Orbital Driving and Detection System of Piezoelectric Gyroscopes...

JOURNAL OF SEMICONDUCTOR TECHNOLOGY AND SCIENCE, VOL.19, NO.5, OCTOBER, 2019 ISSN(Print) 1598-1657 https://doi.org/10.5573/JSTS.2019.19.5.446 ISSN(Online) 2233-4866

Manuscript received Dec. 22, 2018; accepted Oct. 13, 2019 School of Electronic and Electrical Engineering, Daegu Catholic University E-mail : [email protected]

Orbital Driving and Detection System of Piezoelectric Gyroscopes for Inertia Sensors

Byengleul Lee, Seung Joon Paik, and Bonghwan Kim

Abstract—We developed an orbital driving method without time-sharing for piezoelectric gyroscopes operating at atmospheric pressure with a square wave signal having a phase difference of π / 2 by utilizing the resonance characteristics of the gyroscopes, and experimentally verified our method. The operation bandwidth of piezoelectric gyroscopes is limited by the time-sharing between the horizontal and vertical resonance modes. The Lissajous waveform changes from elliptical to circular after controlling the phase. The simulation results show that the natural frequency of the gyroscope is in the order of tens of kHz. The angular response rate is 1 deg/s in the x- and y-directions, and the measurement sensitivity is 17.2 µV/(deg/s). All the designed systems are verified through simulations and experiments. Index Terms—Piezoelectric gyroscope, orbital driving, resonance

I. INTRODUCTION

Advancements in microelectromechanical systems (MEMS) technology have made inexpensive vibrating structure MEMS gyroscopes widely available [1-3]. Multiple-axis gyroscopes and accelerometers with six or nine full degrees of freedom (DOF) have been incorporated in devices to determine the locations and orientations of these devices. In a MEMS gyroscope, the actuator converts an electrical signal, either voltage or

current, into a force that sustains the resonant modes. The amplitude readout of both resonant modes requires converting the position of the vibrating mass into a physical quantity which can be measured by an electronic circuit [4].

Generally, a MEMS gyroscope consists of a micro-resonator with two resonant modes, i.e., the primary mode and the secondary mode. The resonator can vibrate at its primary resonant mode with a constant frequency and amplitude under driving by electrostatic, electromagnetic, piezoelectric or other forces [1-3]. A vibrating structure gyroscope uses a vibrating structure to determine the rate of rotation [5-7]. Vibrating structure gyroscopes can be implemented with various resonating structures. Examples include cylindrical resonator gyroscopes [8], piezoelectric gyroscopes [9], tuning fork gyroscopes [10], wine-glass resonators [11], and vibrating wheel gyroscopes [12]. In vibratory gyroscopes, the excitation and detection of vibrations can be achieved electrostatically or piezoelectrically, or by other ways [13, 14]. In particular, piezoelectric gyroscopes have received much attention because of their rugged construction, good frequency response, and negligible phase shift.

Piezoelectric gyroscopes make use of two vibration modes, the primary mode and the secondary mode, of a piezoelectric body. The piezoelectric material moves in perpendicular directions in the two modes. The modes are hence coupled by the Coriolis force when the gyroscope is rotating [9, 13, 14].

The operation of a piezoelectric gyroscope involves a suspended proof mass moving in two-dimensional space inside a rigid frame which is attached to an object in motion and rotated along with the object [9]. When the proof mass is actuated by an applied alternating electric

JOURNAL OF SEMICONDUCTOR TECHNOLOGY AND SCIENCE, VOL.19, NO.5, OCTOBER, 2019 447

voltage in a designated direction (called the ‘Drive’ axis, or the primary mode) and the object is rotating with an angular rate as observed from the frame, the Coriolis force would actuate the proof mass in a direction perpendicular to the driven direction (called the ‘Sense’ axis, or the secondary mode). The angular rate can then be detected from electrical signals (voltage or current) accompanying the secondary motion [9, 13, 14].

However, the expansion of the operating bandwidth in piezoelectric gyroscopes is limited by the time-sharing between the horizontal and vertical resonance modes. Okada et al. proposed a 3-axis gyroscope which can be continuously operated without time-sharing [15-18]. They showed that the gyroscope must be driven sequentially by X1 → Y1 → X2 → Y2 → X1 … in the orbital driving mode.

This paper aims to develop a multi-axial inertial sensor that operates at atmospheric pressure by fabricating a piezoelectric gyroscope sensor with orbital drive. Orbital drive is a frequency component that uses the gyroscopic

precession to implement a rotational angular velocity sensor, so that the input rotational angular velocity and the force acting on the output are the same. In order to achieve orbital drive, we propose a method with a square wave signal having a phase difference of π / 2 by utilizing the gyroscope resonance characteristics. We experimentally verify the method.

