Abstract: A rocket exhaust recirculation obturator or cover member is designed to extend across the base of a missile in a launch tube between the exit nozzle of the missile rocket exhaust and the walls of the launch tube. The cover member has a central opening which seals against the rocket motor nozzle exit, and an outer periphery which seals against the launch tube walls. During launch, pressure of exhaust gases recirculating back up the launch tube will urge the obturator against the base of the missile, and both the missile and obturator will accelerate together up the launch tube. A release assembly is provided at the upper end of the launch tube which engages corresponding release devices at the outer periphery of the obturator. The engagement releases the pressure bond between the obturator, the missile base, and the launch tube. This allows the rocket exhaust to impinge upon the upper surface of the obturator in opposition to the obturator's momemtum.

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: 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: 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: 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.

Abstract: An antenna feed structure for use with a parabolic reflector in amplitude-comparison monopulse radar applications employs a dedicated transmit feed centered within a four-port receive array of conventional element spacing to eliminate the need for a circulator or other transmit/receive device while retaining satisfactory receive array performance. Isolation pins placed around the transmit port act to decouple it from the receive ports, and a double waveguide run to the transmit port reduces uneven heating and related phase imbalance in adjacent receive waveguide runs.

Abstract: A dissipator device comprises a container having an inlet for connection to a rocket exhaust and a plurality of exhaust orifices of smaller dimensions than the inlet for exhaust flow out of the container in a plurality of different directions. A deflector member is positioned in the container in alignment with the inlet in the path of incoming exhaust gases for deflecting the flow. A disrupter member is positioned between the inlet and deflector member, and has a through bore defining an orifice of area less than the exhaust flow area at the plane of the disrupter member, so that exhaust gases flow both through and around the disrupter member, substantially reducing the downstream pressure and impingement heat transfer.

Abstract: A seal for a piano hinge for preventing passage of electromagnetic energy through the hinge; said seal comprising a first sealing member of conductive material comprising a connecting section for attachment to and for electrical contact with one hinge leaf and an arcuate section shaped to fit over the hinge knuckles, and a second sealing member of conductive material comprising a connecting section for attachment to and for electrical contact with another hinge leaf and an arcuate section for overlapping and for making electrical contact with the arcuate section of the first sealing member. Preferably the sealing members are of hard copper alloy. Another embodiment includes a detachable sealed hinge assembly wherein the hinge includes three leaves; an attached leaf, an insertion leaf, and an attachable leaf.

Abstract: A ring-wing assembly for use in combination with a missile or mortar adapted to be launched from a launch tube or barrel allows attachment of large lifting surfaces to the projectile as it is launched from a barrel. The ring-wing assembly generally comprises a stop ramp for generally encircling a missile body. The stop ramp having a forward-tapering ramp portion, and a sleeve assembly comprising a sleeve for encircling a body of a missile and a plurality of wings peripherally mounted on the sleeve. The sleeve has a rear inside tapered portion having a taper angle that is less than that of the ramp portion of the stop ramp. In use, the sleeve assembly is mounted on the nose end of a launch barrel. Upon missile launch, the sleeve assembly slides over the missile body until encountering and engaging with the stop ramp whereupon the sleeve assembly travels with the missile for extending the range and controllability of the missile.

Abstract: A rigid packaging material having a coating of heat-sealable, anti-static plastic. A fiberboard sheet substrate is coated with a lamina of polyethylene made electrostatic-free by the addition of an organic anti-static compound. When skin-packaged with a film of heat sealable, anti-static plastic material, a static-sensitive item is completely enclosed by a static-free barrier package.

Abstract: A stripline tapped-line filter is disclosed including a first substrate upon which a plurality of N hairpin resonators are disposed alternately on opposite surfaces of the first substrate. Each one of the hairpin resonators is in a parallel coupled relationship with an adjacent hairpin resonator disposed on an opposite surface of the first substrate. The first and last hairpin resonators each have an interconnected member disposed on the substrate for respectively coupling a signal into and out of the plurality of N hairpin resonators. Second and third substrates are included with each being respectively located adjacent to ones of the plurality of N hairpin resonators on opposite surfaces of the first substrate. First and second groundplanes are included with each respectively located adjacent the second and third substrates.

