BR112014029304B1 - Gravity transducer system, method of detecting changes in orientation or localized variations of a gravitational field and method of detecting a hydrocarbon deposit - Google Patents

Abstract

GRAVITY TRANSDUCER AND APPLICATION FOR HYDROCARBIDE EXPLORATION. The present invention relates to a gravity transducer that includes a particle system characterized by internal vibrations relative to its de Broglie wave, a resonant cavity to capture the particle without containing it in a lattice structure; a source of a phonon wave, where the Broglie wave and the phonon wave interact over a junction area; a power source to apply electrical energy across the junction; a reading system for measuring resistance, voltage, or current across the junction and for producing a read signal; and a recording system for recording the read signal. The transducer is used in a method of detecting hydrocarbon deposit potential, the method comprising: providing the transducer to read a change in a spatial orientation of gravity; flying the gravity transducer through the hydrocarbon deposit; reading a change in the spatial orientation of gravity to produce a signal indicative of subsurface geological features generally associated with hydrocarbon deposits; and register the signal.

Description

FIELD OF THE INVENTION

[001] The present invention relates in general to gravity transducers, and more particularly to the detection of minute variation of the gravitational field induced by density and subsurface tension, and even more particularly to an application of said transducer for the exploration of hydrocarbon.

BACKGROUND OF THE INVENTION

[002] Gravity variations were detected using large suspended masses on the order of kilograms. It is believed that the masses have to be large because the force of gravity is the weakest known force. More recently, atom interferometry, and in particular, accelerometers using interferometry have been proposed as gravitational probes. See, for example, B.M. Anderson, J.M. Taylor and V.M. Galitski, "Interferometry with synthetic gauge fields", Physical Review A, 83, 031602(R), 2011.

[003] Said devices have practical limitations. Devices using large masses can only detect large variations in the gravitational field. There are a number of complex technical challenges to overcome in order to make interferometers practical for field operations. Some of the aforementioned needs include cooling and keeping atoms close to absolute zero and removing unwanted inertial effects. Thus, it would be highly desirable to have a device that can detect relatively small gravity fluctuations, such as those due to changes in density and subsurface tension in porous rocks relative to the geological features of interest, and which can be conveniently used at temperatures reasonable, such as ambient temperature.

BRIEF DESCRIPTION OF THE DRAWINGS

[004] Figure 1 is a diagram illustrating a typical geological feature that the present invention may be helpful in distinguishing;

[005] Figure 2 is a block diagram illustrating the main components of a gravity transducer and detection system that is capable of identifying potential hydrocarbon characteristics;

[006] Figure 3 A and B are detailed block diagrams of the system of Figure 2 showing the parts and cabling between the parts;

[007] Figure 4 is a sketch based on a photograph showing the system of Figures 2 and 3 on a Cessna Citation 560 aircraft;

[008] Figure 5 is a sketch of an open sensor case and an associated signal conditioning unit that are employed in the system of Figure 4;

[009] Figure 6A shows a side view of a voltage field detection sensor (SFD) showing typical dimensions;

[0010] Figure 6B shows an end plan view of the SFD sensor of Figure 6A showing typical dimensions;

[0011] Figure 7A is a side perspective view of another embodiment of an SFD sensor;

[0012] Figure 7B is an end view of the SFD sensor of Figure 7A;

[0013] Figure 8 is a sketch showing a microscopic view of an SFD sensor that illustrates how atoms can be captured forming a sensor junction;

[0014] Figure 9 is a sketch illustrating an embodiment of the present invention comprising an embodiment of multiple junctions, each comprising the superposition of the wave of a captured particle and the phonon wave generated in a junction cavity;

[0015] Figure 10 is a sketch illustrating a vertical wave of the captured particle and the phonon wavefront in a highly constrained region between a metal pin and a metal bead (“metal bead”) Figures 6A to 7B;

[0016] Figures 11 - 13 illustrate examples of signals generated by the system of Figures 2 to 6B in test flights that verify the abilities of the system, and more specifically:

[0017] Figure 11 is a signal for a test flight line that crosses the Ladyfern gas field, BC, Canada along the maximum stress line on the plains;

[0018] Figure 12 shows a signal from a second test flight line of the Burnt Timber, AB, Canada gas field using the same sensor as used in Figure 11, and along the maximum voltage line, but at the mountains;

[0019] Figure 13 shows the signals from a third test flight that crosses Ladyfern gas field, BC, Canada, using the same sensor as used for Figures 11 and 12, but in this case the flight is along a minimum voltage line;

[0020] Figure 14 shows a devoo line survey map for a flight on April 14, 2012 over the La Jarilla oil field in Comodoro-Rivadiva, Argentina;

[0021] Figure 15 shows a signal developed along the flight line of Figure 14 obtained from the "Pearl" sensor;

[0022] Figure 16 shows another signal developed along the flight line of Figure 14 obtained from the "String" sensor, a different sensor from the "Pearl" sensor;

[0023] Figure 17 is a sensor signal that illustrates the concept of "signal amplitude";

[0024] Figure 18 is a sensor signal in which the amplitude is averaged;

[0025] Figure 19 is a sensor signal that illustrates the concept of a geological edge;

[0026] Figure 20 is a sensor signal illustrating the concept of "frequency" signal;

[0027] Figure 21 is a sensor signal illustrating various frequency trends;

[0028] Figure 22 is a sensor signal that illustrates the concept of signal pattern change;

[0029] Figure 23 is a sensor signal that illustrates the concept of signal character change;

[0030] Figure 24 is a sensor signal that illustrates the concept of sequence identification;

[0031] Figure 25 shows a side view of an electromechanical sensor embodiment according to the invention.

[0032] Figure 26 shows an end plan view of an electromechanical sensor embodiment according to the invention.

[0033] Figure 27 shows a schematic diagram of an embodiment of a mechanical model of the electrical system according to the invention; and

[0034] Figure 28 shows a typical relative displacement of the preferred mode of the mechanical model of Figure 27 in which it finds the time-dependent gravitational acceleration profile due to rectilinear motion.

DETAILED DESCRIPTION OF THE PREFERRED MODALITIES

[0035] The present application discloses a small-scale gravity-based transducer with sufficient stability. The device is experimentally tested, and consistent results from aerial surveys have been obtained. The new device and the system that controls it have the capability of autonomous reliability.

[0036] The modalities of a practical gravity transducer device that uses one or more of the following three design elements are disclosed in this document: (i) the transducer is in continuous rectilinear motion to operate; (ii) the transducer detects gravity changes using both an active interface and relative displacements between two mechanical elements of the transducer; (iii) the transducer uses an electromechanical conversion through the application of electric current through the contact area between the elements that register the relative displacement. The specific application of the modalities described in this document is in relation to the detection of potential hydrocarbon deposits.

[0037] As will be seen in detail below, the presence of fluid, for example, captured water and/or hydrocarbon, in porous rocks causes the density to decrease and produces a negative gravity change in relation to the bottom. During the detection of potential hydrocarbon deposits, the revealed modalities also detect other geological features within a sedimentary basin, such as lithographic alterations and faults. Fluids in reservoir rocks, lithographic alterations or faults tend to have a density-reducing network effect locally, which is also accompanied by subsurface stress changes. A feature of two typical embodiments of this invention is that they both employ continuous rectilinear motion. Fundamentally, all gravimeters and gravity gradiometers present take statistical measurements; therefore, such statistical instruments (1) require or achieve static equilibrium; (2) lack the ability to obtain a continuous time-dependent gravity signal; and (3) lack the ability to take measurements and/or detect gravity changes in the sensor's natural vibrational frequency.

[0038] In both embodiments, the gravity transducer system utilizes (1) a combination of high altitude (up to 3,000 m) and high speed (up to 500 km/h) which provides an increased frequency domain; (2) a high sample rate (eg, 2000 samples per second) which provides satisfactory spatial scale detection ability.

[0039] In both embodiments, there is a gravity transducer system comprising: a junction comprising a first metal and a second metal different from the first metal; where the first metal is the pin and the second metal is the sphere. The junction forms a capacitance when the two metals are not in direct contact.

[0040] The present application discloses a small-scale device for aerial geophysical exploration, which is sufficiently stable and for which the results are consistent. In this way, the new device and system have the ability to provide unattended reliability.

[0041] Modalities of a practical gravitational field detector are described here. The specific application of the modalities described here is the detection of potential hydrocarbon deposits. As will be seen in detail below, the geological stress and density changes in the region of hydrocarbon deposits in the earth's crust are different from the bottom regions. The transducer described here detects said differences. In the course of detecting the potential of hydrocarbon deposits, it was observed that the described modalities also detect other geological features within a sedimentary basin, such as lithographic alterations and faults. It will also be apparent to those skilled in the art that the voltage field detector and the specific embodiments described have and will have many additional features and applications.

[0042] Figure 1 is a diagram illustrating a typical geological feature 100 that the modalities described here may be helpful in distinguishing. An example area 110 of a sedimentary basin having a plurality of sedimentary layers 102, 104, 106, 108 and 110 is illustrated, which area includes areas having shale sequence 112 that surrounds a porous sandstone formation 114, which may contain fluid, such as, for example, gas, oil, or water. In the aforementioned example, porous sandstone and shale have the same density. Equal density implies equal gravitational acceleration. Therefore, mass-based gravimeters produce the same measurement value with respect to both. However, the two areas will have different stress regimes as suggested by 118, 126, 127, and 120. Shale rock 112 distributes stress and permeability differently from porous sandstone with fluid 114. The difference in elastic properties ( shear) between shale and porous sandstone containing significant fluid creates stress anomalies not related to conventional gravity sensing devices, but detectable by the sensors described here, due to changes in gravitational field vibration associated with stress disturbances and subsurface density.

I. DETAILED DESCRIPTION OF ELECTRONICS

[0043] Figure 2 is a block diagram illustrating the main components of an embodiment of the gravity transducer and detection system capable of identifying potential hydrocarbon characteristics. As shown in Figure 2, the system integrates voltage field detection sensors 154, signal conditioning systems 156, aircraft tracking and communication systems 160, data recording systems 164 and 166, aircraft control systems 170 quality including data post processing systems. All equipment is self-contained and is connected together using appropriate cabling 155, 161, 158, 157, 167 and 168.

[0044] Figure 3 shows a block circuit diagram showing the individual electronics of an embodiment of system 150 incorporated into a survey aircraft. Embodiment 150 includes a first Voltage Field Sensor (SFD) system 202, a second SFD system 204, a data acquisition main computing system 214, a real-time screen computing system 216, and a navigation system. pilot 218. The first SFD sensor system 202 includes an SFD sensor structure including six SFD sensors and 2 accelerometers. The aforesaid are contained in a sensor box 220. The structure of the sensors and the sensor box will be discussed below. The first sensor system 202 also includes an SFD signal conditioning system 222 and a battery 225. Grounds through the system 150 are shown by ground symbols, such as 226. The second SFD system 204 includes a sensor box 230 containing eight SFD sensors and six accelerometers. The second system 204 also includes an SFD signal conditioning system 232 and a battery pack 235.

