Title of Invention	A GYROSCOPE
Abstract	A gyroscope for sensing rate on at least two axes, comprising a substantially planner vibratory resonator (2) having a substantially ring or hoop-like shape structure with inner and outer peripheries extending around a common axis, characterised by comprising carrier mode drive means (4, 14, 22) for causing the resonator (2) to vibrate in a Cosn1θ in-plane carrier mode, where m has an integer value of 2 or more, support means (3) for flexibly supporting the resonator (2) and for allowing the resonator (2) to vibrate, in response to the carrier mode drive means (4, 14, 12), relative to the support means (3), carrier mode pick-off means (5, 15, 23) for sensing in-plane movement of the resonator (2), X axis response mode pick-off means (8, 18, 26) for sensing out-of-plane CosnB response mode movement of the resonator (2) in respect to rotation of the gyroscope around the X axis, where n has a value of ni+1 or m-1, and Y axis response mode pick-off means (10, 20, 28) for sensing out-of-plane Sinnθ response mode movement of the resonator (2) in response to rotation of the gyroscope about the Y axis, where n has a value of m+1 or m-1, identical to that for the X axis response mode.

Title of Invention

A GYROSCOPE

Abstract

A gyroscope for sensing rate on at least two axes, comprising a substantially planner vibratory resonator (2) having a substantially ring or hoop-like shape structure with inner and outer peripheries extending around a common axis, characterised by comprising carrier mode drive means (4, 14, 22) for causing the resonator (2) to vibrate in a Cosn1θ in-plane carrier mode, where m has an integer value of 2 or more, support means (3) for flexibly supporting the resonator (2) and for allowing the resonator (2) to vibrate, in response to the carrier mode drive means (4, 14, 12), relative to the support means (3), carrier mode pick-off means (5, 15, 23) for sensing in-plane movement of the resonator (2), X axis response mode pick-off means (8, 18, 26) for sensing out-of-plane CosnB response mode movement of the resonator (2) in respect to rotation of the gyroscope around the X axis, where n has a value of ni+1 or m-1, and Y axis response mode pick-off means (10, 20, 28) for sensing out-of-plane Sinnθ response mode movement of the resonator (2) in response to rotation of the gyroscope about the Y axis, where n has a value of m+1 or m-1, identical to that for the X axis response mode.

