A user equipment (UE) is described. The UE includes a higher layer processor configured to receive an RRC message for enhanced resource element group (EREG) configuration. The UE also includes a physical downlink control channel receiver configured to monitor an enhanced physical downlink control channel (EPDCCH) on the basis of a first EREG structure if the EREG configuration is not established, and to monitor the EPDCCH on the basis of a second EREG structure if the EREG configuration is established. All resource elements (REs) with number i in a physical resource block (PRB) pair comprise EREG number i.

User equipments, base stations and methods

This paper presents experimental data about the sources of the quadrature error in a fully decoupled microelectromechanical systems gyroscope and demonstrates the extent of performance improvement by the cancellation of this error. Quadrature sources including mass, electrostatic-force, and mechanical-spring imbalances have been compared by FEM simulations, and spring imbalance has been found as the dominant source of the quadrature error. Gyroscopes have been designed with intentional spring imbalances and fabricated with a SOI-based silicon-on-glass fabrication process, the resulting quadrature outputs of the fabricated gyroscopes have been measured, and their agreement with FEM simulations has been verified. Next, it has been experimentally shown that the electrostatic nulling of the quadrature error with closed-loop control electronics improves the bias instability and angle random walk (ARW) of a fully decoupled gyroscope up to ten times. Moreover, the quadrature cancellation improves the scale-factor turn-on repeatability about four times and linearity about 20 times, reaching down to 119 and 86 ppm, respectively. Finally, the quadrature cancellation allows operating the gyroscope with higher drive-mode displacement amplitudes for an increased rate sensitivity. With this technique, outstanding bias instability and ARW performances of 0.39°/h and 0.014 °/√h, respectively, have been achieved.

/pdf/quadrature-error-compensation-and-corresponding-effects-on-2kc44cvhs2.pdf

Quadrature-Error Compensation and Corresponding Effects on the Performance of Fully Decoupled MEMS Gyroscopes

An integrated MEMS gyroscope, is provided with: at least a first driving mass driven with a first driving movement along a first axis upon biasing of an assembly of driving electrodes, the first driving movement generating at least one sensing movement, in the presence of rotations of the integrated MEMS gyroscope; and at least a second driving mass driven with a second driving movement along a second axis, transverse to the first axis, the second driving movement generating at least a respective sensing movement, in the presence of rotations of the integrated MEMS gyroscope The integrated MEMS gyroscope is moreover provided with a first elastic coupling element, which elastically couples the first driving mass and the second driving mass in such a way as to couple the first driving movement to the second driving movement with a given ratio of movement

Integrated microelectromechanical gyroscope with improved driving structure

We report characterization of a silicon MEMS rate gyroscope with measured sub-deg/hr bias stability, enabled by the quality factor (Q) of 1.1 million. The rate sensor utilizes degenerate, dynamically balanced Quadruple Mass Gyroscope (QMG) design, which suppresses substrate energy dissipation and maximizes Q-factors. We demonstrated a 0.9°/hr in-run bias stability and a 0.06°/√hr rate noise density for the 0.1 mTorr vacuum packaged QMG with a 0.2 Hz mode-mismatch between drive- and sense-modes. This level of noise allowed detection of azimuth with 150 mrad precision, showing feasibility of a QMG for gyrocompassing.

http://www.alexandertrusov.com/uploads/pdf/2011-transducers-prikhodko-zotov-trusov-shkel.pdf

Sub-degree-per-hour silicon MEMS rate sensor with 1 million Q-factor

North-finding based on micromachined gyroscopes is an attractive possibility. This paper analyzes north-finding methods and demonstrates a measured 4 mrad standard deviation azimuth uncertainty using an in-house developed vibratory silicon MEMS quadruple mass gyroscope (QMG). We instrumented a vacuum packaged QMG with isotropic Q-factor of 1.2 million and Allan deviation bias instability of 0.2 °/hr for azimuth detection by measuring the earth's rotation. Continuous rotation (“carouseling”) produced azimuth datapoints with uncertainty diminishing as the square root of the number of turns. Integration of 100 datapoints with normally distributed errors reduced uncertainty to 4 mrad, beyond the noise of current QMG instrumentation. We also implemented self-calibration methods, including in-situ temperature sensing and discrete ±180° turning (“maytagging” or two-point gyrocompassing) as potential alternatives to carouseling. While both mechanizations produced similar azimuth uncertainty, we conclude that carouseling is more advantageous as it is robust to bias, scale-factor, and temperature drifts, although it requires a rotary platform providing continuous rotation. Maytagging, on the other hand, can be implemented using a simple turn table, but requires calibration due to temperature-induced drifts.