II. STRUCTURE SCHEMATIC AND SIMULATION

The gyroscope is designed to have a high Q-factor without vacuum packaging with a single proof mass under 3-axis acceleration and 3-axis angular rotation. The driving and sensing methods are based on the piezoelectric effect [19]. Fig. 1 shows the structure of the piezoelectric gyroscope, consisting of a lead zirconate titanate (PZT) film and metal electrodes for driving and sensing, and a suspended bulk silicon acting as a single proof mass [19]. The proof mass is designed with a diameter of 350 µm. The inner circle has a diameter of

Si

Si

PZT

Oxide

Pt (electrode) Pt (ground)

zx

y

350 µm

S

S

SS DD

D

D

D: Driving voltage input

S: Sensing voltage output

600 µm

300 µm

100 µm

100 µm

50 µm

Fig. 1. Structure of piezoelectric gyroscope.

448 BYENGLEUL LEE et al : ORBITAL DRIVING AND DETECTION SYSTEM OF PIEZOELECTRIC GYROSCOPES FOR INERTIA …

300 µm whereas the outermost circle has a diameter of 600 µm. The driving and sensing electrodes are both 100 µm with a 50 µm gap. Fig. 2 shows the simulation results of the gyroscope [19]. The piezoelectric material is deformed by a driving voltage. Therefore, the gyroscope can detect the rotation of the proof mass by converting the deformation to voltage. The rotation and z-translation of the proof mass are simulated for acceleration in the x(y)-direction (Fig. 2(a) left) and z-direction (Fig. 2(a) right), xz(yz) [19]. The simulation results show an angular rate response of 1 deg/s in the x- and y-directions, and a measurement sensitivity of 17.2 µV/(deg/s) as shown in Fig. 3 [19]. Under a sensing electrode potential of 10.2 µV and driving electrode potential of 7 µV, the differential output is 17.2 µV/(deg/s), and the displacement in the z-direction is 3.59 x 10-4 nm. All the designed systems have been verified through simulations and experiments.

III. RESULTS AND DISCUSSION

1. Driving Mode The orbital motion is equivalent to the continuous

movement of the center of mass in the gyroscope

membrane spring on the same horizontal plane to the left → lower → right → upper → left positions with vertical deviation. In order to realize this motion, a voltage is sequentially applied to the piezoelectric driving electrodes (Fx and Fy). Fig. 4 shows the concept of the orbital driving mode and the voltage application method. The gyroscope is fabricated on a silicon-on-insulator (SOI) wafer with a 10 µm silicon layer and a 2 µm sacrificial oxide layer. After patterning the Pt electrode via a photolithography and etching process, the PZT was deposited, and the final Pt electrode was formed.

Fig. 5 shows a fabricated gyroscope and the differential driving signals for the gyroscope [19]. Although it is more efficient to apply the sequential differential voltage in Fig. 5 due to the arrangement of

Electrical potential* Displacement in z-direction

＋7.0 uV

－10.2 uV

* Conductive top electrodes not modeled 3.59 x 10-4 nm

- Measurement sensitivity: 17.2 µV/(deg/s)

Fig. 3. Electrical potential simulation of the gyroscope.

(a)

(b)

Fig. 4. Orbital driving mode (a) Concept of the orbital driving mode, (b) voltage application method for orbital drive.

FxFz

(a)

(b)

(c)

Fig. 2. Simulation of the gyroscope (a) Acceleration in x(y)-direction (left) and acceleration in z-direction (right), (b) xz(yz)-rotation of the proof mass, (c) z-translation of the proof mass.


the electrodes in the gyroscope, the same effect can be obtained with a simple square wave since the driving of the gyroscope utilizes its resonance characteristics. This

is equivalent to phase shifting the x-axis drive signal used in conventional horizontal drive type gyroscopes by π / 2 to simultaneously excite the y-axis drive section.

The y-axis is thus driven in phase with the x-axis oscillation displacement, and the driving unit can be constructed as shown in Fig. 6 and 7. The two horizontal resonance modes of the gyroscope operate in resonance because the natural frequency will almost be the same if the fabrication process is well-controlled. Since the

Fig. 7. Orbital driven Simulink block diagram.

DY1 DY1FY1

DY2 DY2FY2

Y1

Y2DX2

X1FX1

DX1

X2

FX2X2

X2

(a)

(b)

Fig. 5. Voltage application for orbital drive (a) Fabricated gyroscope, (b) differential driving signal.

Fig. 6. Block diagram for orbital drive mode gyroscope.


phases of the oscillation displacements obtained differ by π / 2 from each other, the Lissajous waveform of x-y will take the shape of a circle.

However, a Matlab (MathWorks. Inc. USA) simulation shows that the Lissajous waveform of x-y is not exactly a circle even when the natural frequencies of the x and y modes are almost the same, as shown in Fig. 8. This is because one of the two resonance modes is slightly above the resonance point, and the other mode is below the resonance point. This problem is solved by controlling the phases so that the phase difference between the two oscillation displacement signals is maintained at π / 2,

instead of synchronizing the y-axis drive signal generation to the displacement in the x-axis oscillation mode. Fig. 9 shows that the Lissajous waveform changes from elliptical to circular after controlling the phase.

