Airborne geophysical survey system
An airborne ElectroMagnetic (EM) survey system wherein the system includes; first, a series of transmitter coils, which induce a primary (EM) field into the earth resulting in a secondary EM field being created in any sub-surface electrically conductive bodies; and second, a set of three orthogonal receiver coils which detect the secondary EM field. Multiple transmitter coils through which an electric current is pumped, form part of the structural, aluminum framework of a multi-rotor drone. The receiver sensor may be an EM induction sensor, comprised of multi-turn, copper windings, mounted inside an aerodynamic bird and separated by non-conductive sphalerite, which acts as an electrical insulator to limit self-induction and capacitance. Additionally a lighter-than-air balloon may be used to add vertical lift and increase a pendulum effect.
1. An airborne geophysical survey system comprising:
an aircraft comprising:
a frame including at least one annular element of conductive material which provides structural support to the frame;
a plurality of lifting assemblies supported at spaced apart positions across the frame, the lifting assemblies each comprising a rotor arranged to provide lift when rotated and a motor arranged to drive rotation of the respective rotor;
a flight controller arranged to control the lifting assemblies independent of one another so as to provide unmanned flight to the aircraft;
a transmitting source comprising said at least one annular element of the frame connected to a power source such that said at least one annular element also functions as a transmitting coil arranged to generate a primary electromagnetic field; and
a receiver system supported on the frame of the aircraft and including a receiver sensor arranged to sense a ground response to the primary magnetic field generated by the transmitting source in a geophysical survey.
2. The system according to claim 1 wherein the receiver sensor is supported on the frame of the aircraft so as to be concentric with said at least one annular element.
3. The system according to claim 1 wherein the motor associated with each lifting assembly is an electric motor driven by a battery in which the battery is suspended at a location spaced below the frame of the aircraft so as to function as a ballast.
4. The system according to claim 1 wherein the motor associated with each lifting assembly is an internal combustion motor operatively connected to a fuel supply, the fuel supply being suspended at a location spaced below the frame of the aircraft so as to function as a ballast.
5. The system according to claim 1 wherein said at least one annular element comprises a plurality of annular elements connected conductively in series with one another to commonly define the transmitting coil.
6. The system according to claim 5 wherein at least one of the annular elements defines an outermost circumference of the frame.
7. The system according to claim 5 wherein the frame includes a plurality of auxiliary frame members which are connected between the plurality of annular elements so as to form a truss structure and support the plurality of annular elements relative to one another, the auxiliary frame members being electrically isolated from the annular elements.
8. The system according to claim 1 wherein said at least one annular element comprises a plurality of segments arranged to be selectively coupled to one another in series in a circumferential direction such that the segments can be readily disassembled and reassembled.
9. The system according to claim 8 wherein each segment extends generally linearly between opposing ends such that said at least one annular element is generally polygonal in shape.
10. The system according to claim 1 further comprising a gas envelope containing a lighter-than-air gas therein which is connected to the frame of the aircraft so as to be located spaced above the frame.
11. The system according to claim 10 further comprising a ballast member supported on the frame of the aircraft so as to be suspended at a location spaced therebelow.
12. The system according to claim 1 wherein the receiver system comprises:
at least one receiver coil arranged to sense said ground response;
said at least one receiver coil comprising a plurality of windings of conductive wire supported about a common receiver axis of the receiver coil in which each winding is separated from other ones of the windings by a separation distance which is greater than a diameter of the conductive wire.
13. The system according to claim 12 wherein the receiver system further comprises a solid, non-conductive material spanning between the plurality of windings of said at least one receiver coil and wherein the solid, non-conductive material has a specific gravity of greater than 2.
14. The system according to claim 1 wherein the receiver system comprises:
at least one receiver coil arranged to sense said ground response; and
a magnetometer arranged to sense a magnitude of a magnetic field in the ground responsive to the primary magnetic field.
15. The system according to claim 14 wherein the magnetometer is suspended from the frame of the aircraft at a location spaced below said at least one receiver coil.