A stabilization device for stabilizing an attachment component relative to movements of a basic component which occur outside a permitted plane of movement. The attachment component and the basic component are connected via a stabilization arrangement that includes: a first compensation arrangement for compensating rotational movements of the basic component with respect to an intermediate component, about rotational axes lying in the plane of movement, including a first compensation device which can be actuated actively, a second compensation arrangement for compensating residual linear movements of the intermediate component in a compensation direction, perpendicular to the plane of movement, in relation to the attachment component, having a second compensation device which can be actuated actively, a plurality of inertial sensors assigned to the first and/or second compensation arrangement, and a control device for actuating the compensation devices for movement compensation as a function of sensor data of the inertial sensors.

The disclosure discloses a latitude-free initial alignment method under a swaying base based on gradient descent optimization. Firstly, swaying base latitude-free alignment is regarded as a Wahba attitude determination problem to inhibit device noise interference, and an objective function is established based on a gravitational acceleration vector under an earth system; then an exact solution of the objective function is obtained through a gradient descent optimization method, and inertial system conversion quaternion estimation is achieved under the latitude-free condition; and finally, an attitude quaternion is determined by only using information of an accelerometer and a gyroscope of a strapdown attitude heading reference system, and therefore latitude-free initial alignment under the swaying base is achieved. The disclosure can solve the problem that initial alignment cannot be accomplished with unknown latitude under the swaying base, and thus the application range of the strapdown attitude heading reference system is ensured.

The disclosure discloses a latitude-free initial alignment method under a swaying base based on gradient descent optimization. Firstly, swaying base latitude-free alignment is regarded as a Wahba attitude determination problem to inhibit device noise interference, and an objective function is established based on a gravitational acceleration vector under an earth system; then an exact solution of the objective function is obtained through a gradient descent optimization method, and inertial system conversion quaternion estimation is achieved under the latitude-free condition; and finally, an attitude quaternion is determined by only using information of an accelerometer and a gyroscope of a strapdown attitude heading reference system, and therefore latitude-free initial alignment under the swaying base is achieved. The disclosure can solve the problem that initial alignment cannot be accomplished with unknown latitude under the swaying base, and thus the application range of the strapdown attitude heading reference system is ensured.

A rotation measurement system that includes at least two proof masses and at least one pick-off is provided. Each proof mass is driven in a first axis of motion. The at least one pick-off is configured to measure movement of the at least two proof masses in a second axis when the system is rotated about a rotation point and generate Coriolis signals and Euler signals based on the measured movement of the at least two proof masses.

A rotation measurement system that includes at least two proof masses and at least one pick-off is provided. Each proof mass is driven in a first axis of motion. The at least one pick-off is configured to measure movement of the at least two proof masses in a second axis when the system is rotated about a rotation point and generate Coriolis signals and Euler signals based on the measured movement of the at least two proof masses.

The presently disclosed subject matter includes a method and system directed for calculating azimuth of an airborne platform during flight based on IMU measurements, without using GNSS data, gyrocompassing or magnetometers operating on the ground for determining the azimuth.

The presently disclosed subject matter includes a method and system directed for calculating azimuth of an airborne platform during flight based on IMU measurements, without using GNSS data, gyrocompassing or magnetometers operating on the ground for determining the azimuth.

An electronic apparatus is provided. The electronic apparatus includes an acceleration sensor, a gyro sensor, a geomagnetic sensor, and a processor configured to compare geomagnetic data of the geomagnetic sensor and gyro data of the gyro sensor and correct the gyro data, determine a first value based on a principal component analysis (PCA) of acceleration data of the acceleration sensor, and determine a second value based on a PCA of the gyro data, and estimate a moving direction of the electronic apparatus based on the first value and the second value.

An electronic apparatus is provided. The electronic apparatus includes an acceleration sensor, a gyro sensor, a geomagnetic sensor, and a processor configured to compare geomagnetic data of the geomagnetic sensor and gyro data of the gyro sensor and correct the gyro data, determine a first value based on a principal component analysis (PCA) of acceleration data of the acceleration sensor, and determine a second value based on a PCA of the gyro data, and estimate a moving direction of the electronic apparatus based on the first value and the second value.

A system for orienting a marine vessel is provided. The system includes marine propulsion devices, a gyroscopic stabilizer system, and a controller operably coupled to the marine propulsion devices and the gyroscopic stabilization system. The controller is configured to control operation of the marine propulsion devices to minimize a control torque output of the gyroscopic stabilizer system while maintaining the marine vessel in a selected global position and/or heading.