The self-oscillating characteristics of the orbital drive have been experimentally confirmed to be similar to the simulation. However, except for some gyroscopes, the Lissajous waveforms of x-y show large deviations from circles in most cases. This deviation is attributed to the high frequency selectivity of the high Q secondary vibration system. In other words, for the orbital drive, the two horizontal natural frequencies must be close to each

v X

v Y

v X

v Y

vX

vY

vX

vY

vX

vY

v X : 1 V/div v Y : 1 V/div v X : 1 V/div v Y : 1 V/div Time: 10 ms/div

TimeVoltage

Fig. 8. Orbital drive simulation.

Fx1500 mV/div20 μs/div

Fy1500 mV/div20 μs/div

Sx500 mV/div20 μs/div

Sy500 mV/div20 μs/div

LeCroy 44XS LeCroy 44XS

Fig. 9. Orbital drive experiment.


other, which can be achieved during the fabrication process, but the actual production results often do not meet this requirement. Therefore, a higher level of process control is required for applications. Fig. 10 shows the frequency response as a function of the horizontal resonance (x / y) modes. The two natural frequencies on the left differ slightly while the two frequencies on the right are almost identical.

2. Detection Mode

The operation of gyroscopes by orbital drive is similar

to rotary gyroscopes. That is, if an angular velocity is applied around an axis perpendicular to the rotation axis of a rotating object, a rotational force acts on the third axis orthogonal to the rotation axis. This is called gyroscopic precession, and is equivalent to rotating the center of mass around the z axis. When the rotational angular velocity is applied to the center of the x or y axis in this state, a rotational force is generated around the y or x axis .The angular velocity can hence be detected.

IV. CONCLUSIONS

Orbital drive is a frequency component that uses the gyroscopic precession to implement a rotational angular velocity sensor, so that the input rotational angular velocity and the force acting on the output are the same. In order for the gyroscope to be driven in orbital mode,

we have developed a driving method with a square wave signal having a phase difference of π / 2 by utilizing the resonance characteristics. We experimentally verified the driving method.

ACKNOWLEDGMENTS

This research was also supported by the Basic Science Research Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Education (No. NRF-2013R1A1A4A01012255 and NRF-2016R1D1A3A03919627). This work was supported by the Korea Institute of Energy Technology Evaluation and Planning (KETEP) and the Ministry of Trade, Industry & Energy (MOTIE) of the Republic of Korea (No. 20194010201760).

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(a) (b)

Fig. 10. Frequency response function in horizontal resonance (x / y) mode (a) the difference of two resonant frequencies at a frequency greater than 150 Hz, (b) at approximately 11 Hz.


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Byeungleul Lee is a Professor at Korea University of Technology and Education. He received B.S. degree in Electronics Engineering from the Hanyang University and M.S. degree in Electrical and Electronics engi-neering from Korea Advanced

Institute of Technology, in 1989 and 1991 respectively. He obtained his Ph.D. in Electrical Engineering and Computer Science from the Seoul National University in 2004. From 1991 to 2008, he worked for Samsung Electronics as a principal researcher for MEMS development. His research interests include semiconductor transducer and MEMS applications.


Seung-Joon Paik received his B.S. degree at the School of Electrical Engineering in 1999 and the M.S. and Ph.D. degrees at the Electrical Engineering and Computer Science from Seoul National University, Seoul, Korea, in 2001 and 2005,

respectively. He was with Automation and Systems Research Institute in Seoul National University, as a postdoctoral associate from 2005 to 2007. In 2008, he joined the MicroSensors and MicroActuators Laboratory (MSMA Lab.) in Georgia Institute of Technology, Atlanta, Georgia. Since 2013, he has worked for Georgia Tech as a senior engineer at the Institute for Electronics and Nanotechnology (IEN) in Georgia Tech. His current interests are in research and development for the micromachining of silicon and polymer materials and in biomedical applications of micromachined devices and also in inertial sensors, 3-D multi-chip packaging of MEMS devices, energy storage/conversion devices and nano-scale structures.

Bonghwan Kim received the B.S. degree in electronics engineering from the Kyungpook National University, Daegu, Korea, and M.S. and Ph.D. degrees in Electrical Engineering and Computer Science from the Seoul National University,

Seoul, Korea, in 1996, 1999, and 2005 respectively. From 2001 to 2005, he was a founder and the president of the ICMEMS Inc., Seoul, Korea. From 2005 to 2007, he was a principal engineer with UniTest Inc., where he developed a MEMS probe card. In 2008, he moved to the University of Illinois at Urbana-Champaign and joined the Shannon Group as a post-doctoral research associate. From 2018 to 2019, he was a visiting scholar at School of Electrical and Computer Engineering, Georgia Institute of Technology in his sabbatical year. Since 2009, he has worked for Daegu Catholic University, Gyeongsan, Gyeongbuk, Korea. His current research activities include design and fabrication of MEMS device such as micro cantilever, actuators and MEMS probe card.

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