A wholistic activity context is used to determine whether to calibrate a barometric pressure sensor of a mobile device. A pair of activity transitions are determined from three activities of the mobile device. A time relationship and a position relationship between the activity transitions is determined. An opportunity to calibrate the barometric pressure sensor occurs between the activity transitions. A calibration of the barometric pressure sensor is performed in response to determining that the time relationship and the position relationship indicate that the wholistic activity context surrounding the opportunity to calibrate the barometric pressure sensor is conducive to calibration.

An inertial navigation system includes a first inertial measurement unit with at least a first sensor and a second inertial measurement unit with at least a second sensor corresponding in type to the first sensor. The first inertial measurement unit is rotatably mounted relative to the second inertial measurement unit, The inertial navigation system further include a controller arranged to: acquire a first set of measurements simultaneously from both the first inertial measurement unit and the second inertial measurement unit; rotate the first inertial measurement unit relative to the second inertial measurement unit; acquire a second set of measurements simultaneously from both the first inertial measurement unit and the second inertial measurement unit; and calculate from the first set of measurements and the second set of measurements at least one error characteristic of the first sensor and/or the second sensor.

The invention provides an inertial sensing device the capability to achieve self-alignment (sensor error compensation), by using dual-rotation modulation technique. The self-alignment process is performed based on fully building the sensor's mathematical model and rotating the inertial sensor blocks in a specific order. The advantages of this technology are fast calibration time, high accuracy, and the ability to separate independent movements on the axes of the inertial sensor. The inertial sensor based on a dual-rotation modulation platform is applied to marine and aeronautical fields.

The invention provides an inertial sensing device the capability to achieve self-alignment (sensor error compensation), by using dual-rotation modulation technique. The self-alignment process is performed based on fully building the sensor's mathematical model and rotating the inertial sensor blocks in a specific order. The advantages of this technology are fast calibration time, high accuracy, and the ability to separate independent movements on the axes of the inertial sensor. The inertial sensor based on a dual-rotation modulation platform is applied to marine and aeronautical fields.

A thermal regulation system includes a sensor, one or more temperature adjusting devices, and a filler provided in a space between the sensor and at least one of the one or more temperature adjusting devices. The one or more temperature adjusting devices are (1) in thermal communication with the sensor, and (2) configured to adjust a temperature of the sensor from an initial temperature to a predetermined temperature at a rate of temperature change that meets or exceeds a threshold value.

The present invention relates to a method for calibrating an altitude sensing stereo vision device (122) of an unmanned aerial vehicle (100), wherein the method includes: arranging the unmanned aerial vehicle to take off from ground (G) and ascend; deriving at least one first altitude value (10a-15a) from the stereo vision device and obtaining at least one corresponding second altitude value (10b-15b) from another device (123) of the unmanned aerial vehicle during the ascent (1) of the unmanned aerial vehicle; recording the derived at least one first altitude value and the obtained at least one corresponding second altitude value as calibration data; deriving an additional first altitude value from the stereo vision device while the unmanned aerial vehicle flies a route; and adjusting the derived additional first altitude value based on the recorded calibration data.

The present invention relates to a method for calibrating an altitude sensing stereo vision device (122) of an unmanned aerial vehicle (100), wherein the method includes: arranging the unmanned aerial vehicle to take off from ground (G) and ascend; deriving at least one first altitude value (10a-15a) from the stereo vision device and obtaining at least one corresponding second altitude value (10b-15b) from another device (123) of the unmanned aerial vehicle during the ascent (1) of the unmanned aerial vehicle; recording the derived at least one first altitude value and the obtained at least one corresponding second altitude value as calibration data; deriving an additional first altitude value from the stereo vision device while the unmanned aerial vehicle flies a route; and adjusting the derived additional first altitude value based on the recorded calibration data.

An online trimming device and method for a micro-shell resonator gyroscope is provided. A micro-shell resonator gyroscope fixing fixture and a mode test circuit in the device are placed in a vacuum test cavity provided with a circuit interface. The mode test circuit and a host computer are connected through a circuit interface on the vacuum test cavity. The gyroscope fixing fixture is provided with a signal interface, and the electrodes on the gyroscope substrate are connected to the signal interface. The signal interface on the fixture is connected to the mode test circuit. The laser etching module is located at the top of the device. An opening is formed in the gyroscope fixing fixture. The vacuum test cavity is provided with a transparent trimming window. The laser acts on the edge of the resonant structure of the gyroscope through the trimming window and the through hole of the fixture.

An online trimming device and method for a micro-shell resonator gyroscope is provided. A micro-shell resonator gyroscope fixing fixture and a mode test circuit in the device are placed in a vacuum test cavity provided with a circuit interface. The mode test circuit and a host computer are connected through a circuit interface on the vacuum test cavity. The gyroscope fixing fixture is provided with a signal interface, and the electrodes on the gyroscope substrate are connected to the signal interface. The signal interface on the fixture is connected to the mode test circuit. The laser etching module is located at the top of the device. An opening is formed in the gyroscope fixing fixture. The vacuum test cavity is provided with a transparent trimming window. The laser acts on the edge of the resonant structure of the gyroscope through the trimming window and the through hole of the fixture.

There is provided a drive control device, a drive control method, and a program that allow for an improvement in detection accuracy of a multi-IMU. Angular velocities supplied from a plurality of inertial measurement units (IMUs) are acquired, drive frequencies of the plurality of IMUs are calculated on the basis of acquisition timings of the acquired angular velocities, and on the basis of the drive frequencies of the plurality of IMUs, in a case where an interval between peak frequencies of the drive frequencies is smaller than ½ of a half width of a drive frequency distribution, control is performed so as to change the drive frequencies by heating or cooling temperatures of the IMUs so that the interval can be widened. The present disclosure can be applied to a multi-IMU.