Scale factor measurement for mems gyroscopes and accelerometers

Abstract

An inertial instrument such as an accelerometer or gyroscope having scale factor functionality, and that lies generally in a plane. The gyro detects rotation rate about a gyro input axis. The gyroscope has a substrate, a generally planar scale factor gimbal flexibly coupled to the substrate such that it is capable of oscillatory motion about the input axis, a generally planar support member coplanar with and flexibly coupled to the scale factor gimbal such that the support member is capable of oscillatory motion about a drive axis that is orthogonal to the input axis, and a generally planar gyro member coplanar with and flexibly coupled to the support member such that it is capable of rotary oscillatory motion relative to the support member about an output axis that is orthogonal to the plane of the members. There are one or more first drives for oscillating the support member about the drive axis, and one or more second drives for oscillating the scale factor gimbal about the input axis. One or more gyro output sensors that detect oscillation of the gyro member about an output axis that is orthogonal to both the input axis and the drive axis.

Description

FIELD OF THE INVENTION

This invention relates to MEMS inertial instruments, including gyroscopes and accelerometers.

BACKGROUND OF THE INVENTION

Micro-electro-mechanical systems (MEMS) gyroscopes and accelerometers, such as disclosed in U.S. Pat. Nos. 6,725,719 and 6,859,751, are generally planar instruments. Due to their very small size, and materials and methods of construction, such MEMS inertial instruments are relatively sensitive to ambient temperature and other environmental factors. These sensitivities makes them relatively unstable. Accordingly, it has been necessary to extensively test such instruments under a variety of conditions in order to develop a priori compensation schemes that can then be built into systems employing such instruments. This testing is time consuming and expensive, and also may not anticipate every possible condition that the instrument may be exposed to, which can lead to errors.

SUMMARY OF THE INVENTION

The G2-Gyroscope is a Coriolis gyroscope where the drive and output sense motions are angular oscillations. Its structure is generally planar and composed of two members: a Gyro Member and a Drive Member. The Gyro Member is the gyro. The Drive Member supports the Gyro Member above the substrate and is used to oscillate the Gyro Member about the Drive Axis, without applying direct actuation to the Gyro Member. Under rotation rate input, the Gyro Member responds by oscillating about the Output Axis (orthogonal to the Drive Axis). The Input Axis and Drive Axis are orthogonal to each other and lie in the plane of the gyroscope. The Output Axis is aligned normal to the plane. An attribute of this design is that the Gyro Member can be made symmetric about the Output Axis and therefore reduce sensitivity to cross-axis rotation rate inputs. By using the Drive Member to indirectly drive the Gyro Member, error torques are minimized.

The inventive G2-Gyroscope design is a planar MEMS instrument that is suited for integration into a planar MEMS Inertial Measurement Unit (IMU) whereby gyroscopes and accelerometers, formed onto a single substrate, sense all six-degrees-of-freedom. The G2-Gyroscope is also operational on its own.

This invention relates to designs of the G2-Gyroscope with built-in scale factor measurement capability.

This invention further relates to planar G2-Gyroscope designs with built-in scale factor measurement capability capable of being fabricated with MEMS processing technologies.

This invention further relates to the symmetry of the Gyro Member about the Output Axis to reduce sensitivity to cross-axis rotation rates.

This invention further relates to the indirect drive of the Gyro Member through a Drive Member (DM), to which the Gyro Member is attached. The purpose is to minimize unwanted drive of the Gyro Member about the Output Axis (quadrature source).

This invention further relates to the components of the design and how they provide functionality to operate the gyroscope with built-in scale factor measurement capability.

This invention also relates to the alternate design where the Gyro Member is larger and driven directly to oscillate about the Drive Axis. The larger size of the Gyro Member increases gyroscope sensitivity. In this case, the member that supports the gyro member relative to the substrate is not driven, and thus is not really a “Drive Member.” This member may thus be generally termed, for some preferred embodiments, a “support member.”

This invention also relates to the operation of the G2-Gyroscope with built-in scale factor measurement capability. Although the gyroscope can be operated with any set of Drive Member and Gyro Member (also referred to as Inner Member) natural frequencies, the sensitivity is improved as the difference between them (offset) is reduced. Operation with an offset of zero is the most sensitive and represents a special case.

This invention also relates to the monolithic construction of the gyro with built-in scale factor measurement capability to minimize structural instability. The structure is electrically connected to ground.

This invention relates primarily to the addition of mechanisms to MEMS (Micro-Electro-Mechanical Systems) gyroscopes and accelerometers that enable the measurement of their scale factor (sensitivity). The scale factor measurement can also be referred to as the calibration of the instrument sensitivity.

This invention also relates to the ability to measure scale factor at any time or continuously, including during the period of instrument operation. This capability eliminates the need to conduct extensive testing to fully calibrate the instrument at every state of the environment so that compensation algorithms may be used to correct the instrument during operation. This capability also considers that the calibrations may not remain correct over time.

This invention helps to maintain the accuracy of the MEMS instrument and greatly reduce the cost of calibrations.

The invention contemplates the addition of a gimbal or another structure to MEMS instrument designs that enable the application of a known, reference input motion. The gimbals or the other structures are the mechanisms. For the gyro, the reference motion is a rotation rate about its Input Axis: the motion can be applied with a rotary scale factor gimbal. For the accelerometer, the reference motion is an acceleration along its Input Axis: the motion can be applied with a linear shuttle. The scale factor is the ratio of measured instrument response to the amplitude of the reference input motion.

The reference input motion can be applied as a pulse or as a repetitive waveform of either finite duration or continuous. The repetitive motion/waveform is characterized by its shape, amplitude and repetition frequency. A simple and practical motion is a sinusoid. The frequency selected depends on the dynamics of the vehicle and instrument and the signal processing requirements.

The preferred alignment for the gyro Input Axis and the scale factor gimbal rotation axis is for them to be collinear so that only a rotational reference motion need be applied in order to produce a response in the gyro. This requirement is built-into the designs since the motion mechanisms are integrated with the instrument. Where a separate structure or platform is used, a proper alignment needs to be obtained.

Ultimately the accuracy of the scale factor measurement depends on the stability of the input reference motion. The scale factor measurement will account for changes in output pick-off sensitivity and changes in the mechanical response of the instrument to the input motion.

An embodiment of the invention is described with respect to the G-2 gyroscope design, a planar MEMS instrument. The G2-gyroscope is a single degree of freedom instrument having three orthogonal axes: Input Axis, Output Axis and Drive Axis.

One embodiment of the invention comprises the G2-gyroscope integrated with a rotary gimbal, which when actuated, applies a rotation rate to the gyroscope. The scale factor rotary gimbal can be actuated with capacitive plates located below the gimbal. Its motion can be measured with a second set of capacitive plates. An electronic control circuit can be used to hold the amplitude of the motion constant.

This invention relates to the application of a reference input rotation rate to the G2-Gyroscope.

The invention also relates to the application of a reference rotation rate input to other MEMS and non-MEMS gyroscopes and accelerometers.

This invention also relates to the collinear alignment of the gyro Input Axis with the scale factor rotary gimbal axis of rotation so that only rotary motion is applied.

A preferred sinusoidal reference input rotation rate is applied about the gyroscope Input Axis. The ratio of the gyro response about its Output Axis and the applied reference input rotation rate is the scale factor.

