US20080257038A1 - Gravity Gradiometer - Google Patents

Gravity Gradiometer Download PDF

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Publication number
US20080257038A1
US20080257038A1 US11/722,076 US72207606A US2008257038A1 US 20080257038 A1 US20080257038 A1 US 20080257038A1 US 72207606 A US72207606 A US 72207606A US 2008257038 A1 US2008257038 A1 US 2008257038A1
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Prior art keywords
mount
mounting
bars
housing
bar
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Frank Joachim Van Kann
John Winterflood
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Technological Resources Pty Ltd
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Technological Resources Pty Ltd
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
    • G01V7/00—Measuring gravitational fields or waves; Gravimetric prospecting or detecting
    • G01V7/16—Measuring gravitational fields or waves; Gravimetric prospecting or detecting specially adapted for use on moving platforms, e.g. ship, aircraft

Definitions

  • This invention relates to a gravity gradiometer, and in particular, but not exclusively, to a gravity gradiometer for airborne use.
  • the invention has particular application for measuring diagonal and off-diagonal components of the gravitational gradient tensor.
  • Gravimeters are widely used in geological exploration to measure the first derivatives of the earth's gravitational field. Whilst some advances have been made in developing gravimeters which can measure the first derivatives of the earth's gravitational field because of the difficulty in distinguishing spatial variations of the field from temporal fluctuations of accelerations of a moving vehicle, these measurements can usually be made to sufficient precision for useful exploration only with land-based stationary instruments.
  • Gravity gradiometers are used to measure the second derivative of the gravitational field and use a sensor which is required to measure the differences between gravitational forces down to one part in 10 12 of normal gravity.
  • the gradiometer includes a gimbal bearing arrangement comprised of three concentric rings in which is mounted the sensing equipment.
  • the sensing equipment generally comprises two spaced apart bars respectively located in shielded housings and each mounted on a web bearing.
  • the instrument disclosed in that application is relatively complicated in that it includes a large number of parts and is relatively heavy which is a disadvantage particularly in airborne applications.
  • the invention provides a gravity gradiometer for measuring components of the gravity gradient tensor, comprising:
  • the angular accelerometer is not sensitive to the gravity gradient.
  • the gradiometer is also insensitive to centrifugal force errors and therefore the accelerometer can provide a signal indicative of rotation of the sensor about a predetermined axis so that that rotation can be compensated for.
  • the mass is formed in a housing and coupled to the housing by a flexure web.
  • the mass is formed by a cut through the housing, except for where the mass connects to the housing by the flexure web.
  • the mass is of chevron shape.
  • FIG. 1 is a schematic view of a gradiometer of one embodiment of the invention.
  • FIG. 2 is a perspective view of a first mount forming part of a mounting of the gradiometer of the preferred embodiment
  • FIG. 3 is a view of a second mount of the mounting
  • FIG. 4 is a view from underneath the mount of FIG. 3 ;
  • FIG. 5 is a cross-sectional view along the line IV-IV of FIG. 3 ;
  • FIG. 6 is a cross-sectional view along the line V-V of FIG. 3 ;
  • FIG. 7 is a view of the assembled structure
  • FIG. 8 is a view showing the sensor mounted on the gimbal structure
  • FIG. 9 is a plan view of a bar of the preferred embodiment.
  • FIG. 10 is a diagram showing actuator control
  • FIG. 11 is a block diagram showing operation of the rotatable support system
  • FIG. 12 is a view of a gradiometer of the preferred embodiment
  • FIG. 13 is a view of a first mount of a second embodiment
  • FIG. 14 is a view of part of the mounting of FIG. 13 to illustrate the location and extent of the flexural web of the first mount;
  • FIG. 15 is a view of the mounting of FIG. 13 from beneath;
  • FIG. 16 is a view of the mounting of FIG. 13 including a second mount of the second embodiment
  • FIG. 17 is a cross-sectional view through the assembly shown in FIG. 16 ;
  • FIG. 18 is a view from beneath of the section shown in FIG. 17 ;
  • FIG. 19 is a view from beneath of the second mount of the second embodiment.
