signal.

Abstract: A locking clamp (10) is provided for preventing loosening of two threadedly coupled members (18, 20). The clamp (10) has a band (36) that encircles one of the members (18) around an outer cylindrical surface thereof. A pin assembly (62) prevents circumferential slipping of the band relative to this surface. An indexing member (48) connected to the band is engaged with the second coupled member (20) and thus prevents rotation of the second member relative to the first.

Abstract: Design and construction of a composite material airplane having a high aspect-ratio wing and a horizontal double-lobe fuselage cross-section for cargo and/or passenger accommodations. The fuselage comprises a double-lobe shell of contoured honeycomb core composite panels and an interior vertical plane centerline web forming a divider between the lobes. Piano-hinge type joints are utilized for multi-panel junctures to provide uniform load distribution across the junctures. The piano-hinge juncture utilizes hinge lugs which are dimensioned to interface sequentially along the hinge axis, and the hinge lugs are interconnected by a tubular hinge pin.

Abstract: Phase I (25) and Phase II (20) and III (24) AFRS (Automatic Fault Reporting System) signal processing implementations (FIG. 3) of fault related data permits utilization in steps, viz. Phase I and Phases II and III on board operational aircraft of AFRS, thereby permitting gradual phase in and substitution of AFRS for present state of the art flight crew FRM (Fault Reporting Manual) and ground personnel FIM (Fault Isolation Manual).

Abstract: A hand-held router is provided that includes a motor with a router bit mounted on the motor in driven relationship. A router head is attached to the motor an at least partially surrounds the router bit. A device for controlling the depth of cut of the router bit is mounted on said router head as is a device for adjusting a second parameter of the cut. In one embodiment, the second controlled parameter is the width of cut made by the router bit. Preferably, a guide block is also movably affixed to the cut width adjustment device and acts as a guide to maintain the uniformity of cut of the router bit. The guide block is adjustable to accommodate workpieces of different thickness. In a second embodiment, the second controlled parameter is the angle of the cut. The router head is adapted for receiving an angular adjustment plate that can be used to determine the angle of attack of the router bit on the workpiece.

Abstract: An intrusion detection system that comprises a transmission line for RF energy, a transmitter coupled to one end of the transmission line to supply pulses of RF energy into the line, and a range gated doppler receiver for receiving RF energy from the other end of the transmission line. The receiver includes means for producing a detection signal indicating the presence of doppler components in a range gated portion of the RF energy received from the transmission line.

Abstract: A method of welding together graphite fiber reinforced thermoplastic laminates. The process allowing immediate application of graphite thermoplastic materials for the building and assembly of primary and secondary structural parts used with aircraft airframes and similar structures.

Abstract: Fastener, e.g., stud, installation in a composite panel, such as a graphite epoxy structure having a longitudinal electrical conductivity substantially greater than the transverse electrical conductivity, is achieved in a manner providing increased conductivity between fastener assembly and the panel to which it is attached. Through panel countersink and fastener configurations, e.g., by use of frustro conical countersink to spherical fastener surface configurations, increased electrical contact is made to conductive fibers in the composite material which run at right angles to the central axis of the fastener.

Abstract: The system generally includes an electrochemical pump for pressurizing a cryogenic gas, a heat exchanger for cooling the gas to below its inversion temperature, a Joule-Thomson flow restrictor to cool the gas by adiabatic expansion, a load heat exchanger that is thermally coupled to an electronic component or surface that requires cryogenic cooling, and a low-pressure flow path back to the pump. One or more reservoirs can be provided in the high-pressure and low-pressure flow paths. The flow paths can be thermally coupled by one or more regenerative heat exchangers. The electrochemical pump can be adapted to transport either protons or hydronium ions. Protons are preferably transported using pump components that do not contain water in any chemical form. Either hydrogen or oxygen can serve as the cryogen.

Abstract: An apparatus for controlling flow over a surface, especially transonic flow, including means for embedding within the surface small vortices with their axes parallel to said surface and transverse to said fluid flow, and means for driving said vortices.

Abstract: A pair of cold air driven tubines are mounted in-line with each turbine driving one of two coaxial drive shafts. Each drive shaft is independently supported and separate drive air is supplied to each turbine such that the direction and speed of rotation of each drive shaft is independently controlled. Exhaust air from the forward turbine vents through an exhaust cavity that surrounds the aft turbine. Inlet drive air to the aft turbine is supplied via air ducts formed through the center of struts which extend radially from the inlet of the aft turbine, through the exhaust cavity and to an inlet port external to the turbine housing.