For a linear accelerometer, in which the proof mass moves along the input axis, the scale factor mechanism can be a shuttle integrated with the accelerometer. Preferably, a sinusoidal reference acceleration is applied. The ratio of the response amplitude to the amplitude of the input acceleration is the scale factor.

For a pendulous accelerometer in which the output is a rotation in the plane, a shuttle can also be used. For a pendulous accelerometer in which the output is normal to the plane, a rotary gimbal can be used to apply the reference acceleration.

This invention can accomplish measurement of the scale factor continuously or only in periods of duration, as commanded by the system.

The amplitude of the reference input motion can be increased to increase the response. The amplitude of the reference input motion can be changed to measure the non-linearity of the instrument response to input motion. In the test laboratory, the non-linearity can be measured by adding a fixed reference input motion with increasing rotation rates applied by a test table.

BRIEF DESCRIPTION OF THE DRAWINGS

Other objects, features and advantages will occur to those skilled in the art from the following descriptions of the preferred embodiments, and the accompanying drawings, in which:

FIGS. 1A and B are stick figures representing the inventive G2-Gyroscope design structure.

FIG. 2 is a graph of the Gyro signal dependence with offset frequency.

FIG. 3 is a top view of one embodiment of the inventive G2-Gyroscope mechanical design.

FIG. 4 is a close up view of the W-flexure of the G2-Gyroscope of FIG. 3.

FIG. 5 is a close up view of the rotary comb design of the gyro of FIG. 3.

FIG. 6 shows the differential alignment between rotary comb quadrants of the rotary comb shown in FIG. 5.

FIG. 7 is a schematic representation of the G2-Gyro metallization design for the embodiment of FIGS. 3-6.

FIG. 8 is a top view of an alternative preferred embodiment of the invention, showing a G2-Out Gyroscope mechanical design.

FIG. 9 is a schematic representation of the metallization design for the G2-Out Gyro embodiment of FIG. 8.

FIG. 10 is a schematic diagram of the preferred electronics for operation of the inventive G2-Gyroscope.

FIG. 11 schematically depicts the dissolved wafer process steps for the preferred manner of fabricating the inventive gyro.

FIG. 12 is a schematic side-view of the completed device from FIG. 3 after the silicon is etched by EDP.

FIG. 13 is an illustration of the concept for measuring the scale factor for a MEMS gyroscope or accelerometer.

FIG. 14 is a design of an embodiment of a MEMS gyroscope with an integrated gimbal for measuring the gyroscope scale factor according to this invention.

FIG. 15 is a design of a part of the drive and sense functionality for the gyroscope of FIG. 14.

FIG. 16 is a design of an embodiment of a MEMS linear accelerometer with an integrated shuttle for measuring the accelerometer scale factor according to the invention.

DESCRIPTION OF THE PREFERRED EMBODIMENTS OF THE INVENTION

Design Guidelines

The design of one preferred embodiment of the invention incorporates:

• • a symmetric disk (Gyro Member or “GM” herein) in the plane of the instrument that is driven to oscillate about an axis in the plane (Drive Axis), by the use of an outer structure, the Drive Member; the gyro output motion is the oscillation of the disk about the axis normal to the plane (Output Axis); the purpose of the symmetric disk is to reduce sensitivity to cross-axis rotation rate,
  • the disk is mounted to the Drive Member (DM) so that the drive of the disk about the Drive Axis is accomplished through the DM structure and actuation is not applied directly to the disk itself; the purpose is to minimize the inadvertent drive of the disk about the Output Axis,
  • the Drive Member is connected with a pair of torsional flexures to bonding pads attached to the substrate,
  • a mesa between the bonding pads and the substrate provides the working gap that allows motion of the GM and DM about the drive axis,
  • a set of radial flexures suspends the disk from the Drive Member and allow its oscillation about the Output Axis,
  • each radial flexure incorporates stress reliefs to minimize the DM stress imparted on the disk that affects its free motion,
  • actuation of the Drive Member is done with two sets of capacitor plates located underneath the DM and on both sides of the Drive Axis,
  • motions of the disk and Drive Member are sensed with capacitive pick-offs that operate differentially to cancel common-mode noise; at zero rotation rate, the difference in capacitance is zero and the output is zero,
  • the mechanical structure consists of two moving members cut from one material (monolithic construction); the full structure is connected electrically to ground (or common potential),
  • the monolithic structure is mounted onto a rigid substrate onto which are also located the stators for driving (actuating) and sensing the motion of the members,
  • the rigid substrate provides a stable base for the gyroscope and maintains its alignment,
  • the Pyrex base is a material that enables anodic bonding of the epitaxial silicon to the Pyrex; its electrical insulation property separates the gyroscope from other devices that may be located on the same substrate,
  • the thickness of the gyroscope structure is sufficiently large that the members oscillate as thin plates with little structural distortion, and
  • the working gap is large enough to prevent stiction to the substrate.ModelingG2-Gyroscope Structure

The G2-Gyro structure is based on two nested members that oscillate in angle about orthogonal axes defined by two sets of flexures as shown in FIGS. 1A and 1B. The inner member (IM) is called the Gyro Member (GM) and the outer member (OM) is called the Drive Member (DM). The Gyro Member is mounted with flexures to the Drive Member and rotates by angle θ relative to the Drive Member. The DM is mounted to the case (substrate) with flexures and rotates by angle φ relative to the case (substrate). Since the gyroscope is an oscillatory device, the angles θ, φ are small. The two sets of flexures define axes of rotation that are orthogonal. There are three co-ordinate axes that apply; the first, (s,i,o) is fixed to the Gyro Member; the second, (x,y,z) is fixed to the Drive Member and the third, (a,b,c) is fixed to the case and rotates in inertial space. The case angles of rotation are not limited. The Gyro Member equation of motion describes the motion of the GM under rotation in inertial space and describes the output of the gyro.

Equation of Motion

Analysis is used to derive the equation of motion for the Gyro Member when the Drive Member is oscillated at some frequency and amplitude as the Case undergoes rotation in inertial space. The resultant equation of motion is given by

$\begin{array}{cc}{I}_{\mathrm{GM}}\ddot{\vartheta }+D_{\mathrm{GM}}\stackrel{.}{\vartheta }+\left[K_{\mathrm{GM}}+\left\{\begin{array}{c}\begin{array}{c}\left({\Omega }_b^2-{\Omega }_a^2\right)+\frac{1}{2}\left({\omega }^2-{\Omega }_c^2\right){\tilde{\varphi }}^2-\\ 2{\Omega }_a{\Omega }_c\tilde{\varphi }\sin \omega t+\end{array}\\ 2{\Omega }_b\tilde{\varphi }\mathrm{\omega cos}\mathrm{\omega t}\end{array}\right\}\Delta I\right]\vartheta -\left({\Omega }_a{\Omega }_b+{\Omega }_a{\Omega }_c\tilde{\varphi }\sin \omega t+{\Omega }_a\tilde{\varphi }\mathrm{\omega cos}\omega t\right){\vartheta }^2=I_{\mathrm{GM}}{\Omega }_a\tilde{\varphi }\cos \omega t-\Delta I\left({\Omega }_a{\Omega }_b+{\Omega }_b{\Omega }_c\tilde{\varphi }\sin \omega t+{\Omega }_a\tilde{\varphi }\mathrm{\omega cos}\omega t\right)& \left(1\right)\end{array}$ where

I_GM: GM moment of inertia about the o-axis (Output Axis)

D_GM: GM damping

K_GM: GM flexure stiffness (spring constant)