  • FIG. 20 is a view of the second mount of FIG. 19 from above;
  • FIG. 21 is an exploded view of the second mount of the second embodiment
  • FIG. 22 is view of the assembled mounting and sensors according to the second embodiment
  • FIG. 23 is a perspective view of the gradiometer with some of the outer vacuum container removed;
  • FIG. 24 is a plan view of a housing for supporting a bar according to a further embodiment of the invention.
  • FIG. 25 is a more detailed view of part of the housing of FIG. 24 ;
  • FIG. 26 is a view of a transducer used in the preferred embodiment.
  • FIG. 27 is a view similar to FIG. 25 but showing the transducer of FIG. 26 in place;
  • FIG. 28 is a diagram to assist explanation of the circuits of FIGS. 29 and 30 ;
  • FIG. 29 is a circuit diagram relating to the preferred embodiment of the invention, particularly showing use of one of the sensors as an angular accelerometer;
  • FIG. 30 is a frequency tuning circuit
  • FIG. 31 is a cross-sectional view through an actuator according to one embodiment of the invention.
  • FIG. 32 is a view of part of the actuator of FIG. 31 ;
  • FIG. 33 is a diagram illustrating balancing of the sensors of the gradiometer of the preferred embodiment.
  • FIG. 34 is a circuit diagram of a calibration sensor used when balancing the gradiometer.
  • FIG. 1 is a schematic view of a gravity gradiometer according to the preferred embodiment of the invention.
  • the gradiometer shown in FIG. 1 comprises a double walled Dewar 1 which is supported in an external platform 2 .
  • the external platform 2 enables adjustment of the Dewar and therefore the contents of the Dewar about three orthogonal axes.
  • the external platform 2 is generally known and its adjustment by suitable motors or the like is also known. Thus, a detailed description will not be provided.
  • a vacuum canister 3 is provided in the Dewar and the Dewar is supplied with liquid gas such as liquid helium He so that the gradiometer can operate at cryogenic temperature.
  • the Dewar 1 is closed by an end plate 4 which includes connectors 5 a for connecting electrical leads (not shown) to external components (not shown).
  • the canister 3 is closed by an end plate 9 which includes connectors 5 b for connecting electric leads (not shown) to the connectors 5 a .
  • the gradiometer has a main casing 61 formed from a twelve-sided ring 62 and hemispherical domes 63 (see FIG. 12 ).
  • An internal mounting 5 is connected to the ring 62 .
  • the ring 62 carries a support 65 to which a feed through flange 9 is coupled.
  • a neck plug 11 formed of baffles 11 a which sandwich foam 11 b is provided above the canister 3 .
  • the baffles 11 a are supported on a hollow rod 93 which extends to the canister 3 and which is also used to evacuate the canister 3 .
  • a first mount 10 of a rotatable mounting 5 ( FIG. 7 ) of the gradiometer which comprises a base 12 and an upstanding peripheral wall 14 .
  • the peripheral wall 14 has a plurality of cut-outs 16 .
  • the base 12 supports a hub 18 .
  • FIGS. 3 and 4 show a second mount 20 which comprises a peripheral wall 22 and a top wall 24 .
  • the peripheral wall 22 has four lugs 13 for connecting the mount to the casing 61 .
  • the top wall 24 and the peripheral wall 22 define an opening 28 .
  • the peripheral wall 22 has a first part 25 , a second part 26 and a third part 27 .
  • the second mount 20 is a monolithic integral structure and the first part 25 is formed by making a circumferential cut 19 through the peripheral wall except for the formation of flexure webs as will be described hereinafter.
  • the third part 27 is formed by making a second circumferential cut 29 through the peripheral wall 22 except for flexure webs which will also be described hereinafter.
  • the second mount 20 is mounted on the first mount 10 by locating the hub 18 into the opening 28 and the lugs 13 through respective cut-outs 16 as is shown in FIG. 7 .