Abstract: A dual mode target seeking system for airborne vehicles which operates under two different frequencies simultaneously includes a radio frequency antenna comprising a slotted plate defining a ground plane with an image plate positioned in front of the ground plane at a distance chosen such that multiple reflected rays are in phase with each other and with waves incident on the image plate. The slotted plate and image plate have aligned central openings through which an electro-optical system for operating under a chosen electro-optical frequency range, for example under infrared frequencies, projects. The electro-optical system includes a detector unit positioned behind the antenna and a focussing system for directing incoming electro-optical radiation into the detector unit. The focussing system includes first and second lenses mounted in the openings in the image plate and slotted plate, respectively.

Abstract: A radar return suppressor for use in concealing and camouflaging mobile targets such as trucks, artillery and like vehicles. One or more lengths of a support member attachable to the target and components support and position a radar signal attenuator between the target and the anticipated radar source. In one embodiment, the attenuator is a multiplicity of closely spaced flexible plastic strands having radar signal absorbing material dispersed in the strands to form a labyrinth to entrap and absorb the radar signal. In a second embodiment the labyrinth of strands is replaced by an intertwined plastic vine-like structure secured in the support member for absorbing the energy of the radar signal.

Abstract: Pivotable deflector panels are installed in the transition sections between a plurality of rocket storage and launch chambers and a lower plenum or manifold chamber which is provided to dispose of the exhaust gases from missile firings. The deflector panels are in addition to the sets of doors which are provided to close off the missile storage chambers upon the firing of a missile in another chamber in order to prevent recirculation of exhaust gases into the closed off chambers. The deflector panels act with the doors to control exhaust gas flow, thereby improving the effectiveness of the gas plug which is formed by exhaust gases within a transition section.

Abstract: A retention collar rigidly attaches to a missile guidance assembly, and a transport cart lifts, supports, transports, and lowers the retention collar and thereby a retained assembly. The retention collar comprises a pair of trunnions for attachment to a workpiece, such as a missile guidance assembly, and for positioning on opposite sides of the workpiece. The transport cart includes a movable base with a frame attached thereto. The frame includes left and right side frame members which support a pair of rotatable bearing members so positioned to engage a corresponding one of the retention collar trunnions. A slot in each bearing member engages a collar trunnion. The slots include a bearing position at which the trunnion is held and which is raised or lowered by rotating the bearing member. The trunnions may also be rotated while at the bearing position. A frame/bearing locking pin selectively prevents rotation relative to the frame of the rotatable bearing member.

Abstract: An exhaust dissipator device for a rocket exhaust has an inlet for connection to the exhaust and a plurality of smaller exhaust orifices spaced around its surface to dissipate the flow into a plurality of smaller jets. A deflector surface in the direction of exhaust flow into the container acts to further dissipate the flow and deflect it out of its original path. This may comprise an internal surface of the container, or a separate deflector plate spaced from the container surface.

Abstract: A transition region for a missile launch chamber providing a smooth transition from a generally square cross-section chamber in which a missile is stored and launched to a round exit opening of the chamber which connects with an exhaust manifold or plenum. The transition section is provided with a pair of pivoted doors for closing off the bottom of the missile chamber to prevent the flow of recirculation gases from the plenum into the chamber when a missile in another chamber coupled to the same plenum system is being fired. The portion of the missile exhaust chamber between the square cross-section and the circular exit opening serves to direct the exhaust gases of a missile being fired into a smooth round exhaust plume which functions as a "gas plug", preventing the recirculation of the exhaust gases back into the chamber of the missile being fired.

Abstract: A rigid packaging material having a coating of heat-sealable, anti-static plastic. A fiberboard sheet substrate is coated with a lamina of polyethylene made electrostatic-free by the addition of an organic anti-static compound. When skin-packaged with a film of heat sealable, anti-static plastic material, a static-sensitive item is completely enclosed by a static-free barrier package.

Abstract: A bearing friction testing apparatus includes a bearing support structure having a support arm with a bearing mount for mounting a test bearing with a bi-directional load support ring for attachment to the bearing race with a pendulum attachable to the support ring for adding one direction of force and a tension line attached to the ring for applying a second direction of force transverse to the first direction of force with a pendulum latching device for latching the pendulum in a loaded position and releasing the pendulum with a measuring instrument for measuring the rate of decay in the amplitude of oscillation of the pendulum.