Abstract: Various embodiments of methods and systems for precompensated bus width conversion (“PBWC”) in a portable computing device (“PCD”) are disclosed. Because starting memory addresses for data transfers emanating from a processing engine in a system on a chip (“SoC”) may be misaligned with a starting memory address of a main bus on the SoC, PBWC solutions seek to precompensate data transfers to align the starting addresses. Advantageously, by doing so PBWC embodiments may significantly reduce the amount of “filler” data chunks that are transferred through the main bus, thereby optimizing band width utilization of the main bus.

Abstract: The invention provides a method of estimating free light chain production (FLC) in a subject comprising (i) determining an amount of FLC in a sample from the subject; and (ii) correcting the amount of FLC in the sample for FLC cleared from the source of the sample by glomerular filtration and by reticuloendothelial (RE) clearance.

Abstract: Provisioning, managing and tracking of services provided by a cloud infrastructure system are described. A subscription order request from a customer for services provided by the cloud infrastructure system is received. A separation of roles performed by different customer entities in a customer's organization when the customer subscribes to services in the cloud infrastructure system is determined. The roles relate to providing information about different portions of the subscription order by the customer entities. Upon completion of the assigned roles by the relevant customer entities, the subscription order is provisioned to the customer.

Abstract: A recovery workflow related to processing the cancellation of a subscription order is determined. A request for cancelling processing of the subscription order is received. A provisioning task related to the service, a stage related to the provisioning task and a state of execution related to the provisioning task is identified.

Abstract: Provisioning, managing and tracking of services provided by a cloud infrastructure system are described. A subscription order request from a customer for services provided by the cloud infrastructure system is received. A workflow is defined that includes steps to process the subscription order. The workflow enables a customer to gain access to services requested in a subscription order upon placing the subscription order without the customer having to wait until all the steps involved in processing the subscription order are complete.

Abstract: Method of and system for on-board substantially autonomous control for transferring a spacecraft from an initial orbit to a final geosynchronous orbit, by a trajectory that minimizes remaining transfer time and orbit transfer fuel. The spacecraft determines its orbit using a GPS-based system to determine the spacecraft orbital elements. Based on the measured orbit error, corrected co-state parameters are calculated and used to generate an updated thrust trajectory. The corrections are calculated using an innovative numerical procedure, carried out repetitively at a fixed interval until the target geosynchronous orbit is achieved.

Abstract: In a software environment for team collaboration, a relationship processor defines relationships between collaboration entities (artifacts) in the collaboration environment. The relationship processor is operable to define, capture, and traverse relationships in a generic manner independently of the underlying types of artifacts included in the relationships. Accordingly, participant artifacts of such a relationship may be a set of workspace artifacts of dissimilar types, and may be associated by a 1:1, a 1:N, or an N:M relation. Therefore, relationships may include individual or sets of artifacts of various cardinality and directionality, as discussed further above. A relationship processor captures the defined relationships in a set of DB tables. The tables enumerate the related entities of the various types instantiated by the applications operative in the workspace. In this manner, the workspace employs a variety of type-unrestricted artifacts for further processing and/or organization.

Abstract: One embodiment of the present invention relates to a system for correcting spacecraft thermal distortion pointing errors. The system comprises one or more spacecraft sensors located at positions on a spacecraft and which are adapted to measure spacecraft parameters at those positions. The system also includes a spacecraft distortion prediction module, which is adapted to generate expected spacecraft thermal distortion parameter values and expected antenna thermal distortion pointing errors. Further, the system includes a spacecraft parameter processing module adapted to generate measured spacecraft thermal distortion parameter values from the measured spacecraft parameters, and an antenna pointing error calculation module adapted to calculate antenna pointing error correction commands. Finally, the system includes an antenna pointing control module adapted to receive the antenna pointing correction commands and control the adjustment of the antenna pointing using the correction commands.

Abstract: A sparing system for space vehicle constellations. A plurality of space vehicles arranged in at least one mission orbit plane. The number of space vehicles is at least one greater than a minimum number necessary to provide at least a minimum level of service necessary to carry out a constellation mission. If one of the space vehicles fails the remaining space vehicles are repositioned in the mission orbit plane to provide the minimum level of service necessary to carry out a constellation mission.

Abstract: A velocity change (?V) thruster is operated on a spacecraft, which unavoidably causes attitude error. A reaction wheel (RWA) corrects the attitude. At the beginning of the thruster maneuver, the total attitude control momentum required to at least correct for the ?V thruster attitude errors over the duration of the entire maneuver is determined, and the RWA momentum may also be determined. Attitude control thrusters (REAs) are operated. The REAs are operated to correct at least the net ?V thruster induced attitude error, and preferably also to reset the RWA to its nominal momentum. The maneuver may be stationkeeping.