[0045] One embodiment of main computer 214 includes a QNX 4.25 data acquisition computer 290 along with cards and peripherals including keyboard 240 coupled to a keyboard on port 299 via a docking device 242. Computer 290 is powered from a power source 294, which is powered from the aircraft, which power is sent to 110V AC power in unit 291. Data acquisition computer 290 may also include a data acquisition card 300 connected to the input port sensor data port 250, data acquisition card 304 which is connected to accelerometer data input port 252, serial port of GPS 306 which is connected to COM1 port of GPS 274, NMEA/qtalk serial port 308 which is connected to Com 2 port of GPS 276, pilot image output 310, and USB port 314 which provides output to an external hard drive. Docking device 242 can be a cable or wireless device and allows the keyboard to be moved over the aircraft. Computer 214 may include: cable interface 248, M6259 2kHz 250 data input interface, with up to 16 channels usage by SFD sensor; M6225 200 Hz 252 data acquisition interface for accelerometers; a remote start output 256 for synchronizing the mainframe with the other computers; input port of system one 258 connected to the SFD signal conditioner of system one 222; system two input port 260 connected to system two 232 signal conditioner; and battery monitor/accelerometer input 264. Main computer 214 also includes a GPS module 268 which may include: GPS card 268; GPS antenna 270; Com port 1 274; Com port 2 276; DC 280 power port; 282 GPS battery; and 15 volt dc source 286. The GPS module 268 depletes battery 282, which is charged from the aircraft generator when the aircraft is flying.

[0046] Pilot navigation system 218 includes 5 volt DC power supply 320, pilot navigation interface 324 which receives output from the pilot image output 310 of computer 290, and pilot navigation screen 326 which is designed for -aircraft windshields.

[0047] Real-time imaging computer 216 includes a laptop 330, which can be a Panasonic CF30 with an OziExplorer Motion Map Utility to track survey flights, and a WinDaq data acquisition system to display the waveform SFD during the survey and also serves to record the backup data. Laptop 330 may also include a communication port 334 connected to GPS communication ports 304 and 276 of computer 214, USB port 326, DC power RAM card 338 connected to 28V DC power supply 346, and USB port 340 connected to external hard drive 344. Real-time imaging computer 216 may also include a mapping module 350 which may include a data acquisition card 350, WinDaq input ports 356 and 358, and USB port 354 which connects the USB port 336 on laptop 330. WinDaq ports 356 connect SFD signal conditioning units 222 and 232, respectively.

[0048] Main computer 214 operates to collect and digitize sensor data, accelerometer data, and GPS data. The data acquisition cards mentioned above include analog-to-digital converters that digitize the analog outputs of SFD sensors and accelerometers. Accelerometer data serves a quality control function. If the impact of acceleration on SFD sensors is very high, eg 1g or greater, extra care needs to be exercised regarding data quality. This is accomplished by correlating accelerometer data with SFD sensor data by main computer 214. Main computer 214 also correlates SFD data with aircraft position data output by GPS module 268. real time 216 provides signal outputs during surveys which show the SFD output as a function of time, the waveforms of which will be discussed in detail below. Said waveforms can be output in real time on the laptop screen 330. Time is also correlated to position via the GPS output allowing the system to provide real time images of flights which correlate time with position. Examples of such maps will be shown and discussed below.

[0049] Figure 4 is a sketch of a photograph showing the on-site survey sensor equipment aboard the Cessna Citation 560 380 aircraft. Real-time imaging laptop 330 sits atop the nearest structure 384, while the main computer 290 is directly below it. Mapping module 350 is at the bottom of said structure. Cable interface 248 can be seen at the bottom right of frame 384. System one SFD sensor housing 230 can be seen on top of second frame 388 while system two sensor housing 230 is below it. Signal conditioner for system two 232 can be seen at the airframe level below the sensor case 230. Navigation module 218 can be seen in cockpit 390 at the far end of aircraft 380.

[0050] Figure 5 shows an embodiment of an open sensor case 230 and the multi-channel signal conditioning unit 232. Gravity field sensors are individual units mounted inside the pelican hard case 400 with vibration and shock isolation. In the embodiment of Figure 5 the vibration and shock isolation comprises a silicone gel mat 410. Sixteen SFD sensors 404, 406, 408, 414, 416, 418, 420, 422, 424, 426, 428, 430, 434, 435 , 436, and 437 are mounted on belt 410. Three accelerometers, 440, 441, and 442 are mounted on top of SFD sensors 434, 435, and 437, respectively, and thus are supported on belt 410. Said accelerometers measure the acceleration in each of the three orthogonal directions. Additionally, three accelerometers 444, 445 and 446 are mounted directly to the case 400. These measure acceleration in each of the three orthogonal directions of the fuselage structure. Many other configurations of SFD sensors and accelerometers are possible. Redundancy of SFD sensors and accelerometers is often a feature of modalities. In one embodiment, signals from fourteen SFD sensors in two separate systems are recorded simultaneously in differential mode to reduce the uncertainty of identifying subsurface geological features and eliminate unwanted noise. In another embodiment, twenty-four SFD sensors are contained in three separate systems.

[0051] The gravity field sensor according to the present invention is a small-scale device that responds to captured structural, stratigraphic fluids caused by variations primarily in the subsurface horizontal stress directions in relation to density and stress, thus the term detectors of voltage field. A preferred embodiment of the sensor is described with reference to Figures 6A-10 below. Depending on the design, the sensor is a two- or three-terminal transducer that produces a time-varying analog electrical signal that is fed through a multi-channel signal conditioning unit. The output, in the form of an analog voltage signal, flows into data acquisition cards where it is converted to a digital signal for display on a computer system. Data can be recorded at 2,000 samples per second.

[0052] Such a mode of gravity transducer system consists of an electromechanical sensor and the associated electronic devices that process and record the voltage signal produced by a sensor. Figure 6 shows side (Figure 6A) and plan (Figure 6B) views showing details of an embodiment of an electromechanical sensor 416 in accordance with the present invention. Such an embodiment comprises a pin 450 having a shell 462 and the bead 454 comprising a first ball half 456, a disc 458 and a second ball half 460. In such an embodiment both the ball and pin are fixed and the relative displacement between they are not allowed and detection is based on the movement (vibration) of the active interface (captured particle) 514 in Figure 10. Pin 450 can be made of gold or copper, although it can be made of other materials. Coating 462 can be made from silver oxide, i.e. Ag2O, although it can be made from other oxides or other dielectrics. The thickness of coating 462 can be thirty nanometers or less; more preferably twenty nanometers or less; and even more preferably ten nanometers or less. The circular central disc portion 458 of the bead 454 may be produced from copper, although the same may be produced from many other metals. Examples of dimensions of the various parts are shown in Figures 6A and 6B. Ball halves 456 and 460 can be 2 mm in length, and can be produced from alloys such as tin, nickel, lead and silver alloys. In one embodiment, the first bead half 456 can be 63% Sn and 37% Pb, while the second bead half 460 can be 96.3% Sn and 3.7% Ag. Disc 458 can be 1.75 mm long. The inner surface of the sphere is produced relatively rough. The 450 pin can be 25 mm long and 1.45 mm in diameter. The outside diameter of half of balls 456 and 460 and disc 458 can be 3.5 mm. In operation, pin 450 is held at ground voltage via contact 504, while bead 454 is held at positive voltage VDC via contact 508. Some other materials for the sensor components detailed above may also be used. such as nickel, carbon, platinum, others and their alloys. Metal oxides that can be used to coat pin 450 include tantalum oxide, aluminum oxide, tin oxide, nickel oxide, and others.

[0053] Figures 7A and 7B are side and plan views showing a perspective view of another embodiment of a sensor junction 470. Said embodiment includes pin 474, and bead 476 disc 478, disc 480, and disc 482. Pin 474 is coated with coating 472. Pin 474 and disc 480 can be produced from a good conductor, such as gold or copper. Discs 478 and 482 can be produced from a metal alloy, such as tin, nickel, lead and silver alloys. Coating 472 may be produced from a metal oxide, such as silver oxide or other oxides mentioned above. A contact pin 490 can be made of copper, or other materials mentioned above, and can be grounded at 494. Disc 482 can be connected to positive voltage VDC. The positive voltage VDC can typically be between 6 and 9 volts. In operation, the position of pin 450, 474 is adjusted in bead hole 454, 476 using a precision micromechanical control, which can be adjusted by means of a piezo driven nanopositioner.

[0054] Figures 25 and 26 are side plan views showing a perspective of another embodiment 516 of a sensor junction. Such an embodiment includes pin 550 and ball 554 consisting of discs 558, 556 and 560. Discs 556 and 560 may be produced from a metal alloy such as alloys of tin, nickel, lead and silver. The circular central disk portion 558 of the sphere 554 may be produced from copper, although it may be produced from a variety of other metals. The inner surface 586 of the ball is produced relatively smooth. In such mode, relative displacement between the sphere and the pin is allowed. A thin dielectric polymer spacer 580 that controls ball vibration is placed between pin 550 and ball 554. The spacer may be produced from a polymeric adhesive that contains up to ten percent titanium oxide (TiO2) . Other stickers can also be used. Pin 550 is coated with dielectric material 584. Pin 550 and disc 558 can be produced from a good conductor, such as gold and copper. Coating 584 can be produced from a metal oxide, such as silver oxide or other oxides mentioned above. A pin contact 582 can be produced from copper or other materials mentioned above and can be grounded at 583. The ball can be connected to positive voltage VDC through conductor 588. Positive voltage VDC 589 can typically be between 3 and 9 volts.

[0055] During operation for both modes, the pin position is adjusted in the ball hole for optimal response using a precision micromechanical control, which can be adjusted via a piezo driven nanopositioner.

II. OPERATIONAL PRINCIPLESII.1. . Transducer Model I: Dedection via Active Interface

[0056] Although the system described here has been extensively tested against empirical evidence for approximately 15 years, and the steady improvement of the system has been carried out on the basis of empirical evidence, a discussion in terms of the operating principles can be useful for understanding the system. Figure 8 is a sketch showing the microscopic view of sensor junction 416 illustrating how electrically neutral or charged particle(s) 512, 514 can be captured forming an active junction of sensor 416. As in Figures 6A and 6B, sensor 416 includes bead 454 and metal pin 450. Bead 454 includes portions 456 and 460 that can be produced from metal alloy and portion 458 can be produced from metal, such as copper. The pin 450 is coated with a coating 462 which can be produced from a metal oxide. Pin 450 is grounded at 504 and bead 454 is connected to +VDC voltage at 508. Pin 450 is set in directions orthogonal to its length, as shown at 520. As pin 450 is set, a(s) ) electrically neutral or charged particle(s) such as 512 and 514 can become properly trapped between pin 450 and bead 454. When +VDC voltage is applied across pin 450 and bead 454, electrical current produces heat, which generates phonons. A particle, such as 514, can become properly captured in a phonon resonance that forms at the electronic junction of dissimilar metals.