  • the first mount 10 is joined to the second mount 20 .
  • the first flexure web 31 is formed in the first mount 10 so a primary mount portion of the mount 10 can pivot about a web 31 relative to a secondary mount portion of the mount 10 . This will be described in more detail with reference to the second embodiment shown in FIGS. 13 to 21 .
  • the lugs 13 connect the mounting 5 in the canister 3 which, in turn, locates in the Dewar 1 for cryogenic operation of the gradiometer.
  • the Dewar is in turn mounted in a first external platform for course rotational control of the gradiometer about three orthogonal x, y, x axes.
  • the mounting 5 mounts the sensor 40 (which will be described in more detail hereinafter and which is preferably in the form of a mass quadrupole) for much finer rotational adjustment about the x, y and z axes for stabilising the gradiometer during the taking of measurements particularly when the gradiometer is airborne.
  • the first flexure web 31 allows the first mount 10 to move relative to the second mount 20 about a z axis shown in FIG. 7 .
  • FIGS. 5 and 6 are views along the lines IV and V respectively which in turn are along the cuts 19 and 29 shown in FIG. 3 .
  • the peripheral wall 22 may be cut by any suitable cutting instrument such as a wire cutter or the like.
  • FIG. 5 shows the bottom surface 19 a formed by the cut 27 .
  • the cut 27 has two inverted v-shaped peaks 34 .
  • the apex of the peaks 34 is not cut and therefore form a second flexure web 33 which join the first part 25 to the second part 26 .
  • the second part 26 is able to pivotally rotate relative to the first part 25 about the x axis in FIG. 7 .
  • the second cut 29 is shown in FIG. 6 and again the bottom surface 29 a formed by the cut 29 is visible.
  • the second cut 29 forms two v-shaped peaks 35 and the apexes of the peaks 35 are not cut and therefore form a third flexure web 37 which connect the second part 26 to the third part 27 .
  • the third part 27 is able to pivotal rotate about the y axis shown in FIG. 7 .
  • FIG. 8 shows sensor 40 mounted on the mounting.
  • the sensor 40 is an Orthogonal Quadrupole Responder—OQR sensor formed of a first mass and a second mass in the form of a first bar 41 and a second bar 42 (not shown in FIG. 8 ) orthogonal to the bar 41 and which is of the same shape as the bar 41 .
  • OFR Orthogonal Quadrupole Responder
  • the bar 41 is formed in a first housing 45 and the bar 42 is formed in a second housing 47 .
  • the bar 41 and housing 45 is the same as bar 42 and the housing 47 except that one is rotated 90° with respect to the other so that the bars are orthogonal. Hence only the housing 45 will be described.
  • the housing 45 has an end wall 51 and a peripheral side wall 52 a .
  • the end wall 51 is connected to rim 75 ( FIGS. 2 and 7 ) of the wall 14 of the first mount 10 by screws or the like (not shown).
  • the bar 41 is formed by a cut 57 in the wall 51 except for a fourth flexure web 59 which joins the bar 41 to the wall 51 .
  • the flexure web is shown enlarged in the top view of the bar 41 in FIG. 9 .
  • the bar 41 is able to pivot relative to the housing 45 in response to changes in the gravitational field.
  • the bar 42 is mounted in the same way as mentioned above and also can pivot relative to its housing 47 in response to changes in the gravitational field about a fifth flexure web 59 .
  • the housing 47 is connected to base 12 ( FIG. 2 ) of the first mount 10 .
  • the bar 41 and the housing 45 together with the flexure web 59 are an integral monolithic structure.
  • Transducers 71 are provided for measuring the movement of the bars and for producing output signals indicative of the amount of movement and therefore of the measurement of the differences in the gravitational field sensed by the bars.
  • FIG. 10 is a schematic block diagram showing actuator control to stabilise the gradiometer by rotating the mounting 5 about three orthogonal axes (x, y, z).
  • a controller 50 which may be a computer, microprocessor or the like outputs signals to actuators 52 , 53 , 54 and 55 .