Abstract: A method for increasing the roll offset operating range for a spacecraft using an earth sensor operating in single scan mode includes the steps of moving the spacecraft to a first roll position, which has a roll angle that will cause the earth sensor to have a desired standard chord, switching the earth sensor to single scan mode by deselecting one of the earth sensor scans, whereby switching the earth sensor to a single scan mode, the earth sensor standard chord is locked at or near the desired standard chord. After the desired standard chord is set, the spacecraft is moved to a second roll position, which is a desired roll offset operating position for the spacecraft, and the earth sensor roll output (generated by using the single scan mode) is used to calculate the spacecraft roll at the roll offset operating position.

Abstract: In general, a constellation of spacecraft is used to broadcast to a particular region with high angles of view in order to reduce blockage or shadowing. A constellation of a plurality of spacecraft is placed in 24-hour orbits having inclination of about 55°, eccentricity of about 0.32, semi-major axis of about 42,000 km, longitude of the ascending node of about 43° East, argument of perigee of about 270°, and longitude of the ground track at maximum latitude of about 7° East. The preferred number of spacecraft ranges from three to six. In a particular application of Digital Audio Broadcast to Europe in some embodiments, the most populous cities are provided with service from no more than about 10° from vertical, and broadcast takes place when the spacecraft are above at least 35° North latitude. The broadcast power is reduced during those portions of the orbit in which the ground track lies in the Southern hemisphere.

Abstract: The present invention relates generally to systems and methods for transferring a spacecraft from a first orbit to a second orbit. In accordance with one embodiment of the invention, the method comprises calculating thruster-off regions within an orbit transfer in which it is efficient to turn-off spacecraft thrusters, and in those thruster-off regions, turning off the spacecraft thrusters.

Abstract: One embodiment of the present invention relates to a method for increasing the roll offset operating range for a spacecraft using an earth sensor operating in a single scan mode. In accordance with this embodiment, the method comprises moving the spacecraft to a first roll position, which has a roll angle that will cause the earth sensor to have a desired standard chord. Next, the earth sensor is switched to single scan mode by deselecting one of the earth sensor scans. By switching the earth sensor to a single scan mode, the earth sensor standard chord is locked at or near the desired standard chord. After the desired standard chord is set, the spacecraft is moved to a second roll position, which is a desired roll offset operating position for the spacecraft. Finally, the earth sensor roll output (generating using the single scan mode) is used to calculate the spacecraft roll at the roll offset operating position.

Abstract: A velocity change (&Dgr;V) thruster is operated on a spacecraft, which unavoidably causes attitude error. A reaction wheel (RWA) corrects the attitude. At the beginning of the thruster maneuver, the total attitude control momentum required to at least correct for the &Dgr;V thruster attitude errors over the duration of the entire maneuver is determined, and the RWA momentum may also be determined. Attitude control thrusters (REAs) are operated. The REAs are operated to correct at least the net &Dgr;V thruster induced attitude error, and preferably also to reset the RWA to its nominal momentum. The maneuver may be stationkeeping.

Abstract: A sparing system for space vehicle constellations. A plurality of space vehicles arranged in at least one mission orbit plane. The number of space vehicles is at least one greater than a minimum number necessary to provide at least a minimum level of service necessary to carry out a constellation mission. If one of the space vehicles fails the remaining space vehicles are repositioned in the mission orbit plane to provide the minimum level of service necessary to carry out a constellation mission.

Abstract: A fault tolerant attitude control system for a zero momentum spacecraft. A zero momentum attitude control system is operable to control spacecraft attitude utilizing data received from an earth sensor, a sun sensor, and the inertial measurement unit. A gyroless attitude control system is operable to control spacecraft attitude without receiving data from the inertial measurement unit. A redundancy management system is operable to monitor an inertial measurement unit to detect faults and to reconfigure the inertial measurement unit if a fault is detected and operable to determine when an inertial measurement unit fault is resolved. A controller is operable to automatically switch the spacecraft from the zero momentum attitude control to the gyroless attitude control when a fault in the inertial measurement unit is detected and is operable to automatically switch the spacecraft from the gyroless attitude control to the zero momentum control upon resolution of the fault.

Abstract: The present invention provides a system which uses a number of network nodes (2) which can communicate wire lessly with communications devices (3-8) coupled to the network. The network nodes are all connected to a network server (1) which can be used to provide additional services, such as Internet connection. The system uses at least a local short range radio connection for interconnecting the network nodes (2) to the communications device (3-8), thereby allowing the user of a communications device access to the network from anywhere within range of a suitable network node. This allows network nodes to be located throughout a building, such that a user can have access to the communications network at any location within the building.

Abstract: An attitude control system for a spacecraft that includes a north side, a south side, an east side, a west side, an earth facing side, and an anti-earth facing side. The attitude control system includes a plurality of gimbaled thrusters interconnected with the spacecraft and arranged to produce thrust in a direction parallel to a roll-pitch plane of the spacecraft.

Abstract: A method for correcting differences in measurements between sensors. Misalignment of a roll error of a sun sensor alignment is estimated with respect to a reference roll value measured by an earth sensor. Sun sensor assembly elevation angle residual is calculated utilizing the estimated sun sensor assembly roll misalignment. A yaw attitude of the spacecraft is updated based upon the calculated sun sensor assembly elevation residual.