θrotation angle of the GM relative to the DM

φ: DM rotation angle relative to the case

Ω_a, Ω_b, Ω_c: rotation rates of the case in inertial space about three axes

ΔI=I_i−I_s: difference of GM inertias about the i-axis and s-axis

φ={tilde over (φ)}sin(ωt): DM oscillatory angular motion

{dot over (φ)}=ω{tilde over (φ)}cos(ωt): rate of DM angular motion

To the left of the equals sign are included the torque terms dependent on inertia, damping and stiffness as well as a nonlinear (fourth) term dependent on GM angle squared. The stiffness (third) term is given by

$\begin{array}{cc}\left[K_{\mathrm{GM}}+\left\{\begin{array}{c}\left({\Omega }_b^2-{\Omega }_a^2\right)+\frac{1}{2}\left({\omega }^2-{\Omega }_c^2\right){\tilde{\varphi }}^2-\\ 2{\Omega }_a{\Omega }_c\tilde{\varphi }\sin \omega t+2{\Omega }_b\tilde{\varphi }\mathrm{\omega cos}\omega t\end{array}\right\}\Delta I\right]& \left(2\right)\end{array}$

The stiffness term includes a constant flexure stiffness, K_GM, and a component dependent on vehicle rotation rates, Ω_a,Ω_b,Ω_c, DM drive frequency, ω, and a factor referred to as the tuning inertia, ΔI.

On the right of the equals sign are given terms that drive the GM. They include a gyroscope torque due to rotation rate about the Input Axis and others due to case rotation about cross-axes that are coupled by the tuning inertia. They are respectively:

• I_GMΩ_a{tilde over (φ)}ω cos ωt and ΔI(Ω_aΩ_b+Ω_bΩ_c{tilde over (φ)}sin ωt+Ω_a{tilde over (φ)}ω cos ωt).G2-Gyro Mechanization/Mechanical Response

From the equation of motion, the gyroscope operation is simplified by making the GM symmetric about the o-axis (Output Axis) so that ΔI=0. The resultant equation of motion becomesI_GM{umlaut over (θ)}+D_GM{dot over (θ)}+K_GMθ=I_GMΩ_a{tilde over (φ)}ω cos ωt  (3)The interpretation is that of a simple harmonic GM oscillator driven externally by a gyroscopic torque that results from the oscillatory motion of the DM and input rotation rate. Rewriting the GM EOM in the “Standard Form”, we get

$\begin{array}{cc}\ddot{\vartheta }+2{\mathrm{\xi \omega }}_{\mathrm{GM}}\stackrel{.}{\vartheta }+{\omega }_{\mathrm{GM}}^2\vartheta =\tilde{\varphi }\left(\omega \right){\mathrm{\omega \Omega }}_a\cos \omega t\mathrm{where}2{\xi }_{\mathrm{GM}}{\omega }_{\mathrm{GM}}=D_{\mathrm{GM}}/I_{\mathrm{GM}}{\xi }_{\mathrm{GM}}=\frac{1}{2}\frac{D_{\mathrm{GM}}}{I_{\mathrm{GM}}{\omega }_{\mathrm{GM}}}& \left(4\right)\end{array}$

• • ξ_GM is the GM damping factor, and

$\begin{array}{cc}{\omega }_{\mathrm{GM}}^2=K_{\mathrm{GM}}/I_{\mathrm{GM}}{\omega }_{\mathrm{GM}}=\sqrt{\frac{K_{\mathrm{GM}}}{I_{\mathrm{GM}}}}& \left(6\right)\end{array}$ where ω_GM is the GM natural frequency.

The solution describes the oscillatory motion of the GM in response to gyroscope input rotation rate, and is given byθ(t)={tilde over (θ)} sin(ωt−ε_GM)  (7)where {tilde over (θ)} is the GM oscillatory amplitude and ε_GM is the GM oscillation phase relative to the gyroscopic drive.

$\begin{array}{cc}\tilde{\vartheta }\left(\omega \right)=\frac{\frac{I_{\mathrm{GM}}}{K_{\mathrm{GM}}}{\Omega }_a \omega \tilde{\varphi }\left(\omega \right)}{{\left[{\left(2{\xi }_{\mathrm{GM}}\frac{\omega }{{\omega }_{\mathrm{GM}}}\right)}^2+{\left(1-\frac{{\omega }^2}{{\omega }_{\mathrm{GM}}^2}\right)}^2\right]}^{1/2}}& \left(8\right)\\ {\varepsilon }_{\mathrm{GM}}\left(\omega \right)={\tan }^{-1}\left(\frac{2{\xi }_{\mathrm{GM}}\frac{\omega }{{\omega }_{\mathrm{GM}}}}{1-\frac{{\omega }^2}{{\omega }_{\mathrm{GM}}^2}}\right)& \left(9\right)\end{array}$

These solutions can be plotted to obtain the Transfer Functions or Bode of the GM. Note that the response is also dependent on the DM amplitude, which also varies with angular frequency (the GM is coupled to the DM).

Practical Gyroscope Case—Offset Operation

For the practical gyroscope, the DM is driven at resonance to minimize the drive voltage and to maximize the DM oscillation amplitude. The GM response then depends on the GM and DM natural frequencies (note that the DM comprises the gyro disk for purposes of calculating the DM inertia about the Drive Axis and the DM natural frequency). The maximum DM amplitude and phase at resonance are given by

$\begin{array}{cc}\tilde{\varphi }\left({\omega }_{\mathrm{DM}}\right)=\frac{{\tilde{\Gamma }}_{\mathrm{DM}}}{D_{\mathrm{DM}}{\omega }_{\mathrm{DM}}}\varepsilon \left({\omega }_{\mathrm{DM}}\right)=\frac{\pi }{2}\mathrm{where}& \left(10\right)\\ {\Gamma }_{\mathrm{DM}}=\frac{V^2}{2}\frac{\delta C}{\mathrm{\delta \varphi }}& \left(11\right)\end{array}$ is the torque applied by the capacitive actuator. The GM responses for amplitude and phase for GM and DM natural frequencies are

$\begin{array}{cc}{\tilde{\vartheta }}_{\mathrm{Out}}=\tilde{\vartheta }\left({\omega }_{\mathrm{DM}}\right)=\frac{\frac{I_{\mathrm{GM}}}{K_{\mathrm{GM}}}{\mathrm{\Omega \omega }}_{\mathrm{DM}}\tilde{\varphi }\left({\omega }_{\mathrm{DM}}\right)}{{\left[{\left(2{\xi }_{\mathrm{GM}}\frac{{\omega }_{\mathrm{DM}}}{{\omega }_{\mathrm{GM}}}\right)}^2+{\left(1-\frac{{\omega }_{\mathrm{DM}}^2}{{\omega }_{\mathrm{GM}}^2}\right)}^2\right]}^{1/2}}& \left(12\right)\\ {\varepsilon }_{\mathrm{GM}}\left({\omega }_{\mathrm{DM}}\right)=\frac{\pi }{2}+{\tan }^{-1}\left(\frac{2{\xi }_{\mathrm{GM}}\frac{{\omega }_{\mathrm{DM}}}{{\omega }_{\mathrm{GM}}}}{1-\frac{{\omega }_{\mathrm{DM}}^2}{{\omega }_{\mathrm{GM}}^2}}\right)& \left(13\right)\end{array}$ Matched Frequency Case: Zero Offset

The maximum sensitivity is obtained for the case in which the DM and GM resonances are matched, ω_DM=ω_GM. The output per rotation rate input (Scale Factor) then is given by

$\begin{array}{cc}{\tilde{\vartheta }}_{\mathrm{matched}}=\frac{I_{\mathrm{GM}}}{D_{\mathrm{GM}}}\tilde{\varphi }{\Omega }_a& \left(14\right)\end{array}$

The output amplitude is dependent directly on the GM inertia, inversely with damping and directly with DM oscillation amplitude. A vacuum is necessary to develop the proper damping. In this case, it can readily be seen that the gyro sensitivity scales with size and inversely with damping.