  • the actuator 52 could rotate the mounting 5 about the x axis
  • the actuator 54 could rotate the mounting 5 about the y axis
  • the actuator 54 could rotate the mounting 5 about the z axis.
  • two of the four actuators 52 , 53 , 54 and 55 are used to rotate the mounting about each axis so that rotation about each axis is caused by a combination of two linear movements provided from two actuators.
  • each actuator will be described with reference to FIGS. 31 and 32 .
  • the position of the mounting 5 is monitored so that appropriate feedback can be provided to the controller 50 and the appropriate control signals provided to the actuators to rotate the support 10 as is required to stabilise the support during movement through the air either within or towed behind an aircraft.
  • the preferred embodiment also includes angular accelerometers which are similar in shape to the bars 41 and 42 but the shape is adjusted for zero quadrupole moment.
  • the linear accelerometers are simple pendulous devices with a single micro pivot acting as the flexural hinge.
  • FIG. 11 is a view of a feedback control used in the preferred embodiment.
  • FIG. 12 is a cut away view of the gradiometer ready for mounting in the Dewar 1 for cryogenic operation which in turn is to be mounted in the external platform.
  • FIGS. 2 to 8 show the gradiometer with the bars 41 and 42 top and bottom, the instrument is actually turned on its side (90°) so that the bars 41 and 42 are at the ends as is shown in FIG. 12 .
  • FIG. 12 shows the mounting 5 arranged within the casing 61 and formed by the ring 62 and the transparent hemispherical ends 63 .
  • the ring 22 has connectors 69 for connecting the internal wiring from transducers 71 (see FIG. 8 ) and SQUID (Superconducting Quantum Interference Device) Electronics located in the casing 61 to the connectors 5 b ( FIG. 1 ).
  • transducers 71 see FIG. 8
  • SQUID Superconducting Quantum Interference Device
  • the transducers 71 measure the angle of displacement of the bars 41 and 42 and the control circuitry (not shown) is configured to measure the difference between them.
  • Error correction can be performed numerically based on digitised signals from the accelerometers and a temperature sensor.
  • the transducers 71 are SQuID based transducers and the error correction is made possibly by the large dynamic range and linearity of the SQUID based transducers.
  • FIGS. 13 to 21 show a second embodiment in which like parts indicate like components to those previously described.
  • the first mount 10 has cut-outs 80 which effectively form slots for receiving lugs (not shown) which are connected to the mount 10 in the cut-outs 80 and also to the second mount 20 shown in FIGS. 19 to 21 .
  • the lugs are separate components so that they can be made smaller, and more easily, made than being cut with the second mount section 20 which forms the second flexure web 33 and the third flexure web 37 .
  • a cut 87 is made to define the part 18 a of the hub 18 .
  • the cut 87 then extends radially inwardly at 88 and then around central section 18 c as shown by cut 101 .
  • the cut 101 then enters into the central section 18 c along cut lines 18 d and 18 e to define a core 18 f .
  • the core 18 f is connected to the central section 18 c by the flexural web 31 which is an uncut part between the cut lines 18 e and 18 d .
  • the part 10 a therefore forms a primary mount portion of the mount 10 which is separated from a secondary mount portion 10 a of the mount 10 except for where the portion 18 a joins the portion 10 a by the flexural web 31 .
  • the part 18 a effectively forms an axle to allow for rotation of the part 18 a relative to the part 10 a in the z direction about the flexure web 31 .
  • the cut line 88 tapers outwardly from the upper end shown in FIG. 14 to the lower end and the core 18 c tapers outwardly in corresponding shape, as best shown in FIG. 17 .
  • the first mount 10 is octagonal in shape rather than round, as in the previous embodiment.
  • FIGS. 19 to 21 show the second mount 20 .
  • FIG. 16 shows the second mount 20 mounted in the first mount 10 .
  • the second mount 20 has cut-outs 120 which register with the cut-outs 80 for receiving lugs (not shown).
  • the lugs can bolt to the second mount 20 by bolts which pass through the lugs and into bolt holes 121 .
