Abstract: Methods and apparatuses for applying a correction that accounts for curvature in the space-time continuum in the context of clock synchronization are disclosed. A representative apparatus, among others, includes a memory having a curved space-time correction module and a processor. The processor is adapted to receive a reference message having a time-stamp from a master-clock and determine a correction to the time-stamp using the curved space-time correction module, wherein the correction accounts for curvature in space-time.

Abstract: Included in this disclosure is a quantum positioning system (QPS) that includes a corner cube reflector and a plurality of baselines. Each baseline may include an interferometer, which may include a photon source, a beam splitter, and a photon detector. The interferometer is configured for creating a bi-photon pair and initiating communication of the bi-photon pair with the corner cube reflector. Also included in the QPS is a positioning device configured to calculate a user's position.

Abstract: Methods and systems for synchronizing a first clock with a second clock, wherein the clocks are separated, are disclosed. A representative system, among others, includes a correlated particle emitter that emits a first particle stream and a second particle stream. Particles in the first particle streams are quantum mechanically correlated with particles in the second particle stream. The system also includes: a first target having the first clock and a first particle detector, and a second target having the second clock and a second particle detector. The first target uses the first clock and the first particle detector to determine arrival times of particles included in the first particle stream, and the second target uses the second clock and the second particle detector to determine arrival times of particles included in the first particle stream.

Abstract: A system for determining position coordinates and attitude coordinates of a moving object employs a plurality of transmitters that transmit navigation signals, the transmitters having known positions and orientations in a given coordinate system. A single antenna that is carried by the moving object receives signals associated with far-field regions of electromagnetic fields of the navigation signals transmitted from the transmitters. A satellite receiver that is carried by the moving object obtains the signals received by the antenna. Phase difference circuitry derives a phase difference between an open circuit voltage of the antenna and a reference phase of a local oscillator in the receiver. A calculation circuit calculates position coordinates and three-dimensional attitude coordinates, within the given coordinate system, of the antenna relative to the transmitters based on the known positions and orientations of the transmitters and the phase difference obtained by the phase difference circuitry.

Abstract: An electromagnetic launcher includes a single or multi-polar, multi-phase electrical generator powered by an external source; electrical conductors leading from output coils of the generator and from a center point joining the output coils; a plurality of rails connected to the electrical conductors; and an armature having at least two channels; whereby there is at least one position of the armature along the plurality of rails where current flows simultaneously through both of the at least two channels.