General Offset Description

Gyro sensitivity is dependent on the separation (offset) between the GM and DM natural frequencies. In FIG. 2 is plotted the modeled dependence for a typical gyro case. The top curve is of the DM amplitude φ(f_DM) and it is held constant. The lower curve is of the GM amplitude response for an input rotation rate of 1 rad/sec. Its amplitude θ(f_DM) depends on the DM frequency and it increases as the offset is reduced.

G2-Gyro Requirements

• • the DM is driven at resonance to the maximum amplitude possible as limited by the working gap between the device and the substrate,
  • a phase-lock loop is used to maintain the operation of the DM at resonance,
  • the DM amplitude is held constant with an amplitude control loop,
  • the DM-GM frequency offset is held constant,
  • excitation frequencies for operating the DM and GM capacitive sensors need to be sufficiently different to minimize pick-up between them,
  • GM and DM oscillation axes are orthogonal to prevent drive of the GM by the DM oscillation, and
  • DM actuation is done without actuating the GM directly.G2-Gyro Operation

The DM is driven at some frequency and amplitude about the Drive Axis. When the gyro is rotated about the Input Axis (orthogonal to both the Drive Axis and Output Axis), the GM responds with an oscillation amplitude that is proportional to the Input Rotation Rate. Demodulation of the oscillatory output with a reference waveform at the same frequency and with the appropriate phase generates a gyro output DC voltage proportional to the Input Rotation Rate.

G2-Gyro Quadrature

A signal that is in “quadrature” with the gyro signal is an error signal generated by the improper operation of the gyroscope and the gyroscope design. Fortunately it is always out of phase by 90 degrees with the gyro signal and can be separated and filtered by proper demodulation. The phase of the demodulation reference waveform is to be controlled to prevent leakage of the quadrature signal into the gyro signal channel.

G2-GYROSCOPE EMBODIMENT

Mechanical Design

The mechanical design of one preferred embodiment of the inventive G2-Gyroscope 10 is shown in FIG. 3. The rectangular shapes on each end are bonding pads 12, 13 used to bond the device to the Pyrex substrate 14. Two torsional flexures 16, 17 connect the Drive Member 18 to the bonding pads. The flexures are stress-relieved by the oval cutouts 20, 21 in the bonding pads. The square DM shape allows the placement of sufficiently large capacitive plates underneath for actuation. Sense plates are used to measure the motion of the DM. The Gyro Member 22 is an annular disk connected to the DM with four W-shaped flexures 24, 25, 26, 27. The W-flexure design 42 shown in FIG. 4 is made up of two U-shaped flexures 43, 44. One end of each is connected to the DM 45 and the other to the GM disk 46 through L-shaped segments 47, 48 essentially tangent to the disk curvature. The L-shaped segment is added to enable the U-structure to bend with GM rotation and to absorb stress between the DM and GM. The radial alignment of the flexures along diagonals across the DM makes a symmetric arrangement with each flexure experiencing the equivalent stress.

The working gap between the gyro structure and the Pyrex substrate is 10 microns but the gap used depends on several factors: geometry, actuation capacity, sensitivity and fabrication constraints. The gap is fabricated by etching a well in the silicon and a well in the Pyrex.

The use of Pyrex is dependent on the need to anodically bond epitaxial silicon to a substrate as described below in the DWP process. Other processes are possible. It is preferred to use a substrate that has similar thermal characteristics to the device material, which in this case is silicon. An option is to also use silicon as the substrate for a close thermal match and to enable anodic bonding with a deposited Pyrex-equivalent film added to the substrate silicon. This would also preserve the electrical isolation between devices on the same substrate.

It is preferred for the device to be monolithic for mechanical stability and to connect it to electrical ground.

On the inside diameter of the GM is constructed a radial comb 30 for sensing the rotation of the GM. The comb teeth are aligned radially with the GM center of rotation. Four sets of mating combs are constructed on four separate quadrants fixed separately to the substrate that serve as stators for the moving comb rotor on the GM. By connecting the bonding pads to traces, the silicon structure is connected to electrical ground.

The gyro is driven by actuation of the DM about the Drive Axis 4. The Output Axis 5 is normal to the plane of the DM. The Input Axis 6 is orthogonal to the other two.

Rotary Comb Capacitive Sensor

The rotary comb design 30 is illustrated in FIG. 5. It is separated into four quadrants 32, 33, 34, 35. For each quadrant, the comb is divided into a stator with stator comb fingers 36 attached to the substrate 14 and a rotor with rotor comb fingers 38 that are part of the moving GM disk structure 40. The stator fingers and rotor fingers are aligned radially with the center of rotation of the disk. For each rotor finger there is a stator finger with the two separated by a small gap. They make up a comb finger pair. Pairs of comb fingers are separated by a large gap. A number of comb finger pairs makes up each quadrant. The sensitivity of the comb sensor scales with the number of comb finger pairs. By reducing the small gap between the comb finger pairs, the sensitivity is increased.

Neighboring quadrants 33, 34 are designed symmetrically about the axis that separates them as shown in FIG. 6. For rotation of the rotor in either direction, the small gap 37 of comb finger pairs in one quadrant decreases while the small gap of comb finger pairs in the other quadrant increases. The purpose of the rotary design, based on neighboring quadrants, is that when the signals from the comb finger pairs located on neighboring quadrants are differenced, the signals add and the common-mode noise subtracts; this is differential operation. At zero rotation of the GM, the output is also zero. When the output from the third and fourth quadrants are added to the first and second, the signal is doubled again. This is the preferred operation of the rotary comb of the gyro for maximum sensitivity.

Alternate uses of the rotary comb are possible if one set of neighboring quadrants is connected for rotary sensing and the other set for actuation. One use is to test the operation of the Gyro Member separately. The second use is to cancel quadrature error by adding a counter motion of the Gyro Member.

Metallization Design of the G2-Gyroscope

The metallization design 50 is shown in FIG. 7. It consists of capacitive plates, conductor traces and pads. Capacitive plates 51 and 52 are located under part of the DM on one side of the Drive Axis. They are connected by a trace. Capacitive plates 53, 54 are located on the other side. They are connected by a trace. Drive voltages are applied to the actuator plates to predominantly pull down on one side of the DM during the first half of the drive cycle and to predominantly pull down on the other side of the DM during the second half of the drive cycle. The result is an oscillatory motion of the DM about the Drive Axis. The sensing of the DM motion is accomplished with two capacitive plates 55, 56. The outputs are connected differentially, since for any motion, the gap for one increases and the gap for the other decreases.

Trace 57 connects capacitive plates 53, 54 to pad 58, for example.

Stators of the rotary comb are connected to pads with traces 59 that are crimped between the stator structure and the Pyrex substrate during anodic bonding. The monolithic gyro structure containing the GM and DM is connected to pads by traces 63, 64 crimped between the mounting structures 61, 62 and the Pyrex substrate. The preferred electrical connection of the gyro structure is to ground.

