A mechanism to reduce the amplitude of acceleration experienced by IMUs for tracked objects while maintaining a more accurate estimate of the device orientation. The invention uses parallel mechanisms to maintain the correct orientation of an IMU while allowing for damped translational degrees of freedom to limit the degradation of performance while spatially tracking a body.

In general, the subject matter described in this disclosure can be embodied in methods, systems, and program products for receiving an indication that a vehicle has begun accelerating from a stationary state. A computing system sets, in response to having received the indication that the vehicle has begun accelerating from the stationary state, an orientation value generated using a gyroscope to a default orientation value. The computing system repeatedly updates the orientation value generated using the gyroscope, based on changes in gyroscope orientation that occurred after the computing system set the orientation value to the default orientation value. The computing system determines that the updated orientation value satisfies criteria that indicates that the vehicle is likely to encounter or has encountered a dangerous situation. The computing system outputs a signal to cause the vehicle to employ a safety measure.

The present invention relates to capacitive micromechanical accelerometers, and in particular to acceleration sensors with movable rotors which may rotate out of a substrate plane when the accelerometer undergoes movement with an acceleration component perpendicular to the substrate plane. The capacitive micromechanical accelerometer includes additional damping springs to reduce unwanted movement of the rotor in the substrate plane, thereby reducing the parasitic capacitance that results from motion of the rotor in the substrate plane. The damping springs are vertically recessed with respect to other components of the accelerometer in order to minimise the effect of the damping springs on movement of the rotor out of the substrate plane.

A resonator having a support and a seismic mass. Movement means include a first electromagnetic assembly comprising a first electric coil that is not electrically powered. An actuator is connected to a processor unit, the processor unit electrically powering the actuator with adjustable electrical power. A resilient member is interposed between said seismic mass and said support.

A micromechanical sensor that is produced surface-micromechanically includes at least one mass element formed in a third functional layer that is non-perforated at least in certain portions. The sensor has a gap underneath the mass element that is formed by removal of a second functional layer and at least one oxide layer. The removal of the at least one oxide layer takes place by introducing a gaseous etching medium into a defined number of etching channels arranged substantially parallel to one another. The etching channels are configured to be connected to a vertical access channel in the third functional layer.

An inertial sensor includes oscillating-type angular velocity sensing element (32), IC (34) for processing signals supplied from angular velocity sensing element (32), capacitor (36) for processing signals, and package (38) for accommodating angular velocity sensing element (32), IC (34), capacitor (36). Element (32) and IC (34) are housed in package (38) via a vibration isolator, which is formed of TAB tape (46), plate (40) on which IC (34) is placed, where angular velocity sensing element (32) is layered on IC (34), and outer frame (44) placed outside and separately from plate (40) and yet coupled to plate (40) via wiring pattern (42).

The present disclosure relates to an inertia measurement module for an unmanned aircraft, which comprises a housing assembly, a sensing assembly and a vibration damper. The vibration damper comprises a first vibration-attenuation cushion; and the sensing assembly comprises a first circuit board, a second circuit board and a flexible signal line for connecting the first circuit board and the second circuit board. An inertia sensor is fixed on the second circuit board, and the first circuit board is fixed on the housing assembly. The inertia measurement module further comprises a weight block, and the second circuit board, the weight block, the first vibration-attenuation cushion and the first circuit board are bonded together. The present disclosure greatly reduces the influence of the operational vibration frequency of the unmanned aircraft on the inertia sensor and improves the measurement stability of the inertia sensor.

A vibration sensor includes a mass block supported with the aid of at least one spring in a manner allowing movement relative to a frame in a measuring direction, a displacement of the mass block in the measuring direction relative to the frame being detectable by a position-measuring device. The position-measuring device includes a measuring standard and a scanning head aligned with the measuring standard. One of these two components is secured on the mass block, and the other is secured on the frame.

Linear accelerometer comprising a fixed part, a rotationally moving part in the plane of the accelerometer around an axis of rotation orthogonal to the plane of the accelerometer, the moving part comprising a centre of gravity distinct from the point of intersection of the axis of rotation and the plane of the accelerometer, means forming pivot link between the moving part and the fixed part, means for detecting the displacement of the moving part with respect to the fixed part, means for viscous damping the displacement of the moving part in said plane, said viscous damping means comprising interdigitated combs, at least one first comb on the moving part and at least one second comb on the fixed part (2), the first comb and the second comb being interdigitated.

An inertia measure unit (IMU) includes a housing assembly, a weight block assembly, a circuit board, and a signal line. The housing assembly includes a cavity and a first opening in communication with the cavity. The weight block assembly is arranged in the cavity of the housing assembly. The weight block assembly includes a weight block forming an inner chamber and a second opening in communication with the inner chamber. An opening direction of the second opening is opposite to an opening direction of the first opening. The circuit board is disposed in the inner chamber. The signal line is coupled to an edge of the circuit board and sequentially extends out from the second opening and the first opening.