/pdf/what-is-mems-gyrocompassing-comparative-analysis-of-3gwby4zng8.pdf

What is MEMS Gyrocompassing? Comparative Analysis of Maytagging and Carouseling

We report progress toward a MEMS gyroscope suitable for northfinding in pointing and targeting applications. In-run bias stability of 0.03 deg/hr and ARW of 0.002 deg/rt(hr) have been achieved. Gyro performance was measured on tuning-fork type MEMS gyroscopes using DSP-based breadboard electronics. These bias stability and ARW results are within about 6X and 2X, respectively, of meeting the typical gyrocompass requirements for pointing and targeting applications (1 milliradian azimuth precision at 65 degrees latitude with 5 minute integration time). A MEMS gyrocompass meeting these requirements would substantially reduce the size, weight and power of pointing and targeting instruments. The test methodology will be presented, as well as test data on carouseling the sensor to reduce the effects of long-term bias drift.

Development of a MEMS gyroscope for northfinding applications

A Micro-Electro-Mechanical Systems (MEMS) inertial sensor systems and methods determine linear acceleration and rotation in the in-pane and out-of-plane directions of the MEMS inertial sensor. An out-of-plane linear acceleration of the MEMS sensor may be sensed with the first out-of-plane electrode pair and the second out-of-plane electrode pair. An in-plane rotation of the MEMS sensor may be sensed with the first out-of-plane electrode pair and the second out-of-plane electrode. An in-plane linear acceleration of the MEMS sensor may be sensed with the first in-plane sense comb and the second in-plane sense comb. An out-of-plane rotation of the MEMS sensor may be sensed with the first in-plane sense comb and the second in-plane sense comb.

Systems and methods for acceleration and rotational determination from an in-plane and out-of-plane mems device

A lateration system comprising at least one transmitter attached to a first object and configured to emit pulses, three or more receivers attached to at least one second object and configured to receive the pulses emitted by the transmitter, and a processor configured to process information received from the three or more receivers, and to generate a vector based on lateration. Lateration is one of multilateration and trilateration. The vector is used by the processor to constrain error growth in a navigation solution.

Ultrasonic multilateration system for stride vectoring

Systems and methods for a micro-electromechanical system (MEMS) device are provided. In one embodiment, a system comprises a first outer layer and a first device layer comprising a first set of MEMS devices, wherein the first device layer is bonded to the first outer layer. The system also comprises a second outer layer and a second device layer comprising a second set of MEMS devices, wherein the second device layer is bonded to the second outer layer. Further, the system comprises a central layer having a first side and a second side opposite that of the first side, wherein the first side is bonded to the first device layer and the second side is bonded to the second device layer.

Systems and methods for a three-layer chip-scale MEMS device

A Micro-Electro-Mechanical Systems (MEMS) inertial sensor systems and methods are operable to determine linear acceleration and rotation. An exemplary embodiment applies a first linear acceleration rebalancing force via a first electrode pair to a first proof mass, applies a second linear acceleration rebalancing force via a second electrode pair to a second proof mass, applies a first Coriolis rebalancing force via a third electrode pair to the first proof mass, applies a second Coriolis rebalancing force via a fourth electrode pair to the second proof mass, determines a linear acceleration corresponding to the applied first and second linear acceleration rebalancing forces, and determines a rotation corresponding to the applied first and second Coriolis rebalancing forces.

Systems and methods for acceleration and rotational determination from an out-of-plane MEMS device

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