Traces are also capacitive sensing plates when they are located beneath the moving structure and this needs to be taken into consideration. A rule is to make the lengths under the moving parts equal and symmetric. Pick-up between plates and traces is also a consideration. The usual design practices apply. Electrical pick-up can be a source of quadrature in the gyro output.

Flexures

The purposes of flexures are to:

• • set orientational alignment between members,
  • govern rotation of the members about prescribed axes, and
  • provide support for the members of the structure.

The orientational alignment between members is an especially important consideration for the gyroscope because misalignment introduces mechanical coupling between the DM oscillation and the Gyro Member and will generate quadrature error.

The ideal flexure allows only motion about one axis in the dynamic environment.

The support capability is especially important when considering shock capability. It depends on the masses of the members and the spring stiffness of the flexures. Modeling is used to identify the strain on the flexures. A maximum strain level less than one tenth the fracture limit is a good condition to set.

DM Flexure Relief Structure

The stress relief absorbs the tension on the flexure that is due to the differential thermal contraction as the Pyrex and silicon cool from the elevated anodic bonding temperature. The stress can cause a potato-chip deformation of the DM that affects the GM suspended from it.

IM Flexure

The W-flexure enables rotation of the GM about the axis normal to the plane. Four are used in this design. Each W-flexure is composed of two bending U-flexures with a stress relief in each. For cases where the DM applies a tension or compression to the W-flexure, the stress relief can bend and absorb the stress. In this way, the flexure does not kink and inhibit rotation of the GM.

G2-OUT GYROSCOPE

Alternative Preferred Embodiment

The G2-Out Gyroscope 70, FIGS. 8 and 9, is a variation on the G2-Gyroscope where the Gyro Member 80 is the structural outer member, and the Gyro Member is driven directly about the Drive Axis 84. The Output Axis is still normal to the plane. The alignments of the Drive Axis and Input Axis 85 are as specified with the G2 Gyroscope.

Mechanical Design of the G2-Out Gyroscope

The mechanical design of the G2-Out gyro embodiment of the invention is described with FIG. 8. The gyro is mounted to the Pyrex substrate 71 via the mounting post 72 in the center. Ring structure 73 is attached to central post 72 with four radial flexures 74. The radial flexures allow oscillation of the gyro about the Output Axis (normal to the plane). From the ring is attached the rotor 75 of the capacitive rotary comb sensor. The fingers of the rotor extend radially towards the center of rotation. Four radial comb stators 76, 77, 78, 79 are mounted to the Pyrex substrate. The fingers of each stator extend outwards in between the rotor fingers. The radial comb sensor design is identical to the component used for the G2-Gyro.

The ring structure 73 is connected to the disk 80 with two torsional flexures 82, 83. These flexures allow oscillation of the GM about the Drive Axis.

Metallization Design of the G2-Out Gyroscope

The metallization design is similar to that of the G2-Gyro. Plates located beneath the GM disk are used to actuate and sense the motion of the disk about the Drive Axis. Unlike the G2-Gyro, however, the GM is driven directly by the actuator plates. This can lead to direct drive of the disk about the Output Axis (quadrature error). The benefit is that the disk of the G2-Out Gyro is much larger, allowing for greater sensitivity since the inertia is greater.

The metallization design 90 is shown in FIG. 9. It consists of capacitive plates, conductor traces and pads. Capacitive plates 91 and 92 are located under part of the GM disk on one side of the Drive Axis. They are connected by a trace. Capacitive plates 93, 94 are located on the other side. They are connected by a trace. Drive voltages are applied to the actuator plates to predominantly pull down on one side of the disk during the first half of the drive cycle and to predominantly pull down on the other side of the disk during the second half of the drive cycle. The result is an oscillatory motion of the GM disk about the Drive Axis. The sensing of the GM disk motion about the Drive Axis is accomplished with two capacitive plates 95, 96. The outputs are connected differentially since for any motion, the gap for one increases and the gap for the other decreases.

Trace 97 connects capacitive plates 91, 92 to pad 98, for example.

Stators of the rotary comb are connected to pads with traces 99 that are crimped between the stator structure and the Pyrex substrate during anodic bonding. The monolithic gyro structure is connected to pad 66 by trace 67 crimped between the mounting structure 72 and the Pyrex substrate. The preferred electrical connection of the monolithic gyro structure is to ground.

Traces are in themselves capacitive sensing plates when they are located beneath the moving structure and this needs to be taken into consideration. A rule is to make the lengths under the moving parts equal and symmetric. Pick-up between plates is also a consideration. The usual design practices apply. Electrical pick-up can be a source of quadrature in the gyro output.

G2-Out Gyro Operation

For the operation of the G2-Out Gyro, the GM is oscillated about the Drive Axis. With Input Rate applied about the Input Axis, the GM disk also oscillates about the Output Axis. The rotary comb sensor measures the output motion of the GM.

DESCRIPTION OF PREFERRED ELECTRONICS

The preferred electronics for the various embodiments of the invention can be described schematically with FIG. 10. An oscillator generates an AC voltage with a frequency close to the DM resonant frequency. The AC voltage is added to a DC bias voltage greater than the AC amplitude to develop a sinusoidal drive waveform. The drive voltage is applied to a set of capacitor plate actuators to drive the DM into oscillation. A set of capacitor plates under the DM is used to sense the motion of the DM about the Output Axis. A Phase-lock loop acts on the phase of the DM signal to keep the DM on-resonance by varying the oscillator frequency. An amplitude control loop compares the DM signal voltage to a reference voltage and varies the AC drive voltage to maintain the DM amplitude constant.

Input rotation rate generates an oscillation of the Gyro Member about the Output Axis with an amplitude that is proportional to the rotation rate. By demodulating the AC output signal with a reference waveform, the gyro output is converted to a DC voltage that is proportional to rotation rate. The gyroscope is operated open-loop.

Dissolved Wafer Processing

Dissolved Wafer Processing (DWP) is a MEMS fabrication process for making relatively large parts with good flatness and square profiles. The process requires two wafers: the first Pyrex and the second silicon, with a Boron-doped epitaxial layer. The combination of materials enables the two wafers to be anodically bonded. The thickness of the epitaxy determines the final device thickness, while Boron doping of the epitaxial layer inhibits EDP etching.

Typical dimensions include: device size of about 3 mm in the plane, device thickness of 40 microns, smallest flexure thickness of 5 microns and gaps between comb fingers of 5 microns.

Four process masks are needed: two for processing the silicon and two for the Pyrex. Instrument functions are distributed between the two layers: the mechanical structure and stator comb components are fabricated in the doped silicon layer and the electrical connections and flat capacitive plate components are deposited onto the Pyrex layer.

Process Steps

The process steps are described with FIG. 11. The starting silicon wafer includes a grown epitaxial layer with heavy boron diffusion of 43-micron thickness. In step 1, the epitaxial layer is etched to form mesas that support the silicon structures on the Pyrex as patterned by Mask 1. The mesa thickness also sets part of the gap between the device and the substrate that allows motion of parts. In step 2, deep reactive ion etching is used to etch through the epitaxial layer to form the device geometry that includes the structure, mass and combs as patterned with Mask 2. In step 3, wells are formed in the Pyrex to form the rest of the required gap using Mask 3. With Mask 4 (step 4), metal deposited on the Pyrex is patterned to form capacitive plates for driving and sensing out of plane motions. In addition, it patterns traces (conductors) that connect the structure, capacitive plates and the comb stators to the pads. In step 5, the silicon wafer is anodically bonded to the Pyrex wafer at the mesas. In step 6 the wafer is cut with a saw along outlines (streets) that separate devices. Each device is then EDP (Ethylene-Diamene-Pyrocatechol) etched to remove the silicon, leaving behind epitaxial devices with movable parts. The thickness of the devices is equal to the epitaxial thickness minus the mesa thickness, approximately 40 microns for the present devices. A conceptual side view of the finished device is shown in FIG. 12.

