Abstract: Secured data access in virtual data processing is described. An example includes instructions to receive a request from an application in a compute node of a compute cluster in a virtual data processing environment to access a secured data source for a user, the virtual data processing environment including a multiple secured data sources that are accessible by compute nodes of the virtual compute cluster; fetch a credential in a current application context and forward the credential for validation; validate the credential with a credential authority; and, upon successfully validating the credential, authenticate the user at the secured data source and establish a connection with the secured data source.

Abstract: Secured data access in virtual data processing is described. An example includes instructions to receive a request from an application in a compute node of a compute cluster in a virtual data processing environment to access a secured data source for a user, the virtual data processing environment including a multiple secured data sources that are accessible by compute nodes of the virtual compute cluster; fetch a credential in a current application context and forward the credential for validation; validate the credential with a credential authority; and, upon successfully validating the credential, authenticate the user at the secured data source and establish a connection with the secured data source.

Abstract: Secured data access in virtual data processing is described. An example includes instructions to receive a request from an application in a compute node of a compute cluster in a virtual data processing environment to access a secured data source for a user, the virtual data processing environment including a multiple secured data sources that are accessible by compute nodes of the virtual compute cluster; fetch a credential in a current application context and forward the credential for validation; validate the credential with a credential authority; and, upon successfully validating the credential, authenticate the user at the secured data source and establish a connection with the secured data source.

Abstract: A system for electrically coupling a first structure with a second structure in a vehicle is disclosed, and includes a control module receiving at least one of electrical power and data, a cable, and a reel. The cable has a variable length and is electrically coupled to the control module. The cable transmits at least one of electrical power and data from the first structure to the second structure. The reel is located at the first structure and defines an axis of rotation. The cable is windable around the reel, and the reel is rotatable about the axis of rotation to adjust the variable length of the cable. The variable length of the cable is a portion of the cable that extends between the first structure to the second structure that is not wound around the reel.

Abstract: A system for electrically coupling a first structure with a second structure in a vehicle is disclosed, and includes a control module receiving at least one of electrical power and data, a cable, and a reel. The cable has a variable length and is electrically coupled to the control module. The cable transmits at least one of electrical power and data from the first structure to the second structure. The reel is located at the first structure and defines an axis of rotation. The cable is windable around the reel, and the reel is rotatable about the axis of rotation to adjust the variable length of the cable. The variable length of the cable is a portion of the cable that extends between the first structure to the second structure that is not wound around the reel.

Abstract: Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

Abstract: A knit fabric having a modified knit structure comprising a first layer of jersey knit fabric and a second layer of jersey knit fabric, wherein the first and second layers of jersey knit fabric are joined to each other by a third layer of tuck stitches, and wherein the first and second jersey stitch layers include at least one continuous strand of bare rubber and a plurality of continuous strands selected from the group consisting of continuous strands of bare rubber and continuous strands of non-elastic yarn, and the third layer of tuck stitches are made of continuous strands of non-elastic yarn, knit together into the fabric so as to hold the first and second jersey stitch layers together.

Abstract: A container comprising a body portion and a neck portion, the neck portion having a pump dispenser thereon, the pump dispenser comprising a pump mechanism, a dip tube on one end of the pump mechanism, a pump outlet on another end of the pump mechanism, the dip tube extending downwardly from the pump mechanism into the body portion, the body portion containing a first liquid, the dip tube having a central bore along which the first liquid is pumped from the body portion when the pump mechanism is actuated, and a reservoir containing a second liquid, the reservoir communicating with the dip tube and adapted to introduce the second liquid into the first liquid within the pump mechanism or dip tube under the action of first liquid flowing through the dip tube.

Abstract: Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

Abstract: Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

Abstract: A method is provided for analyzing debris events after a launch of a rocket-propelled vehicle. Radar and Doppler data of the launch of the rocket-powered vehicle is collected for a period of time. Atmospheric conditions are determined at the time of launch. A trajectory of the rocket-propelled vehicle is determined during ascent. The collected radar and Doppler data is aligned and calibrated. A first portion of the collected radar and Doppler data is processed with a first means for assessing and characterizing debris. In parallel with the first portion of the collected radar and Doppler data, a second portion of the collected radar and Doppler data is processed with a second means for assessing and characterizing debris. Assessed and characterized debris is identified that may be a threat to the vehicle. And, reports of the identified debris are generated.

Abstract: Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

Abstract: A knit fabric having a modified knit structure comprising a first layer of jersey knit fabric and a second layer of jersey knit fabric, wherein the first and second layers of jersey knit fabric are joined to each other by a third layer of tuck stitches, and wherein the first and second jersey stitch layers include at least one continuous strand of bare rubber and a plurality of continuous strands selected from the group consisting of continuous strands of bare rubber and continuous strands of non-elastic yarn, and the third layer of tuck stitches are made of continuous strands of non-elastic yarn, knit together into the fabric so as to hold the first and second jersey stitch layers together.

Abstract: Object-code instruction traces are employed to analyze selected instructions of a year-2000 (Y2K) remediated application program for possible remediation failure when confronted by a year-2000 date. The analysis includes directly identifying one or more instructions of the remediated application program that may fail. A remediation-failure-pattern descriptor is assigned to each examined instruction which is indicative of whether the remediated instruction may fail when confronted by a date in the year-2000 range. The analysis employs user-specifiable run-control values, as well as predetermined filter-specification values in comparing traces of each selected object-code instruction to predefined remediation-failure patterns.

Abstract: A new and improved window sill extension kit and method of using this kit is disclosed for use in extending the available space around the sill of a window. The window sill extension kit comprises a display deck and a support bracket. The generally rectangular display deck having a first planar area, a second planar area positioned substantially perpendicular to the first planar area and a third planar area positioned substantially perpendicular to the second planar area and positioned substantially parallel to the first planar area. The display deck configuration allows for a stable platform when the first planar area is placed in the sill and secured by a closed window. The support bracket adds additional stabilization to the display deck. The support bracket comprises an L-shaped brace, a cap attached to the top of the L-shaped brace and a base attached to the bottom of the L-shaped brace.

Abstract: A central processing unit of an information handling system is provided with a Trap instruction to facilitate transfer of control from a user program to a trap program. A dispatchable unit control block (DUCT) of the CPU is loaded with the address of a trap control block, which in turn contains the addresses of a trap save area and a trap program. The user program is provided with Trap instructions at the desired transfer points. Upon decoding a Trap instruction in the user program, the CPU saves state information from the program status word (PSW), general registers and access registers in the designated trap save area, loads the address of the trap control block into a general register, and copies the address of the trap program into the instruction address field of the PSW to transfer control to the trap program. Upon completion of execution, the trap program may issue a Resume Program (RP) instruction to restore the previously saved state information to return control to the user program.

Abstract: A method of reclaiming a solid rocket motor which allows the motor case to be reused. The method comprises cooling the propellant to a temperature below the Tg range of the binder, shattering the cooled propellant and removing the shattered propellant from the rocket motor case.