[0057] Figure 9 is a sketch illustrating an embodiment comprising an embodiment of multiple junctions, each comprising the superposition wave, such as 515, of the captured particle, such as 514, and the phonon wave, such as 530, generated in the junction cavity. As shown, setting 526 captures particle 514 in a vertical phonon wave 530, and setting 536 captures particle 533 in a vertical phonon wave 534. The captured particle is confined in the space 500 between the pin oxide coating 450 and the inner surface 460 of the bead 454. Figure 10 is a sketch illustrating the capture 520, 501 of a particle 514 between the metal pin 450 and the metal bead 460.

[0058] The phonon wave controlled active interface resonance transducer is a geophysical sensor system that is capable of detecting sudden variations in the earth's gravitational field. Due to its compact and highly portable configuration, the sensor is easily employed in aerial survey applications, which ideally position it as a fast and cost-effective tool for wide area mineral exploration. The present survey system is specifically designed for oil and gas prospecting. Additional future applications of the system include metallic mineral exploration, kimberlite (diamond) prospecting, location of shallow freshwater beds, prediction of earthquakes and volcanic eruptions, identifying and testing quantum mechanical interactions (phenomenon and processes), investigating events quantum mechanics in the field of general relativity, exploring the understanding of the origin of mass, gravity and inertia from the most fundamental laws of physics, and testing the postulates of general relativity, and potential astronomical and astrophysical observations. However, said applications may require modifications from current designs and material selection, added control functions, and proper particle selection.

[0059] The basic operational assumptions of the active interface are based on the functional relationship between stress and gravity.

[0060] The vertical voltage component of the earth is dominated by gravity which acts on the overload. Differently, the horizontal maximum and minimum stress components significantly affect horizontal gravity. Therefore, most gravitational anomalies with changes in orientation will occur in the horizontal direction. Hayes showed that stress fields will not only introduce changes in the magnitude of gravity, but also couple in the tensor directions (TJ Hayes, KF Tiampo, J. Fernandez, and JB Rundle, "A gravity gradient method for characterizing the post-seismic field deformation for a finite fault", Geophysical Journal International, 173 802-805, 2008). Using extensive calculations and Joshua Tree Earthquake models, Hayes showed that gravity gradiometry will exhibit a similar shape as a stress model over a finite attack glide motion in the horizontal plane. One exception where the stress does not follow the gravity gradient is in trapped fluids. If a solid is in contact with a fluid, the shear stress at the interface must be zero (fluids cannot withstand shear), but the normal component of stress (ie, the tension) must be continuous. The effects of seismic shear waves are identical for captured fluids. The stress fields of trapped fluids therefore differ significantly from those of solid rocks and also cause unique gravitational perturbations.

[0061] According to the theory of general relativity, all forms of energy are sources for the gravitational field, and the addition or subtraction of energy changes the potential gravitational field of an object. Consequently, gravitational bodies will develop real perturbations in the geometry of their gravitational field in response to applied stress. Tensioners can include heat, rotation, compression or tension, and the source of said tensions can be internal or external to the body.

[0062] The transducer of the present invention is a non-linear scale meso-copic device designed (1) to selectively respond to voltage-induced gravitational anomalies; (2) to achieve dynamic signal integration with time; (3) to reject constant or gradually varying gravitational sources; (4) to perform said functions from high altitudes, eg, 1,000 to 20,000 feet, and at a high sample coefficient (eg, 2,000 samples per second); (5) to allow the interaction of classical and mechanical domains through a specially designed interface. The gravity transducer system exploits the stress-gravity relationship to infer changes in stress patterns within a sedimentary basin and/or the shallow Earth's crust by focusing on detecting sudden variations in the form of vibration of gravitational fields arising from stress disturbances. -density. To be clear, the gravity transducer system according to the present invention is designed to detect anomalies, such as variations in vibrations, in the gravity-frequency energy domain, other than measuring the magnitude of acceleration that gravimeters are based on. and conventional state-of-the-art gravity gradiometers. As such, the system of the present invention represents a substantial improvement over known technologies employed in the field of geophysics.

[0063] The large 'test mass' is inadequate for measuring small distortions in gravity in large scale interactions. Furthermore, large masses have short waves of Broglielength. Differently, the particle-scale mass has a long wave of Broglielength. Energy density is related to mass, and mass can be defined in terms of the de Broglie frequency (JWG Wignall, "Proposal for an absolute, atomic definition of mass", Physical Review Letters, 68, 5 to 8, 1992; S .-Y. Lan, P.-C. Kuan, B. Estey, D. English, J. Brown, M. Hohensee, and H. Müller, "A clock directly linking time to a particle's mass", Science, 339, 554 to 557, 2013). Therefore, all vibrations experienced by the mass are fundamentally associated with its de Broglie frequency.

[0064] As the sensor is passed through the gravitational field at a high speed, its vibrating active interface is tuned to the specific frequency of interest. This will allow the sensor to interact with the gravitational energy density located within a specific space-time geometry relative to specific subsurface voltage and density perturbations. Disturbances with an energy density comparable to that of the sensor will bring about localized interference vibrations with the preset vibrations of the sensor and initiate changes in the phonon population within the resonant junction cavity. Thus the resulting electrical waveform output can be used to identify signal attributes indicative of captured fluids and other geological features. Additionally, orientation effects are induced by anisotropic "stress states" and in situ subsurface density associated with subsurface discontinuities, which can be detected as the sensor is passed along a flat path. Stress and density perturbations associated with buoyancy (an upward force exerted by the fluid opposing the weight of an immersed object) can be identified as well, based on stress energy patterns and frequency deviations.

[0065] Short-wavelength gravitational field vibrations, such as those produced by voltage and density perturbations, can be transferred to particles with the corresponding wavelength, for example, from the detection element consisting of the phonons and the particle captured. The process described above allows for an efficient transfer of energy momentum and amplification of the effects resulting from small vibrations and field distortions. The gravitational energy density spectrum of the SFD probes are designed to investigate and discern subsurface tension and density changes associated with captured fluids and other geological features. The present invention explores a new approach towards identifying and describing gravitational effects that have not been previously detected.

[0066] The device described here may be a vertical controlled phonon wave transducer consisting of a resonant cavity or a low-resistance, low-interaction metal-metal oxide junction (LONCI Junction) with highly restricted spatial regions. Between the ends of the junction a particular non-lattice bonded matter structure having its associated wave, i.e. a particle element can be captured. The particle element will be called the captured particle from now on. Without the application of excitation, the captured particle will naturally oscillate about its equilibrium position. However, with proper excitation, the captured particle can behave as an active interface in conjunction with the vertical phonon wave in detecting localized gravitational vibrations or distortions. The coupling of the captured particle's matter wave and the phonon vertical wave constitutes the gravity detection mechanism.

[0067] Other quantum mechanics devices employ "passive junction interfaces" in which the junction barrier is composed of gas/air or a thin film or some other dielectric, etc., characterized by high strength and generally operating at extremely high temperatures. casualties. Conversely, an active-interface sensor may use low junction resistance where particles can move across the junction as waves, unlike high-resistance junctions of about 4.1 kQ or more where particles move through the junction. junction as particles. Furthermore, the described sensor operates at room temperature and employs the active interface in a form of a vibrating captured particle matter wave, which is directly coupled to the vertical phonon wave system. The resulting arrangement is used in detecting highly localized minute changes of vibration and direction in the gravitational field.

[0068] The LONCI junction is DC current driven. Current passing through the low-resistance junction produces Joule heat. When phonons are absorbed at a junction, they are rapidly thermalized, which raises the junction temperature. As a result, the sensor system undergoes excitation and phonons are generated. This results in electron-phonon scattering, junction impedance change, Coulomb formation and blocking, and starts the channeling of the particles. The system is electromechanically tuned (1) to achieve the desired resonance by modifying the cavity dimensions and/or by changing the junction capacitance, (2) to produce a vertical coherent phonon wave within the cavity in two phonon waves that travel in directions opposite each other, (3) to allow a complex wave particle to couple to the gravitational field locally, and (4) to amplify the signals, and (5) to exploit stochastic resonance. By the help of the ubiquitous Johnson-Nyquist electronic noise (due to the thermal agitation of freight vehicles) generated at the sensor junction, the amplification and optimization of extremely weak signals resulting from gravity interactions can be achieved. This also affects how the sensor operates.

[0069] As the sensor is moved along a survey path, the captured particle's matter wave coupled with the vertical phonon wave will stretch, compress, or relax in response to field variations. The changing wave system continuously affects the junction impedance, which is observed as a voltage signal output with respect to time. This is partially due to electron-phonon scattering with control of electrical charge distribution across the junction.

[0070] Although the impedance shift is evident, its cause is not yet fully understood. Some of the processes that govern impedance change are potentially: superposition of fields and coupling waveforms, phonon-phonon coupling, electron-phonon coupling, Coulomb block formation, and particle channeling. As steering voltage is applied, freight vehicles can channel across the junction. The conductance varies with the charge energy of the junction, the thermal energy of the system, the quantization of the conductance, and the polarization of the spin as the charge vehicle moves through the oxide layer.

[0071] The current transducer system is calibrated to focus in an effective observation window of approximately 0.5 to 1.5 radial kilometers. At this scale, empirical evidence suggests that most gravity effects arise from the internal play of in-situ tectonic stresses that act on local geological features. As a result, inferred stress patterns are often indicative of prospective hydrocarbon uptake and reservoir conditions in sedimentary basins including, for example, the presence of faulty blocks, channeled reservoirs, or carbonate reefs. Certain other stress patterns may indicate changes in the geological domain, such as system faults, fracture belts, lithological boundaries, and overpressure.II.2. . Transducer Model II: Relative Displacement Detection

[0072] Various modalities of the system described in this document are extensively tested against empirical evidence and constant refinement of the system has been undertaken. To understand how the sensor junction detects the gravity anomaly, a mathematical model of classical mechanics can be useful to characterize the relative motion between the pin and the ball. In its basic configuration, this mechanical model is comprised of two test masses, two springs and a damper.

[0073] Figure 27 shows a schematic diagram of a mechanical model. The two test masses m1 and m2 are vertically connected by a spring with spring constant k2 and a damper with damping coefficient α. Test mass m1 corresponds to pin 450 and test mass m2 corresponds to sphere 454. Test mass m2 is vertically connected to the earth platform by a spring with spring constant k3.