  • the lugs (not shown) are mounted to the mount 20 before the mount 20 is secured to the first mount 10 .
  • the peaks 34 and inverted peaks 35 are flattened rather than of V-shape as in the previous embodiment.
  • top wall 24 is provided with a central hole 137 and two attachment holes 138 a .
  • Three smaller holes 139 a are provided to facilitate pushing of the housing 45 off the part 18 a if disassembly is required.
  • the housings 45 and 47 and their associated bars 41 and 42 are therefore able to move about three orthogonal axes defined by the flexure web 31 , the flexure web 33 and the flexure web 37 .
  • FIG. 21 is an exploded view of the three parts 25 , 26 and 27 which make up the second mount 20 .
  • an opening extends through the mount 20 which is formed by the hole 137 , hole 138 and hole 139 .
  • the mount 20 shown in FIG. 21 is a monolithic structure and is merely shown in exploded view to clearly illustrate the location of the flexural webs 33 and 35 .
  • the flexural web 33 shown in FIG. 21 joins with the part 26 and the flexural web 35 shown in FIG. 21 joins with the part 27 .
  • the holes 137 , 138 and 139 define a passage through which the axle or first portion 18 a of the first mount 10 can extend when the second mount 20 is located in the first mount 10 .
  • the second mount 20 when the second mount 20 is fixed to the part 18 a , the second mount 20 can pivot with the first portion 10 a of the first mount 10 about a z axis defined by the flexure web 31 whilst the second portion formed by the part 18 a remains stationary. Movement about the x and y axes is achieved by pivotal movement of the second mount 20 about the flexure webs 33 and 35 as previously described.
  • FIG. 22 shows the linear and annular accelerometers 90 fixed to the housings 45 and 47 .
  • the gravity gradient exerts a torque on a rigid body with any mass distribution provided it has a non-zero quadrupole moment.
  • the quadrupole is the difference between moments of inertia in the x and y directions.
  • a square or circle has zero quadrupole moment, while a rectangle has a non-zero value.
  • the torque produced is what constitutes the signal measured by the gradiometer.
  • the first is linear acceleration.
  • the second is angular motion.
  • the first is aspect angular acceleration.
  • Angular acceleration produces a torque on the mass distribution through its moment of inertia (even if the quadrupole moment is zero). This is an enormous error and two preferred techniques are used to counteract it.
  • the first is to use internal rotational stabilization.
  • Ho(s) represents the sensor assembly pivoted about the mounting 5 (as per FIG. 9 ).
  • the block A(s) represents the actuator, which provides the feedback torque to effect the stabilization by canceling the applied disturbances.
  • T(s) represents the sensor (or transducer) which measures the effect of the applied disturbance.
  • This is the angular accelerometer.
  • angular accelerometers in rotational control is unusual—usually gyros and/or highly damped tilt meters are used, but for our purpose the angular accelerometers are better, as the error is proportional to the angular acceleration disturbance.
  • CMRR common mode rejection
  • the gradient is sensed but not the angular acceleration.
  • two separate angular accelerometers 90 (labeled 901 in FIG. 22 for ease of identification) are provided.
  • the x and y axes require separate angular accelerometers. Rotational stabilization about these axes is required because the pivot axes of the two bars are not exactly parallel and also to counteract the second form of error produced by angular disturbance, discussed below.
  • the second aspect is angular velocity.
  • Angular velocity produces centrifugal forces, which are also a source of error.
  • the internal rotational stabilization provided by the actuators reduces the angular motion so that the error is below 1 Eotvos.
  • FIG. 23 shows main body 61 and connector 69 with the hemispherical ends removed.
  • FIG. 24 is a plan view of housing 45 according to a still further embodiment of the invention. As is apparent from FIG. 24 , the housing 45 is circular rather than octagonal, as is the case with the embodiment of FIG. 8 .
  • the housing 45 supports bar 41 in the same manner as described via flexure web 59 which is located at the centre of mass of the bar 41 .