Full Text	FORM 2 THE PATENTS ACT 1970 [39 OF 1970] PROVISIONAL/ COMPLETE SPECIFICATION [See Section 10] "A GYROSCOPE" BAE SYSTEMS PLC, a company organised and existing under the laws of the United Kingdom., Warwick House, P.O. Box 87, Famborough Aerospace Centre, Famborough, Hampshire GUM 6YU, United Kingdom The following specification particularly describes the nature of the invention and the manner in which it is to be performed :- This invention relates to a gyroscope for sensing rate on at least two axes. Preferably, this invention relates to a gyroscope for sensing rate on three axes. A reference is drawn to the co-pending Indian patent application No. IN/PCT/2000, 00316/MUM. Vibrating structure gyroscopes may be fabricated using a variety of different structures as the resonant element. These include beams, tuning forks, cylinders, hemispherical shells and rings. Successful commercial exploitation is dependent upon optimising the device performance while minimising the cost. An additional goal for some applications is reducing the size of the device. Some conventional vibrating structure gyro designs are suitable for fabrication using modern micro-machining techniques. These may be constructed from bulk Silicon, polysilicon or electro-formed metal. These fabrication methods provide the capability of producing miniature gyros in high volume and at reduced cost. Many applications for gyroscopic devices require rate sensitivity about all three axes. Conventional vibrating structure gyros provide single axis rate sensitivity and therefore three devices are required which must be aligned along orthogonal axes. For example conventional single axis gyroscopes are disclosed in "A rate gyroscope based on interaction of sonic waves" by G C Newton Jr published in IEEE transactions on automatic control, volume AC-10 number 3, July 1965, pages 235 to 243, GB-A-2154739, EP-A-0461761, and EP-A-0729010. The Gyroscopes disclosed in the above four references are all single axis devices incapable of providing any multi-axes sensing capability. The paper entitled "A rate gyroscope based on interaction of sonic waves" describes a single axis gyroscope design incorporating a solid ring-shaped structure as shown in Figure 6 thereof which has four straight support legs or rods at 90° angular intervals attached perpendicularly to the lower planar surface of the ring. The support legs are provided at the nodal points for the vibration mode employed which will induce a frequency split between the in-plane and out of plane mode pairs as the nodal points for one mode of the pair are anti-nodal points for the complementary mode. Hence the X and P waves shown in Figures 2 and 3 in the paper will be split in frequency by the support legs which prevents the structure from being used as a multi-axes sensor. GB-A-2154739 discloses a piezo-ceramic disk structure which uses in-plane extensional or dialation modes to provide a single axis gyroscope. EP-A-0461761 and EP-A-0729010 both describe single axis gyroscopes using planar ring structures in the form of planar ring resonators supported by eight legs. The number and periodicity of these legs is set to match the symmetry of the Cos 26 vibration modes employed to enable the frequencies of the primary and secondary modes to be matched precisely. These support leg structures are not suitable for matching the frequency of other in-plane or out of plane vibration mode pairs and thus cannot be used to provide a gyroscope for sensing rate on at least two axes. US-A-3206985 discloses apparatus for simultaneously sensing movement of a body around a plurality of mutually perpendicular axes. The apparatus includes a piezo-ceramic toroid or ring structure 13 made up of a ring like driven member 14 mounted internally of the ring on a resilient support 15 and mounted externally of the ring on beam-like bymorphic sensor elements 2 7 bonded to the outer peripheral surface of the ring 14 . The ring 14 vibrates in an extensional or breathing type mode which modules the outer diameter thereof such that when rate is applied about any axis the sensor elements 27 experience Coriolis forces which excite them into resonate motion. The signals from these sensor elements 27 may be interpreted to give rate sensitivity about three axes. There is no use of flexural modes of vibration within a single monolithic ring structure to sense rate on at least two axes. A vibrating structure gyro incorporating a resonator design which is inherently capable of sensing around three axes simultaneously would therefore be of great benefit. A single device would thus replace three conventional single axis units with obvious cost benefits. Also, the process of mounting and aligning the three single axis gyros would not be required. There is thus a need for an improved gyroscope which can sense rate on at least two axes. According to a first aspect of the present invention there is provided a gyroscope for sensing rate on at least two axes, including a substantially planar vibratory resonator having a substantially ring or hoop¬like shape structure with inner and outer peripheries extending around a common axis, characterised by including carrier mode drive means for causing the resonator to vibrate in a Cosn1θ in-plane carrier mode, where n1 has an integer value of 2 or more, support means for flexibly supporting the resonator and for allowing the resonator to vibrate, in response to the carrier mode drive means, relative to the support means, carrier mode pick-off means for sensing in-plane movement of the resonator, X axis response mode pick-off means for sensing out-of-plane Cosnθ response mode movement of the resonator in respect to rotation of the gyroscope around the X axis, where n has a value of n1 + l or n1-1, and Y axis response mode pick off means for sensing out-of- plane Sinnθ response mode movement of the resonator in respect to rotation of the gyroscope about the Y axis, where n has a value of n]_ + l or n^-1, identical to that for the X axis response mode. Preferably the gyroscope includes X axis response mode drive means for nulling the X axis response mode movement of the resonator to permit the gyroscope to be operated in a forced feedback configuration. Conveniently the gyroscope includes Y axis response mode drive means for nulling the Y axis response mode movement of the resonator to permit the gyroscope to be operated in a forced feed back configuration. Advantageously for sensing rate about two axes the support means includes a plurality of flexible legs flexibly connecting the resonator to a support, with the number of legs NT being given by Np=4n and with the angular separation between the legs being given by 360°/NT. Preferably for sensing rate about three axes the gyroscope includes Z axis response mode pick off means for sensing in-plane Sin n1θ response mode movement of the resonator in respect to rotation of the gyroscope around the Z axis, where n1θ has an integer value of 2 or more, identical to that for the in-plane carrier mode. Conveniently the gyroscope for sensing rate about three axes includes Z axis response mode drive means for nulling the Z axis response mode movement of the resonator to permit the gyroscope to be operated in a forced feedback configuration. Advantageously the support means includes a plurality of flexible legs flexibly connecting the resonator to a support, with the number of legs NT being given by Np=4nni and with the angular separation between the legs being given by 360°/Np. Preferably in a gyroscope of the present invention for sensing rate about two axes the carrier mode is an in-plane Cos2θ mode, with the carrier mode drive means including two drive elements, for initiating the carrier mode motion, located at 0° and 180° with respect to a fixed reference axis in the plane of the resonator, with the carrier mode pick off means including two pick off elements, for detecting the carrier mode motion, located at 90° and 270° with respect to the fixed reference axis, wherein the X axis response mode is a Cos 36 mode, with the X axis pick off means including three pick off elements located at 0°, 120°, and 240° with respect to the fixed reference axis, with the X axis drive means including three drive 'elements located at 60°, 180° and 3 00° with respect to the fixed reference axis, and wherein the Y axis response mode is a Sin 39 mode, with the Y axis pick off means including three pick off elements located at 30°, 150° and 270° with respect to the fixed reference axis and with the Y axis drive means including three drive elements located at 90°, 210° and 330° with respect to the fixed reference axis, which X and Y axis drive and pick off elements are operable to detect and nullify the response mode motions. Alternatively the carrier mode is an in-plane Cos 39 mode, with the carrier mode drive means including three drive elements located at 0°, 120^ and 240° with respect to a fixed reference axis in the plane of the resonator, with the carrier mode pick off means including three pick off elements located at 60°, 180° and 300° with respect to the fixed reference axis, wherein the X axis response mode is a Cos 29 mode, with the X axis pick off means including two pick off elements located at 0° and 180° with respect to the fixed reference axis, with the X axis drive means including two drive elements located at 90° and 270° with respect to the fixed reference axis, and wherein the Y axis response mode is a Sin 2θ mode, with the Y axis pick off means including two pick off elements located at 45° and 225° with respect to the fixed reference axis and with the Y axis drive means including two drive elements located at 135° and 315° with respect to the fixed reference axis. Conveniently the carrier mode is an in-plane Cos 36 mode, with the carrier mode drive means including three drive elements located at 0°, 120° and 240° with respect to a fixed reference axis in the plane of the resonator, with the carrier mode pick off means including three pick off elements located at 60°, 180° and 300° with respect to the fixed reference axis, wherein the X axis response mode is a Cos 46 mode, with the X axis pick off means including four pick off elements located at 0°, 90°, 180° and 270° with respect to the fixed reference axis, with the X axis drive means including four drive elements located at 45°, 135°, 225° and 315° with respect to the fixed reference axis and wherein the Y axis response mode is a Sin 49 mode, with the Y axis pick off means including four pick off elements located at 22.5°, 112.5° and 292.5° with respect to the fixed reference axis, and with the Y axis drive means including four drive elements located at 67.5°, 157.5°, 247.5° and 337.5° with respect to the fixed reference axis. Advantageously a gyroscope for sensing rate of three axes, includes Z axis response mode pick off means for sensing in-plane Sin 2θ response mode movement of the resonator, which Z axis pick off means includes two pick off elements located at 45° and 225° with respect to the fixed reference axis, and including Z axis response mode drive means having two drive elements located at 135° and 315° with respect to the fixed reference axis. Preferably a gyroscope for sensing rate on three axes, includes Z axis response mode pick off means for sensing in-plane Sin 39 response mode movement of the resonator, which Z axis pick off means includes three pick off elements located at 90°, 210° and 330° with respect to the fixed reference axis, and including Z axis response mode drive means having three drive elements located at 30°, 150° and 270° with respect to the fixed reference axis. Advantageously the resonator is made from metal, quartz, polysilicon or bulk silicon. Advantageously the drive means and the pick off means are electrostatic, electromagnetic, piezoelectric or optical. For a better understanding of the present invention, and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings in which: Figure la is a schematic diagram of a vibrating structure gyroscope not according to the present invention, Figure lb shows the three orthogonal axes along which the velocity, rotation and force vectors lie with the structure of Figure la, Figures 2a and 2b show graphically the shapes of mode pairs exhibiting Cosn1θ and Sinn1θ radial displacements for n1=2, Figures 3a and 3b are graphical shapes similar to those of Figures 2a and 2b for n=3, Figures 4a and 4b are graphical shapes similar to those of Figures 2a and 2b and Figures 3a and 3b but for n]_=4, Figures 5a and 5b are graphical representations on three axes for the force components generated by a rotation of a gyroscope according to the present invention about the Y axis, for a Cos29 in-plane carrier mode. Figures 6a and 6b are similar graphical representations to those of Figures 5a and 5b but representing rotation about the X axis, Figures 7a and 7b are graphical representations on three axes of the vibration mode shapes exhibiting Cosn0 and Sinn6 out-of-plane displacements for n=l, Figures 8a and 8b are graphical representations similar to those of Figures 7a and 7b but for n=2, Figures 9a and 9b are graphical representations similar to those of Figures 8a and 8b but for n=3, Figures 10a and 10b are graphical representations similar to those of Figures 9a and 9b but for n=4, Figure 11a shows in plan view a diagrammatic example of a resonator and support legs suitable for use in a gyroscope according to the present invention, Figure 11b shows in plan view a further resonator and support leg structure for use with a gyroscope according to the present invention, Figure 12 is a schematic diagram in plan view of part of a gyroscope according to a first embodiment of the present invention showing drive and pick off elements, Figure 13 is a cross sectional view on a diagonal of the structure of Figure 12 showing additional detail, Figure 14 is a schematic plan view of part of a gyroscope according to a second embodiment of the present invention, Figure 15 is a diagrammatic plan view of part of a gyroscope according to a third embodiment of the present invention, Figure 16 is a diagrammatic plan view of part of a gyroscope according to a fourth embodiment of the present invention, Figure 17 is a diagrammatic plan view of part of a gyroscope according to a fifth embodiment of the present invention and, Figure 18 is a diagrammatic plan view of part of a gyroscope according to a sixth embodiment of the present invention. A common feature of all conventional vibrating structure gyro designs is that they maintain a resonant carrier mode oscillation. This provides the linear momentum which produces the Coriolis force Fc, when the gyro is rotated around the appropriate axis. The magnitude of this force is given by: Fc = 2 m v . . (1) where is the applied rate, m is the mass and v the linear velocity. The velocity, rotation and force vectors lie along mutually orthogonal axes as shown in Figures la and lb of the accompanying drawings. One of the simplest implementations for a vibrating structure gyro is a beam 1 shown in Figure la. The carrier mode vibration is a bending motion in the xz-plane as shown in Figures la and lb. A rotation applied about the axis of the beam 1 (z-axis) will generate Coriolis forces which set the beam 1 into motion in the yz-plane, at the carrier frequency. The amplitude of motion in this axis will be proportional to the applied rotation rate. The sensitivity of such a device may be enhanced by designing the structure such that