Abstract: A system for curing advanced composite workpieces including a portable heat gun that provides a flow of heated air against a workpiece. The heat gun is controlled to direct a flow of heated air against an advanced composite workpiece at a predetermined temperature for a predetermined time period and upon cessation of the time period to thereafter direct an unheated flow of air against the advanced composite for a second period of time thereby causing a resin component of the advanced composite to flow within the composite in a prescribed manner and to cure to a desired hardness.

Abstract: A point focus solar concentrator which uses various geometries of cylindrical reflector strips some of which are tilted to simulate a point focus by overlaying the line focii of each segment at a coincident point. Several embodiments of the invention are disclosed that use cylindrical parabolic, cylindrical hyperbolic or flat reflector strips to concentrate incident solar energy for use by a solar dynamic engine located at the focal point. Also disclosed is a combined photovoltaic/solar dynamic engine concentrator energy system that uses this arrangement of mirrors.

Abstract: A thermostat (10) comprising a metal hydride (26) encased in a bellows (16) and a second bellows (20) encasing available hydrogen gas (32) to be adsorped and desorped by the metal hydride (26). The metal hydride (26) mechanically expands its encasing bellows (16) during adsorption and contracts during desorption of the hydrogen gas while a change in gas pressure due to this adsorption/desorption expands and contracts its encasing bellows (20). Each bellows (16,20) is oppositely acting and each engage a valve seat (36,40), respectively, so that the flow of fluid is directed alternately through one valve seat opening or the other depending upon temperature affecting the gas absorping/desorping properties of the metallic hydride. The temperature at which the thermostat (10) operates may be adjusted by controlling the pressure of the gas in the gas bellows. Also disclosed is a variation of the invention as a thermal switch for space applications.

Abstract: A space rail (10) having two basic elements, a box structure (12) which is configured to permit installation of payload hardware and payload services hardware along its length and a deployable back structure (14) which provides stiffness to the assembly of space rails when deployed. The box structure (10) is preferably a flat rectangular frame comprising body members (12) and the back structure (14) comprises a plurality of struts (24a-d, 30) pivotally attached to the body member (14) and to each other so as to fold into a retracted deployable position and to be deployed (unfolded) by a suitable mechanism.

Abstract: An apparatus for seating and tightening clamps around joints between tubular sections comprises an elongate flexible member such as a chain for extending around a clamp positioned over a joint, the member having rollers spaced along its length, and a tightening device for applying tension to the member to tighten it around the clamp so that the rollers roll around the surface of the clamp and apply a radial force to the clamp.

Abstract: A logic driver having control circuitry for receiving an input bistate data bit and providing power at an output at first and second predetermined voltage levels when an input bistate data bit is respectively of first and second states. Sensing circuitry is coupled to the control circuitry for detecting the level of current at the output and providing a corresponding current level indication. The driver further includes overcurrent circuitry, responsive to the current level indication, for generating an overcurrent command when the output current exceeds a predetermined level. The control circuitry is responsive to the overcurrent command for disabling the output of power at the corresponding predetermined voltage level at the output.

Abstract: A method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position. Discrepancy parameters are introduced to indicate misalignment between missile and launching platform (or ship) inertial frames where the missile onboard executive computer simultaneously processes the data provided from missile onboard sensors and target relevant data uplinked from the launching platform. The discrepancy parameters are employed to construct correction factors used to reduce the discrepancies. This updated missile configuration is then coupled with the target state estimator outputs to reconstruct smoothed line-of-sight (LOS) angles for terminal homing engagement.

Abstract: An endless track (52) for a track laying vehicle has a construction that facilitates replacement and repair of track components as well as providing an extended lifetime of use as compared to conventional vehicle tracks. The components of the track which facilitate its construction and maintenance include a track shoe (60), a replaceable road pad (62) for the track shoe (60), a pin assembly (64) for connecting laterally aligned pairs of the track shoes (60), a hollow pin (66) of the pin assembly (64), a center guide (68) that guides the track on the associated vehicle roadwheels, an end connector (72) that connects ends of the pins (66) associated with adjacent shoe assemblies (70), and a center connector (74) that cooperates with the end connectors (72) in connecting the shoe assemblies (70).

Abstract: An endless track (52) for a track laying vehicle has a construction that facilitates replacement and repair of track components as well as providing an extended lifetime of use as compared to conventional vehicle tracks. The components of the track which facilitate its construction and maintenance include a track shoe (60), a replaceable road pad (62) for the track shoe (60), a pin assembly (64) for connecting laterally aligned pairs of the track shoes (60), a hollow pin (66) of the pin assembly (64), a center guide (68) that guides the track on the associated vehicle roadwheels, an end connector (72) that connects ends of the pins (66) associated with adjacent shoe assemblies (70), and a center connector (74) that cooperates with the end connectors (72) in connecting the shoe assemblies (70).

Abstract: A metal skin trimming device which cuts an edge of a first metal skin to a net shape that is complementary to the edge of a second metal skin that has been previously attached to a frame, such as the airframe of an aircraft fuselage. A guide carried by the device is adjustable to set the gap that will appear between the edges of the first and second metal skins when they are attached as by riveting to the airframe.

