Abstract: Examples include techniques to improve signal integrity performance for a 3-connector design. The techniques include mounting a socket connector to a first side of a hot swap backplane such that pins of the first socket connector mirror pins of a second socket connector mounted to a second side of the hot swap backplane. The mirrored pins associated with routing data signals. The socket connector having a housing configured to receive a first plug connector of a cable assembly that has a second plug connector coupled with a processor baseboard socket connector.

Abstract: Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

Abstract: In a general aspect, interfacial surface structures for removing carbon dioxide from a gaseous feed are presented. In some cases, a method of removing carbon dioxide gas from a gaseous feed includes wetting surfaces of an interfacial surface structure in a gas-liquid contactor with an alkaline capture solution. The gaseous feed containing the CO2 gas is passed across the wetted surfaces of the interfacial surface structure to dissolve the CO2 gas in the alkaline capture solution. A CO2-rich alkaline capture solution is collected from the gas-liquid contactor. The CO2-rich alkaline capture solution includes dissolved CO2 gas from the gaseous feed.

Abstract: The present disclosure relates to a genetically modified host cell having increased production of one or more vitamin B compounds, wherein the host cell is genetically modified by mutating one or more native polynucleotide constructs for reducing formation of a CRP-cAMP complex in the host cell and/or introducing one or more genetic alterations increasing the degradation and/or non-CRP binding of cAMP in the host cell; whereby the production of the vitamin B compound in the genetically modified host cell is increased compared to a parent host cell.

Abstract: In a general aspect, interfacial surface structures for removing carbon dioxide from a gaseous feed are presented. In some cases, a method of removing carbon dioxide gas from a gaseous feed includes wetting surfaces of an interfacial surface structure in a gas-liquid contactor with an alkaline capture solution. The gaseous feed containing the CO2 gas is passed across the wetted surfaces of the interfacial surface structure to dissolve the CO2 gas in the alkaline capture solution. A CO2-rich alkaline capture solution is collected from the gas-liquid contactor. The CO2-rich alkaline capture solution includes dissolved CO2 gas from the gaseous feed.

Abstract: Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.

Abstract: Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

Abstract: Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

Abstract: A method and system for controlling autonomous vehicles comprises a flight controller comprising at least one processor and a computer-usable medium embodying computer program code, the computer-usable medium capable of communicating with at least one processor, the computer program code comprising instructions executable by at least one processor and configured for controlling a vehicle, the flight controller further comprising: an obstacle avoidance module, a state machine, a data link module, and a control computer module.

Abstract: Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.

Abstract: A system for controlling one or more fans, comprising an open loop control system configured to receive a CPU power level and to maintain a fan speed at an open loop fan speed level. A closed loop control system configured to receive the CPU power level and temperature, and to modify the fan speed as a function of the CPU power level and temperature, wherein the fan speed is maintained at a level that is not lower than the open loop fan speed level.

Abstract: Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

Abstract: The present invention relates to a delivery device for delivering predetermined amounts of fluid, comprising a body (10), a container (16) filled with fluid to be delivered arranged inside said body, said container comprising an opening for expelling said fluid and a wall (18) movable inside said container (16), a threaded plunger rod (46) arranged movable inside said body (10) in the longitudinal direction and in contact with said movable wail (18), a manually operated push means (14, 60) movable in the longitudinal direction capable of, upon operation, move said plunger rod (46) towards said movable wall (18), thereby expelling fluid, and means for transforming a generally linear movement of said push means (14, 60) to a rotational movement of said plunger rod (46).

Abstract: Components of a device may transmit signals between one another using piezo electric transducers (PETs). In a basic system, a first PET may be coupled to and/or in contact with a first location on a member. A second PET may be coupled to and/or in contact with a second location on the member and separated from the first PET by a distance. The first PET may receive a signal (e.g., an electrical voltage) and convert the signal to a mechanical force/stress causing vibration of the member. The vibration may propagate through the member to other locations about the member. The second PET receive the vibration and may convert the vibration back to the signal, such as by converting mechanical force/stress to the electrical voltage (i.e., the signal). A similar process may be performed in reverse to enable the first and second PET to provide two-way communication.

Abstract: Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

Abstract: Methods and systems for supporting similar thermal devices may involve collecting, by a thermal module on a management controller of an information handling system, device information about an add-in card, determining whether the add-in card was previously defined by matching the device against a table, searching the table based on the determination that the add-in card was not previously defined, determining whether the add-in card is supported by finding a match in the table, and applying a thermal tier associated with the match in the table based on the determination that the add-in card is supported. The device information collected may involve at least two of a reseller part number, description, device identifier, sub device identifier, vendor identifier, sub vendor identifier, slot identifier, lane width, and auxiliary power indicator. The search of the table may involve at least one of the description, lane width, and sub vendor identifier.

Abstract: A system to determine position and/or heading may include a receiver including at least two antennas configured to be coupled to the vehicle and receive electromagnetic signals including at least one of microwaves or radio waves. The system may also include a navigation module configured to determine first and second locations associated with respective first and second transmitters that send respective first and second signals. The navigation module may also be configured to determine, based at least in part on the first signals, a first relative orientation of the receiver relative to the first transmitter, and determine, based at least in part on the second signals, a second relative orientation of the receiver relative to the second transmitter. The navigation module may also be configured to determine a position and/or heading of the vehicle based at least in part on the first and second relative orientations of the receiver.

Abstract: A system for controlling one or more fans, comprising an open loop control system configured to receive a CPU power level and to maintain a fan speed at an open loop fan speed level. A closed loop control system configured to receive the CPU power level and temperature, and to modify the fan speed as a function of the CPU power level and temperature, wherein the fan speed is maintained at a level that is not lower than the open loop fan speed level.

Abstract: Systems for landing and facilitating power flow or data transfer between an unmanned aerial vehicle (UAV) and a charging mat using a boom are described. The system includes a mat with a conductive mesh on the top and a conductive surface on the other bottom of the mat. The conductive mesh and bottom conductive surface are separated (electrically isolated) by an isolation core. The outer portion of the boom contacts part of the conductive mesh of the mat to create an electrical pathway. An inner portion of the boom penetrates through the top layer conductive mesh, through the isolating core, and contacts the bottom conductive surface of the mat to create another electrical pathway.

Abstract: Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.