Abstract: A control system for rolling airframes utilizing variable pitch control surfaces includes a variable inertia device within the control system connected to the servo control motors that control the control surfaces, with the variable inertia device selectively controllable to optimize the inertia of the control system for optimizing the power requirements of the control system. The variable inertia means includes a rotatable mass with means for moving the effective position of the mass radially inwardly and outwardly from the rotary shaft of the control system for selectively varying the inertia of the control system.
Abstract: A cooled infrared detector post includes a detector post formed of a stack of wafer disks with a detector substrate wafer forming one end of the post and a cooling chamber adjacent to the detector substrate with coolant supply and return passages formed in the series of wafers with a supply passage contained to a supply port with a supply passage forming a plurality of serpentine passages at various planes within the post and a return passage including a plurality of precooling chambers with the wafer stacked in a predetermined arrangement and fused together to form a monolithic post structure.
Abstract: The leads for an infrared detector unit are arranged to pass through bores in a cooled detector housing with intimate contact with the cooled detector housing for precooling the leads extending from the detector elements to the respective preamp leads.
Abstract: A highly accurate rapid gimbal assembly method utilizes two fixtures for establishing the critical gimbal assembly parameters of yield and axis of intersection and an adhesive for bonding each mating surface of the gimbal assembly for holding the components of the gimbal assembly in their adjusted positions. The fixtures include an inner/outer gimbal fixture for holding the inner and outer gimbals in relative position for bonding and a gimbal/post fixture for holding the gimbal assembly in alignment on the support post for bonding. These fixtures and assembly method eliminate the need for use of shims between the mating surfaces for establishing alignment of the critical parameters.
Abstract: Apparatus for preventing a missile's rocket exhaust gases from contacting and adversely affecting, such as by overheating, the launch rails from which a missile may be launched. Such apparatus includes an angled member having first and second leg portions, the end of the first leg portion being pivotably secured to the rail. A member having an angled surface is mounted to the second leg portion. Prior to the launching of said missile, the apparatus is in a first operative position such that it is out of contact with said launch rail. When the exhaust gases are emitted from said missile, a portion of the exhaust is incident upon the angled surface which causes the apparatus to rotatably pivot into contact with the launch rail, whereby portions of two surfaces of the launch rail are protected from the exhaust.
Abstract: A dielectric heat sensor system for monitoring and measuring the effects of electromagnetic radiation on the performance or physical integrity of an electrical or electronic component includes a dielectric receiver in the form of a rectilinear array of fiber optic ends positioned to receive infrared heat waves from a bridgewire of an electro-explosive device and transmitting the infrared heat waves by way of a waveguide of electro optic fibers to an infrared detecting unit which is effective to activate an indicator.
Abstract: A holding fixture and method for using the same are disclosed which enable great accuracy in performing measurements of concentricity, diameter, and wall thickness of a cylindrical workpiece. The present invention supports the workpiece for rotation at two fixed locations characterized by orthogonal tangents, while making measurements at a location on the workpiece on the opposite side of one of the support locations. The device is simple and economical in construction, easy to use while providing reliable measurements of the specified parameters, and it improves production line operation by expediting particular measuring procedures.
Abstract: A zero insertion force electrical connector for multiple electrical connections includes a circuit board having a pair of contact strips on opposite faces thereof with opposed clamp members disposed adjacent the contact strips for biasing connector pins into engagement with the strips and a second connector member having a plurality of lined pins disposed for positioning on each side of the board adjacent the connector strips for contacting the connector strips upon biasing by the clamp members into engagement therewith.
October 21, 1983
Date of Patent:
August 6, 1985
General Dynamics Pomona Division
Adelmo A. Scoccia, Donald B. Schellin, deceased
Abstract: A clustered munition in a system for low altitude aerial delivery, which releases multiple rocket powered missiles, each having the capability to cruise at a constant altitude and search for a target. Once a target is identified, the missile homes on and strikes the target. In the preferred form the target seeking means is a radiometric seeker operating in the millimeter wavelength range, in which metal or similarly reflective targets stand out against the background and provide a significant signal which is used to program the terminal action of the missile.
November 12, 1973
Date of Patent:
June 11, 1985
General Dynamics, Pomona Division
Clair K. Lair, Jules Jonas, Keith D. Anderson
Abstract: An assembly of fiber optic couplers of substantially identical form in an integrated array comprising two sets of optical fibers arranged side by side across an arcuate surface, epoxied in place, and lapped to develop mating planar surfaces which expose at least partially lapped portions of the respective optical fibers. Preferably, a launch coupler array is provided in which one set of optical fibers is of smaller diameter than those of the other set and is lapped to a depth sufficient to sever the fiber cores. The two lapped faces are then aligned so that one set of severed ends of the smaller fibers is joined with the exposed core portions of the other set of fibers. Selection of fiber size and lapping of the second set of fibers is performed to develop opposed mating portions of individual fibers which are substantially equal in extent and dimensions.
