Abstract: Embodiments of the present disclosure relate to projection stabilization systems and maskless lithography systems having projection stabilization systems. The projection stabilization system compensates for propagating vibrations that move image projection systems (IPS's). The IPS's are in a processing position prior to operation of the maskless lithography process. One or more stiffeners are coupled to the IPS. The one or more stiffeners apply pressure to flexures coupled to each stiffener. The flexures are coupled to the IPS to provide stabilization to the IPS during the operations of the maskless lithography process. For example, the one or more of stiffeners protect the IPS from vibrations that propagate through the system during operation.

Abstract: A method can be performed by a browser. The method can include presenting at least a portion of a resource address; presenting a rendered webpage in a browser content window, the rendered webpage being associated with the resource address; presenting an annotation area, the annotation area being outside the browser content window; receiving, in association with a user account, an annotation in the annotation area; and storing the annotation in association with the user account and the resource address.

Abstract: A method can be performed by a browser. The method can include presenting at least a portion of a resource address; presenting a rendered webpage in a browser content window, the rendered webpage being associated with the resource address; presenting an annotation area, the annotation area being outside the browser content window; receiving, in association with a user account, an annotation in the annotation area; and storing the annotation in association with the user account and the resource address.

Abstract: Embodiments of the present disclosure relate to projection stabilization systems and maskless lithography systems having projection stabilization systems. The projection stabilization system compensates for propagating vibrations that move image projection systems (IRS's). The IRS's are in a processing positon prior to operation of the maskless lithography process. One or more stiffeners are coupled to the IPS. The one or more stiffeners apply pressure to flexures coupled to each stiffener. The flexures are coupled to the IPS to provide stabilization to the IPS during the operations of the maskless lithography process. For example, the one or more of stiffeners protect the IPS from vibrations that propagate through the system during operation.

Abstract: A method can be performed by a browser. The method can include presenting at least a portion of a resource address; presenting a rendered webpage in a browser content window, the rendered webpage being associated with the resource address; presenting an annotation area, the annotation area being outside the browser content window; receiving, in association with a user account, an annotation in the annotation area; and storing the annotation in association with the user account and the resource address.

Abstract: Embodiments of methods, apparatuses, or systems relating to clustering identical or disjoint keyword sets for use with auctions for online advertising space.

Abstract: Described are techniques for clustering a data set of objects. Divide phase processing is performed to partition the data set into two or more partitions forming a hierarchy of the objects. Merge phase processing may be performing using the hierarchy to determine one or more disjoint clusters of objects of the data set. Optional preprocessing may be performed to determine weights for one or more features of an object.

Abstract: A system and method are disclosed for rewriting queries. The queries may be rewritten and evaluated based on an end benefit, such as an optimum advertising benefit. Queries may be associated with advertisements and the benefit of those advertisements may be used in selecting query rewrites for an original user query. Multiple query rewrites from various techniques may be analyzed to generate a subset of query rewrites that are optimized for a particular benefit.

Abstract: Described are techniques for clustering a data set of objects. Divide phase processing is performed to partition the data set into two or more partitions forming a hierarchy of the objects. Merge phase processing may be performing using the hierarchy to determine one or more disjoint clusters of objects of the data set. Optional preprocessing may be performed to determine weights for one or more features of an object.

Abstract: Methods and structures are provided that enhance the accuracy of the service attitude of an inclined-orbit spacecraft and, thereby, facilitate reduction of service error between a communication service area and the spacecraft's payload beam. The enhancement is realized by configuring a beacon-receiving antenna to have a beacon-receiving field-of-view that substantially matches a beacon-station window. Preferably, the beacon-receiving field-of-view is elongated and tilted to enhance its match with the beacon-station window in both size and orientation. The goals are also realized by configuring the beacon-receiving antenna to have a beacon-receiving field-of-view that is substantially smaller than the beacon-station window and successively steering a beacon-receiving boresight to successive beacon-receiving attitudes that maintain the beacon station within the beacon-receiving field-of-view over each solar day.

Abstract: Methods and structures are provided that enhance the accuracy of the service attitude of an inclined-orbit spacecraft and, thereby, facilitate reduction of service error between a communication service area and the spacecraft's payload beam. The enhancement is realized by configuring a beacon-receiving antenna to have a beacon-receiving field-of-view that substantially matches a beacon-station window. Preferably, the beacon-receiving field-of-view is elongated and tilted to enhance its match with the beacon-station window in both size and orientation. The goals are also realized by configuring the beacon-receiving antenna to have a beacon-receiving field-of-view that is substantially smaller than the beacon-station window and successively steering a beacon-receiving boresight to successive beacon-receiving attitudes that maintain the beacon station within the beacon-receiving field-of-view over each solar day.