  • the bar 41 is of chevron shape, although the chevron shape is slightly different to that in the earlier embodiments and has a more rounded edge 41 e opposite flexure web 59 and a trough-shaped wall section 41 f , 41 g and 41 h adjacent the flexure web 59 .
  • the ends of the bar 41 have screw-threaded bores 300 which receive screw-threaded members 301 which may be in the form of plugs such as grub screws or the like.
  • the bores 300 register with holes 302 in the peripheral wall 52 a of the housing 45 .
  • the bores 300 are a 45° angle to the horizontal and vertical in FIG. 24 .
  • the two bores 302 shown in FIG. 24 are at right angles with respect to one another.
  • FIG. 25 is a more detailed view of part of the housing of FIG. 24 showing the openings 305 .
  • the openings 305 have shoulders 401 which form grooves 402 .
  • a spring 403 is arranged adjacent surface 406 .
  • the coil 408 and the bar 41 form an 1 c circuit so that when the bar 41 moves, the current passing through the coil 408 is changed.
  • transducers 71 are arranged adjacent the ends of the bar 41 .
  • the other housing 47 also has four transducers arranged adjacent the bar 42 .
  • eight transducers 71 are provided in the gradiometer.
  • FIG. 28 is a diagram of the bars 41 and 42 showing them in their “in use” configuration.
  • the transducers which are located in the openings 305 are shown by reference numbers 71 a to 71 e to equate to the circuit diagrams of FIGS. 29 and 30 .
  • Input terminals 361 provide input current to the superconducting circuits shown in FIG. 29 .
  • Heat switches which may be in the form of resistors 362 are provided which are used to initially set the superconducting current within the circuit.
  • the heat switches 362 are initially turned on for a very short period of time to heat those parts of the circuit at which the resistors 362 are located to stop those parts of the circuit from superconducting. Currents can then be imposed on the superconducting circuit and when the heat switches formed by the resistors 362 are switched off, the relevant parts of the circuit again become superconducting so that the current can circulate through the circuits subject to any change caused by movement of the bars 41 and 42 under the influence of the gravity gradient and angular acceleration, as will be described hereinafter.
  • the transducers 71 a , 71 b , 71 g and 71 e are connected in parallel to circuit line 365 and to circuit line 366 which connect to a SQUID 367 .
  • the line 366 is connected to a transformer 370 .
  • the polarity of the signals from the transducers 71 a and 71 b and 71 g and 71 h are reversed so that the output of the transducer 370 on lines 371 and 372 is an addition of the signals rather than a substraction, as is the case when the gradient is measured so the addition of the signals gives a measure of the angular movement of the bars.
  • the outputs 371 and 372 are connected to SQUID device 375 for providing a measure of the angular acceleration which can be used in the circuit of FIG. 10 to provide compensation signals to stabilise the mounting 5 .
  • FIGS. 31 and 32 show an actuator for receiving the control signals to adjust the mounting in response to angular movement of the mounting 5 .
  • FIGS. 31 and 32 are schematically shown in FIG. 10 by reference numerals 52 , 53 , 54 and 55 . All of the actuators are the same and FIGS. 31 and 32 will be described with reference to the actuator 52 which makes adjustment around the x axis shown in FIG. 10 .
  • Actuator 52 shown in FIG. 31 has a hollow disc housing 310 which has a mounting bracket 311 for connecting the disc housing 310 to mounting 5 .
  • the hollow disc housing 310 therefore defines an inner chamber 312 in which is located coil support plate in the form of a disc 313 .
  • the disc 313 has a wide hub section 314 and two annular surfaces 315 and 316 onto which windings W 1 and W 2 of coils are wound about the hub 314 .
  • the disc 313 is also provided with a radial bore 319 and a hole 320 at the periphery of the disc 313 which communicates with the bore 319 .
  • a hole 321 is provided at the hub 314 and communicates with the bore 319 and extends to a hollow rod 328 which locates in a tube 330 .
  • the rod 330 is fixed to the disc 313 and also to support frame 340 which is fixed to main body 61 (not shown in FIG. 31 ).