[0074] The Lagrange Function of the mechanical system described in Figure 5 is given by

[0075] where l2 and l3 are the equilibrium lengths of the respective springs and vi and v2 are the velocities of the respective test masses. The damping effect is added once and the equations of motion are obtained from the Lagrange Function. The equation of motion for mi is obtained through the Euler-Lagrange equation augmented by the dissipation force d/dL\ dL

[0076] that yields

[0077] The expression -α(v1 - v2) represents the dissipation force that acts on m1. It is zero when both test masses move with the same speeds. Under this condition, the damper does not absorb energy from the movements of the two test masses. If the speed of m1 is greater than that of m2, and both are moving in the same direction, then the dissipation force acts to reduce the speed of m1 . If the speed of m2 is greater and both are moving in the same direction, then the dissipation force causes m1 to gain more speed. This effect is due to the fact that the two ends of the damper are fixed to two different masses, so that m1 is pushed up if m2 moves up with a higher speed, or m1 is pulled down if m2 moves up. down with a higher speed. However, if both masses move in opposite directions, then the dissipation force acts to reduce the velocity of m1.

[0078] The equation of motion for m2 is also obtained by the Euler-Lagrange equation added by the dissipation force

[0079] that generates

[0080] Due to the fact that mass m1 cannot be lower than mass m2, one must have x1 - x2 > 0. If spring k2 is a spring of zero length, then one has x1 - x2 > 0. k2 is a spring of zero length if l2 = 0. Sensitive detection of gravitational acceleration changes in this invention depends on isolating the relative displacement between the two masses:

[0081] Gravitational acceleration is assumed to have the following time dependence

[0082] where g0 and Δg are background of constant gravitational acceleration and gravity anomaly, respectively, and T > 0.

[0083] Assuming that the upper spring (k2) has a length of zero when it is in equilibrium, that is, l2 = 0, the solution for the relative displacement is

[0084] where H(t - t) is a unit step function that has a value of 1 if t > T and zero otherwise. This solution is obtained by numerically assuming that k3 > k2 » α > m1 « m2 in the same system of units. The relative displacement Ç(t) has oscillatory components, which are not included due to the approximations used when performing the Laplace transform inversion. The solution presented above is the slowly varying envelope function without the high frequency oscillation components.

[0085] The solution ξ(t) above shows that the background of constant gravitational acceleration can be completely removed by filtration by the preferred mode. To see this effect, consider the immersion of the preferred modality in the constant bottom with no presence of gravity anomaly ∆g. The time t is always less than τ at which the gravity anomaly begins to appear, so that only the first two terms of the solution are obtained.

[0086] Due to the geometric constraint of the preferred modality, the position of m1, x1, must be at least equal to the position of m2, x2, so that ξ(t < 𝑇) cannot be less than zero. As time progresses, the relative displacement decreases exponentially and will reach zero, indicating that the oscillations due to the constant gravitational background are completely suppressed. The time at which g0 is completely suppressed occurs when ξ(t < 𝑇) = 0, yielding

[0087] While it is preferred that k2 approaches zero, the approximation constraint k3 > k2 » a > m1 « m2 requires that k2 be numerically greater than α, m1, or m2 in the SI or Imperial system of measurement unit.

[0088] Figure 28 shows a typical relative displacement of the preferred mode when it meets the time-dependent gravitational acceleration profile

[0089] After the constant go is suppressed at time to within 0 < t < T, there will be a gravity anomaly Δg that occurs at T > t0. The solution term that carries the gravity anomaly is

[0090] in this way, any gravity anomaly with Δg > 0 will not be detected as it will generate a negative relative displacement. The expression above is positive if Δg is positive and t > T. Thus, the preferred mode has two advantages: (i) it suppresses the constant gravitational background and (ii) it rejects the positive gravity anomaly.

[0091] The modality's ability to reject the positive gravity anomaly is suitable for hydrocarbon exploration. Most, if not all, oil and gas-bearing porous rock systems have densities less than the bottom density for the constant bottom g0. Constant background suppression is also suitable for hydrocarbon exploration as the products of standard gravity analysis using a LaCoste-Romberg gravimeter or total tensor gradiometer are gravity anomaly maps. Standard gravity analyzes require a constant background subtraction and correction for local topography variations. The present modality performs the subtraction and correction dynamically as the sensor performs the analysis of an aircraft.

[0092] The magnitude of relative displacement due to gravity anomaly is equal to

[0093] The mass of the sphere in the modality is approximately 0.25 grams, while k2 is estimated to be 1.0 Newton/meter. Assuming a gravity anomaly of 10-5 meter/s2 (1 milligal), one obtains

[0094] It would be a challenge to detect this small magnitude of displacement in the field, let alone measured, using completely mechanical means. There can be many sources of noise when generic equipment is deployed in the field, and by suppressing all sources of noise there will be a huge measurement barrier to overcome. It should be noted that a gravity anomaly of 10-5 m/s2 (1 milligal) represents the typical current measurement limit of gravimetry (see, I. Marson, "A short walk along the gravimeters path", International Journal of Geophysics, 2012 , 687813, 2012).

[0095] The constant background suppression technology provided by the modality can effectively block any quasi-steady-state noise source. In the mathematical model presented, it can be considered that g0 represents any noise source in the time-dependent gravitational acceleration profile.

[0096] The present analysis shows that the suppression time is given by

[0097] for the noise source with a magnitude g0. Therefore, in general, one wants to have

[0098] in order to have t0 as short as possible for noise suppression to work using the present modality. in the limit-

[0099] For a noise source g0, its suppression depends entirely on the initial velocity of the sphere, vi(0), which, in practice, cannot be readily controlled by an external means for the present modality. vi(0) corresponds to the speed of the sphere as the preferred mode hovers above an area that has a gravitational acceleration g0. However, maximum suppression can be achieved at the α^0 limit, yielding

[00100] However, the limit α^0 can never be reached since even without any spring connecting the ball and pin, i.e. k2 = 0, there will always be a drag force that will dampen the relative displacement oscillation in modality. Therefore, it is necessary to use

[00101] as the suppression time limiting behavior t0. For a measurement limit of 10-5 m/s2 (1 milligal), one needs vi(0) to be at most 0.1 mm/s in order to have t0 on the order of 1 second. This is achieved in the present preferred embodiment by making the spring constant of the pin as rigid as possible. The preferred embodiment has an effective pin spring constant of about 104 N/m by placing the ball approximately 15 mm away from the base of the pin and using copper as the material for the pin. Copper has a Young's modulus of 117 GPa and the radius of the pin is 0.725 mm.

[00102] In the preferred embodiment, the magnitude of the relative displacement is converted into a voltage signal across the electrical junction. The dynamic transducer model is a sphere that acts on the top test mass, which is inserted into a solid pin that acts as the bottom test mass. The schematic diagram of the pin and ball assembly is shown in Figures 1 to 4. Under static equilibrium, the inner surface of the ball will contact the surface of the pin and the spacing between the inner surface of the ball and the surface of the pin is in order of oxide thickness to allow the ball to oscillate independently of oscillation of the pin. A thin dielectric spacer is placed between the pin and the ball, which is represented by the spring characterized by k2 and the damper characterized by α in Figure 5.

[00103] The static capacitance between the ball and the pin is given by the formula for the capacitance of concentric cylinders

[00104] where L is the length of the sphere, R1 is the radius of the pin, and R2 is the inner radius of the pin. The relative displacement ^ between the pin and the ball can be represented by a change in R2 and the resulting change in capacitance is

[00105] The factor ln(R2/Ri) < 1 provides an amplification gain for the static capacitance C0 and thus compensates for the low value of Ç(t)/R2 < 1. It is beneficial to have a low value of R2 and bring it closer to R1. As a result, the preferred modality has small size and sensitive detection. Since capacitance C is related to voltage V through

[00106] where Q is the electric charge, we get

[00107] where the voltage change ΔV is the output signal of the dynamic gravity transducer.

[00108] Given that ΔC is a function of time, one obtains

[00109] Due to V0 = Q/C0, we have

[00110] Therefore, the voltage output is proportional to the relative displacement Ç(t). Therefore, the submillimeter range of ^Δg = 0.25 micrometer can be amplified with the gain

[00111] In the present preferred embodiment, the gain is about 1 due to the small ratio ^(t)/R2. It is estimated that the preferred modality generates ln(R2/Ri) = 1/8. Miniaturizing the preferred mode will increase the gain much more.

[00112] Although the output voltage signal ΔV(t) is directly proportional to the relative displacement Ç(t), the inverse process to obtain the gravity anomaly magnitude Δg would require a thorough characterization of (i) pin assembly and geometry of the sphere including spacing distances for every sensor used; and (ii) spring constants and damping constant of the pin and ball assembly, which significantly depend on the manufacturing processes.

[00113] The baseline voltage V0 may change if the electrical current dQ/dt does not remain constant over time or the static capacitance C0 changes, eg from charge build-up in the oxide layer. A calibration procedure involving the electrical charging and discharging cycles of a stationary model in Figure 7A can be performed in order to determine the charging and discharging time constants. These capacitance time constants should be smaller than the mechanical time constants α/k2 in order to achieve correct interpretations.

[00114] The main advantage of placing the model in continuous constant altitude rectilinear motion is that the geological source of the gravity anomaly will produce a sharper profile of gravitational force in the vertical direction. Continuous motion gives the following gravitational profile used in the analysis of the model 0<t<T g (go + Δg t > T .

[00115] To see this sharpening effect, one can consider the model as a pointed particle of mass, m1 + m2, located at (x',y',z'), which gravitationally interacts with a subsurface region shaped like a rectangular parallelepiped of volume Q = abc. The gravitational potential energy is

[00116] where the position (x, y, z) belongs to a point in the subsurface volume and p is the subsurface density. G is the gravitational constant. If the subsurface thickness c can be assumed to be less than the location depth z0 of the subsurface, the gravitational force in the vertical (z) direction will be

[00117] where h is the vertical distance between the vertical coordinate of the sensor z' and the location of the top edge z0 of the subsurface volume. h in practice is the sum of the altitude of the aircraft carrying the transducer and the vertical depth of the subsurface volume. If the subsurface volume Q has a lower density p than the background density p0, then the volume Q contributes to the decrease in the constant gravitational background g0. This is the origin of the gravity anomaly Δg

[00118] where pQ is the mass of the subsurface porous rock system that produces the anomaly. The additional effects on Δg due to subsurface stresses can be described by the volume change ΔQ, which occurs when compression and/or stress is applied to the rock system. Density change Δp can be correlated with subsurface tensions, ie volume change ΔQ. It is therefore possible that ΔQ and Δp are indicative of subsurface voltage changes that occur simultaneously and cooperatively to produce a detectable Δg.

[00119] When the aircraft carrying the transducer moves with a constant altitude velocity of v, one can write

[00120] where x0 < 0 is the initial horizontal position of the transducer. The gravity anomaly Δg becomes explicitly weather dependent.

[00121] As the aircraft speed v increases, Fz'(t) becomes more acute without affecting its magnitude. Thus, for sufficiently high aircraft speed, the gravity anomaly Δg can be described as occurring abruptly at t > T.