Abstract: A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the satellite central body with maximum torque along the thermal shock axis. Subsequently, a rate-dominated thermal shock suppression controller, which is coupled to the satellite central body, receives the rate signal from the sensor to control the actuator.

Abstract: Methods and structures are provided that enhance the accuracy of the service attitude of an inclined-orbit spacecraft and, thereby, facilitate reduction of service error between a communication service area and the spacecraft's payload beam. The enhancement is realized by configuring a beacon-receiving antenna to have a beacon-receiving field-of-view that substantially matches a beacon-station window. Preferably, the beacon-receiving field-of-view is elongated and tilted to enhance its match with the beacon-station window in both size and orientation. The goals are also realized by configuring the beacon-receiving antenna to have a beacon-receiving field-of-view that is substantially smaller than the beacon-station window and successively steering a beacon-receiving boresight to successive beacon-receiving attitudes that maintain the beacon station within the beacon-receiving field-of-view over each solar day.

Abstract: The present invention is directed to spacecraft that have, for any reason, lost the spacecraft's service attitude that permits it to carry out the service operations for which it was designed. The invention provides methods and structures for acquiring and determining a power-safe attitude (i.e., one in which wing current is sufficient to support the spacecraft's housekeeping operations) from which the spacecraft can be subsequently returned to a service attitude. The methods are particularly useful because they a) require only a single star tracker for sensing attitude, comprise simple maneuvers, and typically acquire a power-safe attitude that does not significantly differ from the spacecraft's service attitude to thereby reduce the spacecraft's return-to-service time.

Abstract: A simple, robust algorithm for power acquisition for power, thermal, and momentum safety for high heater-power spacecraft uses current sensors rather than sun sensors and includes a wing sun search phase, an xz slew phase, and a safe hold phase. Solar wing current is continuously monitored against a high current threshold and a low current threshold. Wing sun search phase transitions either to xz slew phase or safe hold phase. When current is too low, the xz slew phase is entered and slews the spacecraft about an axis in the xz plane until current is high enough. When current is high enough, the algorithm transitions or remains in safe hold phase and the spacecraft is spun about its wing axis. A low current persistence timer is longer than a high current persistence timer in order to bias the algorithm to prefer safe hold phase over xz slew phase.

Abstract: A spacecraft with a reaction wheel system can be autonomously safed by setting the solar wings to continuous tracking, determining a slew rate vector based on the total angular momentum, and slewing the spacecraft using the slew rate vector until commanded to stop autonomous safing. When the total angular momentum of the spacecraft to large to be handled by rotisserie, then the spacecraft is reoriented to align a suitable rotation vector with the system momentum. In a typical application, the spacecraft has a reaction wheel assembly with four wheels arranged to form a right regular pyramid. Two reaction wheels on opposite edges of the pyramid form a first pair and the two remaining reaction wheels forming a second pair.

Abstract: The present invention is directed to spacecraft that have, for any reason, lost the spacecraft's service attitude that permits it to carry out the service operations for which it was designed. The invention provides methods and structures for acquiring and determining a power-safe attitude (i.e., one in which wing current is sufficient to support the spacecraft's housekeeping operations) from which the spacecraft can be subsequently returned to a service attitude. The methods are particularly useful because they a) require only a single star tracker for sensing attitude, comprise simple maneuvers, and typically acquire a power-safe attitude that does not significantly differ from the spacecraft's service attitude to thereby reduce the spacecraft's return-to-service time.

Abstract: A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the satellite central body with maximum torque along the thermal shock axis. Subsequently, a rate-dominated thermal shock suppression controller, which is coupled to the satellite central body, receives the rate signal from the sensor to control the actuator.

Abstract: A spacecraft with a reaction wheel system can be autonomously safed by setting the solar wings to continuous tracking, determining a slew rate vector based on the total angular momentum, and slewing the spacecraft using the slew rate vector until commanded to stop autonomous safing. When the total angular momentum of the spacecraft to large to be handled by rotisserie, then the spacecraft is reoriented to align a suitable rotation vector with the system momentum. In a typical application, the spacecraft has a reaction wheel assembly with four wheels arranged to form a right regular pyramid. Two reaction wheels on opposite edges of the pyramid form a first pair and the two remaining reaction wheels forming a second pair.