the Coriolis force directly excites a resonant mode. The amplitude of motion is then amplified by the Q of the response mode. For a simple beam made of isotropic material this will be achieved using a beam of square cross-section where the X and Y dimensions are matched. A rotation about the Y-axis will also induce Coriolis forces in the beam 1. These will act along the length of the beam (z-axis) . The beam is extremely stiff in this direction and is therefore insensitive to these forces. However this simple linear vibration along a single axis is able to respond to rotations around two axes. Implementation of a practical gyroscope based on these responses requires a resonator design that enables these Coriolis force components to couple directly into response modes along the appropriate axes. In order to produce a gyroscope capable of sensing rate along three axes the carrier mode motion must contain velocity components along two orthogonal axes. The structure must also be designed such that the Coriolis forces induced as a result of rotation about each axis couple into response modes whose resonant frequency may be matched to that of the carrier. Planar ring structures utilising Cosn1θ in-plane carrier modes (where 0 is the angular location around the ring circumference relative to a fixed datum and n1 has a fixed integer value of 2 or more, are particularly suited to this application. The n1 = l mode is not a suitable carrier as it is a rigid body translation of a ring resonator and thus only has velocity components along a single axis. For perfect ring resonator structures the Cosn1θ in- plane vibration modes exist as degenerate pairs at a mutual angle of (90/n1°. The 0=0° reference axis R for the modal diagrams is along the Y-axis in the positive direction. Using this fixed reference the mode pairs will have shapes exhibiting Cosn1θ and Sinn1θ radial displacements. The mode shapes for n1 = 2 are shown in Figures 2a and 2b. The two extremes of maximum displacement from the unexcited ring position, during a -single vibration cycle, are shown for each mode of the pair. The axes indicate the displacement from the unexcited ring position for a ring of radius 1.0 (arbitrary units). The modes exist at a mutual angle of 45°. The mode shapes for n1 = 3 are similarly shown in Figures 3a and 3b. These exist at a mutual angle of 30°. The corresponding shapes for the n1=4 modes are shown in Figures 4a and 4b and exist at a mutual angle of 22.5o. Vibrating structure gyro designs using ring structures, capable of sensing rate about a single axis, are well known. These use one of the in-plane Cosn1θ mode pair (typically n1=2) as the carrier. A rotation about the axis normal to the plane of the ring (z-axis) couples energy into the second mode of the pair with the induced amplitude of motion being proportional to the applied rate. Using these carrier modes, rotations about axes in the plane of the ring will also give rise to Coriolis forces. These will act along the z-axis and will tend to set the ring into out-of-plane motion. The distribution of these forces will vary with angular position 0 and, for rotation about the Y-axis, y, will be given by: ... (2) The parameters Fn^ + l and Fn]-1 are constants which depend on the precise geometry of the ring and the support means, the material and the value of n1. The out-of-plane Coriolis force thus has components which vary as Sin(n] + 1)θ and Sin(n]_-1)θ. For the same carrier mode, a rotation about the X-axis will induce Coriolis forces given by: ... (3) The out-of-plane Coriolis force in this instance has components varying as Cos(n1+l)θ and Cos(n1-l)θ. By way of example, for the case where the carrier is the Cos2θ in-plane mode shown in Figure 2a, a rotation about the Y-axis will generate force components which vary as Sinθ and sin3θ. These are shown in Figures 5a and 5b, respectively. A rotation about the X-axis will generate components which vary as Cosθ and cos3θ. These are shown in Figures 6a and 6b. The z-axis displacement of the out-of-plane modes will also exhibit a Cosnθ angular dependence and, like the in-plane modes these exist as degenerate pairs at a mutual angle of (90/n)°. The mode shapes for n=l exist at a mutual angle of 90° (i.e. Sinθ and Cosθ radial displacements) and are shown in Figures 7a and 7b. As with the previous modal diagrams, the two extremes of motion are shown with the rest position of the ring indicated by the broken lines. The corresponding plots for the n=2, 3 and 4 modes are shown in Figures 8a, 8b, 9a, 9b, 10a and 10b. The functional forms of the Coriolis force components shown in Figures 5a and 6a precisely match those of the n=l out-of-plane mode shown in Figures 7a and 7b. Similarly, the forms of the Coriolis force components shown in Figures 5b and 6b precisely match those of the n=3 out-of-plane modes shown in Figures 9a and 9b. Clearly, these modes may be directly excited as a result of the rotation induced Coriolis forces. Examination of equations 2 and 3 indicates that any Cosn1θ in-plane carrier mode can couple into Cos (n1 + l)0, Sin(n]_ + 1)θ, Cos(n]_-l) and Sin(ni-1)θ out-of-plane modes when rotated around the appropriate axis. To be of practical use in any gyro configuration, the amplitude of motion generated must be as large as possible to maximise the gyro sensitivity. This is achieved by matching the mode frequencies of the carrier and a chosen pair out-of-plane response modes. The resultant motion is thus amplified by the Q of the response mode vibration. The in-plane mode frequencies are not affected by changing the depth (ie z-axis dimension) of the ring. The out-of-plane mode frequencies are directly sensitive to this parameter and may therefore be independently adjusted. By judicious control of the dimensions of the ring resonator and support structure it is possible to match the Cosn1θ in-plane carrier frequency with either the Cos(n1 + 1)θ and Sin(n]_ + 1)θ or the Cos(n1-1)θ and Sin(n1-1)θ out-of-plane modes. It is therefore possible to design multi-axis gyro schemes using a variety of carrier and response mode combinations. The Cos20 carrier mode can couple into the Sin0, Cos0, Sin30 and Cos30 out-of-plane response modes. These are shown in Figures 7a, 7b, 9a and 9b respectively. The use of the Cos20 carrier in combination with the Sin30 and Cos36 response modes according to the present invention is capable of being implemented as a three axis rate sensor. The resonator in a vibrating structure gyro preferably is substantially planar having a ring or hoop like shape resonator structure 2 with inner and outer peripheries extending around a common axis A normal to a fixed reference axis R in the plane of the resonator structure 2, which axis R extends in the direction of the Y axis. The ring structure is supported by support means including a plurality of compliant support legs 3. When driven in a Cos20 carrier mode both the ring and support legs are in motion. However, the ring 2 is very stiff in comparison to the support legs 3 and the carrier frequency is predominantly set by the ring dimensions. This effectively isolates the resonator from the mounting and reduces environmental sensitivity. The Sinθ and Cosθ out-of-plane modes (Figures 7a and 7b) will involve significant deflection and stress in the support legs 3 with insignificant distortion of the ring 2. Due to the compliance of the legs this Cosθ mode naturally occurs at a significantly lower frequency than the Cos2θ carrier. The Sin3θ and Cos3θ response modes (Figures 9a and 9b) distort and stress the ring significantly. Its natural mode frequency will therefore be significantly higher than that of the Cosθ mode. The Cos 2θ carrier and the Sin3θ and Cos3θ response mode frequencies may thus be matched with considerably less adjustment of the leg to ring stiffness ratio. This helps to maintain the environmental capability of the gyroscope. When using the out-of-plane Cosθ response modes, the legs 3 will always transmit a non-zero torque to the support structure as the ring 2 rocks about the input rotation axis. In contrast, the out-of-plane Sin30 and Cos39 response mode will not transmit any net reaction force to the support structure if an appropriate number of legs are used. This will be true for all Cosnθ modes where n>l. Practical gyroscopes of the present invention may be constructed using higher order in-plane carrier modes. The Cos3θ in-plane mode (Figure 3b) may be used as the carrier in conjunction with either the Cos2θ and Sin2θ or the Cos4θ and Sin4θ out-of-plane response modes. These response modes are shown in Figures 8a, 8b, 10a and 10b respectively. The Cos4θ carrier (Figure 4a) will couple into the Sin 3θ, Cos3θ, Sin5θ and Cos5θ response modes. Corresponding combinations of higher order are also feasible. In practice, however, the higher order mode combinations become increasingly onerous to implement. The mode shapes become progressively more complex and require a larger number of discrete drive and pick off elements to excite and sense the vibrations. Also, the support legs 3 act as point spring masses which perturb the mode frequencies. The number and location of these legs need to be matched to the mode symmetry to avoid induced splitting of the degenerate mode frequencies. The number of legs required increases rapidly with the mode order thus rendering some designs impractical on a small size gyroscope. A three axis gyroscope according to the present invention may be constructed by using a combination of Sin20 and Cos26 in-plane and the Sin30 and Cos38 out-of -plane' modes. This gyroscope requires the frequencies of four modes to be matched (one carrier plus three response modes). However, for a perfectly symmetric ring 2 of uniform thickness, the Sin26 and Cos20 mode pair will have identical frequencies. Similarly, the Sin30 and Cos3G mode pair will also be matched. Therefore, due to the high degree of symmetry, the design of the resonator dimensions is, in practice, reduced to an exercise in matching only two frequencies (ie those of the two degenerate mode pairs). For the dimensions commonly used in ring resonators designed for single axis operation the Cos39 out-of-plane and Cos20 carrier mode frequencies naturally occur relatively closely matched in frequency. Adjusting the depth (z-axis dimension) of the ring does not alter the in-plane frequencies. It does, however, have a distinct affect of the out-of-plane frequencies. Matching the Sin2θ, Cos2θ, Sin3θ and Cos30 mode frequencies may therefore be achieved by appropriate adjustment of a single ring dimension. In terms of the mode dynamics, the support legs 3 appear as point spring masses acting at the point of attachment which differentially perturb the mode frequencies. In order to prevent frequency splitting and maintain the positional indeterminacy of the modes, the number and location of the legs must be matched to the mode symmetry. For any Sinn1θ and Cosn1θ mode pair this necessitates the use of 4n1 equi-angularly spaced legs (where n1 is 2 or more) . The Sin29 and Cos2G in-plane modes therefore require 8 equally spaced legs. The Sin39 and Cos39 out-of-plane modes require 12 legs to maintain their indeterminacy. To satisfy this requirement simultaneously for both mode pairs implies the use of 24 legs equally spaced at 15° intervals around the ring 2. This number is the lowest common multiple of the in-plane and out-of-plane leg numbers and may be derived for any three axis gyro mode combination from the following expression: Number of legs NT= nxn1x4 ... (4) The angular spacing of these legs is given by [360/NT]°. For planar ring resonator structures the support legs 3 are designed such that the modal behaviour is dominated by the ring characteristics. This requires the legs to be radially and tangentially compliant, in comparison to the ring itself. Many design variations are possible which achieve these requirements. Figures lla and l1b show two possibilities for the twenty-four support leg structure of one embodiment of the present invention. These designs are consistent with the use of larger numbers of support legs 3. Vibrating structure gyroscopes of the invention may be constructed using standard fabrication and machining techniques. They are also suitable for fabrication using micro-machining techniques. The principle of operation and drive and pick off orientations will be identical regardless of the fabrication route. The resonator may be constructed from any material possessing suitable mechanical properties including metal, quartz, polysilicon or bulk silicon. The ring 2 may be driven into oscillation using a variety of drive means. These include electrostatic, electromagnetic, piezo or optical means. The amplitude of motion may similarly be detected using electrostatic, electromagnetic, piezo or optical pick off means. The preferred three axis gyroscope embodiment uses electrostatic drive and pick off means. The orientation of drive and pick off elements for this embodiment is shown in Figure 12. The location of the ring 2 is indicated by the dashed lines. The in-plane Cos26 carrier mode is driven into oscillation using drive elements 4 whose effective centres are located at oO and 180° around the outer periphery of the ring 2 with respect to the fixed reference axis R. For each element, the surface normal to the plane of the ring 2 facing the ring circumference forms one plate of the capacitor with the facing segment of the ring circumference forming the other plate. The ring 2 is maintained at a fixed potential with respect to the drive elements 4. An oscillating voltage applied to the drive element plates at the carrier mode frequency will generate an electrostatic force setting the ring 2 into oscillation. Pick off elements 5, for the carrier mode located at 90° and 270°with respect to the fixed reference axis R, similarly form capacitors with the facing ring segments and are used to detect the motion of the ring 2 as the capacitor gap varies. Pick off elements 6 located at 45° and 225° with respect to the axis R detect the amplitude of the in-plane Sin29 response mode when the gyroscope is rotated around the z-axis. Z axis drive elements 7 located at 135° and 315° with respect to the axis R, may be used to null the mode movement to allow the gyroscope to operate in a forced feedback configuration. When operated in this mode the nulling drive is proportional to the applied rate. This mode of operation provides performance advantages over the open loop mode. The Cos30 out-of-plane response mode providing the X-axis rate sensitivity will have anti-nodes at 0°, 60°, 120°, 180°, 240° and 300° locations, with respect to the axis R, around the ring circumference. The sin36 Y-axis response mode will have anti-nodes at 30°, 90°, 150°, 210°, 270° and 330° with respect to the axis R. Drive and pick off elements may be located at any appropriate combinations adjacent to these points. Conveniently, twelve plate like elements are positioned directly under the rim to form capacitors between said plates and the parallel facing segments of the bottom surface of the ring. Conveniently, the plates should extend beyond the inner and outer edges of the ring rim. The in-plane motion of the carrier mode will not therefore change the effective plate area and will not be inadvertently detected by these plate like elements. Elements 8 located at 0°, 120° and 240° are used as X-axis pick off elements. The signals from these elements will be in phase and may be conveniently