  • the tube 330 is connected to the disc housing 310 for movement with the disc housing 310 relative to disc 313 , rod 328 and frame 340 .
  • the winding W 1 provided on the face 315 has a lead 331 which passes through the hole 320 and then through the bore 319 to the hole 321 and then through the tube 328 to the right, as shown in FIG. 31 .
  • a lead 332 from the other end of the winding W 1 passes through the hole 321 and through the hollow rod 328 also to the right so that current can be supplied to the winding W 1 through the leads 331 and 332 .
  • the disc housing 310 When the windings W 1 and W 2 are energised or the current passing through the windings changes, the disc housing 310 is moved relative to the disc 313 and frame 340 and because the disc housing 310 is connected to the mounting by the bracket 311 , the mounting 5 , in the case of the actuator 52 , is adjusted.
  • the movement of the disc housing 310 is generally a longitudinal movement (i.e. linear movement) in the direction of the axis of the tube 330 and rod 328 . To facilitate such movement, clearance is provided between the ends of the rod 330 and the frame 340 and about the disc 313 .
  • the bracket 311 is offset relative to the flexure web (such as the flexure web 37 ) so that movement of the housing 310 applies a torque to the first part 25 of the mounting 5 to cause rotation of the part 25 about the flexure web 37 .
  • actuators are provided for providing actual adjustment about the various axes and flexure webs and the actuators operate in combination in response to signals received from the angular accelerometers to maintain stability of the mounting 5 when the gradiometer is in use.
  • the mounting 5 , housings 45 and 47 , bars 41 and 42 , the hollow disc housing 310 , coils, and electrical leads referred to previously, are all made from superconducting material such as niobium.
  • the components can be formed from other materials such as aluminium.
  • the angular accelerometers 90 ′ have zero quadrupole moment which means that the centre of mass coincides with the flexure web and that consequentially they are insensitive to both gravity gradient and centrifugal force.
  • Linear accelerometers 90 ′′ ( FIG. 22 ) could also be provided.
  • the linear accelerometers 90 ′′ do not apply active compensation but may apply corrections to the final measured gradient data. Thus, data relating to linear acceleration can be recorded and possibly used in later processing.
  • One or both of the bars 41 and 42 can also be used as an angular accelerometer to provide a measure of angular movement of the mounting 5 so that appropriate feedback signals can be generated to compensation for that movement by control of the actuators previously described.
  • four angular accelerometers are provided with two of the accelerometers being formed by the bars 41 and 42 .
  • the use of four accelerometers arranged at 45° angles with respect to one another enables adjustment about the x, y and z axes by torque supplied from two or more of the actuators at any one time.
  • the disc 310 prevents flux from the windings W 1 and W 2 from leaving the actuator and because the leads 331 and 332 and 333 and 338 leave the actuator through the elongate tube 330 , the ability of flux to pass out of the actuator is substantially prevented.
  • spurious magnetic fields which may detrimentally effect operation of the instrument are not generated by the actuator and therefore do not influence the sensitivity or operation of the instrument.
  • the tube 330 preferably has a length to diameter ratio of 10:1 at the least.
  • the disc plate 316 is preferably formed from macor and the hollow disc housing 310 is formed in two parts 310 a and 310 b .
  • the part 310 b forming a closure panel which enables the disc 313 to be located in the chamber 312 and then the disc housing 310 closed by locating the plate 310 b in place.
  • a pair of displacement sensors formed by capacitors 400 and 401 are provided for two main purposes:
  • the bars 41 and 42 are rotated in a jig (not shown) through 360°.
  • This provides an acceleration range of 2 g E , which is typically 100 times greater than the accelerations which may be conveniently applied at low temperature.
  • a typically requirement is for the capacitors 400 and 401 to be able to detect 0.1 nm over a period of 1 to 20 minutes.
