Abstract: Apparatus and method of using satellite ranging channels for transmitting 3-d video signals for space applications.

Abstract: A signal-coding unit, to be used with a radio receiver compatible with the RDS standard, receiving as input an input signal according to RDS standard comprising not indicative information about the radio receiver, and emitting as output an output signal, comprising signal-combining means for combining at least one portion of the input signal with a signal component comprising indicative information about the radio receiver, the combination between the above mentioned portion of the input signal and the signal component being the output signal (FIG. 2).

Abstract: A self-monitoring satellite system is disclosed to more quickly and accurately convey satellite signal information and verification of its reliability to users of the signal. In a first aspect, the satellite includes one or more receivers on the satellite to monitor the reliability of signals transmitted from the satellite. In a second aspect, a warning signal is generated and transmitted substantially simultaneous with an unreliable satellite signal and at the same frequency as the satellite signal. Exemplary embodiments to implement the various aspects of the self-monitoring satellite system invention are configured as global positioning system (GPS) satellites, signals, and receivers.

Abstract: A high performance diplexer is disclosed having a common conductor which branches into two resonators in distributive form. The diplexer may be used reciprocally, has low insertion loss, is tuneable, has high signal isolation and impedance matching, and may be readily produced to meet the space requirements relating to size, temperature, radiation and performance. A method of tuning the resonators of the diplexer is also disclosed. Specific applications for the diplexer are also disclosed and include use in a GPS transmitter, GPS receiver and as part of an electronic scan array (ESA) antenna. The diplexer's small size and weight, and its resistance to the conditions of space make it ideal for use in satellite applications.

Abstract: An orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a geosynchronous-transfer orbit (GTO) to a predetermined low-earth orbit (LEO). Upon entering low-earth orbit, the payload satellite is deployed from the orbit-transfer vehicle. To reduce the cost and complexity of the payload satellite, the orbit-transfer vehicle is configured to provide common functional services, such as communications and power regulation, to the payload satellite during the transport, and/or after deployment. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit.

Abstract: A hinge system for deploying panels or other structures from a satellite or spacecraft has at least two configurations. The panels are held in a substantially stacked disposition in the stowed configuration by the hinge system which connects to each panel and includes an intermediate arm sized to span any necessary space between the two panels in the stowed configuration. A deployment cable is attached to one of the panels and threaded over a series of pulleys disposed on the hinge system and onto a spool in the other panel. When the spool is driven to wind the deployment cable onto it, the tension in the cable pulls on the pulleys, causing the hinge to unfold and then slide into a housing located on one of the panels. This deployed configuration allows the panels to be held aligned and directly adjacent to one another by the tension of the deployment cable.

Abstract: A substantially rigid tonneau cover is provided which is hingedly connectable to a truck bed and moveable between open and closed positions. A latch mechanism mounted on the interior surface of the cover is selectively engagable with the truck bed to secure the cover in the closed position. A latch release handle is mounted in a recessed compartment formed on the exterior surface of the cover and is connected to the latch mechanism. A hatch is connected to the cover proximate the latch handle and is moveable between a hatch open position and a hatch closed position. In the hatch closed position the hatch covers the recessed compartment and the latch release handle mounted therein. The hatch is preferably mounted such that in the hatch closed position the exterior surface of the hatch is generally flush with exterior surface of the cover and conforms to the contour of the cover.

Abstract: A system for aligning a laser beam with the end of an optical fiber includes optics for focusing the laser beam toward the end of the optical fiber. A plurality of light receptors are positioned around the end of the optical fiber and, as intended for the present invention, each light receptor generates a light signal which is indicative of the light intensity from the laser beam that is incident on it. Connected with this plurality of light sensors is a comparator which creates an error signal that is proportional to a difference between selected light signals from the light receptors. The laser beam can then be moved relative to the end of the optical fiber in response to the error signal to align the laser beam with the end of the optical fiber. When alignment is achieved, the light signals will be substantially equal to each other and the error signal will be a null.

Abstract: A rotary accelerometer having a nonrotatable cylindrical magnet return path formed out of magnetic permeable material. One or more permanent magnets, with two opposite poles, are disposed around the magnetic return path. An electrically conductive cup with an access for rotation therearound in which the cup surrounds the permanent magnets and the permanent magnets are arranged so as to produce a magnetic field through the cup into the nonrotatable cylindrical magnet return path, thereby inducing eddy currents inside the cup when rotating in the magnetic field. A stator core is formed out of magnetic permeable material surrounding the cup and nonrotatable relative thereto, the stator core having at least two pickup members. The stator is formed from at least one continuous piece of magnetic permeable material. One or more stator windings are disposed on to the pickup members of the stator core for sensing changes in a secondary magnetic field generated by the eddy currents in the cup.

Abstract: A boom assembly for a rocket-launched spacecraft, the boom assembly comprising a plurality of rigid sections and a plurality of elastic sections that pivotally connect each of the rigid sections together so as to enable the boom assembly to be folded into a storage configuration and so as to enable the boom assembly to be automatically unfolded into a deployed configuration that provides the spacecraft with a large rigid extending platform. At least one of the rigid sections is mounted to the spacecraft so as to secure the boom assembly to the spacecraft. In one embodiment, a plurality of extendable components, such as solar panels and radar antennae, are mounted to the rigid sections so as to allow for storing and deploying the extendable components. In another embodiment, there may be no components mounted other than a length of wire or a length of metal tape which will allow the boom to act as an antenna.

