Abstract: Various aspects of the present disclosure generally relate to wireless communication. In some aspects, a user equipment (UE) may establish a voice call. The UE may receive a configuration for a discontinuous reception (DRX) cycle indicating at least an ON duration and a DRX cycle duration. The UE may receive a configuration for a scheduling request (SR) indicating an SR period duration for transmitting an SR. The UE may detect that the SR period duration is greater than the DRX cycle duration. The UE may generate, based at least in part on the SR period duration being greater than the DRX cycle duration, a voice data packet to be available for transmission within a threshold time of a start of the ON duration. The UE may transmit the voice data packet on a resource identified by a grant received from the network. Numerous other aspects are described.

Abstract: Various aspects of the present disclosure generally relate to wireless communication. In some aspects, a user equipment (UE) may identify an indication of an occurrence of a handover. The UE may adjust a delay used by a buffer based at least in part on the indication of the occurrence of the handover. The UE may process one or more packets of the buffer based at least in part on the adjustment of the delay used by the buffer. Numerous other aspects are described.

Abstract: A conical scanning method and system is provided for orienting a spacecraft with respect to a source. The system includes a spacecraft and an incidence angle sensor secured to the spacecraft to sense a signal from a source. The incidence angle sensor has a boresight that is canted with respect to the principal axis. A processor communicates with actuators on the spacecraft to adjust an attitude of the spacecraft based on information received from the incidence angle sensor and to thereby align a principal axis of the spacecraft with a direction from the spacecraft to the source. The method and system can also rely on information received from source presence sensors. The source may be the Sun, or a non-solar signal source.

Abstract: A conical scanning method and system is provided for orienting a spacecraft with respect to a source. The system includes a spacecraft and an incidence angle sensor secured to the spacecraft to sense a signal from a source. The incidence angle sensor has a boresight that is canted with respect to the principal axis. A processor communicates with actuators on the spacecraft to adjust an attitude of the spacecraft based on information received from the incidence angle sensor and to thereby align a principal axis of the spacecraft with a direction from the spacecraft to the source. The method and system can also rely on information received from source presence sensors. The source may be the Sun, or a non-solar signal source.

Abstract: A communication system is provided. The communication system includes a directional antenna, an antenna steering system to steer the directional antenna, a memory, and one or more processors coupled to the memory, the directional antenna, and the antenna steering system. The one or more processors are configured to identify a communication target and state information associated with the communication target, instruct the antenna steering system to steer the at least one directional antenna towards the communication target based on the state information, instruct the antenna steering system to perform a received power scan within a scan area to determine a maximum received power direction associated with a signal transmitted from the communication target, and track the maximum received power direction.

Abstract: A load relief system for a launch vehicle including a wind sensing system responsive to wind speed and direction at selected locations for providing an output of sensed wind speed and wind direction at the selected locations, a plant model responsive to the sensed wind speed and direction within a finite horizon, a current state of the launch vehicle, and control commands of the launch vehicle to predict the trajectory of the launch vehicle, an error circuit responsive to the predicted trajectory and a reference trajectory to produce a trajectory error, and an optimizer responsive to the trajectory error and configured to provide control commands to compensate for wind load over the finite horizon of the launch vehicle by reducing the total angle of attack.

Abstract: A load relief system for a launch vehicle including a wind sensing system responsive to wind speed and direction at selected locations for providing an output of sensed wind speed and wind direction at the selected locations, a plant model responsive to the sensed wind speed and direction within a finite horizon, a current state of the launch vehicle, and control commands of the launch vehicle to predict the trajectory of the launch vehicle, an error circuit responsive to the predicted trajectory and a reference trajectory to produce a trajectory error, and an optimizer-responsive to the trajectory error and configured to provide control commands to compensate for wind load over the finite horizon of the launch vehicle by reducing the total angle of attack.