Abstract: A tool for removal of round internally threaded collars from high efficiency aerospace fasteners. The tool includes a central cylindrical pin having a head at one end held against rotation, a non-round extension at the second end and a transverse bore intermediate the ends, containing a ball which is spring biased to project slightly beyond the pin wall. A mandrel assembly surrounds the pin and is rotatable relative thereto. A gripping collet is positioned between the mandrel and pin with collet fingers at one end extending beyond the mandrel and a threaded second end threaded into said mandrel. An axial slot in said collet is adapted to receive said ball when aligned therewith to form a releasable latch mechanism. In operation, the open collet fingers are placed over a threaded collar with said extension in engagement with a corresponding recess in the end of the bolt within the collar. The socket and mandrel are rotated in the collar unthreading direction.

Abstract: Metallic insulation for superconducting magnets to provide coil to coil and pancake insulation. Exemplary metal alloys and an anodization coating for such insulation are identified and may be selectively removed to provide shunt current paths. The coating for such insulation may be selectively removed to provide shunt current paths when the coil experiences a quench condition to preclude coil damage. Various applications of metallic insulation to superconducting coils are discussed.

Abstract: A missile support structure comprises at least two sabots or packing bodies which surround a missile in a launch tube and extend along at least part of its length. The sabots substantially fill the gap between the outer surface of the missile and the walls of the launch tube to restrict lateral movement. A capture assembly is provided to capture the sabots at the launch tube exit as the missile leaves the tube, and a return mechanism is provided on each sabot for intercepting the missile exhaust flow to urge the sabots back down into the launch tube.

Abstract: A variable microwave power divider which includes an orthomode transducer having a first section capable of supporting a vertically polarized wave and a second section capable of supporting two orthogonal linearly polarized waves. Suitable probes for inserting or extracting RF energy are coupled to each section. A similar orthomode transducer is connected to the first transducer through a circular hollow waveguide with the transducers being angularly offset from one another a predetermined angular amount. A septum is positioned within the waveguide which is fixed thereto at one end with the other end being controlled to a predetermined spiral configuration in order to direct RF energy flowing through the waveguide to the sections of one transducer in a determinable manner.

Abstract: An attachable, ablating shield comprises a metalized sheath for fitting closely over, for covering, and for protecting an electronics section in a missile from external electromagnetic radiation, particularly from high-energy radio frequency radiation, during launch. The sheath has weakened seams so that the sheath will separate from the missile when a seam is split. The sheath splitting system comprises an explosive device located near a seam, a detector for sensing the firing of the rocket motor, and a transfer line therebetween for receiving a motor-fire signal from the detector and for transferring a corresponding signal to the explosive device to split the sheath. A preferred embodiment employs a low-explosive and a transfer line that is a high-intensity shock pulse tube. The transfer line ablates with the sheath.

Abstract: An apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A disrupter body positioned within the exhaust plume along the central longitudinal axis thereof disrupts and disperses the plume concentration. The body has a central passage through which a portion of the exhaust may pass. The body and passage are sized and shaped to provide a flow area normal to the exhaust flow less than the cross-sectional area of the exhaust plume at the position of the body. The reduced flow area causes the exhaust flow to undergo a normal shock wave upstream of the body before passing through and around the body at a subsonic velocity. The presence and configuration of the body disrupts and disperses the plume concentration, and the reduced flow velocity significantly reduces the downstream pressure and thermal effects of the exhaust gas plume.

Abstract: A fiber optic data bus that includes a multiplexer means for generating a plurality of optical signals and for intensity modulating each of the optical signals in response to a respective one of a plurality of input RF signals each at a different RF carrier frequency to provide a plurality of intensity modulated optical signals. A signal collection means combines the plurality of intensity modulated optical signals into a combined optical signal. A conducting means conducts the combined optical signal to a signal distribution means which distributes the combined optical signal to each of a plurality of output ports. A demultiplexer means extracts from a portion of one of the distributed combined optical signals an output RF signal substantially identical to a predetermined one of the plurality of RF input signals.

Abstract: A multi-octave thick dielectric radome wall which includes a dielectric slab having a pair of surfaces and a plurality of pyramidal-shaped dielectric elements mounted on at least one of the surfaces of the dielectric slab. The dielectric constant of the elements is typically greater than the dielectric constant of the slab. In an alternate embodiment, a second dielectric slab is provided adjacent to one of the first dielectric slab surfaces having the elements mounted thereupon with support means for supporting the second dielectric slab in a spaced apart relationship with the first dielectric slab.

Abstract: A suspension and drive system for a mechanical microwave power divider for spacecraft applications. The mechanical power divider includes a control which extends longitudinally therethrough. Torsion springs connect each end of the control rod to fixed surfaces and an electromagnetic control is coupled to the control rod to rotate it to a predetermined angular position. A selectively energizeable friction brake surrounds at least a portion of the control rod for holding it in a predetermined angular position.

Abstract: Apparatus and method for providing a floating seal for an inert gas solder reflow chamber. The seal floats with respect to upper and lower chucks and is made of a substantially non-deformable material. The seal permits lateral, axial and rotational movement between the lower and upper chucks while facilitating accurate control of bonding pressure. The structure of this floating seal permits use of seal materials which facilitate use of higher melting point solders, some in excess of 350.degree. C., for flip-chip bonding.