Abstract: A system and related methods for passively detecting range and/or elevation of a signal emitting target by employing an X-beam antenna system which has a fixed angle .theta. between planes of receipt and which rotates those planes of receipt at a rate of sweep .gamma.. A first correlator is employed to measure the time delay .DELTA.T.sub.1 between receipt of a signal directly from a target in the first plane of the X-beam and receipt of a signal from the target in that first plane but reflected from a remote surface. A second correlator is employed to measure the time delay .DELTA.T.sub.2 between receipt of a signal from the target in the first plane and subsequent receipt of a signal from that target in the second plane as the first and second planes rotate. Receiver altitude R.sub.H is measured by conventional means and thereafter target range and/or elevation is calculated in response to .theta., .gamma., .DELTA.T.sub.1, .DELTA.T.sub.2 and R.sub.H.

Abstract: A pulse height counter for counting the number of excursions of an incoming analog signal through each of a plurality of amplitude ranges. The pulse height counter automatically records not only the number of excursions through each amplitude level, but also records the number of amplitude excursions for each of a plurality of intervals. An analog input signal to be analyzed is synchronously applied to each of a plurality of comparators (VCO - VCF), which have reference voltages that are related so as to define predetermined amplitude ranges. During a count cycle, a counting circuit (CO - CF) receives the output signals from each of the comparators and produces a set of count data that indicates the number of occurrences of the analog input signal within each of the amplitude ranges. The count cycle is followed by a write cycle, during which the count values are stored in separate data bins, or event memories (MO - MF).

Abstract: An airfoil having a trailing edge flap assembly comprising a flap member having a pair of tracks mounted thereto at spanwise spaced locations. Each track member is operatively connected to a slide member which is in turn mounted to a stationary structure. The flap member is attached to the two track members by means of pivotal links and ball joint connections to alleviate problems relating to wing deflection and also differences in linear movement of the flap member due to conical movement from the stowed to the deployed positions. Other embodiments show specific features relating to the actuating means, the track location, and the slide member location.

Abstract: A method and apparatus selects the minimum value of a sequence of power measurements taken from each range of a radar's target area. This is preferably performed for two channels of a radar, and the minimum values of both channels for each range are compared to determine the likelihood of a target in each range. Once such likelihood is established, then further processing takes place with regard to ranges with high likelihoods of having targets. The determined minimum value for each range may also be used to normalize each range's power measurements, while preserving phase information, for moving target detection.

Abstract: Apparatus for adjustably mounting an ejection seat (16) in an aircraft in which outer catapult cylinders (58, 60) support inner catapult cylinders (62, 64) and supply force to the inner cylinders to eject the inner cylinders and the seat from the aircraft, the inner cylinders being connected to an upper rear end of the seat (66, 68). The seat (16) is supported in the aircraft by the inner and outer catapult cylinders (62, 64, 58, 60), by adjusting actuators (40) to raise and lower and to tilt the seat forwardly and rearwardly, by lower anchor links (30) pivotally connected to the aircraft and to lower end (26, 28) of the outer catapult cylinders and to the actuators (40), and by upper links (50). The seat is connected to the catapult cylinders (58, 60) by slipper blocks 82. The slipper blocks (82) are pivotally connected to the seat by pins (84) and are slidably engaged with the outer catapult cylinders.

Abstract: In the operation of modern tactical aircraft, crew members are subjected to periodic high acceleration loads that cause fatigue and a decrease in operating capacity. Restraining the torso of a crew member and pulling the crew member back against the ejection seat (2) of the aircraft would help prevent such fatigue. Known restraint and haul back apparatus for use during ejection are not adapted for repeated in flight use. The invention provides a single mechanism that retracts torso restraint straps (6) any number of times during in flight maneuvering and also retracts straps (6) for ejection. A loop (7) of each strap (6) extends around an inflatable member (28). When in flight acceleration loads exceed a preset limit, engine bleed air inflates member (28) to expand loops (7). This retracts straps (6) and positions the crew member. Member (28) is allowed to deflate when the acceleration subsides. When the ejection procedure is initiated, a gas generator (44) inflates member (28).