[00122] The time-dependent gravity anomaly Δg(t), has an optimal vertical distance given by

[00123] where the gravitational field magnitude is the maximum, which is obtained by differentiating the function

[00124] with respect to h, setting it to zero and solving the resulting equation for optimal hopt vertical distance. b is the linear size of the hydrocarbon deposit in the direction perpendicular to the aircraft movement. h in practice is the sum of the altitude of the aircraft carrying the sensor and the vertical depth of the subsurface volume. Assuming that the aircraft altitude is typically 3,000 meters, the gravity-based transducer system in such an embodiment can detect basin-level hydrocarbon deposits.

[00125] The explicit time dependence of Δg, which is detected through the model, allows the sensor not to conserve energy. As the sensor flies along a flight line and encounters multiple Δg anomalies, it accumulates mechanical energy from the work done by the Δg anomalies.

[00126] where d^ is the relative displacement inside the sensor. The integral is performed over an anomaly, while the summation includes all anomalies that the sensor finds along its flight path.

II.3. Discussion

[00127] As discussed, the oscillatory components of the relative displacement Ç(t) are omitted from the above mathematical model to demonstrate some fundamental features involved in transducer operation. However, it is important to note that continuous rectilinear motion induces and maintains the oscillation of the transducer pin and ball complex at their natural frequencies through dynamic interaction with the gravity field. Such oscillatory behavior allows the transducer to selectively react to gravity anomalies on a small spatial scale while eliminating filters in order to eliminate the slowly varying gravity background. Such oscillatory behavior also allows for the accumulation of minute gravity variations across resonance so that recognizable waveform interference for gravity anomalies is displayed in the signal.

[00128] However, the oscillatory behavior does not allow the transducer to settle when it is in continuous rectilinear motion. Consequently, on the one hand, a high sample rate for data acquisition to follow the evolution of small-scale gravitational patterns can be used without the need to establish the test mass equilibrium condition; on the other hand, dynamic detection of gravity anomalies becomes more complex compared to conventional static gravimeters. It is thus necessary to explore the acquired signal in terms of wave attributes that include the biased development of amplitude, frequency, phase, and so on. It is pattern recognition rather than every single point value that is used in data interpretation. This implies that the transducer in this invention trades measurement accuracy to gain superior detection sensitivity and superior efficiency in identifying anomalous areas of gravity for potential hydrocarbon deposits.

[00129] The transducer of this invention detects gravitational anomalies due to the physical contrast of density and tension between the geological discontinuities and the bottom. In addition to subsurface density changes, principal stresses also play a significant role in the development of subsurface conditions associated with discontinuities (see JS Bell, "In situ stresses in sedimentary rocks - part 2: applications of stress measurements", Geoscience Canada, 23, 135 to 153, 1996). In general, maximum horizontal stress (SHmax) controls fluid migration and minimum horizontal stress (Shmin) dictates fluid expulsion. As the fluid moves into the reservoir rocks, the SHmax will decrease and the Shmin will increase as the pore pressure increases. Reduction of shear and increase in permeability distribution in reservoirs (controlled by SHmax) will lead to a condition of higher subsurface homogeneity. Where significant stress changes occur in rocks at fractures and faults or in reservoirs at the edges, they will be accompanied by a significant density change. Investigations of gravity gradients and stress changes have shown that there is a physical relationship between the two at small scales (see TJ Hayes et al., "A gravity gradient method for characterizing the post-seismic deformation field for a finite fault", Geophysical Journal International, 173, 802 to 805, 2008).

[00130] For transducer response, changes in subsurface homogeneity are critical in producing the physical contrast of interest. In general, porous rocks and the presence of fluid generate a decrease in volume density, which will produce a lower gravitational field. If more fluid is accumulated in a trap with high porosity and effective permeability distribution, then the reservoir system becomes more homogeneous. Consequently, there is an increase in spatial subsurface homogeneity. Based on such considerations, a geological (or non-anomalous) bottom condition can be characterized by a random distribution of Δp with hydrostatic pressure gradients. An anomalous condition of interest can be characterized by an isolated homogeneous distribution of Δpπ due to the presence of fluid and intensified porosity typically limited by abnormal stress gradients. The anomalous condition can also be characterized by a marked reduction in shear stress within the reservoir and a reorientation of the horizontal principal stresses around it.

[00131] The most significant physical contrast that the transducer "perceives" is at the beginning of the anomaly, which occurs due to the change in rock properties and the increase in anomalous fluid volume. The negative gravity anomaly produced by the presence of the body of fluid will induce a relative displacement of the transducer components and affect the state of resonance. As a result, the transducer responds strongly to the edges of the anomaly.

[00132] To summarize, in response to small-scale anomalous conditions in gravitational acceleration, the modality is shaped to employ a reduced proof mass assembly to minimize inertial effects and to allow high-frequency interaction with the gravity field at a high-altitude, high-speed survey environment, to allow mechanical instability to enhance detection sensitivity, to utilize rectilinear motion to continuously accumulate the Δg needed to resolve reservoir scale features and to obtain patterns wave-based signal via electromechanical transduction for analysis as opposed to standard magnitude measurement in traditional gravimetry.

[00133] In hydrocarbon exploration, the five main criteria evaluated are source, migration, trap, reservoir and seal. The transducer of this invention can react to anomalous density and voltage conditions produced by the combined presence of trap, reservoir and seal. Therefore, it can be employed as a powerful gravity-based tool to provide information about conductive areas for fluid capture in the sedimentary column.

[00134] A feature of a described embodiment is that it includes dynamic signal integration while in motion. All gravimeters and gravity gradiometers present take static measurements, that is, the sensor does not need to be in motion and therefore such instruments (1) cannot perform dynamic signal integration or detect energy accumulation over time; (2) they do not have the ability to selectively respond to energy changes induced by subsurface tension (perturbations of each subsurface discontinuity); (3) cannot sample gravitational field vibration signals at a high sample rate (eg 2000 samples per second); and (4) they do not have the ability to identify the presence of captured fluids located in the subsurface.

[00135] In one embodiment, there is a gravity transducer system comprising: a junction comprising a first metal and a second metal other than the first metal, wherein the junction forms a resonant cavity; a particle characterized by a de Broglie wave, the particle being contained within the resonant cavity; a phonon wave inside the resonant cavity, the de Broglie wave is coupled to the phonon wave; a power supply to apply electrical power across the junction; a sensor that can detect resistance, voltage, or current, where the sensor is electrically connected to the junction, the sensor produces a read signal; and a recording system for recording the read signal. In an alternative, the particle is not trapped in a lattice structure. In another alternative, the system additionally comprises an accelerometer. In an alternative, the recording system comprises a geographic positioning system (GPS). In one embodiment, the system further comprises a vehicle that can move the transducer system. In an alternative, the vehicle is an airplane. In an alternative, the recording system comprises a mapping system for mapping the location of the vehicle. In one embodiment, the joint comprises: a conductive ball having a longitudinal hole therethrough; and a conductive pin having a dielectric coating, the pin being located in the longitudinal hole to form the electrical junction. In an alternative, the ball and pin are produced from metal and the dielectric comprises a metal oxide. In one embodiment, the metal oxide comprises silver oxide. In one embodiment, the ball comprises a sandwich comprising a copper or gold layer formed between the first and second alloy layers. In another embodiment, the power supply is a voltage source and the voltage is between 3 volts and 9 volts.

[00136] In another embodiment, there is a method to detect changes in orientation or localized variations of a gravitational field associated with subsurface tension, the method comprising: creating a resonant cavity; capturing a particle in the resonant cavity; applying an electric field across the particle in the resonant cavity to create an electrical junction; exposing the junction to changes in orientation or localized variations of a gravitational field; detecting resistance, voltage, or current across the junction to produce a read signal characteristic of orientation changes or localized variations of a gravitational field associated with subsurface voltage; and recording the read signal; and analyzing the signal to detect changes in orientation or localized variations of a gravitational field. In one embodiment, the method further comprises moving the captured particle in the resonant cavity through the gravitational field. In an alternative, the movement comprises moving the captured particle in the resonant cavity in a vehicle. In another embodiment, the movement comprises moving the captured particle in the resonant cavity in a plane. In an alternative, recording comprises recording the read signal as a function of time. In another embodiment, recording comprises recording the read signal as a function of the geographic position of the captured particle in the resonant cavity. In one embodiment, the analysis comprises analyzing signal amplitude, signal frequency, or signal character and signal pattern.

[00137] In another embodiment, there is a method for detecting a hydrocarbon deposit, the method comprising: providing a gravity transducer to detect a change in a gravity field; moving the gravity transducer through the atmosphere or a land above the hydrocarbon deposit; detecting a change in gravity field to produce a gravity change signal indicative of the hydrocarbon deposit; record the severity change signal; and analyzing the gravity change signal to detect the hydrocarbon deposit. In an alternative, the movement is accomplished by placing the gravity transducer in a vehicle and moving the vehicle. In one embodiment, the method further comprises tracking the position of the vehicle and the recording comprises recording the position of the vehicle. In an alternative, the analysis comprises correlating the recorded gravity change signal with the vehicle's position. In one embodiment, the movement comprises placing the transducer on an aircraft and flying the aircraft over the depot. In one embodiment, the method further comprises tracking the geographic position of the aircraft and recording the tracked position. In another embodiment, the method further comprises displaying the real-time position of the aircraft. In another embodiment, the display comprises displaying a planned flight line and flight line deviations. In another embodiment, the display comprises displaying the planned flight line and deviations on the windshield of the aircraft. In another embodiment, the method further comprises monitoring the rotation of the aircraft along a horizontal plane to provide a roll signal, recording comprises recording the roll signal, and the analysis comprises using the roll signal to improve the quality of the roll signal. severity change. In one embodiment, the flight comprises flying the aircraft at an altitude of between 0.3 km and 6.1 km (1,000 ft and 20,000 ft). In another embodiment, the method comprises integrating the change in severity signal dynamically over time. In another embodiment, the method further comprises detecting the accumulation of energy in the signal over time. In another embodiment, the signal is sampled at a sample rate of 1000 samples per second or more.

[00138] There is also a method for detecting underground fluid captured under a layer of earth, the method comprising: providing an underground fluid transducer that can detect captured underground fluid; moving the transducer through the atmosphere or a land above the captured fluid; detecting the captured fluid to produce a captured fluid signal indicative of the captured fluid; recording the captured fluid signal; and analyzing the captured fluid signal to detect the captured fluid. In one embodiment, the movement is accomplished by placing the transducer in a vehicle and moving the vehicle. In another embodiment, the movement comprises placing the transducer on an aircraft and making the aircraft fly over the depot. In another embodiment, the method further comprises tracking the geographic position of the aircraft and recording the tracked position. In another embodiment, the method further comprises monitoring the rotation of the aircraft along a horizontal plane to provide a roll signal, the recording comprising recording the roll signal and the analysis comprising using the roll signal to improve the quality of the gravity change signal. In another embodiment, the flight comprises flying the aircraft at an altitude of between 0.3 km and 6.1 km (1,000 feet and 20,000 feet). In one embodiment, the captured fluid is a hydrocarbon.