Abstract: An improved airframe body decoupling system for a body gimballed sensor on an interceptor aircraft or guided missile. Body rate gyro information is employed for internal decoupling so as to eliminate decoupling match sensitivity to receiver errors. The true measure of sensor position from the gimballed antenna potentiometer is differentiated and then externally decoupled to produce the desired line-of-sight rate for use by the guidance/control section of the proportional navigation guidance system.
Abstract: A technique for correlating two images, differing in size, but of identical spatial content. The technique is based on the Cauchy-Schwarz Inequality and is derived in such a way as to eliminate the requirement for division, thereby realizing practical real time implementation with presently available electronic hardware. In the embodiment disclosed, reference and data image signals require no pre-processing for the removal of mean and gain factors prior to being individually supplied to the correlator. The correlator is built around modules which can be configured serially with delay lines to adapt to virtually any image configuration. Simulation tests have shown the embodiment to be superior to prior art correlators utilizing other algorithms under conditions of noise, offset and gain differences.
Abstract: A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a third order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation with a target acceleration feed forward term and a navigation ratio which is a function of time-to-go and the control effort weighting factor. This third order system may also implement another optimal control law to even greater advantage, taking into account not only target acceleration but also missile acceleration in a feedback loop which, together with the navigation ratio, are both functions of time-to-go and autopilot dynamics, whereby first order autopilot time lag is accounted for. This system is particularly useful for high and medium altitude targets and results in significant miss distance improvement for terminal guidance against small maneuvering targets.
Abstract: A system for testing digital circuit units at the design speed of the circuit. A first memory stores a minimized set of optimum generated predetermined test patterns for application to a unit under test. A second memory stores expected signature patterns corresponding to signature patterns that are derived from the unit under test in response to the predetermined test patterns when the unit under test is functioning properly. A signature analyzer derives signature patterns from a unit under test in response to the application of the test patterns to the unit. A comparator compares the derived signature patterns with the expected signature patterns and provides an indication of the results of the comparison.
Abstract: Method and apparatus which allows the component leads of pre-taped electronic components to be solder tinned to preserve the solderability and shelf life of such component leads. Pre-taped electronic components and the like are prepackaged in a reel and positioned in the apparatus such that the reel is free to rotate. Both leads of each component are secured to corresponding adjacent component leads by tape. The electronic components are moved through a plurality of processing stages such that one lead of each component is solder tinned, one of the processing stages removing the tape from the leads to enable the soldering thereof. After soldering of the leads, tape is applied thereto. The process is then repeated for the other leads of each component.
Abstract: A pouch for protecting electrosensitive components contained therein from physical shock and electrostatic damage during handling and storage. In one embodiment, the pouch comprises two composite panels, each comprising a sheet of conductive material as the outside layer, a sheet of electrostatic-free material as the inside layer and a layer of open cell cushioning material sandwiched therebetween. Each panel is sealed to enclose the material therein and both panels are then sealed together on both sides and one end. The open end has an interlocking closure to allow components to be inserted into the pouch and for the pouch to be thereafter closed.In another embodiment, the pouch is formed of a pair of extruded, tubular members respectively constituting the conductive material layer and the electrostatic-free material layer with sheets of cushioning material sandwiched between them. The assembly is sealed at one end and provided with a releasable closure member at the other end.
Abstract: A fragile, movable apparatus such as a rotatable infrared optical prism assembly is mounted in a projectile housing on a crushable support pad. When the projectile is launched, the fragile, movable apparatus crushes the pad and receives effective support from the pad. After launch, a resilient member positions the fragile, movable apparatus away from the crushed pad and provides the necessary freedom of movement for the fragile, movable apparatus.
Abstract: A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a fourth order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation with target and missile information terms and a navigation ratio which is a function of time-to-go. By employing a fourth order system, enhanced use may be made of information already available in the guidance computer and missile control system to decouple target motion information from the missile control signals. Decoupled target motion information facilitates blind-mode operation in the end game, the last few seconds before intercept. Decoupled missile control information enables the airframe to be controlled to predefined orientations for aimed warhead applications.
Abstract: A method for augmenting the value of range uplink information in a predictive proportional navigation terminal guidance scheme. A second order configuration, with noise adaptive varying gain parameters calculated as a function of time-to-go, is particularly useful for high altitude, minimally maneuvering targets. This configuration results in acceptable miss distances, better than conventional proportional navigation, with sensitivity to unmodeled errors being substantially less than that in modern guidance systems. A third order configuration makes enhanced use of range uplink information to provide improved terminal guidance against lower altitude maneuvering targets. The sensitivity of the third order configuration is similar to that of conventional proportional navigation but with better miss distance results.