Abstract: Technologies for computing context replay include a computing device having a persistent memory and a volatile memory. The computing device creates multiple snapshots that are each indicative of a user's computing context at a corresponding sync point. The snapshots may include metadata created in response to system events, memory snapshots stored in a virtual machine, and/or video data corresponding to the computing context. At least a part of the snapshots are stored in the persistent memory. The computing device presents a timeline user interface based on the snapshots. The timeline includes multiple elements that are associated with corresponding sync points. The timeline elements may visually indicate a salience value that has been determined for each corresponding sync point. In response to a user selection of a sync point, the computing device activates a computing context corresponding to the snapshot for the selected sync point. Other embodiments are described and claimed.

Abstract: A radial bleed total thrust control system for a rocket propelled missile. In the preferred embodiment, the apparatus employs at least two pairs of straight radial nozzles which are disposed within and penetrate the skin of the missile and at least two pairs of tangentially canted radial nozzles which are also disposed within and penetrate the skin of the missile to provide control moments necessary to control the pitch, yaw, roll and/or the axial thrust of the missile. In one embodiment the radial and tangential nozzles are supplied by the same source of propelling gas as the main thrust nozzle, and in a second embodiment the straight radial and tangentially canted radial nozzles have a separate gas supply source.

Abstract: A radial bleed total thrust control system for a rocket propelled missile. In the preferred embodiment, the apparatus employs at least two pairs of straight radial nozzles which are disposed within and penetrate the skin of the missile and at least two pairs of tangentially canted radial nozzles which are also disposed within and penetrate the skin of the missile to provide control moments necessary to control the pitch, yaw, roll and/or the axial thrust of the missile. In one embodiment the radial and tangential nozzles are supplied by the same source of propelling gas as the main thrust nozzle, and in a second embodiment the straight radial and tangentially canted radial nozzles have a separate gas supply source.