[00139] In another embodiment, the invention provides: a gravity transducer system comprising: a joint comprising a first metal and a second metal, said joint forming a resonant cavity due to mechanical vibration of the pin assembly and ball; a power supply for applying electrical power across said junction; a sensor that can detect resistance, voltage or current, said sensor being electrically connected to said junction, said sensor producing a read signal; and a recording system for recording said read signal. In one embodiment, the gravity transducer further comprises a plane that can move said transducer system in a rectilinear motion. In another embodiment, the joint comprises: a conductive sphere having a longitudinal hole therethrough; and a conductive pin having a dielectric coating, said pin being located in said longitudinal hole to form said electrical junction. In another embodiment, there is a pin and ball assembly that can produce relative displacement between said ball and said pin under said rectilinear motion of said aircraft. In another embodiment, the ball and pin are produced from metal and said dielectric comprises a metal oxide. In another embodiment, there is an oxide layer between the pin and ball, which oxide layer comprises silver oxide, copper oxide or other metal oxide. In another embodiment, the sphere comprises a sandwich structure comprising a copper or gold layer formed between the first and second alloy layers. In another embodiment, the power supply is a voltage source and the voltage is between 3 volts and 9 volts.

[00140] The invention also provides a method for detecting orientation changes or localized gravitational field variations associated with changing subsurface densities and stresses, the method comprising: creating a resonant cavity due to mechanical vibration of the pin assembly and sphere, with mechanical vibration representing the relative displacement between the sphere and the pin; applying an electric field across the junction in the resonant cavity to create an electric junction; exposing the joint to changes in orientation or localized variations of a gravitational field through the relative displacement between the sphere and the pin; detecting the voltage across the junction to produce the signal characteristics read from changes in orientation or localized variations of a gravitational field; acquiring changes in orientation or localized variations of a gravitational field continuously from a moving airplane without the need to establish a state of static equilibrium; use mechanical instability to enhance detection sensitivity and search effectiveness; explore the high-altitude, high-velocity interaction with a gravitational field, allow small oscillating test masses to gain access to the high-frequency domains of the gravitational field; act as a mechanical transducer to quickly respond and convert displacement energy for electrostatic charge distribution and as a capacitance transducer to modulate the output through integration; record the read signal; and analyzing the signal to detect changes in orientation or localized variations of a gravitational field associated with changes in voltage or changing subsurface densities. In one embodiment, recording comprises recording the signal read as a function of time.

[00141] The invention also provides a method for detecting the hydrocarbon deposit, the method comprising: providing a gravity transducer that depends on the relative displacement between the ball and the pin to detect a change in a gravitational field; moving the gravity transducer through the atmosphere or on land above the hydrocarbon deposit in a straight line motion; detecting a change in the gravitational field through electromechanical conversion across the electrical junction to produce a voltage signal indicative of the hydrocarbon deposit; eliminate the constant background gravitational field through relative displacement; record the severity change signal; explore where-based detection patterns as opposed to standard magnitude measurement; and analyzing the gravity change signal to detect the hydrocarbon deposit. In one embodiment, the flight comprises flying the aircraft at an altitude of up to 3,000 meters. In another embodiment, altitude is a function of the size of the hydrocarbon deposit.

[00142] A practical gravitational detector has been described, and the detector is stable, compact, robust and can be operated at room temperature.

[00143] Any part of any of the embodiments described herein may be combined with any part of any of the other embodiments. Equivalent structures and processes may be substituted for the various structures and processes described; the sub-processes of the method of the invention may, in some cases, be carried out in a different order; or a variety of different materials and elements can be used. Consequently, the invention should be interpreted to encompass any and all innovative features and combination of innovative features present in and/or contained by the described apparatus and gravity transducer methods.III. EXAMPLES OF HYDROCARBID READING RESULTS

[00144] To verify that the system according to the present invention works, flights were produced over several distinct potentials of hydrocarbon sites and the results compared to previous knowledge of the fields. The first of these fields is the Canadian onshore carbonate field referred to as the Ladyfern gas field in BC, Canada. Found in 2000, the Ladyfern field was estimated to contain 1.5 Tcf of natural gas reserves. Three lines of flight were performed in different directions to confirm the relationship of porous areas to the sensor signal. The Ladyfern gas field is enclosed within a carbonate barrier reef with preserved porosity through a leaching and dolomitization process. Faults and boundary fracture systems are transient in nature. Based on seismic, dolomitization and capture are not readily visible, although decay characteristics are relatively clear.

[00145] Ladyfern is an accumulation of natural gas housed in a stratigraphic trench - Devonian slave point reef. The fading of productive reservoirs developed through burial of digenesis called hydrothermal dolomitization ("HTD"). Funnels and antithetical faults associated with the proximity of the Hay River dextral transformation system are believed to have acted as conduits for the hydrothermal fluids. The aggressive nature of HTD digenesis has created a series of 'decay' or 'collapse' features in and around the reef, which are readily visible through seismic studies.

[00146] Figures 11 to 13 show the sensor sials obtained from two flights performed over the Ladyfern field and one performed over the Burnt Timber gas field, AB, Canada. Figures 11 to 13 each show the output signal in volts versus time of flight. The output voltage is normalized to be between zero and 1 volt. The resulting sensor signals indicate subsurface geological changes and anomalies that are indicators of potential hydrocarbon reservoirs. A very strong correlation of the distribution of captured reservoirs was observed. In this field, it was difficult to identify pockets of carbonate using seismic alone, and the readout system described here provided good corroboration of reservoir opportunities.

[00147] Figure 11 shows a signal from sensor 600 developed along the maximum voltage line over British Columbia aircraft. In 602 the signal begins to appear showing a change in the geological approach. Sharp peaks at 604 indicate stress fractures and a geological shift indicated by arrow 606. The curve can be better understood by viewing it as a whole. It is seen that there is a strong anomaly at 614 contained by similar signals 608 and 620 on each side. Following the broad line interpretations discussed below, it was interpreted that this is a hydrocarbon reserve in area 615 with typical approaches to 610 and 619. At 618 the signal shows elevation out of the anomaly. Area 615 corresponds to an area of wells drilled. You can also see a minor anomaly at 625 indicated by bar 626. This is an unperforated area. At 630, a signal decline is observed indicating that the aircraft is leaving the anomalous area.

[00148] Figure 12 is a 630 signal developed with the same sensor as used in Figure 11, but in the Rocky Mountains and also along the maximum voltage line. Here the geological change is indicated by the sharp peak at 632, which is marked by the arrow 633. The signal begins to rise at 634 along the 636 direction. The structures in parentheses are at 642 and 654 in areas 640 and 658, respectively. A 650 anomaly is indicated by the signal dropping to 646 in area 644. The signal drops to 664 indicating a geological shift indicated by arrow 660. Overall, said signal is much more fractured, as shown at 638 and 646 which indicates that the ground is more fractured.

[00149] Figure 13 is a 670 signal developed over the same anomaly as the 614 anomaly of Figure 11, except along the minimum voltage line. The same anomaly is shown at 672 in area 674.

[00150] Figures 14, 15 and 16 show signals developed in an R&D test flight over the "La Jarilla" oil field in Comodoro-Rivadiva, Argentina. This particular series is shown illustrating that different sensors will not show identical signals. Figure 14 shows screen 700 as shown by mapping computer 216. Screen 700 shows the "La Jarilla" field at 707 and several smaller fields at 720 and 722. The flight identification number is shown at 712 and the direction of the flight is shown at 714. The raised area is shown at 710, and the timeline is shown at 714. Figures 15 and 16 show the same area and time covered, but with different sensors.

[00151] When comparing Figures 15 and 16, it is seen that a geological change site 734 in Figure 15 and 750 in Figure 16 and the beginning of an anomalous area is shown differently. In Figure 15 it is indicated by a sharp peak at 730, and in Figure 16, it is indicated by a signal increase at 752. The local geological change 736 in Figure 15 and 758 in Figure 16 is shown similarly. as minor peaks 738 in Figure 15 and 755 in Figure 16. The anomaly is shown by a descent at 741 and 742 in area 766 in Figure 15 and a single descent at 762 in area 00 740 in Figure 16. The end of the anomaly area is shown at 746 in Figure 15 for a frequency shift and amplitude shift. This is also shown by a change in frequency and amplitude deviation at 770 in Figure 16, although the change is not pronounced. These curves show what is important is the changes in the signals, not the absolute values of the signals. This will be clearly seen in the Signal Interpretation section below.

IV. SYSTEM OPERATIONIV. 1. Aircraft Tracking and Communication Systems

[00152] Aircraft tracking and communication systems consist of two parts. The first part is a "flight path tracking system" that gives the registry operator on the aircraft and ground staff the ability to track the flight path and ensure the aircraft is on its intended course. The system updates the aircraft's position every minute. This ensures that the ground crew has access to the plane's location with a high degree of accuracy. The main purpose of the tracking system is to carry out safe flights and allow R&D engineers and, in the future, potential customers, governments and military agencies to accurately control the aircraft during research flights. The system is based on satellite via the iridium network, which allows global access to position data and enables voice and data communications outside cellular coverage areas.

[00153] The second tracking system is connected to GPS navigation and provides a real-time map-based update to the sensor operator monitoring the onboard quality control system. The onboard Novatel GPS System is supplemented by an Omnistar subscription service for Wide Area Differential GPS Corrections. This configuration gives a very high degree of positioning accuracy to data within +/2 meters.IV. 2. Data Recording Systems

[00154] Two computer systems are used to record data independently and simultaneously: the QNX system with 16-bit precision and the WinDaq system with 14-bit precision. All systems are controlled via the main QNX computer. Specifically, the QNX computer maintains automatic synchronization of redundant data acquisition by automatically signaling the start and end of logging within 0.5 seconds. In addition, the QNX computer also records GPS position and elevation information, visual ground references and any other relevant in-flight data needed for proper quality control at the end of the flight. Elevation data in the GPS is used together with DEM data provided by the USGS at the end of the flight to calculate the height of the plane above the ground. This ensures that the flight, preferably taken at 10,000 feet, was carried out within the altitude tolerance limits of the sensors. However, flights can be performed within a range of 1,000 feet and 20,000 feet.

IV. 3. Data Quality Control Systems

[00155] The quality control system incorporates the raw digital output of QNX and the graphical view of the output of the WinDaq acquisition system. Since this is similar to the signal that is used for interpretation, determination of signal quality can be done in flight. The result of the real-time GPS output and the planned flight are compared to ensure minimum deviation. The transverse range, an indicator of how far off the planned course the aircraft is, is monitored in real time during flight by both the operator and pilots. Typically, a cross lane distance within 10 meters is maintained.