summed together to give enhanced sensitivity in detecting the mode movement. Plate like elements 9 located at 60°, 180° and 300° with respect to the axis R are used as drive elements with the same drive voltage being applied to all these elements to null the motion to facilitate force feedback operation. Similarly, plate like elements 10 located at 30°, 150° and 270o with respect to the axis R are the Y-axis pick off elements with plate like elements 11 located at 90°, 210° and 330°, with respect to the axis R forming the drive elements for that mode. Figure 13 shows a cross-section view through the centre of the resonator ring 2 along the Y-axis showing additional detail of the device architecture. The X and Y axis drive and pick off elements are conductive sites laid onto the surface of an electrically insulating substrate layer 12. These element sites are connected via tracks to bond pads (not shown) which can be electrically connected to the control circuitry. The ring 2 is attached, via the support legs 3, to a central support pedestal 13. This pedestal extends beneath the ring 2 and attaches rigidly to the substrate layer 12 such that the ring and support legs are freely suspended above the substrate layer. The in-plane mode drives and pick off elements are rigidly attached to the substrate 12 with tracking and bond pads provided as require to enable connection to the control circuitry. Modifications to this structure are possible. The addition of a second insulating substrate layer rigidly fixed above the resonator ring 2, duplicating the out-of- plane drive and pick off element capacitor plate array, would enhance the sensitivity of the gyroscope along the X and Y axes. This would, however, complicate the fabrication process and would not alter the essential design features or functionality of the gyroscope. A two axis gyroscope according to the present invention may be fabricated using the same Cos2G in-plane carrier mode and Sin3θ and Cos3θ out-of-plane response modes. For this embodiment the resonator design is such that the in-plane Sin2θ and Cos2θ mode frequencies are deliberately separated. Advantageously, this frequency split will fix the carrier mode position at a known angular location which may be aligned to the carrier mode drive and pick off means. The carrier mode frequency must still be matched to that of the out-of-plane response modes. If twelve support legs 3 are used then the symmetry of the Cos 3θ modes is maintained. This will, however, generate a splitting of the in-plane Sin2G and Cos26 modes and thus fix the mode positions as required. Generally, for two axis gyroscope operation the required number of support legs is given by the following expression: Number of legs N-p = nx4 ... (5) The angular spacing is [360/NT]°. This implementation will provide rate sensitivity about the X and Y axes only. The in-plane response mode drive and pick off means are thus not required. Figure 14 shows a schematic of the gyroscope layout for this embodiment. This is essentially the same as the three axis embodiment of Figures 12 and 13, with the exception of the absence of the Z axis in-plane response mode drive elements 7 and pick off elements 6 and the different number of support legs, and hence like reference numerals have been used. No further description will therefore be given. A two or three axis gyroscope may be fabricated using Sin30 and Cos30 in-plane modes in conjunction with sin20 and Cos20 out-of-plane response modes. For the three axis embodiment the degeneracy of both the in-plane sin39 and Cos30 and out-of-plane Sin20 and Cos28 mode pairs must be maintained. This dictates the use of twenty-four support legs 3 on the resonator ring 2. A schematic of the orientation of the drive and pickoff elements is shown in Figure 15. The topology of the gyroscope is largely identical to the previously described embodiments with the exception of the drive and pick off element layout. The Cos30 in-plane carrier drive means elements 14 are located at 0°, 120° and 240° with respect to the fixed reference axis R with the pick off means elements 15 located at 60°, 180° and 300° with respect to the axis R. The Z axis sin30 in-plane response mode drive elements 16 are located at 30°, 150° and 270° with respect to the axis R with the pick off Elements. 17 at 90°, 210° and 330° with respect to the axis R. The out-of-plane Cos20 X axis response mode pick off elements 18 are located at 0° and 180° with the nulling drive elements 19 at 90° and 270° with respect to the axis R. The Y axis out-of-plane Sin2G pick off elements 20 are located at 45° and 225° with respect to the axis R with the nulling Y axis drive elements 21 at 135° and 315° with respect to the axis R. The two axis embodiment of this Cos39 in-plane carrier and out-of-plane Sin20 and Cos26 response mode combination requires the in-plane mode degeneracy to be lifted. This may be achieved by the use of eight support legs. Otherwise, this embodiment differs from the three axis one only in the omission of the in-plane response mode drive elements 16 and pick off elements 17. The drive and pick off means layout is shown in Figure 16. A two or three axis gyroscope of the invention may be fabricated using a Sin36 and Cos30 in-plane and a Sin40 and Cos40 out-of-plane mode combination. The three axis embodiment requires the use of forty-eight support legs 3 to maintain all the appropriate mode symmetries. This embodiment is shown schematically in Figure 17. The Cos30 in-plane carrier mode drives 22 are located at 0°, 120° and 240° with respect to the fixed reference axis R with the pick off elements 23 at 60°, 180° and 300° with respect to the axis R. The in-plane Z axis Sin30 response mode drive elements 24 are located at 30°, 150° and 270° with respect to the axis R with the z axis Cos30 Methodein-plane pick off elements 25 at 90°, 210° and 300° with respect to the axis R. The X axis Cos4θ out-of-plane response mode pick off elements 26 are located at 0°, 90°, 180° and 270° with respect to the fixed reference axis R, with X axis Cos46 out-of-plane response mode nulling drive elements 27 at 45°, 135°, 225° and 315° with respect to the axis R. The Y axis Sin4G out-of-plane response mode pick off elements 28 are located at 22.5°, 112.5° 202.5° and 292.5° with respect to the axis R with Y axis Sin40 out-of-plane response mode nulling drive elements 29 at 67.5°, 157.5°, 247.5° and 337.5° with respect to the axis R. The corresponding two axis gyroscope embodiment of the invention requires sixteen support legs 3. The layout for this embodiment, shown in Figure 18, is otherwise identical to the three axis one of Figure 17 with the exception of the omission of the z axis in-plane response mode drive elements 24 and pick off elements 25. Like parts have been given like numbers to those of Figure 17 and will not be further described. Two and three axis rate sensors may be fabricated using higher order in-plane and out-of-plane mode combinations. These will require progressively higher numbers of support legs to maintain the necessary mode symmetries and a larger number of drive and pick off elements. As a result of this these embodiments, while feasible, become progressively more complicated to fabricate, particularly in a small size gyroscope. Additonally in a gyroscope of the invention for sensing rate about two axes, the resonator 2 and support means are dimensioned so that the Cosn1θ in-plane carrier mode and SinnG and Cosnθ out-of-plane response mode frequencies are matched, and for sensing rate about three axes the dimensions are such that the Cosn1θ in-plane carrier mode, Sinn10in-plane response mode and SinnG and CosnG out-of-plane response mode frequencies are matched. We claim: 1. A gyroscope for sensing rate on at least two axes, comprising a substantially planner vibratory resonator (2) having a substantially ring or hoop-like shape structure with inner and outer peripheries extending around a common axis, characterised by comprising carrier mode drive means (4, 14, 22) for causing the resonator (2) to vibrate in a Cosn1θ in-plane carrier mode, where m has an integer value of 2 or more, support means (3) for flexibly supporting the resonator (2) and for allowing the resonator (2) to vibrate, in response to the carrier mode drive means (4, 14, 12), relative to the support means (3), carrier mode pick-off means (5, 15, 23) for sensing in-plane movement of the resonator (2), X axis response mode pick-off means (8, 18, 26) for sensing out-of-plane CosnB response mode movement of the resonator (2) in respect to rotation of the gyroscope around the X axis, where n has a value of ni+1 or m-1, and Y axis response mode pick-off means (10, 20, 28) for sensing out-of-plane Sinnθ response mode movement of the resonator (2) in response to rotation of the gyroscope about the Y axis, where n has a value of m+1 or m-1, identical to that for the X axis response mode. 2. A gyroscope as claimed in claim 1, comprising X axis response mode drive means (9, 19, 27) for nulling the X axis response mode movement of the resonator (2) to permit the gyroscope to be operated in a forced feedback configuration. 3. A gyroscope as claimed in claim 1 or 2, comprising Y axis response mode drive means (11, 21, 29) for nulling the Y axis response mode movement of the resonator (2) to permit the gyroscope to be operated in a forced feed-back configuration. 4. A gyroscope as claimed in anyone of the claims 1 to 3, wherein for sensing rate about two axes the support means comprises a plurality of flexible legs (3) flexibly connecting the resonator (2) to a support (13), with the number of legs NT being given by NT=4n and with the angular separation between the legs (3) being given by 360°/NT. A gyroscope as claimed in anyone of claims 1 to 3, for sensing rate about three axes, comprising Z axis response mode pick off means (6, 17, 25) for sensing in-plane Sin m0 response mode movement of the resonator (2) in respect to rotation of the gyroscope around the Z axis, where m has an integer value of 2 or more, identical to that for the in-plane carrier mode. A gyroscope as claimed in claim 5, comprising Z axis response mode drive means (7, 16, 24) for nulling the Z axis response mode movement of the resonator (2) to permit the gyroscope to be operated in a forced feedback configuration. A gyroscope as claimed in claim 5 or 6, wherein the support means comprises a plurality of flexible legs (3) flexibly connecting the resonator to a support (13), with the number of legs NT being given by NT=4nni and with the angular separation between the legs (3) being given by 360°/NT. A gyroscope as claimed in claims 1, 2, 3 or 4, for sensing rate about two axes, wherein the carrier mode is an in-plane Cos26 mode, with the carrier mode drive means comprising two drive elements (4) for initiating the carrier mode motion, located at 0° and 180° with respect to a fixed reference axis (R) in the plane of the resonator (2), with the carrier mode pick-off means comprising two pick-off elements (5), for detecting the carrier mode motion, located at 90° and 270° with respect to the fixed reference axis (R), wherein the X axis response mode is Cos 36 mode, with the X axis pick-off means comprising three pick-off elements (8) located at 0°, 120° and 240° with respect to the fixed reference axis (R), with the X axis drive means comprising three drive elements (9) located at 60°, 180° and 300° with respect to the fixed reference axis (R), and wherein the Y axis response mode is a Sin 30 mode, with the Y axis pick-off means comprising three pick-off elements (10) located at 30°, 150° and 270° with respect to the fixed reference axis (R) and with the Y axis drive means comprising three drive elements (11) located at 90°, 210° and 330° with respect to the fixed reference axis, which X and Y axis drive and pick-off elements (8, 9, 10, 11) are operable to detect and nullify the response mode motions. A gyroscope as claimed in claims 1, 2, 3 or 4, wherein the carrier mode is an in-plane Cos 30 mode, with the carrier mode drive means comprising three drive elements (14) located at 0°, 120° and 240° with respect to a fixed reference axis in the plane of the resonator (2), with the carrier mode pick-off means comprising three pick-off elements (15) located at 60°, 180° and 300° with respect to the fixed reference axis (R), wherein the X axis response mode is a Cos 20 mode, with the X axis pick-off means comprising two pick-off elements (18) located at 0° and 180° with respect to the fixed reference axis (R), with the X axis drive means comprising two drive elements (19) located at 90° and 270° with respect to the fixed reference axis (R), and wherein the Y axis response mode is a Sin 20 mode, with the Y axis pick-off means comprising two pick-off elements (20) located at 45° and 225° with respect to the fixed reference axis (R) and with the Y axis drive means comprising two drive elements (21) located at 135° and 315° with respect to the fixed reference axis (R). A gyroscope as claimed in claims 1, 2, 3 or 4, wherein the carrier mode is an in-plane Cos 30 mode, with the carrier mode drive means comprising three drive elements (22) located at 0°, 120° and 240° with respect to a fixed reference axis (R) in the plane of the resonator (2), with the carrier mode pick-off means comprising three pick-off elements (23) located at 60°, 180° and 300° with respect to the fixed reference axis (R), wherein the X axis response mode is a Cos 49 mode with the X axis pick-off means comprising four pick-off elements (26) located at 0°, 90°, 180° and 270° with respect to the fixed reference axis (R), with the X axis drive means comprising four drive elements (27) located at 45°, 135°, 225° and 315° with respect to the fixed reference axis (R) and wherein the Y axis response mode is a Sin 40 mode, with the Y axis pick-off means comprising four pick-off elements (28) located at 22.5°, 112.5° and 292.5° with respect to the fixed reference axis (R) and with the Y axis drive means comprising four drive elements (29) located at 67.5°, 157.5°, 247.5° and 337.5° with respect to the fixed reference axis (R). A gyroscope as claimed in claim 8, for sensing rate of three axes, comprise Z axis response mode pick-off means for sensing in-plane Sin 26 response mode movement of the resonator (2), which Z axis pick-off means comprises two pick-off elements (6) located at 45° and 225° with respect to the fixed reference axis (R) and comprising Z axis response mode drive means having two drive elements (7) located at 135° and 315° with respect to the fixed reference axis (R). A gyroscope as claimed in claim 9 or 10, for sensing rate on three axis comprises Z axis response mode pick-off means for sensing in-plane Sin 30 response mode movement of the resonator, which Z axis pick-off means comprises three pick-off elements (17) located at 90°, 210° and 330° with respect to the fixed reference axis (R), and comprising Z axis response mode drive means having three drive elements (16) located at 30°, 150° and 270° with respect to the fixed reference axis (R). A gyroscope as claimed in any one of claims 1 to 12, wherein the resonator (2) is made from metal quartz, polysilicon or bulk silicon. 14. A gyroscope as claimed in any one of claims 1 to 13, wherein the drive means (4) and the pick off means are electrostatic, eletromagnetic, piezoelectric or optical. Dated this the 22nd day of August, 2000. (Dr. RAMESH KUMAR MEHTA) OF REMFRY & SAGAR ATTORNEY FOR THE APPLICANTS

