A noise cancelling gradiometer probe includes an insulating material having a first side and a second side; a first, second, third and fourth coaxial cables forming a first, second, third and fourth loops, respectively, where a portion of each of the first, second, third and fourth loops is locating on the first side of the insulating material and a portion of the first, second, third and fourth loops is locating on the second side of the insulating material.

A noise cancelling gradiometer probe includes an insulating material having a first side and a second side; a first, second, third and fourth coaxial cables forming a first, second, third and fourth loops, respectively, where a portion of each of the first, second, third and fourth loops is locating on the first side of the insulating material and a portion of the first, second, third and fourth loops is locating on the second side of the insulating material.

A high bandwidth gravimeter or accelerometer includes laser(s), modulator(s), and an atomic interferometer. The laser(s) and modulator(s) produce four laser frequencies. A first and second pair of laser frequencies are each separated by w.sub.m. The first and second pair are offset by w.sub.shift. A first laser frequency of the first pair and a second laser frequency of the second pair are separated by w.sub.m+w.sub.shift. A second laser frequency of the first pair and a first laser frequency of the second pair are separated by w.sub.m−w.sub.shift. The first pair is routed to arrive from a first direction at atoms in an interaction region, and the second pair from a second direction. The first pair are phase stable with respect to the second pair. w.sub.m is adjusted so that w.sub.m+w.sub.shift or w.sub.m−w.sub.shift corresponds to a Raman resonance for the atomic interferometer.

A high bandwidth gravimeter or accelerometer includes laser(s), modulator(s), and an atomic interferometer. The laser(s) and modulator(s) produce four laser frequencies. A first and second pair of laser frequencies are each separated by w.sub.m. The first and second pair are offset by w.sub.shift. A first laser frequency of the first pair and a second laser frequency of the second pair are separated by w.sub.m+w.sub.shift. A second laser frequency of the first pair and a first laser frequency of the second pair are separated by w.sub.m−w.sub.shift. The first pair is routed to arrive from a first direction at atoms in an interaction region, and the second pair from a second direction. The first pair are phase stable with respect to the second pair. w.sub.m is adjusted so that w.sub.m+w.sub.shift or w.sub.m−w.sub.shift corresponds to a Raman resonance for the atomic interferometer.

The disclosure relates to a gravity gradiometer including a pair of magneto-optical traps for measuring a gravity gradient. A cold atom gravity gradiometer system includes comprising: first and second magneto-optical traps, each having a plurality of mirrored surfaces arranged to reflect an incident laser beam to trap respective first and second cold atom clouds separated from each other by a separation distance; an optical subsystem arranged to transmit a first laser beam in a first direction along a first longitudinal axis towards the first magneto-optical trap and a second laser beam in an opposite second direction along a second longitudinal axis towards the second magneto-optical trap, the second longitudinal axis being parallel to the first longitudinal axis.

The disclosure relates to a gravity gradiometer including a pair of magneto-optical traps for measuring a gravity gradient. A cold atom gravity gradiometer system includes comprising: first and second magneto-optical traps, each having a plurality of mirrored surfaces arranged to reflect an incident laser beam to trap respective first and second cold atom clouds separated from each other by a separation distance; an optical subsystem arranged to transmit a first laser beam in a first direction along a first longitudinal axis towards the first magneto-optical trap and a second laser beam in an opposite second direction along a second longitudinal axis towards the second magneto-optical trap, the second longitudinal axis being parallel to the first longitudinal axis.

A system implementing a method for generating a navigation output is provided. The method includes determining a gravitational anomaly estimate based at least in part on inertial sensor data and navigation output; generating navigation and sensor corrections that are due at least in part on inherent sensor errors that include vertical accelerometer/gravimeter corrections from at least a navigation output estimate, the gravitational anomaly estimate, and the gravity map data; and generating the navigation output based on the inertial sensor data, gravity map data and the navigation and sensor corrections.

A system implementing a method for generating a navigation output is provided. The method includes determining a gravitational anomaly estimate based at least in part on inertial sensor data and navigation output; generating navigation and sensor corrections that are due at least in part on inherent sensor errors that include vertical accelerometer/gravimeter corrections from at least a navigation output estimate, the gravitational anomaly estimate, and the gravity map data; and generating the navigation output based on the inertial sensor data, gravity map data and the navigation and sensor corrections.

An inertial navigation system (INS) device includes three or more atomic interferometer inertial sensors, three or more atomic interferometer gravity gradiometers, and a processor. Three or more atomic interferometer inertial sensors obtain raw inertial measurements for three or more components of linear acceleration and three or more components of rotation. Three or more atomic interferometer gravity gradiometers obtain raw measurements for three or more components of the gravity gradient tensor. The processor is configured to determine position using the raw inertial measurements and the raw gravity gradient measurements.

An inertial navigation system (INS) device includes three or more atomic interferometer inertial sensors, three or more atomic interferometer gravity gradiometers, and a processor. Three or more atomic interferometer inertial sensors obtain raw inertial measurements for three or more components of linear acceleration and three or more components of rotation. Three or more atomic interferometer gravity gradiometers obtain raw measurements for three or more components of the gravity gradient tensor. The processor is configured to determine position using the raw inertial measurements and the raw gravity gradient measurements.