Abstract: A permanent magnet rotary accelerometer comprising: a cylindrical magnetic return path formed out of magnetic permeable material; an electrically conductive cup with an axis for rotation there around, the cup surrounding the magnetic return path; one or more sets of permanent magnets having opposite magnetic polarity, surrounding the cup, for a producing magnetic field through the cup into the magnetic return path, thereby inducing eddy currents inside the cup when rotating in the magnetic field; a stator core formed out of magnetic permeable material surrounding the cup and nonrotatable relative thereto, the stator core comprising at least two pick up members and a stator core return path therein, wherein the pick up members and the stator core return path are formed from at least one continuous piece of magnetic permeable material; and one or more pickup coils disposed on the pickup members of the stator core for sensing changes in a secondary magnetic filed generated by the eddy currents in the cup.

Abstract: A thermal transfer printing device, i.e. thermal printer, includes a printing film saving system wherein the print head is lifted during media advancement so that the print film is not advanced during media advancement, and further includes an associated arrangement for tensioning of the print media during printing and print head lifting operations so that the print media maintains print registration and the printing film does not pull upwardly when the print head is lifted. Single print station (monochrome) and multiple print station (color) embodiments are disclosed. Forward tensioning is accomplished by the use of a feed drive positioned forwardly of the single print station in the monochrome embodiment, or forwardly of the last print station in the color embodiment. The feed drive comprises a nip that pulls the print media through the print stations. In the color embodiment, rearward tensioning is accomplished by the print media supply roll, or further upstream by adjacent print stations.

Abstract: The excess space and weight capacity of a conventional geosynchronous-transfer launch vehicle is used to deploy satellites to a low-earth orbit (LEO). In a preferred embodiment, an orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a geosynchronous-transfer orbit (GTO) to a predetermined low-earth orbit. Upon entering low-earth orbit, the payload satellite is released from the orbit-transfer vehicle. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit.

Abstract: A rotary accelerometer having a nonrotatable cylindrical magnet return path formed out of magnetic permeable material. One or more permanent magnets, with two opposite poles, are disposed around the magnetic return path. An electrically conductive cup with an access for rotation therearound in which the cup surrounds the permanent magnets and the permanent magnets are arranged so as to produce a magnetic field through the cup into the nonrotatable cylindrical magnet return path, thereby inducing eddy currents inside the cup when rotating in the magnetic field. A stator core is formed out of magnetic permeable material surrounding the cup and nonrotatable relative thereto, the stator core having at least two pickup members. The stator is formed from at least one continuous piece of magnetic permeable material. One or more stator windings are disposed on to the pickup members of the stator core for sensing changes in a secondary magnetic field generated by the eddy currents in the cup.

Abstract: A spacecraft architecture is defined that distinguishes components and sub-systems based on both functional and physical dependencies. On one side of the interface are kernel components that are both functionally and physically independent of the vehicle configuration and functionally and physically independent of the mission-specific system. On the other side of the interface are components that depend on either the spacecraft configuration or the mission-specific system. The kernel components can be included in a variety of spacecraft, independent of the spacecraft architecture and independent of the spacecraft mission. The kernel includes a communications system for communicating with an earth station, a command and data handling processor, and a power regulation and distribution system.

Abstract: A printing assembly for use with a printing device as provided. The printing assembly includes an adjustable platen assembly including a platen having a jack member constructed and arranged to adjustably maintain the platen in parallel relation to a print head when the print head is in a first position, so as to prevent deformities in the printed image as an article passes through the printing assembly.

Abstract: A spacecraft, such as a satellite, includes a panel array comprised of a plurality of panels that are stacked together and secured to the side of the satellite during launch. At least one shear tie device is configured to couple the panels together in shear to increase the resistance to deformation of the stack of panels. The shear tie device preferably comprises a male member that mates with a female member. A plurality of fingers secure the male member within the female member during launch. Upon reaching orbit, a bladder is inflated which deforms the fingers and releases the male member from engagement with the female member.

Abstract: A transport apparatus and method for transporting labels along a printing path of a printing device is disclosed. The transport apparatus includes a label transfer station including a first peeling device for deflecting the web supplied by the payoff roller to a take-up roller, the deflection of the web being at such an angle that a label mounted on the web is peeled from the web as the web passes over the first peeling device, a discrete carrier for receiving the peeled label from the web and transporting the label along the printing path and through the printing assembly and a second peeling device for deflecting the discrete carrier, the deflection of the discrete carrier being at such an angle that the label mounted on the discrete carrier is peeled from the discrete carrier as it passes over the second peeling device.

Abstract: A device and method for aligning the focal point of a laser beam into coincidence with the active area of a detector includes an optical element for focusing the laser beam to the focal point at a location on the surface of the detector. Also included is a selectively activated light source and a camera which establishes a reference location for the active area within an x-y grid coordinate system whenever the surface of the detector is illuminated by the light source. Further, by using the light that is reflected from the focal point location through a beam splitter, the camera also establishes the location of the laser beam focal point in the same coordinate system. The optical element is then adjusted to move the focal point in the x and y directions, as required, to thereby bring the focal point location into coincidence with the active area.

Abstract: The invention relates to a device structure and crystal growth process for making the same, whereby single-crystal semiconductor layers are formed over metal or composite layers. The metal layers function as buried reflectors to enhance the performance of LEDs, solar cells, and photodiodes. The structure may also have application to laser diodes. The structures are made by a modification of a well-established metallic solution growth process. The lateral overgrowth process can be enhanced by imposing an electric current at the growth interface (termed liquid-phase electro-epitaxy). However, the use of an electric current is not crucial. The epitaxial lateral overgrowth technique was also applied to silicon growth on metal-masked silicon substrates.