Full Text

FORM 2
THE PATENTS ACT 1970
[39 OF 1970]
PROVISIONAL/ COMPLETE SPECIFICATION
[See Section 10]
"A GYROSCOPE"
BAE SYSTEMS PLC, a company organised and existing under the laws of the United Kingdom., Warwick House, P.O. Box 87, Famborough Aerospace Centre, Famborough, Hampshire GUM 6YU, United Kingdom
The following specification particularly describes the nature of the invention and the manner in which it is to be performed :-

This invention relates to a gyroscope for sensing rate on at least two axes. Preferably, this invention relates to a gyroscope for sensing rate on three axes.
A reference is drawn to the co-pending Indian patent application No. IN/PCT/2000, 00316/MUM.
Vibrating structure gyroscopes may be fabricated using a variety of different structures as the resonant element. These include beams, tuning forks, cylinders, hemispherical shells and rings. Successful commercial exploitation is dependent upon optimising the device performance while minimising the cost. An additional goal for some applications is reducing the size of the device.
Some conventional vibrating structure gyro designs are suitable for fabrication using modern micro-machining techniques. These may be constructed from bulk Silicon, polysilicon or electro-formed metal. These fabrication methods provide the capability of producing miniature gyros in high volume and at reduced cost.
Many applications for gyroscopic devices require rate sensitivity about all three axes. Conventional vibrating structure gyros provide single axis rate sensitivity and therefore three devices are required which must be aligned along orthogonal axes.
For example conventional single axis gyroscopes are disclosed in "A rate gyroscope based on interaction of sonic waves" by G C Newton Jr published in IEEE transactions on automatic control, volume AC-10 number 3, July 1965, pages 235 to 243, GB-A-2154739, EP-A-0461761,

and EP-A-0729010. The Gyroscopes disclosed in the above four references are all single axis devices incapable of providing any multi-axes sensing capability.
The paper entitled "A rate gyroscope based on interaction of sonic waves" describes a single axis gyroscope design incorporating a solid ring-shaped structure as shown in Figure 6 thereof which has four straight support legs or rods at 90° angular intervals attached perpendicularly to the lower planar surface of the ring. The support legs are provided at the nodal points for the vibration mode employed which will induce a frequency split between the in-plane and out of plane mode pairs as the nodal points for one mode of the pair are anti-nodal points for the complementary mode. Hence the X and P waves shown in Figures 2 and 3 in the paper will be split in frequency by the support legs which prevents the structure from being used as a multi-axes sensor.
GB-A-2154739 discloses a piezo-ceramic disk structure which uses in-plane extensional or dialation modes to provide a single axis gyroscope.
EP-A-0461761 and EP-A-0729010 both describe single axis gyroscopes using planar ring structures in the form of planar ring resonators supported by eight legs. The number and periodicity of these legs is set to match the symmetry of the Cos 26 vibration modes employed to enable the frequencies of the primary and secondary modes to be matched precisely. These support leg structures are not suitable for matching the frequency of other in-plane or

out of plane vibration mode pairs and thus cannot be used to provide a gyroscope for sensing rate on at least two axes.
US-A-3206985 discloses apparatus for simultaneously sensing movement of a body around a plurality of mutually perpendicular axes. The apparatus includes a piezo-ceramic toroid or ring structure 13 made up of a ring like driven member 14 mounted internally of the ring on a resilient support 15 and mounted externally of the ring on beam-like bymorphic sensor elements 2 7 bonded to the outer peripheral surface of the ring 14 . The ring 14 vibrates in an extensional or breathing type mode which modules the outer diameter thereof such that when rate is applied about any axis the sensor elements 27 experience Coriolis forces which excite them into resonate motion. The signals from these sensor elements 27 may be interpreted to give rate sensitivity about three axes. There is no use of flexural modes of vibration within a single monolithic ring structure to sense rate on at least two axes.
A vibrating structure gyro incorporating a resonator design which is inherently capable of sensing around three axes simultaneously would therefore be of great benefit. A single device would thus replace three conventional single axis units with obvious cost benefits. Also, the process of mounting and aligning the three single axis gyros would not be required.
There is thus a need for an improved gyroscope which can sense rate on at least two axes.

According to a first aspect of the present invention there is provided a gyroscope for sensing rate on at least two axes, including a substantially planar vibratory resonator having a substantially ring or hoop¬like shape structure with inner and outer peripheries extending around a common axis, characterised by
including carrier mode drive means for causing the resonator to vibrate in a Cosn1θ in-plane carrier mode,
where n1 has an integer value of 2 or more, support means
for flexibly supporting the resonator and for allowing
the resonator to vibrate, in response to the carrier mode
drive means, relative to the support means, carrier mode
pick-off means for sensing in-plane movement of the
resonator, X axis response mode pick-off means for
sensing out-of-plane Cosnθ response mode movement of the
resonator in respect to rotation of the gyroscope around the X axis, where n has a value of n1 + l or n1-1, and Y
axis response mode pick off means for sensing out-of-
plane Sinnθ response mode movement of the resonator in
respect to rotation of the gyroscope about the Y axis, where n has a value of n]_ + l or n^-1, identical to that
for the X axis response mode.
Preferably the gyroscope includes X axis response mode drive means for nulling the X axis response mode movement of the resonator to permit the gyroscope to be operated in a forced feedback configuration.
Conveniently the gyroscope includes Y axis response mode drive means for nulling the Y axis response mode

movement of the resonator to permit the gyroscope to be
operated in a forced feed back configuration.
Advantageously for sensing rate about two axes the
support means includes a plurality of flexible legs
flexibly connecting the resonator to a support, with the number of legs NT being given by Np=4n and with the
angular separation between the legs being given by 360°/NT.
Preferably for sensing rate about three axes the
gyroscope includes Z axis response mode pick off means for sensing in-plane Sin n1θ response mode movement of
the resonator in respect to rotation of the gyroscope around the Z axis, where n1θ has an integer value of 2 or
more, identical to that for the in-plane carrier mode.
Conveniently the gyroscope for sensing rate about three axes includes Z axis response mode drive means for nulling the Z axis response mode movement of the resonator to permit the gyroscope to be operated in a forced feedback configuration.
Advantageously the support means includes a
plurality of flexible legs flexibly connecting the resonator to a support, with the number of legs NT being
given by Np=4nni and with the angular separation between
the legs being given by 360°/Np.
Preferably in a gyroscope of the present invention for sensing rate about two axes the carrier mode is an in-plane Cos2θ mode, with the carrier mode drive means including two drive elements, for initiating the carrier mode motion, located at 0° and 180° with respect to a

fixed reference axis in the plane of the resonator, with the carrier mode pick off means including two pick off elements, for detecting the carrier mode motion, located at 90° and 270° with respect to the fixed reference axis, wherein the X axis response mode is a Cos 36 mode, with the X axis pick off means including three pick off elements located at 0°, 120°, and 240° with respect to the fixed reference axis, with the X axis drive means including three drive 'elements located at 60°, 180° and 3 00° with respect to the fixed reference axis, and wherein the Y axis response mode is a Sin 39 mode, with the Y axis pick off means including three pick off elements located at 30°, 150° and 270° with respect to the fixed reference axis and with the Y axis drive means including three drive elements located at 90°, 210° and 330° with respect to the fixed reference axis, which X and Y axis drive and pick off elements are operable to detect and nullify the response mode motions.
Alternatively the carrier mode is an in-plane Cos 39 mode, with the carrier mode drive means including three drive elements located at 0°, 120^ and 240° with respect to a fixed reference axis in the plane of the resonator, with the carrier mode pick off means including three pick off elements located at 60°, 180° and 300° with respect to the fixed reference axis, wherein the X axis response mode is a Cos 29 mode, with the X axis pick off means including two pick off elements located at 0° and 180° with respect to the fixed reference axis, with the X axis drive means including two drive elements located at 90°

and 270° with respect to the fixed reference axis, and wherein the Y axis response mode is a Sin 2θ mode, with the Y axis pick off means including two pick off elements located at 45° and 225° with respect to the fixed reference axis and with the Y axis drive means including two drive elements located at 135° and 315° with respect to the fixed reference axis.
Conveniently the carrier mode is an in-plane Cos 36 mode, with the carrier mode drive means including three drive elements located at 0°, 120° and 240° with respect to a fixed reference axis in the plane of the resonator, with the carrier mode pick off means including three pick off elements located at 60°, 180° and 300° with respect to the fixed reference axis, wherein the X axis response mode is a Cos 46 mode, with the X axis pick off means including four pick off elements located at 0°, 90°, 180° and 270° with respect to the fixed reference axis, with the X axis drive means including four drive elements located at 45°, 135°, 225° and 315° with respect to the fixed reference axis and wherein the Y axis response mode is a Sin 49 mode, with the Y axis pick off means including four pick off elements located at 22.5°, 112.5° and 292.5° with respect to the fixed reference axis, and with the Y axis drive means including four drive elements located at 67.5°, 157.5°, 247.5° and 337.5° with respect to the fixed reference axis.
Advantageously a gyroscope for sensing rate of three axes, includes Z axis response mode pick off means for sensing in-plane Sin 2θ response mode movement of the

resonator, which Z axis pick off means includes two pick off elements located at 45° and 225° with respect to the fixed reference axis, and including Z axis response mode drive means having two drive elements located at 135° and 315° with respect to the fixed reference axis.
Preferably a gyroscope for sensing rate on three axes, includes Z axis response mode pick off means for sensing in-plane Sin 39 response mode movement of the resonator, which Z axis pick off means includes three pick off elements located at 90°, 210° and 330° with respect to the fixed reference axis, and including Z axis response mode drive means having three drive elements located at 30°, 150° and 270° with respect to the fixed reference axis.
Advantageously the resonator is made from metal, quartz, polysilicon or bulk silicon.
Advantageously the drive means and the pick off means are electrostatic, electromagnetic, piezoelectric or optical.
For a better understanding of the present invention, and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings in which:
Figure la is a schematic diagram of a vibrating structure gyroscope not according to the present invention,
Figure lb shows the three orthogonal axes along which the velocity, rotation and force vectors lie with the structure of Figure la,

