An inertial measurement apparatus based on atom interferometry. In one example, the inertial measurement apparatus includes a vacuum chamber, first and second atom capture sites housed within the vacuum chamber, each of the first and second atom capture sites being selectively configured to trap and cool first and second atom samples of distinct atom species, an atom interferometry region disposed between the first and second atom capture sites, and first and second atom interferometers operating in the atom interferometry region, the first atom interferometer being configured to generate a first measurement corresponding to a common inertial input based on the first atom sample, and the second atom interferometer being configured to generate a second measurement corresponding to the same common inertial input based on the second atom sample.

An inertial measurement apparatus based on atom interferometry. In one example, the inertial measurement apparatus includes a vacuum chamber, first and second atom capture sites housed within the vacuum chamber, each of the first and second atom capture sites being selectively configured to trap and cool first and second atom samples of distinct atom species, an atom interferometry region disposed between the first and second atom capture sites, and first and second atom interferometers operating in the atom interferometry region, the first atom interferometer being configured to generate a first measurement corresponding to a common inertial input based on the first atom sample, and the second atom interferometer being configured to generate a second measurement corresponding to the same common inertial input based on the second atom sample.

Atom-scale particles, e.g., neutral and charged atoms and molecules, are pre-cooled, e.g., using magneto-optical traps (MOTs), to below 100 μK to yield cold particles. The cold particles are transported to a sensor cell which cools the cold particles to below 1 μK using an optical trap; these particles are stored in a reservoir within an optical trap within the sensor cell so that they are readily available to replenish a sensor population of particles in quantum superposition. A baffle is disposed between the MOTs and the sensor cell to prevent near-resonant light leaking from the MOTs from entering the sensor cell (and exciting the ultra-cold particles in the reservoir). The transporting from the MOTs to the sensor cell is effected by moving optical fringes of optical lattices and guiding the cold particles attached to the fringes along a meandering path through the baffle and into the sensor cell.

Embodiments of the present disclosure are directed towards a micro-electromechanical system (MEMS) sensing apparatus, including a laser arrangement configured to generate a light beam, a first waveguide configured to receive and output the light beam, and a second waveguide aligned endface to endface with the first waveguide. The second waveguide may be configured to receive at least a portion of the light beam from the first waveguide via optical coupling through the aligned endfaces. Either the first or second waveguide may be configured to be moveable in response to an inertial change of the apparatus, wherein movement of the first or second waveguide causes a corresponding change in light intensity of the portion of the light beam, the change in light intensity indicating a measure of the inertial change. Other embodiments may be described and/or claimed.

Embodiments of the present disclosure are directed towards a micro-electromechanical system (MEMS) sensing apparatus, including a laser arrangement configured to generate a light beam, a first waveguide configured to receive and output the light beam, and a second waveguide aligned endface to endface with the first waveguide. The second waveguide may be configured to receive at least a portion of the light beam from the first waveguide via optical coupling through the aligned endfaces. Either the first or second waveguide may be configured to be moveable in response to an inertial change of the apparatus, wherein movement of the first or second waveguide causes a corresponding change in light intensity of the portion of the light beam, the change in light intensity indicating a measure of the inertial change. Other embodiments may be described and/or claimed.

The invention relates to a device for detecting acceleration. The device contains: a frame; a mass; a lever arm connected to the mass, wherein the mass is provided at a first lever position; an optical fiber having a fiber-optic sensor; and a compensation element for disturbance variables, wherein the compensation element for disturbance variables is connected to the lever arm or the mass and wherein the compensation element for disturbance variables is connected to the frame.

The invention relates to a device for detecting acceleration. The device contains: a frame; a mass; a lever arm connected to the mass, wherein the mass is provided at a first lever position; an optical fiber having a fiber-optic sensor; and a compensation element for disturbance variables, wherein the compensation element for disturbance variables is connected to the lever arm or the mass and wherein the compensation element for disturbance variables is connected to the frame.

A high-precision magnetic suspension accelerometer for measuring the linear acceleration of a spacecraft is provided, comprising a magnetically shielded vacuum chamber system, a magnetic displacement sensing system, a magnetic suspension control system and a small magnetic proof mass. A optical coherence displacement detection technique is utilized for precisely measuring the position and the posture of the small magnetic proof mass in real time, and a magnetic suspension control technique is utilized for precisely controlling the position and the posture of the small magnetic proof mass to be brought back to the origin, so as to keep the small magnetic proof mass in the center of the systemic inner chamber. When the spacecraft is subject to a non-conservative force, the magnitude and direction of the acceleration can be precisely measured via the measurement of currents in the position control coils due to the acceleration of the spacecraft proportional to the currents of the position control coils. The accelerometer of the invention can avoid the technical bottleneck of high-precision machining, is easy to be produced and can achieve more high-precision measurement of the acceleration vector.

Embodiments of the present disclosure set forth techniques for compensating for a roll effect for an optical sensor. The techniques include receiving sensor data from at least one sensor associated with the vehicle, detecting an amount of a roll of the vehicle based on the sensor data, generating a command based on the detected amount of roll, and controlling an orientation of the optical sensor based on the command.

Embodiments of the present disclosure set forth techniques for compensating for a roll effect for an optical sensor. The techniques include receiving sensor data from at least one sensor associated with the vehicle, detecting an amount of a roll of the vehicle based on the sensor data, generating a command based on the detected amount of roll, and controlling an orientation of the optical sensor based on the command.