Advantages/Disadvantages of DWP

DWP has several advantages:

• • devices are made of one material (doped silicon) for greater thermal stability,
  • Pyrex serves as a robust substrate since it can be made as thick as desired,
  • multiple devices can be fabricated on the same Pyrex substrate, while making them physically separate,
  • thicker doped silicon devices can be made subject to the epitaxial process,
  • the process is a relatively low-temperature process, thereby generating low internal stresses.The disadvantages of DWP are not limiting, but can contribute to cost of fabrication and greater design complication. They include:
  • epitaxial growth limits the device thickness and introduces stresses,
  • chemical etching of most of the silicon wafer by EDP,
  • induced stresses from differential expansion of the silicon and Pyrex from the anodic bonding operation, and
  • reactive ion etching produces some tapering which makes it difficult to attain a desired resonant frequency.

A particularly critical requirement is the formation of flexures with precise geometry having a rectangular cross-section. A small variation in the wall verticality can greatly affect the stiffness and hence the dynamics. A conical cross-section would also have the effect of changing the rotation axis of the GM, and perhaps the orthogonality between the DM and GM axes. This misalignment leads to “quadrature error” in gyroscopes.

Derivation of the Equation of Motion

The analysis prescribed by J. S. Ausman (G. R. Pitman, Jr., Editor, Inertial Guidance, University of California Engineering and Physical Sciences Extension Series, J. Wiley and Sons, Inc., New York, 1962, J. S. Ausman, ch. 3) for the gimbal structure of the Single-Degree-of-Freedom Gyroscope is applicable to the common structure of the G2-Gyro.

The fundamental equation applied is that the rate of change of angular momentum is equal to the applied torque:

$\begin{array}{cc}\stackrel{\_}{L}={\left(\frac{d\stackrel{\_}{H}}{dt}\right)}_I& \left(15\right)\end{array}$

This is Newton's second law in rotational form. In equation (15) (d H/dt)_I is the time rate of change of H, the angular momentum vector, with respect to inertial space, while L represents the applied torque vector. When equation (15) is applied to the GM we get

$\begin{array}{cc}{\left(\frac{\stackrel{\_}{d{H}_{\mathrm{GM}}}}{dt}\right)}_I={\left(\frac{\stackrel{\_}{d{H}_{\mathrm{GM}}}}{dt}\right)}_{\mathrm{GM}}+\stackrel{\_}{\omega }\times \stackrel{\_}{H_{\mathrm{GM}}}=\stackrel{\_}{L_{\mathrm{GM}}}& \left(16\right)\end{array}$ where H_GM is the angular momentum of the GM,

${\left(\frac{\stackrel{\_}{d{H}_{\mathrm{GM}}}}{dt}\right)}_{\mathrm{GM}}$ is the time derivative of H_GM relative to the s, i, o coordinate system, and ω is the angular velocity of the GM or s, i, o coordinate system in inertial space.

The GM angular momentum, H_GM, is given byH_GM= I_GM· ω  (17)where ŝ is a unit vector in the s direction. I_GM is the moment of inertia tensor of the GM.Calculate ω

Since the GM is mounted to the DM, which is mounted to the case, the angular velocity of the GM in inertial space is given by the angular velocity of the GM gimbal, measurable relative to the DM, plus the motion of the DM, measurable relative to the case, plus the motion of the case. This is expressible as a vector sum of the separate angular velocities

$\begin{array}{cc}\omega ={\stackrel{\_}{\omega }}_{s,i,o}+{\overrightarrow{\omega }}_{x,y,z}+{\stackrel{\_}{\omega }}_{a,b,c}=\stackrel{.}{\vartheta }\hat{o}+{\stackrel{.}{\varphi }}_x\hat{x}+{\stackrel{.}{\varphi }}_y\hat{y}+{\stackrel{.}{\varphi }}_z\hat{z}+{\stackrel{.}{\gamma }}_a\hat{a}+{\stackrel{.}{\gamma }}_b\hat{b}+{\stackrel{.}{\gamma }}_c\hat{c}& \left(18\right)\end{array}$ where θ, φ, γ are angles of rotation for the GM, DM and case (or vehicle) axes, respectively. {dot over (θ)} relates that the motion of the GM is only about the o-axis. Further, we expect that the motion of the DM will only be about the y-axis, therefore,ω={dot over (θ)}ô+{dot over (φ)}_yŷ+{dot over (γ)}_aâ+{dot over (γ)}_b{circumflex over (b)}+{circumflex over (γ)}_cĉ  (19)The motion of the vehicle is unconstrained in inertial space.

Since we are interested in the motion of the GM in the s,i,o frame, we need to convert the latter terms in equation (19). We know the relationship between the s,i,o and x,y,z frames is a rotation about the o-axis. We apply the rotational transformation:{circumflex over (x)}=ŝ cos θ−î sin θ≅ŝ−îθŷ=î cos θ+ŝ sin ≅î+ŝθ{circumflex over (z)}=ô  (20)Since the GM is held at null, only small motions need to be considered, hence the small angle approximation is used.

We also know that the DM can only rotate about the y-axis, therefore the two axes are related by the rotational transformation:â={circumflex over (x)} cos φ−{circumflex over (z)} sin φ≅{circumflex over (x)}−{circumflex over (z)}φ{circumflex over (b)}=ŷĉ={circumflex over (x)} sin φ+{circumflex over (z)} cos φ≅{circumflex over (x)}φ+{circumflex over (z)}  (21)The DM motion is also small hence the small angle approximation is again used. Substituting the rotations (20) and (21) into (19), we getω=ω_sŝ+ω_iî+ω_oô  (22)whereω_s=(θ{dot over (φ)}_y+{dot over (γ)}_a+θ{dot over (γ)}_b+φ{dot over (γ)}_c), ω_i=({dot over (φ)}_y−θ{dot over (γ)}_a+{dot over (γ)}_b−θφ{dot over (γ)}_c), ω_o=({dot over (θ)}−φ{dot over (γ)}_a+{dot over (γ)}_c)  (23)Calculate H_GM

The moment of inertia tensor for the GM is given by

$\begin{array}{cc}\stackrel{=}{I}=\left(\begin{array}{ccc}{I}_s& 0& 0\\ 0& I_i& 0\\ 0& 0& I_o\end{array}\right)& \left(24\right)\end{array}$ assuming s, i, o are the principal axes of inertia for the GM. If s, i, o are not principal axes of inertia, it will generally be most convenient first to compute the vector components of I• ω along a set of principal axes and then to transform the vector I• ω into the s, i, o coordinate system. We assume that our designs have the appropriate symmetries.