Figures 2a and 2b show graphically the shapes of mode pairs exhibiting Cosn1θ and Sinn1θ radial
displacements for n1=2,
Figures 3a and 3b are graphical shapes similar to
those of Figures 2a and 2b for n=3,
Figures 4a and 4b are graphical shapes similar to
those of Figures 2a and 2b and Figures 3a and 3b but for n]_=4,
Figures 5a and 5b are graphical representations on three axes for the force components generated by a rotation of a gyroscope according to the present invention about the Y axis, for a Cos29 in-plane carrier mode.
Figures 6a and 6b are similar graphical representations to those of Figures 5a and 5b but representing rotation about the X axis,
Figures 7a and 7b are graphical representations on three axes of the vibration mode shapes exhibiting Cosn0 and Sinn6 out-of-plane displacements for n=l,
Figures 8a and 8b are graphical representations similar to those of Figures 7a and 7b but for n=2,
Figures 9a and 9b are graphical representations similar to those of Figures 8a and 8b but for n=3,
Figures 10a and 10b are graphical representations similar to those of Figures 9a and 9b but for n=4,
Figure 11a shows in plan view a diagrammatic example of a resonator and support legs suitable for use in a gyroscope according to the present invention,

Figure 11b shows in plan view a further resonator and support leg structure for use with a gyroscope according to the present invention,
Figure 12 is a schematic diagram in plan view of part of a gyroscope according to a first embodiment of the present invention showing drive and pick off elements,
Figure 13 is a cross sectional view on a diagonal of the structure of Figure 12 showing additional detail,
Figure 14 is a schematic plan view of part of a gyroscope according to a second embodiment of the present invention,
Figure 15 is a diagrammatic plan view of part of a gyroscope according to a third embodiment of the present invention,
Figure 16 is a diagrammatic plan view of part of a gyroscope according to a fourth embodiment of the present invention,
Figure 17 is a diagrammatic plan view of part of a gyroscope according to a fifth embodiment of the present invention and,
Figure 18 is a diagrammatic plan view of part of a gyroscope according to a sixth embodiment of the present invention.
A common feature of all conventional vibrating
structure gyro designs is that they maintain a resonant
carrier mode oscillation. This provides the linear momentum which produces the Coriolis force Fc, when the

gyro is rotated around the appropriate axis. The magnitude of this force is given by:
Fc = 2 m v . . (1)
where is the applied rate, m is the mass and v the linear velocity. The velocity, rotation and force vectors lie along mutually orthogonal axes as shown in Figures la and lb of the accompanying drawings.
One of the simplest implementations for a vibrating structure gyro is a beam 1 shown in Figure la. The carrier mode vibration is a bending motion in the xz-plane as shown in Figures la and lb. A rotation applied about the axis of the beam 1 (z-axis) will generate Coriolis forces which set the beam 1 into motion in the yz-plane, at the carrier frequency. The amplitude of motion in this axis will be proportional to the applied rotation rate. The sensitivity of such a device may be enhanced by designing the structure such that the Coriolis force directly excites a resonant mode. The amplitude of motion is then amplified by the Q of the response mode. For a simple beam made of isotropic material this will be achieved using a beam of square cross-section where the X and Y dimensions are matched. A rotation about the Y-axis will also induce Coriolis forces in the beam 1. These will act along the length of the beam (z-axis) . The beam is extremely stiff in this direction and is therefore insensitive to these forces. However this simple linear vibration along a

single axis is able to respond to rotations around two
axes. Implementation of a practical gyroscope based on
these responses requires a resonator design that enables
these Coriolis force components to couple directly into
response modes along the appropriate axes.
In order to produce a gyroscope capable of sensing
rate along three axes the carrier mode motion must
contain velocity components along two orthogonal axes.
The structure must also be designed such that the
Coriolis forces induced as a result of rotation about
each axis couple into response modes whose resonant
frequency may be matched to that of the carrier. Planar ring structures utilising Cosn1θ in-plane carrier modes
(where 0 is the angular location around the ring circumference relative to a fixed datum and n1 has a
fixed integer value of 2 or more, are particularly suited to this application. The n1 = l mode is not a suitable
carrier as it is a rigid body translation of a ring resonator and thus only has velocity components along a
single axis.
For perfect ring resonator structures the Cosn1θ in-
plane vibration modes exist as degenerate pairs at a
mutual angle of (90/n1°. The 0=0° reference axis R for
the modal diagrams is along the Y-axis in the positive
direction. Using this fixed reference the mode pairs will have shapes exhibiting Cosn1θ and Sinn1θ radial
displacements. The mode shapes for n1 = 2 are shown in
Figures 2a and 2b. The two extremes of maximum displacement from the unexcited ring position, during a

-single vibration cycle, are shown for each mode of the
pair. The axes indicate the displacement from the
unexcited ring position for a ring of radius 1.0
(arbitrary units). The modes exist at a mutual angle of 45°. The mode shapes for n1 = 3 are similarly shown in
Figures 3a and 3b. These exist at a mutual angle of 30°. The corresponding shapes for the n1=4 modes are shown in
Figures 4a and 4b and exist at a mutual angle of 22.5o.
Vibrating structure gyro designs using ring
structures, capable of sensing rate about a single axis, are well known. These use one of the in-plane Cosn1θ
mode pair (typically n1=2) as the carrier. A rotation
about the axis normal to the plane of the ring (z-axis)
couples energy into the second mode of the pair with the
induced amplitude of motion being proportional to the
applied rate.
Using these carrier modes, rotations about axes in
the plane of the ring will also give rise to Coriolis
forces. These will act along the z-axis and will tend to
set the ring into out-of-plane motion. The distribution
of these forces will vary with angular position 0 and, for rotation about the Y-axis, y, will be given by:
... (2)
The parameters Fn^ + l and Fn]-1 are constants which
depend on the precise geometry of the ring and the support means, the material and the value of n1. The
out-of-plane Coriolis force thus has components which vary as Sin(n] + 1)θ and Sin(n]_-1)θ. For the same carrier

mode, a rotation about the X-axis will induce Coriolis forces given by:
... (3)
The out-of-plane Coriolis force in this instance has components varying as Cos(n1+l)θ and Cos(n1-l)θ. By way
of example, for the case where the carrier is the Cos2θ in-plane mode shown in Figure 2a, a rotation about the Y-axis will generate force components which vary as Sinθ and sin3θ. These are shown in Figures 5a and 5b, respectively. A rotation about the X-axis will generate components which vary as Cosθ and cos3θ. These are shown in Figures 6a and 6b.
The z-axis displacement of the out-of-plane modes will also exhibit a Cosnθ angular dependence and, like the in-plane modes these exist as degenerate pairs at a mutual angle of (90/n)°. The mode shapes for n=l exist at a mutual angle of 90° (i.e. Sinθ and Cosθ radial displacements) and are shown in Figures 7a and 7b. As with the previous modal diagrams, the two extremes of motion are shown with the rest position of the ring indicated by the broken lines. The corresponding plots for the n=2, 3 and 4 modes are shown in Figures 8a, 8b, 9a, 9b, 10a and 10b.
The functional forms of the Coriolis force components shown in Figures 5a and 6a precisely match those of the n=l out-of-plane mode shown in Figures 7a and 7b. Similarly, the forms of the Coriolis force

components shown in Figures 5b and 6b precisely match
those of the n=3 out-of-plane modes shown in Figures 9a
and 9b. Clearly, these modes may be directly excited as
a result of the rotation induced Coriolis forces.
Examination of equations 2 and 3 indicates that any Cosn1θ in-plane carrier mode can couple into Cos (n1 + l)0,
Sin(n]_ + 1)θ, Cos(n]_-l) and Sin(ni-1)θ out-of-plane modes
when rotated around the appropriate axis. To be of practical use in any gyro configuration, the amplitude of motion generated must be as large as possible to maximise the gyro sensitivity. This is achieved by matching the mode frequencies of the carrier and a chosen pair out-of-plane response modes. The resultant motion is thus amplified by the Q of the response mode vibration. The in-plane mode frequencies are not affected by changing the depth (ie z-axis dimension) of the ring. The out-of-plane mode frequencies are directly sensitive to this parameter and may therefore be independently adjusted. By judicious control of the dimensions of the ring resonator and support structure it is possible to match the Cosn1θ in-plane carrier frequency with either the
Cos(n1 + 1)θ and Sin(n]_ + 1)θ or the Cos(n1-1)θ and Sin(n1-1)θ
out-of-plane modes. It is therefore possible to design multi-axis gyro schemes using a variety of carrier and response mode combinations.
The Cos20 carrier mode can couple into the Sin0, Cos0, Sin30 and Cos30 out-of-plane response modes. These are shown in Figures 7a, 7b, 9a and 9b respectively. The use of the Cos20 carrier in combination with the Sin30

and Cos36 response modes according to the present invention is capable of being implemented as a three axis rate sensor.
The resonator in a vibrating structure gyro preferably is substantially planar having a ring or hoop like shape resonator structure 2 with inner and outer peripheries extending around a common axis A normal to a fixed reference axis R in the plane of the resonator structure 2, which axis R extends in the direction of the Y axis. The ring structure is supported by support means including a plurality of compliant support legs 3. When driven in a Cos20 carrier mode both the ring and support legs are in motion. However, the ring 2 is very stiff in comparison to the support legs 3 and the carrier frequency is predominantly set by the ring dimensions. This effectively isolates the resonator from the mounting and reduces environmental sensitivity.
The Sinθ and Cosθ out-of-plane modes (Figures 7a and 7b) will involve significant deflection and stress in the support legs 3 with insignificant distortion of the ring 2. Due to the compliance of the legs this Cosθ mode naturally occurs at a significantly lower frequency than the Cos2θ carrier. The Sin3θ and Cos3θ response modes (Figures 9a and 9b) distort and stress the ring significantly. Its natural mode frequency will therefore be significantly higher than that of the Cosθ mode. The Cos 2θ carrier and the Sin3θ and Cos3θ response mode frequencies may thus be matched with considerably less adjustment of the leg to ring stiffness ratio. This

helps to maintain the environmental capability of the gyroscope.
When using the out-of-plane Cosθ response modes, the legs 3 will always transmit a non-zero torque to the support structure as the ring 2 rocks about the input rotation axis. In contrast, the out-of-plane Sin30 and Cos39 response mode will not transmit any net reaction force to the support structure if an appropriate number of legs are used. This will be true for all Cosnθ modes where n>l.
Practical gyroscopes of the present invention may be constructed using higher order in-plane carrier modes. The Cos3θ in-plane mode (Figure 3b) may be used as the carrier in conjunction with either the Cos2θ and Sin2θ or the Cos4θ and Sin4θ out-of-plane response modes. These response modes are shown in Figures 8a, 8b, 10a and 10b respectively. The Cos4θ carrier (Figure 4a) will couple into the Sin 3θ, Cos3θ, Sin5θ and Cos5θ response modes. Corresponding combinations of higher order are also feasible. In practice, however, the higher order mode combinations become increasingly onerous to implement. The mode shapes become progressively more complex and require a larger number of discrete drive and pick off elements to excite and sense the vibrations. Also, the support legs 3 act as point spring masses which perturb the mode frequencies. The number and location of these legs need to be matched to the mode symmetry to avoid induced splitting of the degenerate mode frequencies. The number of legs required increases rapidly with the