  • a pair of capacitors 400 and 401 is required for each bar to provide some discrimination against sensor drift, since rotation of the bar 41 will cause one capacitor 400 to increase and the other capacitor 401 to decrease by the same amount, as is shown in FIG. 33 , whereas thermal expansion will cause both outputs of the capacitors 400 and 401 to increase.
  • the capacitors 400 and 401 remain in place, even though they are unusable at low temperatures, and therefore their components need to be non-magnetic so as to not interfere with the operation of the gradiometer and, in particular, its nearby superconducting circuitry.
  • FIG. 33 shows that as the bar 41 pivots, the gap applicable to the capacitor 400 decreases and the gap of the capacitor 401 increases.
  • the capacitors 400 and 401 are formed by the face 41 a of the bar 41 (and the corresponding face on the other bar 42 ) and second plates 405 which are spaced from the face 41 a .
  • the gap between the plates of the respective capacitors 400 and 401 must typically be resolved to about 1 ppm.
  • FIG. 34 shows the calibration circuit applicable to the capacitor 400 .
  • a circuit for the other capacitor 401 is identical.
  • the capacitor 400 forms a high Q-factor resonant circuit with inductor 410 .
  • the inductor 410 and capacitor 400 are provided parallel to capacitors 411 and 412 and connect via capacitor 413 to an amplifier 414 .
  • the output of the amplifier 414 is provided to a frequency counter 415 and also fed back between the capacitors 412 and 411 by line 416 .
  • the capacitor 400 therefore determines the operating frequency of the amplifier 414 which can be read to a high precision.
  • the frequency counter 45 will tend to drift because of the imbalance of the bar. This can be adjusted by moving the grub screws 301 into and out of the masses as previously described until balance takes place.
  • the amplifier 414 can then be disconnected from the frequency counter 415 so that the gradiometer can be arranged within the Dewar 1 with the other parts of the circuits shown in FIG. 34 in place.

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  • Measurement And Recording Of Electrical Phenomena And Electrical Characteristics Of The Living Body (AREA)
  • Measuring Fluid Pressure (AREA)
  • Ink Jet (AREA)
  • Force Measurement Appropriate To Specific Purposes (AREA)
  • Containers, Films, And Cooling For Superconductive Devices (AREA)
  • Testing Of Balance (AREA)
US11/722,076 2005-10-06 2006-08-31 Gravity Gradiometer Abandoned US20080257038A1 (en)

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AU2005905524 2005-10-06
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AU2005906669A AU2005906669A0 (en) 2005-11-29 Gravity Gradiometer
AU2006900193A AU2006900193A0 (en) 2006-01-13 Gravity gradiometer
AU2006900193 2006-01-13
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US11/722,077 Active US7788974B2 (en) 2005-10-06 2006-08-31 Gravity gradiometer
US11/722,031 Active US7784343B2 (en) 2005-10-06 2006-08-31 Gravity gradiometer
US11/722,058 Active 2027-06-15 US7823448B2 (en) 2005-10-06 2006-08-31 Actuatory and gravity gradiometer
US11/722,040 Abandoned US20080302179A1 (en) 2005-10-06 2006-08-31 Gravity Gradiometer
US11/722,050 Abandoned US20080302180A1 (en) 2005-10-06 2006-08-31 Gravity Gradiometer
US12/643,492 Active US7938003B2 (en) 2005-10-06 2009-12-21 Gravity gradiometer
US12/646,186 Active US7975544B2 (en) 2005-10-06 2009-12-23 Gravity gradiometer
US12/646,110 Expired - Fee Related US7942054B2 (en) 2005-10-06 2009-12-23 Gravity gradiometer
US12/647,982 Active US7980130B2 (en) 2005-10-06 2009-12-28 Gravity gradiometer
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US11/722,058 Active 2027-06-15 US7823448B2 (en) 2005-10-06 2006-08-31 Actuatory and gravity gradiometer
US11/722,040 Abandoned US20080302179A1 (en) 2005-10-06 2006-08-31 Gravity Gradiometer
US11/722,050 Abandoned US20080302180A1 (en) 2005-10-06 2006-08-31 Gravity Gradiometer
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