Multiplying equation (22) by the moment of inertia tensor (24), and substituting into equation (17) gives

$\begin{array}{cc}\stackrel{\_}{H_{\mathrm{GM}}}=\stackrel{=}{I}·\stackrel{\_}{\omega }=\left(\begin{array}{ccc}{I}_s& 0& 0\\ 0& I_i& 0\\ 0& 0& I_o\end{array}\right)·\left({\omega }_s\hat{s}+{\omega }_i\hat{i}+{\omega }_o\hat{o}\right)=I_s{\omega }_s\hat{s}+I_i{\omega }_i\hat{i}+I_o{\omega }_o\hat{o}& \left(25\right)\\ =H_{\mathrm{IMs}}\hat{s}+H_{\mathrm{IMi}}\hat{i}+H_{\mathrm{IMo}}\hat{o}\mathrm{where}& \left(26\right)\\ H_{\mathrm{IMs}}=I_s{\omega }_s,H_{\mathrm{IMi}}=I_i{\omega }_i,H_{\mathrm{IMo}}=I_o{\omega }_o& \left(27\right)\end{array}$ Calculate ω× H_GM

The expression ω× H_GM is given by

$\begin{array}{cc}\stackrel{\_}{\omega }\times \stackrel{\_}{H_{\mathrm{GM}}}=\begin{array}{ccc}\hat{s}& \hat{i}& \hat{o}\\ {\omega }_s& {\omega }_i& {\omega }_o\\ H_{\mathrm{GMs}}& H_{\mathrm{GMi}}& H_{\mathrm{GMo}}\end{array}=\left(\begin{array}{c}{\omega }_i{H}_{\mathrm{GMo}}-\\ {\omega }_o{H}_{\mathrm{GMi}}\end{array}\right)\hat{s}-\left(\begin{array}{c}{\omega }_s{H}_{\mathrm{GMo}}-\\ {\omega }_o{H}_{\mathrm{GMs}}\end{array}\right)\hat{i}+(\begin{array}{c}{\omega }_s{H}_{\mathrm{GMi}}-\\ {\omega }_i{H}_{\mathrm{GMs}}\end{array})\hat{o}& \left(28\right)\end{array}$

We will restrict ourselves to the o-axis solution since we will assume that motions of the GM about the other axes do not occur.

$\begin{array}{cc}{\left(\stackrel{\_}{\omega }\times {\stackrel{\_}{H}}_{\mathrm{GM}}\right)}_o={\omega }_s{H}_{\mathrm{GMi}}-{\omega }_i{H}_{\mathrm{GMs}}={\omega }_s{I}_i{\omega }_i-{\omega }_i{I}_s{\omega }_s={\omega }_s{\omega }_i{I}_i-{\omega }_s{\omega }_i{I}_s=\left(I_i-I_s\right){\omega }_s{\omega }_i& \left(29\right)\end{array}$ Calculate

$\frac{d{H}_{\mathrm{GMo}}}{dt}+{\left(\stackrel{\_}{\omega }\times {\stackrel{\_}{H}}_{\mathrm{GM}}\right)}_o$ to get the equation of motion.

$\begin{array}{cc}\frac{d{H}_{\mathrm{GMo}}}{dt}+{\left(\stackrel{\_}{\omega }\times {\stackrel{\_}{H}}_{\mathrm{GM}}\right)}_o=I_o{\stackrel{.}{\omega }}_o+\left(I_i-I_s\right){\omega }_s{\omega }_i& \left(30\right)\end{array}$

Substituting for ω_o, ω_i, ω_s and adding damping and spring terms to the motion of the GM, as well as the pendulous torque, we get the full GM Equation of Motion. The variables for the angles can change in rotational or oscillatory mode or both.I_GMo{umlaut over (θ)}+D_GM{dot over (θ)}+└K_GM+({dot over (φ)}_y²+{dot over (φ)}_y{dot over (γ)}_b−{dot over (γ)}_a²−φ{dot over (γ)}_a{dot over (γ)}_c+{dot over (φ)}_y{dot over (γ)}_b+{dot over (γ)}_b²−φ{dot over (γ)}_a{dot over (γ)}_c−φ²{dot over (γ)}_c²)ΔI┘θ−({dot over (φ)}_y{dot over (γ)}_a+φ{dot over (φ)}_y{dot over (γ)}_c+{dot over (γ)}_a{dot over (γ)}_b+φ{dot over (γ)}_b{dot over (γ)}_c)θ²=I_GMo(φ{umlaut over (γ)}_a+{dot over (φ)}{dot over (γ)}_a−{umlaut over (γ)}_c)−ΔI({dot over (φ)}_y{dot over (γ)}_a+{dot over (γ)}_a{dot over (γ)}_b+φ{dot over (φ)}_y{dot over (γ)}_c+φ{dot over (γ)}_b{dot over (γ)}_c)  (31)Note that: φ=φ_y, ΔI_GM=I_GMi−I_GMs where

θ GM rotation angle relative to the DM,

φ DM rotation angle relative to case,

γ_a, γ_b, γ_c case rotation angles.

Making substitutions for φ and {dot over (φ)}=ω{tilde over (φ)} cos ωt and {dot over (γ)}_a=Ω_a,{dot over (γ)}_b=Ω_b,{dot over (γ)}_c=Ω_c, we get the final form for the equation of motion with all the angular rotation dependences.

$\begin{array}{cc}{I}_{\mathrm{GMo}}\ddot{\vartheta }+D_{\mathrm{GM}}\stackrel{.}{\vartheta }+\left[K_{\mathrm{GM}}+\left\{\begin{array}{c}\begin{array}{c}\left({\Omega }_b^2-{\Omega }_a^2\right)+\frac{1}{2}\left({\omega }^2-{\Omega }_c^2\right){\tilde{\varphi }}^2-\\ 2{\Omega }_a{\Omega }_c\tilde{\varphi }\sin \omega t+\end{array}\\ 2{\Omega }_b\tilde{\varphi }\mathrm{\omega cos\omega }t\end{array}\right\}\Delta I\right]\vartheta -\left({\Omega }_a{\Omega }_b+{\Omega }_b{\Omega }_c\tilde{\varphi }\sin \omega t+{\Omega }_a\tilde{\varphi }\mathrm{\omega cos\omega }t\right){\vartheta }^2=I_{\mathrm{GMo}}{\Omega }_a\tilde{\varphi }\mathrm{\omega cos\omega }t-\Delta I\left(\begin{array}{c}{\Omega }_a{\Omega }_b+{\Omega }_b{\Omega }_c\tilde{\varphi }\sin \omega t+\\ \frac{1}{2}{\Omega }_c\sin 2\mathrm{\omega t}+{\Omega }_a\tilde{\varphi }\mathrm{\omega cos\omega }t\end{array}\right)& \left(32\right)\end{array}$

Scale Factor Embodiments

One inventive concept as applied to a MEMS gyro such as the G2 gyro described above is to apply a sinusoidal rotation rate about the gyro Input Axis and to measure the corresponding oscillatory output. The ratio of the amplitudes is the scale factor. FIG. 13 shows a typical gyro output vs. input rate curve having a constant slope over its linear region that we wish to probe. The horizontal axis is the input angular rate and the vertical axis gives the gyro output. This illustration shows that an oscillation of the gyro about the input axis results in an oscillatory gyro output. When an input rate is added, the output oscillation is about the resulting output mean value. The scale factor measurement does not affect the measurement of the vehicle input rate and can be done concurrently. The scale factor measurement accuracy is also not sensitive to the bias.

G2-Gyroscope with Scale Factor Rotary Gimbal:

The device design shown in FIGS. 14-15 comprises three flexurally connected concentric members that rotate about three orthogonal axes. All three members are generally planar, and are generally co-planar such that they lie in the plane. The innermost two members form the gyro. The outer member is the rotary gimbal.