mode order thus rendering some designs impractical on a small size gyroscope.
A three axis gyroscope according to the present invention may be constructed by using a combination of Sin20 and Cos26 in-plane and the Sin30 and Cos38 out-of -plane' modes. This gyroscope requires the frequencies of four modes to be matched (one carrier plus three response modes). However, for a perfectly symmetric ring 2 of uniform thickness, the Sin26 and Cos20 mode pair will have identical frequencies. Similarly, the Sin30 and Cos3G mode pair will also be matched. Therefore, due to the high degree of symmetry, the design of the resonator dimensions is, in practice, reduced to an exercise in matching only two frequencies (ie those of the two degenerate mode pairs). For the dimensions commonly used in ring resonators designed for single axis operation the Cos39 out-of-plane and Cos20 carrier mode frequencies naturally occur relatively closely matched in frequency. Adjusting the depth (z-axis dimension) of the ring does not alter the in-plane frequencies. It does, however, have a distinct affect of the out-of-plane frequencies. Matching the Sin2θ, Cos2θ, Sin3θ and Cos30 mode frequencies may therefore be achieved by appropriate adjustment of a single ring dimension.
In terms of the mode dynamics, the support legs 3 appear as point spring masses acting at the point of attachment which differentially perturb the mode frequencies. In order to prevent frequency splitting and maintain the positional indeterminacy of the modes, the

number and location of the legs must be matched to the mode symmetry. For any Sinn1θ and Cosn1θ mode pair this necessitates the use of 4n1 equi-angularly spaced legs (where n1 is 2 or more) . The Sin29 and Cos2G in-plane modes therefore require 8 equally spaced legs. The Sin39 and Cos39 out-of-plane modes require 12 legs to maintain their indeterminacy. To satisfy this requirement simultaneously for both mode pairs implies the use of 24 legs equally spaced at 15° intervals around the ring 2. This number is the lowest common multiple of the in-plane and out-of-plane leg numbers and may be derived for any three axis gyro mode combination from the following expression:
Number of legs NT= nxn1x4 ... (4)
The angular spacing of these legs is given by [360/NT]°.
For planar ring resonator structures the support legs 3 are designed such that the modal behaviour is dominated by the ring characteristics. This requires the legs to be radially and tangentially compliant, in comparison to the ring itself. Many design variations are possible which achieve these requirements. Figures lla and l1b show two possibilities for the twenty-four support leg structure of one embodiment of the present invention. These designs are consistent with the use of larger numbers of support legs 3.
Vibrating structure gyroscopes of the invention may be constructed using standard fabrication and machining

techniques. They are also suitable for fabrication using micro-machining techniques. The principle of operation and drive and pick off orientations will be identical regardless of the fabrication route. The resonator may be constructed from any material possessing suitable mechanical properties including metal, quartz, polysilicon or bulk silicon. The ring 2 may be driven into oscillation using a variety of drive means. These include electrostatic, electromagnetic, piezo or optical means. The amplitude of motion may similarly be detected using electrostatic, electromagnetic, piezo or optical pick off means.
The preferred three axis gyroscope embodiment uses electrostatic drive and pick off means. The orientation of drive and pick off elements for this embodiment is shown in Figure 12. The location of the ring 2 is indicated by the dashed lines. The in-plane Cos26 carrier mode is driven into oscillation using drive elements 4 whose effective centres are located at oO and 180° around the outer periphery of the ring 2 with respect to the fixed reference axis R. For each element, the surface normal to the plane of the ring 2 facing the ring circumference forms one plate of the capacitor with the facing segment of the ring circumference forming the other plate. The ring 2 is maintained at a fixed potential with respect to the drive elements 4. An oscillating voltage applied to the drive element plates at the carrier mode frequency will generate an electrostatic force setting the ring 2 into

oscillation. Pick off elements 5, for the carrier mode located at 90° and 270°with respect to the fixed reference axis R, similarly form capacitors with the facing ring segments and are used to detect the motion of the ring 2 as the capacitor gap varies. Pick off elements 6 located at 45° and 225° with respect to the axis R detect the amplitude of the in-plane Sin29 response mode when the gyroscope is rotated around the z-axis. Z axis drive elements 7 located at 135° and 315° with respect to the axis R, may be used to null the mode movement to allow the gyroscope to operate in a forced feedback configuration. When operated in this mode the nulling drive is proportional to the applied rate. This mode of operation provides performance advantages over the open loop mode.
The Cos30 out-of-plane response mode providing the X-axis rate sensitivity will have anti-nodes at 0°, 60°, 120°, 180°, 240° and 300° locations, with respect to the axis R, around the ring circumference. The sin36 Y-axis response mode will have anti-nodes at 30°, 90°, 150°, 210°, 270° and 330° with respect to the axis R. Drive and pick off elements may be located at any appropriate combinations adjacent to these points. Conveniently, twelve plate like elements are positioned directly under the rim to form capacitors between said plates and the parallel facing segments of the bottom surface of the ring. Conveniently, the plates should extend beyond the inner and outer edges of the ring rim. The in-plane motion of the carrier mode will not therefore change the

effective plate area and will not be inadvertently detected by these plate like elements. Elements 8 located at 0°, 120° and 240° are used as X-axis pick off elements. The signals from these elements will be in phase and may be conveniently summed together to give enhanced sensitivity in detecting the mode movement. Plate like elements 9 located at 60°, 180° and 300° with respect to the axis R are used as drive elements with the same drive voltage being applied to all these elements to null the motion to facilitate force feedback operation. Similarly, plate like elements 10 located at 30°, 150° and 270o with respect to the axis R are the Y-axis pick off elements with plate like elements 11 located at 90°, 210° and 330°, with respect to the axis R forming the drive elements for that mode.
Figure 13 shows a cross-section view through the centre of the resonator ring 2 along the Y-axis showing additional detail of the device architecture. The X and Y axis drive and pick off elements are conductive sites laid onto the surface of an electrically insulating substrate layer 12. These element sites are connected via tracks to bond pads (not shown) which can be electrically connected to the control circuitry. The ring 2 is attached, via the support legs 3, to a central support pedestal 13. This pedestal extends beneath the ring 2 and attaches rigidly to the substrate layer 12 such that the ring and support legs are freely suspended above the substrate layer. The in-plane mode drives and pick off elements are rigidly attached to the substrate

12 with tracking and bond pads provided as require to
enable connection to the control circuitry.
Modifications to this structure are possible. The
addition of a second insulating substrate layer rigidly
fixed above the resonator ring 2, duplicating the out-of-
plane drive and pick off element capacitor plate array,
would enhance the sensitivity of the gyroscope along the
X and Y axes. This would, however, complicate the
fabrication process and would not alter the essential
design features or functionality of the gyroscope.
A two axis gyroscope according to the present
invention may be fabricated using the same Cos2G in-plane
carrier mode and Sin3θ and Cos3θ out-of-plane response
modes. For this embodiment the resonator design is such
that the in-plane Sin2θ and Cos2θ mode frequencies are
deliberately separated. Advantageously, this frequency
split will fix the carrier mode position at a known
angular location which may be aligned to the carrier mode
drive and pick off means. The carrier mode frequency
must still be matched to that of the out-of-plane
response modes. If twelve support legs 3 are used then
the symmetry of the Cos 3θ modes is maintained. This
will, however, generate a splitting of the in-plane Sin2G
and Cos26 modes and thus fix the mode positions as
required. Generally, for two axis gyroscope operation
the required number of support legs is given by the
following expression:
Number of legs N-p = nx4 ... (5)
The angular spacing is [360/NT]°.

This implementation will provide rate sensitivity about the X and Y axes only. The in-plane response mode drive and pick off means are thus not required. Figure 14 shows a schematic of the gyroscope layout for this embodiment. This is essentially the same as the three axis embodiment of Figures 12 and 13, with the exception of the absence of the Z axis in-plane response mode drive elements 7 and pick off elements 6 and the different number of support legs, and hence like reference numerals have been used. No further description will therefore be given.
A two or three axis gyroscope may be fabricated using Sin30 and Cos30 in-plane modes in conjunction with sin20 and Cos20 out-of-plane response modes. For the three axis embodiment the degeneracy of both the in-plane sin39 and Cos30 and out-of-plane Sin20 and Cos28 mode pairs must be maintained. This dictates the use of twenty-four support legs 3 on the resonator ring 2. A schematic of the orientation of the drive and pickoff elements is shown in Figure 15. The topology of the gyroscope is largely identical to the previously described embodiments with the exception of the drive and pick off element layout. The Cos30 in-plane carrier drive means elements 14 are located at 0°, 120° and 240° with respect to the fixed reference axis R with the pick off means elements 15 located at 60°, 180° and 300° with respect to the axis R. The Z axis sin30 in-plane response mode drive elements 16 are located at 30°, 150° and 270° with respect to the axis R with the pick off

Elements. 17 at 90°, 210° and 330° with respect to the axis R. The out-of-plane Cos20 X axis response mode pick off elements 18 are located at 0° and 180° with the nulling drive elements 19 at 90° and 270° with respect to the axis R. The Y axis out-of-plane Sin2G pick off elements 20 are located at 45° and 225° with respect to the axis R with the nulling Y axis drive elements 21 at 135° and 315° with respect to the axis R.
The two axis embodiment of this Cos39 in-plane carrier and out-of-plane Sin20 and Cos26 response mode combination requires the in-plane mode degeneracy to be lifted. This may be achieved by the use of eight support legs. Otherwise, this embodiment differs from the three axis one only in the omission of the in-plane response mode drive elements 16 and pick off elements 17. The drive and pick off means layout is shown in Figure 16.
A two or three axis gyroscope of the invention may be fabricated using a Sin36 and Cos30 in-plane and a Sin40 and Cos40 out-of-plane mode combination. The three axis embodiment requires the use of forty-eight support legs 3 to maintain all the appropriate mode symmetries. This embodiment is shown schematically in Figure 17. The Cos30 in-plane carrier mode drives 22 are located at 0°, 120° and 240° with respect to the fixed reference axis R with the pick off elements 23 at 60°, 180° and 300° with respect to the axis R. The in-plane Z axis Sin30 response mode drive elements 24 are located at 30°, 150° and 270° with respect to the axis R with the z axis Cos30