[00156] In addition, the quality control system contains supply monitors to ensure proper voltage levels are maintained throughout the data acquisition process. Gauges Accelerometers are also used to control the aircraft's acceleration in the vertical and two horizontal axes during the data acquisition process.

IV. 4. Data Post-Processing Systems

[00157] At the end of the flight, the QNX system automatically transfers all data to an external disk. Raw data is verified to ensure correct record lengths. In particular, the data is verified to ensure that both the QNX and WinDaq acquisition systems have recorded the raw data without any problems.

[00158] Raw data in hexadecimal format is processed to verify data consistency and then reformatted for entry into the DADiSP engineering spreadsheet. DADiSP is a commercial interactive graphical spreadsheet, a visually oriented software package for the display, management, analysis and presentation of scientific and technical data. It can be used to manipulate, edit, reduce, transform, visualize and analyze technical data. DADiSP can handle and simplify the large volumes of data sent by the sensor system. As mentioned above, scanned sensor output contains 2000 points per second and flights can average around 10,000 seconds, resulting in a data volume of 1GB per flight or more in raw form.

[00159] Once data is uploaded to DADiSP, it can average more than 6GB per flight.

[00160] This large volume of data from two systems of record can be handled by DADiSP in an efficient way.

IV. 5. Flight Planning Process

[00161] The overall sensor survey flight planning process begins by researching and understanding the following:

[00162] 1) Maps - Topographic and aviation maps of the target area are prepared in paper and digital form.

[00163] 2) Sensor Technology Requirements - Certain parameters must be followed to obtain reliable quality data. These include long straight segments, large turning radius and low turbulence. As a general rule, in one modality, the minimum linear length is 100 km, the minimum turning radius is 25 km, and the acceleration is not greater than 1 g.

[00164] 3) Aircraft base of operations - selected based on the following criteria: proximity to the survey area, runway length (minimum 5000 feet), fuel availability (A1 jet with Prist), flight planning, security, accommodation and communications facilities.

[00165] 4) Other flight restrictions - these include both regulatory agency and geographic considerations as follows:

[00166] • Air traffic control rules that include departure and entry vectors, permit approval processes, and IFR flight rules.

[00167] • Air Force permits required for restricted and prohibited airspace.

[00168] • Military restrictions that include hostile regions, border buffer zones, and altitude restrictions.

[00169] • Geographic restrictions, including mountains and borders.

[00170] • Trends in prevailing weather conditions, including precipitation, winds, storms and clouds.

[00171] The above information is used to start designing each individual target flight line. Flight lines are designed as a sequence of linear segment report points and precisely controlled turn report points.

[00172] In one embodiment, to be ready to fly, there are six processes that are performed: 1) Notification points are loaded into the aircraft's flight management system.

[00173] This system guides the autopilot mode of the aircraft along the planned route to a high degree of accuracy. 2) Notification points are also loaded into the flight tracking sensor system. This allows the onboard sensor operator to track the aircraft's progress to ensure the correct trajectory is followed. This system also provides exact location information for the data being collected.3) Sensors are loaded onto the aircraft and calibrated.4) Pilots present the flight plan with the relevant air traffic control administration.5 ) The pilots and the sensor operator go aboard the aircraft and perform the planned flight.6) After completing the flight, the data is then evaluated to ensure that it meets the established quality standards.

[00174] In this process, it is important to realize that gradual changes in altitude (in the vertical direction) do not adversely affect the sensors; however, a slight rotation of the aircraft along the horizontal plane occurs. The inherent noise within the signal signal originates largely from rotational movements of the aircraft.

IV. 6. Data Interpretation Process

[00175] The process of interpreting the sensor signal is usually performed at headquarters and, in one embodiment, involves three main steps. The first step is the single-line sensor by sensor interpretation. This is followed by the integration of the multi-line sensor signal. Then, the results go through a final classification and mapping.

[00176] The identification and characterization of sensor signals is the ultimate goal of the sensor interpretation process. The sensor signal interpretation process involves recognizing anomalous patterns within the waveform of a sensor signal from its background. The main challenge is to recognize a section of anomalous changes in signal character from a noisy background signal with confidence. Sensor signal interpretation employs several methods to enhance the ability to identify an anomaly, including spatial confirmation of anomalies across multiple sensors, recognition of the specific sequence of changes in signal character, and independent identification of anomalies by multiple teams. For interpretation purposes, the signal is recorded continuously from the beginning of a stable flight path until just before landing. In one embodiment, it is important that the interpretation process captures the relative changes in "baseline" signal characteristics for each sensor throughout the entire flight. This allows recognition of normal background waveforms and changes in specific mode or pattern.

[00177] For a potential anomaly to be submitted for interpretation, it must appear in a plurality of sensors. The use of multiple sensors plays an important role in quality control. For a potential anomaly to become further analyzed, it has to be independently located at the same spatial location in at least two distinct interpreter teams. Also, in all cases, it must occur in a specific sequence.

[00178] A fundamental part of the interpretation process is the recognition of trends and changes in the character of the background signal and the identification of the sensor "mode". A mode is a long-term trend signal that is recognizable to a particular sensor.

[00179] A sensor signal character is considered anomalous over an area when it conforms to a pattern or sequence of idealized responses that are known to correlate with subsurface geological changes. These changes include the development of a fluid-laden reservoir or the existence of structural or stratigraphic trapping mechanisms. Although the sensor signal may indicate the presence of enclosed fluid, it currently cannot distinguish between hydrocarbons and water.

[00180] Anomalies can exist as point changes in signal patterns and are often indicative of a significant change in geology. Area anomalies consist of signal changes with a defined start and end and will have a recognizable shape, sequence, character change, or pattern. Anomalies in the gravity sensor signal are often recognized by frequency changes across different rolling window sizes, trend changes across different window lengths, and magnitude and slope changes across an area.

[00181] Correct recognition of "changes" is a complex process. Fundamentally, the process is complicated by the existence of several background modes for each sensor. The development of anomaly character will depend on the background mode. Also, the character in the sign is relative; that is, initial conditions will affect subsequent sensor responses. For example, crossing a major fault may mask a minor anomaly that follows it closely.

[00182] The result of the sensor data interpretation process is a prospect map, which displays recommendation boxes that describe the spatial extent of the reservoir portion of the geological anomaly within the sensor survey area.

[00183] The following section covering Figures 17 to 24 is a basic description of the most important concepts involved in interpreting SFD data using examples of ideal or near-ideal sensor response. Figures 17 to 24 each show the signal voltage at the ordinates as a function of time along the abscissa. This description is intended to introduce those skilled in the art to the process of interpreting sensor data. The most common anomaly attributes and sequences are presented. All major anomalies can be identified by one of the following generalized interpretation concepts and many less significant anomalies can be identified by an extension, corollary or clustering of these concepts. Since sensors may exhibit stochastic behavior, this description may not apply to all sensors. The present description is centered on the concepts applicable to some of the primary sensors. The concepts can be extended with some variations to other sensors. However, it should be understood that it may be advisable to learn the response of each sensor individually from empirical data. There are many subtle variations of these examples which may or may not change the identification of the anomaly. To serve the above purpose, the emphasis of the present document will be placed on the detailed visual inspection of waveforms, although various signal processing techniques can be applied in the interpretation process.

IV.6.1. Signal Attributes Used in SFD Interpretation

[00184] The following signal attributes are used in the present description for most of the interpretation process: signal amplitude; signal frequency; character and sign pattern. The actual representation of the SFD sensor output is a simple 2D voltage-versus-time graph which therefore implies that each of the above mentioned attributes can be represented by a particular behavior of the sensor voltage output as a function of time. . This section of the document therefore attempts to describe each as applicable to the SFD interpretation process. It is important to note that SFD attributes are not defined in absolute terms. Each of the following terms/attributes refers to a sequence observed over a fluctuation time period, nominally on the order of 10-50 seconds.

IV.6.1.1. Amplitude

[00185] The term "amplitude" as applied to SFD implies a change in the observed average output voltage of the SFD sensor over a given interval. There is no fixed definition of the time interval to use to define the average output voltage, nor is it necessary for the time intervals to be of equal duration. Figure 17 highlights the output voltages and their perceived average values over a series of time intervals. In sections A and B, the mean values shown by arrows 802 and 803 do not appear to have changed; however, the two areas can be distinguished based on the remaining signal attributes: frequency and character. In Section C, the amplitude shown by arrow 806 has changed. This section can be classified as a transition period from A and B to D. The term amplitude, and the quantities and concepts derived from it, such as amplitude change, baseline voltage, etc., therefore, refer to to the voltage value represented by arrows 802, 804, 806 and 808, which are 0.7V in sections A and B, 0.65V in area C and 0.55V in area D, as opposed to the time amplitude value distinct, such as 0.69V at the 6475 date and time. The amplitude and amplitude trends are therefore directly obtained from the average magnitude of the signal voltage in any given time window and play an important role in the identification and classification of the anomaly. Referring to the previous example shown in Figure 17, calculating a moving average using 5 second time intervals over the same signal duration produces the 810 curve of Figure 18. While such a moving average is useful for identifying key trend intervals, in D and E, it tends to obscure the trend of baseline voltages within the time window. These trends often play a role in determining the classification of SFD anomalies. So, in this mode, moving averages are not the best way to analyze the data.

[00186] Figure 19 shows an example of an edge 820 in an SFD signal 812. The edge is an example of a sudden amplitude change between a first area 814 and a second area 818 and may or may not be accompanied by a change in the amplitude. default/background mode. An edge is often used to interpret the sensor transition from one scenario to another - identification of these points is often used to determine the start/end of signal sequences that are used to define anomalies.

IV.6.1.2. Frequency

[00187] The term "frequency", as applied to SFD, implies the number of significant peak-to-peak (Vmax-Vmin) values observed during a given time interval. Significance is determined based on comparison with waveforms before and after the time interval of interest. There is no fixed definition of the time interval to use to define the average output voltage, nor is it necessary for the time intervals to be of equal duration. In most cases, an identified frequency change or deviation will need to be of a length of more than 10 seconds (based on the aircraft's current flight speed) to be considered applicable for SFD interpretation purposes. Consider signal 830 in Figure 20. Areas A and F will fall within the definition of the high-frequency characteristics described earlier, while areas C and D will be considered low-frequency areas. Area G can be considered as an example of a tight-mode signal and, in this case, the notion of frequency, as applied to the SFD, is not relevant. Anomaly identification in this mode will be primarily guided by amplitude and pattern characteristics. In particular, note area E, in which four subareas a, b, c, and d are defined. Within these subareas, the Vmax-Vmin differences and the number of times the particular change described by the Vmax-Vmin event, which happens during the transitions of ab, bc, and cd, will fall into the definition of high frequency and, more appropriately , can be thought of as a frequency transition from ABCD to E. Consequently, only area E will be considered to have high frequency relevant for anomaly identification purposes.