G2 gyroscope with scale factor rotary gimbal 102 according to the invention is attached with bonding pads 104, 105 to Pyrex substrate 106. A gap between gyroscope 102 and substrate 106 allows the gyroscope members to move. Scale factor rotary gimbal 108 is attached with two in-line torsional flexures 111, 112 to bonding pads 104 and 105, respectively: these two flexures are aligned with Gyro Input Axis 131. Gyro 114 is connected by way of gyro outer drive member 121 to scale factor rotary gimbal 108 with two in-line torsional flexures 115, 116: these two flexures are aligned with Drive Axis 141 of gyroscope 102. Inner member 118 is connected with four radial flexures 124, 125, 126, 127 to outer drive member 121. Inner member 118 oscillates about the Gyro Output Axis 51, which is normal to the plane. Radial comb pick-off 132 measures the gyro output response to input rotation rate.

Scale factor gimbal 108 is actuated to apply a reference input motion with a set of capacitive plates 134, 135. A second set of capacitive plates 136, 137 is part of the pick-off for sensing the motion of gimbal 108. The gimbal oscillation amplitude is kept constant with control circuitry.

A third set of capacitive plates 143, 144 is used to drive outer drive member 121. A fourth set of capacitive plates 146, 147 is part of the pick-off for sensing the motion of member 121.

G1-Gyroscope with Scale Factor Rotary Gimbal:

The structure is identical to the G2 gyroscope with scale factor rotary gimbal. The functionality of the scale factor rotary gimbal is the same. The roles of the innermost members are reversed. For the G1 gyroscope, the inner member is driven into oscillation by the rotary combs and the amplitude of the oscillation sensed and held constant with control circuitry. The gyroscope response to the same Input Axis is given by the oscillation of the gyro outer member. The axes of the oscillations are defined by the flexures. The inner member oscillates about the Drive Axis which is normal to the plane. The gyro outer member oscillates about the Output Axis, which is in the plane.

Other Planar Gyroscopes:

In addition to the G1 gyroscope and G2 gyroscope, the use of the scale factor rotary gimbal applies to other planar gyroscopes having the Input Axis in the plane. For those having the Input Axis normal to the plane, an in-plane rotary gimbal is used.

Linear Accelerometer with a Scale Factor Shuttle:

The linear accelerometer with shuttle 150 is shown in FIG. 16. The output of a linear accelerometer is a displacement with acceleration. Thus, for the linear accelerometer a shuttle 157, 158 can be used to accomplish the scale factor motion: this allows the application of a linear oscillatory input.

The linear accelerometer 152 is flexurally mounted with its four flexures 172, 173, 174, 175 to the shuttle instead of to the substrate. The shuttle is then flexurally-mounted to the substrate with four flexures 176, 177, 178, 179 and four bonding pads 153, 154, 155, 156. Actuator comb drives 166, 167 mounted to the substrate and the shuttle are used to apply an oscillatory drive to the shuttle. Pick-off combs 168, 169 are used to sense the amplitude of the oscillatory motion applied to the shuttle. Accelerometer capacitive combs 162, 163, 164, 165 are used to measure the accelerometer response to the drive for obtaining the scale factor and the acceleration input.

Specific features of the invention are shown in some drawings and not others, but this is not a limitation of the invention, the scope of which is set forth in the following claims.

Claims

1. A gyroscope that lies generally in a plane, for detecting rotation rate about a gyro input axis, the gyroscope having scale factor functionality, comprising: a substrate;a generally planar scale factor gimbal flexibly coupled to the substrate such that the scale factor gimbal is capable of oscillatory motion about the input axis;a generally planar support member coplanar with and flexibly coupled to the scale factor gimbal such that the support member is capable of oscillatory motion about a drive axis that is orthogonal to the input axis;a generally planar gyro member coplanar with and flexibly coupled to the support member such that the gyro member is capable of rotary oscillatory motion relative to the support member about an output axis that is orthogonal to the plane of the support and gyro members;one or more first drives for oscillating the support member about the drive axis;one or more second drives for oscillating the scale factor gimbal about the input axis; andone or more gyro output sensors that detect oscillation of the gyro member about an output axis that is orthogonal to both the input axis and the drive axis.

2. The gyroscope of claim 1 in which the first and second drives comprise capacitive drives.

3. The gyroscope of claim 2 in which the first and second drives comprise plates.

4. The gyroscope of claim 1 in which there is at least one first drive on each side of the drive axis and at least one second drive on each side of the input axis.

5. The gyroscope of claim 1 in which the gyro output sensors comprise capacitive sensors.

6. The gyroscope of claim 5 in which the gyro output sensors comprise comb sensors.

7. The gyroscope of claim 6 in which the comb sensors comprise sectors that are radially arranged around the output axis.

8. The gyroscope of claim 7 comprising two pairs of diametrically opposed comb sensor sectors, with the signals from the pairs differenced, to increase the signal strength and reduce common-mode noise.

9. The gyroscope of claim 1 further comprising one or more support member motion sensors that sense motion of the support member about the drive axis.

10. The gyroscope of claim 9 in which the support member motion sensors comprise capacitive plate sensors.

11. The gyroscope of claim 9 further comprising one or more scale factor gimbal motion sensors that sense motion of the scale factor gimbal about the input axis.

12. The gyroscope of claim 11 in which the scale factor gimbal motion sensors comprise capacitive plate sensors.

13. The gyroscope of claim 11 further comprising a controller, responsive to the support member motion sensors, for maintaining an oscillation amplitude of the support member constant.

14. The gyroscope of claim 11 further comprising a controller, responsive to the scale factor gimbal sensors, for maintaining an oscillation amplitude of the scale factor gimbal constant.

15. The gyroscope of claim 1 in which the gyro member is flexibly coupled to the support member by a plurality of gyro member flexures.

16. The gyroscope of claim 15 in which the gyro member flexures each comprise two bending “U” flexures.

17. The gyroscope of claim 1 in which the support and gyro members are both generally annular.

18. The gyroscope of claim 1 in which the support member is flexibly coupled to the scale factor gimbal by a pair of linear flexures.

19. The gyroscope of claim 1 in which the gyro member is located within the support member.

20. The gyroscope of claim 19 in which the gyro member is coupled to the support member by flexures that are generally radial relative to the output axis.

21. A linear accelerometer with integral scale factor functionality, the accelerometer lying generally in a plane, for detecting acceleration along an acceleration input axis that lies in the plane, comprising: a substrate defining a surface;spaced bonding pads coupled to the substrate and projecting from the surface of the substrate;a shuttle spaced from the surface of the substrate and flexibly coupled to the bonding pads by shuttle flexures, such that the shuttle is capable of linear oscillatory motion relative to the substrate parallel to the input axis;a linear accelerometer located within and flexibly coupled to the shuttle by flexures such that the linear accelerometer is capable of motion along the input axis relative to the shuttle;one or more shuttle drives that oscillate the shuttle parallel to the input axis at a shuttle oscillation frequency, and thereby also oscillate the linear accelerometer along the input axis at the shuttle oscillation frequency;one or more shuttle oscillation sensors that determine the amplitude of the shuttle oscillation; andone or more accelerometer motion sensors that determine the accelerometer motion that is caused by both the shuttle oscillatory displacement due to the shuttle drives and any acceleration along the input axis.