Methodein-plane pick off elements 25 at 90°, 210° and 300° with respect to the axis R.
The X axis Cos4θ out-of-plane response mode pick off elements 26 are located at 0°, 90°, 180° and 270° with respect to the fixed reference axis R, with X axis Cos46 out-of-plane response mode nulling drive elements 27 at 45°, 135°, 225° and 315° with respect to the axis R. The Y axis Sin4G out-of-plane response mode pick off elements 28 are located at 22.5°, 112.5° 202.5° and 292.5° with respect to the axis R with Y axis Sin40 out-of-plane response mode nulling drive elements 29 at 67.5°, 157.5°, 247.5° and 337.5° with respect to the axis R.
The corresponding two axis gyroscope embodiment of the invention requires sixteen support legs 3. The layout for this embodiment, shown in Figure 18, is otherwise identical to the three axis one of Figure 17 with the exception of the omission of the z axis in-plane response mode drive elements 24 and pick off elements 25. Like parts have been given like numbers to those of Figure 17 and will not be further described.
Two and three axis rate sensors may be fabricated using higher order in-plane and out-of-plane mode combinations. These will require progressively higher numbers of support legs to maintain the necessary mode symmetries and a larger number of drive and pick off elements. As a result of this these embodiments, while feasible, become progressively more complicated to fabricate, particularly in a small size gyroscope.

Additonally in a gyroscope of the invention for
sensing rate about two axes, the resonator 2 and support means are dimensioned so that the Cosn1θ in-plane carrier
mode and SinnG and Cosnθ out-of-plane response mode
frequencies are matched, and for sensing rate about three axes the dimensions are such that the Cosn1θ in-plane
carrier mode, Sinn10in-plane response mode and SinnG
and CosnG out-of-plane response mode frequencies are
matched.

We claim:
1. A gyroscope for sensing rate on at least two axes, comprising a
substantially planner vibratory resonator (2) having a
substantially ring or hoop-like shape structure with inner and
outer peripheries extending around a common axis,
characterised by comprising carrier mode drive means (4, 14,
22) for causing the resonator (2) to vibrate in a Cosn1θ in-plane
carrier mode, where m has an integer value of 2 or more,
support means (3) for flexibly supporting the resonator (2) and
for allowing the resonator (2) to vibrate, in response to the
carrier mode drive means (4, 14, 12), relative to the support
means (3), carrier mode pick-off means (5, 15, 23) for sensing
in-plane movement of the resonator (2), X axis response mode
pick-off means (8, 18, 26) for sensing out-of-plane CosnB
response mode movement of the resonator (2) in respect to
rotation of the gyroscope around the X axis, where n has a
value of ni+1 or m-1, and Y axis response mode pick-off means
(10, 20, 28) for sensing out-of-plane Sinnθ response mode
movement of the resonator (2) in response to rotation of the
gyroscope about the Y axis, where n has a value of m+1 or m-1,
identical to that for the X axis response mode.
2. A gyroscope as claimed in claim 1, comprising X axis response
mode drive means (9, 19, 27) for nulling the X axis response
mode movement of the resonator (2) to permit the gyroscope to
be operated in a forced feedback configuration.
3. A gyroscope as claimed in claim 1 or 2, comprising Y axis
response mode drive means (11, 21, 29) for nulling the Y axis
response mode movement of the resonator (2) to permit the
gyroscope to be operated in a forced feed-back configuration.
4. A gyroscope as claimed in anyone of the claims 1 to 3, wherein
for sensing rate about two axes the support means comprises a

plurality of flexible legs (3) flexibly connecting the resonator (2) to a support (13), with the number of legs NT being given by NT=4n and with the angular separation between the legs (3) being given by 360°/NT.
A gyroscope as claimed in anyone of claims 1 to 3, for sensing rate about three axes, comprising Z axis response mode pick off means (6, 17, 25) for sensing in-plane Sin m0 response mode movement of the resonator (2) in respect to rotation of the gyroscope around the Z axis, where m has an integer value of 2 or more, identical to that for the in-plane carrier mode. A gyroscope as claimed in claim 5, comprising Z axis response mode drive means (7, 16, 24) for nulling the Z axis response mode movement of the resonator (2) to permit the gyroscope to be operated in a forced feedback configuration. A gyroscope as claimed in claim 5 or 6, wherein the support means comprises a plurality of flexible legs (3) flexibly connecting the resonator to a support (13), with the number of legs NT being given by NT=4nni and with the angular separation between the legs (3) being given by 360°/NT. A gyroscope as claimed in claims 1, 2, 3 or 4, for sensing rate about two axes, wherein the carrier mode is an in-plane Cos26 mode, with the carrier mode drive means comprising two drive elements (4) for initiating the carrier mode motion, located at 0° and 180° with respect to a fixed reference axis (R) in the plane of the resonator (2), with the carrier mode pick-off means comprising two pick-off elements (5), for detecting the carrier mode motion, located at 90° and 270° with respect to the fixed reference axis (R), wherein the X axis response mode is Cos 36 mode, with the X axis pick-off means comprising three pick-off elements (8) located at 0°, 120° and 240° with respect to the fixed reference axis (R), with the X axis drive means comprising three drive elements (9) located at 60°, 180° and 300° with

respect to the fixed reference axis (R), and wherein the Y axis response mode is a Sin 30 mode, with the Y axis pick-off means comprising three pick-off elements (10) located at 30°, 150° and 270° with respect to the fixed reference axis (R) and with the Y axis drive means comprising three drive elements (11) located at 90°, 210° and 330° with respect to the fixed reference axis, which X and Y axis drive and pick-off elements (8, 9, 10, 11) are operable to detect and nullify the response mode motions. A gyroscope as claimed in claims 1, 2, 3 or 4, wherein the carrier mode is an in-plane Cos 30 mode, with the carrier mode drive means comprising three drive elements (14) located at 0°, 120° and 240° with respect to a fixed reference axis in the plane of the resonator (2), with the carrier mode pick-off means comprising three pick-off elements (15) located at 60°, 180° and 300° with respect to the fixed reference axis (R), wherein the X axis response mode is a Cos 20 mode, with the X axis pick-off means comprising two pick-off elements (18) located at 0° and 180° with respect to the fixed reference axis (R), with the X axis drive means comprising two drive elements (19) located at 90° and 270° with respect to the fixed reference axis (R), and wherein the Y axis response mode is a Sin 20 mode, with the Y axis pick-off means comprising two pick-off elements (20) located at 45° and 225° with respect to the fixed reference axis (R) and with the Y axis drive means comprising two drive elements (21) located at 135° and 315° with respect to the fixed reference axis (R).
A gyroscope as claimed in claims 1, 2, 3 or 4, wherein the carrier mode is an in-plane Cos 30 mode, with the carrier mode drive means comprising three drive elements (22) located at 0°, 120° and 240° with respect to a fixed reference axis (R) in the plane of the resonator (2), with the carrier mode pick-off means comprising three pick-off elements (23) located at 60°, 180° and

300° with respect to the fixed reference axis (R), wherein the X axis response mode is a Cos 49 mode with the X axis pick-off means comprising four pick-off elements (26) located at 0°, 90°, 180° and 270° with respect to the fixed reference axis (R), with the X axis drive means comprising four drive elements (27) located at 45°, 135°, 225° and 315° with respect to the fixed reference axis (R) and wherein the Y axis response mode is a Sin 40 mode, with the Y axis pick-off means comprising four pick-off elements (28) located at 22.5°, 112.5° and 292.5° with respect to the fixed reference axis (R) and with the Y axis drive means comprising four drive elements (29) located at 67.5°, 157.5°, 247.5° and 337.5° with respect to the fixed reference axis (R).
A gyroscope as claimed in claim 8, for sensing rate of three axes, comprise Z axis response mode pick-off means for sensing in-plane Sin 26 response mode movement of the resonator (2), which Z axis pick-off means comprises two pick-off elements (6) located at 45° and 225° with respect to the fixed reference axis (R) and comprising Z axis response mode drive means having two drive elements (7) located at 135° and 315° with respect to the fixed reference axis (R).
A gyroscope as claimed in claim 9 or 10, for sensing rate on three axis comprises Z axis response mode pick-off means for sensing in-plane Sin 30 response mode movement of the resonator, which Z axis pick-off means comprises three pick-off elements (17) located at 90°, 210° and 330° with respect to the fixed reference axis (R), and comprising Z axis response mode drive means having three drive elements (16) located at 30°, 150° and 270° with respect to the fixed reference axis (R). A gyroscope as claimed in any one of claims 1 to 12, wherein the resonator (2) is made from metal quartz, polysilicon or bulk silicon.

14. A gyroscope as claimed in any one of claims 1 to 13, wherein the drive means (4) and the pick off means are electrostatic, eletromagnetic, piezoelectric or optical.
Dated this the 22nd day of August, 2000.
(Dr. RAMESH KUMAR MEHTA) OF REMFRY & SAGAR ATTORNEY FOR THE APPLICANTS

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Patent Number

204388

Indian Patent Application Number

IN/PCT/2000/00315/MUM

PG Journal Number

23/2007

Publication Date

08-Jun-2007

Grant Date

19-Feb-2007

Date of Filing

22-Aug-2000

Name of Patentee

BAE SYSTEMS PLC

Applicant Address

WARWICK HOUSE, P.O. BOX 87, FARNBOROUGH AEROSPACE CENTRE, FARNBOROUGH, HAMPSHIRE, GU14 6YU, UNITED KINGDOM,

Inventors:

#	Inventor's Name	Inventor's Address
1	CHRISTOPHER FELL	BRITISH AEROSPACE (SYSTEMS & EQUIPMENT) LIMITED, CLITTAFORD ROAD, SOUTHWAY, PLYMOUTH, DEVON, PL6 6DE, U.K.
2	COLIN HENRY JOHN FOX	UNIVERSITY OF NOTTINGHAM, UNIVERSITY PARK, NOTTINGHAM, NG7 2RD, UNITED KINGDOM

PCT International Classification Number

G 01 C 19/56

PCT International Application Number

PCT/GB99/00722

PCT International Filing date

1999-03-10

PCT Conventions:

#	PCT Application Number	Date of Convention	Priority Country
1	9805388	1998-03-14	U.K.