[00188] Signal 840 of Figure 21 shows a transition from a low frequency area (A) to a high frequency area (B) and finally to a sealed mode area (C). It is quite evident that area B is the densest part of the signal. The event described by the change in the mean value of Vmax-Vmin can therefore be simplified by looking at the following two items: it represents a change from a low Vmax-Vmin to a high Vmax-Vmin along the transition from A to B ; and the frequency of the high Vmax-Vmin event is much higher in area B. It can be seen that the inverse transition event (high low Vmax-Vmin) is equally applicable to the interpretation and identification of anomalies. This is a direct consequence of the original observation that single time events and changes in the SFD are usually meaningless and have value only if part of an overall signal development. Frequency and frequency trends are therefore directly recognized by the occurrence and regularity (or lack thereof) of a significant standard deviation change in signal voltage in any given time window and play an important role in the identification and classification of anomalies.

IV.6.1.3. Character and Pattern

[00189] A change in the character of an SFD signal can imply the occurrence of a large and diverse number of events. Character changes can be very loosely related to changes in the average output voltage, but this is not always the case. In general, a pattern change in an SFD sensor output is observed as a deviation or change in a sequence of regularly occurring signal events. These events are a combination of deviations in frequency and amplitude as described above. Most of these discernible pattern changes result from historical research and model crossovers. A character change in general determines the overall shape of the signal as characterized by amplitude, frequency, envelope evolution, etc. A particular waveform consisting of these character changes is visually perceptible in an SFD signal. Some SFD signal events associated with character changes include: a change or deviation in the signal amplitude trend; a change or deviation in the developmental character of the signal - for example, a signal that shows only positive deviations from the perceived baseline moves into a state where it shows both positive and negative deviations; a change or deviation in the pattern of the signal - for example, a signal showing a high-frequency baseline trend moves into a low-frequency baseline trend or a variable-frequency trend; a change or shift in the signal envelope - for example, a signal that exhibits cyclic/periodic behavior for more distinct development. Signal character changes are, therefore, directly obtained by a sequence-oriented combination of the frequency and/or amplitude characteristics, as described above, in any given time window and play an important role in the determination and classification of the anomaly. Some signal pattern changes are illustrated at signal 850 in Figure 22. At arrow 856, it is observed that baseline voltages move up from area 854 to area 860. Also at this point, the response type changes to high frequency, with a development of the waveform to a U-shape, specifically U's 861 and 862, which are accompanied by high frequency, as in 863. Also, when comparing signals on either side of arrow 856, it is observed that the response range changes from mostly above the baseline to either side of the baselines.

[00190] Figure 23 illustrates various signal character changes that are relevant to signal interpretation. The baseline voltage of the signal at 867 is shown at 868. The baseline voltage of the signal at 869 is shown at 870. It is evident that there is a change in character by the fact that the baseline voltages drop. It can be seen that downward development in area 867 changes to high frequency, with upward development only in region 869, which forms a depression in area 866. It is also evident in Figure 23 that the response changes from mostly below the baseline to start to either side of the baseline in region 869 and then back to the high frequency downtrend signal in region 872. These are examples of signal character changes.

IV.6.2. Sequence Identification

[00191] The starting point of the SFD interpretation process is the determination of the start and end of the applicable time windows, i.e. - the date and time at which the change in frequency, amplitude or character/pattern can be observed and/or established. The identification of these time windows can be useful to establish the global signal quality sequences that will eventually be used to identify anomalies. The determination of the anomaly and its subsequent intensity will be determined by the type and sequence of attribute changes observed within and in the immediate periphery of these time windows. Consider the signal sequence shown in Figure 24. It was divided into a succession of time windows - A, B and C, which were differentiated based on a change or deviation in one of the attributes of the primary SFD signal. The transition from area A to area B is defined by the following events. As shown by comparing levels 876 and 872, there is a change in baseline amplitude and a change in signal character due to the fact that the signal changes both trends, i.e., rising trend to flat trend, and change of standard, that is, the directionality of deviations from the baseline. There is also a change in signal frequency when comparing signal 874 with signal 880. Similarly, the deviation from area B to area C is defined by the following events: a change in baseline amplitude, as indicated by the arrows 872 and 886; and a change in signal frequency when comparing the signals at 880 and 884. Determining these sequences is useful in interpreting the signal in relation to anomalous vs. anomalous waveforms. non-anomalous which would then be related to the global classification of the area/areas.

[00192] It should be particularly noted that the signal waveform is a series of continuous changes where the same attributes that determine anomalous areas can also determine areas without anomalies. Signal development along the entire length of the signal is made up of a series of changes to the individual attributes. However, the primary difference between an area and waveform marked as anomalous, when compared to an area or waveform not considered anomalous, is the sequence of changes to the individual attributes. Signal development over the course of a spatial interval will generally comprise a series of possible sequential changes in attributes and the starting point is usually the identification of the beginning and end of a particular development subsection. This is said to be the determination of "time windows".

Claims (31)

1. Gravity transducer system characterized in that it comprises: a junction (470) comprising a first metal and a second metal different from said first metal, said junction (470) forming a resonant cavity, wherein said junction (470) ) comprises a conductive bead (476) having a longitudinal hole therethrough, wherein said joint (470) also comprises a conductive pin (474) having a dielectric coating (472), said pin (474) located in said longitudinal hole to form an electrical junction; a particle (514) typified by a de Broglie wave, said particle contained within the resonant cavity; a phonon wave (530) within said resonant cavity, said de Broglie wave coupled to said phonon wave; a power source (508) for applying electrical energy across said junction (470); a sensor (416) capable of detecting voltage, or current, said sensor being electrically connected to said the junction (470), said sensor producing a detected signal characteristic of a gravitational signal; and a recording system for recording said detected signal characteristic of said gravitational signal. 2. Gravity transducer system according to claim 1, characterized in that said particle (514) is not held in a lattice structure. 3. Gravity transducer system, according to claim 1, characterized in that it comprises an accelerometer. 4. Gravity transducer system, according to claim 1, characterized in that said recording system comprises a geographic positioning system, GPS, (268). 5. Gravity transducer system, according to claim 1, characterized in that it comprises a vehicle capable of moving said transducer system. 6. Gravity transducer system according to claim 1, characterized in that said vehicle is an aircraft (380). 7. Gravity transducer system, according to claim 5, characterized in that said registration system comprises a mapping system to map the location of said vehicle. 8. Gravity transducer system according to claim 1, characterized in that said bead and pin are made of metal, and said dielectric comprises a metal oxide. 9. Gravity transducer system according to claim 8, characterized in that said metal oxide comprises silver oxide. 10. Gravity transducer system according to claim 1, characterized in that said bead (476) comprises a sandwich comprising a copper or gold layer formed between a first alloy layer and a second alloy layer. turns on. 11. Gravity transducer system according to claim 1, characterized in that said power source (508) is a voltage source and said voltage is between 3 volts and 9 volts. 12. Method of detecting orientation changes or localized variations of a gravitational field associated with subsurface stresses, said method characterized in that it comprises: creating a junction (470) of a first metal and a second metal that is different of said first metal, said joint (470) forming a resonant cavity, wherein said joint (470) comprises a conductive bead (476) having a longitudinal hole therethrough, wherein said joint (470) also comprises a pin conductor (474) having a dielectric coating (472), said pin (474) located in said longitudinal hole to form an electrical junction; capturing a particle (514) in said resonant cavity; applying an electric field through said particle (514) ) in said resonant cavity; expose said electrical junction to said orientation changes or localized variations of a gravitational field; detect resistance, voltage, or current at across said electrical junction to produce detected signal characteristics of said orientation changes or localized variations of a gravitational field; recording said detected signal characteristic; and analyzing said signal characteristic to detect said orientation changes or localized variations of a gravitational field associated with subsurface tensions. 13. Method according to claim 12, characterized in that it optionally comprises moving said captured particle (514) in said resonant cavity through said gravitational field. 14. Method according to claim 13, characterized in that moving comprises moving said captured particle (514) in said resonant cavity in a vehicle. 15. Method according to claim 14, characterized in that moving comprises moving said captured particle (514) in said resonant cavity in an aircraft (380). 16. Method according to claim 12, characterized in that recording comprises recording said detected signal characteristic as a function of time. 17. Method according to claim 12, characterized in that recording comprises recording said detected signal characteristic as a function of the geographic position of said captured particle (514) in said resonant cavity. 18. Method according to claim 12, characterized in that analyzing comprises analyzing a signal amplitude, signal frequency, or a signal character and pattern of said signal characteristic. 19. Method of detecting a hydrocarbon deposit, said method being characterized in that it comprises: providing a gravity transducer that depends on an adjustable resonant cavity or relative displacement between a pin (474) and a bead (476) for detecting a change in a gravity field, wherein the bead comprises a conductive bead (476) having a longitudinal hole therethrough, wherein the pin (474) is a conductive pin having a dielectric coating, the said pin (474) located in said longitudinal hole to form an electrical junction; move said gravity transducer through an atmosphere or on earth above said hydrocarbon deposit; dynamically interact with and detect the change in gravitational field through electromechanical conversion through an electrical junction to produce a voltage signal indicative of said hydrocarbon deposit; record said gravity change signal at 2,000 samples per second; and analyzing said gravity change signal to detect said hydrocarbon deposit. 20. Method according to claim 19, characterized in that said movement is performed by arranging said gravity transducer in a vehicle and moving said vehicle. 21. Method, according to claim 20, characterized in that it additionally comprises tracking the position of said vehicle and recording comprises recording said position of said vehicle. 22. Method, according to claim 21, characterized in that analyzing comprises correlating said recorded gravity change signal with said position of said vehicle. 23. Method according to claim 20, characterized in that moving comprises arranging said transducer in an aircraft (380), and flying said aircraft (380) over said depot. 24. Method, according to claim 23, characterized in that it additionally comprises tracking the geographic position of said aircraft (380) and recording said tracked position. 25. Method according to claim 24, characterized in that it additionally comprises displaying the real-time position of said aircraft (380). 26. Method according to claim 25, characterized in that said display comprises displaying a planned flight line and deviations from said flight line. 27. The method of claim 26, wherein said display comprises displaying said planned flight line and said deviations on a windshield of said aircraft (380). 28. Method according to claim 23, characterized in that it additionally comprises monitoring the rotation of said aircraft (380) along a horizontal plane to provide a rotation signal, said recording comprises recording said signal of rotation, and said analysis comprises using said rotation signal to improve the quality of said gravity change signal. 29. Method according to claim 23, characterized in that flying comprises flying said aircraft (380) at an altitude of between 0.3048 kilometers (1,000 feet) and 6.096 kilometers (20,000 feet). 30. Method, according to claim 19, characterized in that it additionally comprises integrating said gravity change signal dynamically with time. 31. Method according to claim 19, characterized in that it additionally comprises detecting the accumulation of energy in said signal over time.

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