An electromechanical integrated electrical connection device for the transmitting coil of the time-domain airborne electromagnetic method

Abstract

In view of the limited load capacity of the flight platform, the present invention proposes an electrical connection device for the electromechanical integration of the transmitting coil of the time-domain airborne electromagnetic method, which includes three main parts: electrical components, an installation barrel, and a connector. The connector includes a hub, an electrode plate, an electrode plate connecting rod, and a device support frame. The electrical components include a resonant capacitor bank, a thyristor radiator, a power supply, and a control circuit board. The transmitting coil is fixed on the installation barrel through the hub, and the electrical components are fixed in the installation barrel through the connector to form an electrical connection device for the transmitting coil. The overall connection of the device is fixed through fastening screws, one part is the connection between the connector and the installation barrel, and the other part is the connection between the electrical components and the connector. The present invention has the characteristics of small size and light weight, greatly reducing the weight of the electromagnetic transmitting coil and improving the efficiency of the system.

Description

Technical Field

[0001] The present invention relates to the technical field of airborne electromagnetic prospecting, and particularly to an electromechanical connection device for a large-depth airborne electromagnetic method transmitting coil that is small in volume, light in weight, and strong in stability. Background Art

[0002] With the progress of society, people's living standards have been continuously improved, and the consumption of various mineral resources has also increased day by day. In recent years, the proven mineral resources in the country are on the verge of exhaustion, and the contradiction between supply and demand has become increasingly acute. Due to China's vast territory and large topographical differences, the mineral resources in areas with good topography and shallow surface have been mined for a long time, and the reserves of mineral resources in these areas have decreased significantly. Therefore, it is necessary to explore areas with relatively complex terrain and difficult direct access for personnel, such as alpine and cold mountainous areas, deserts, gobi in the northwest of the country, alpine forest-covered areas in the northeast, and karst-developed areas in the southwest. Due to the complex and changeable terrain and wide coverage area of these mining areas, the difficulty coefficient of exploration is large, and the traditional land exploration system cannot be effectively used for exploration. To solve the problem of difficult exploration due to complex terrain, the airborne electromagnetic prospecting technology based on Faraday's law of electromagnetic induction has emerged. This method mainly uses a helicopter as a carrying tool, which can overcome the problems of inconvenient operation such as complex terrain and harsh environment. It has the advantages of wide exploration area, high detection efficiency, and large exploration depth, and is widely used in the field of geological exploration.

[0003] The working process of the helicopter airborne electromagnetic method transmitting system is that the helicopter carries an electromagnetic transmitting coil device and flies to a certain height above the ground. A strong primary electromagnetic field is emitted into the air and the ground through the electromagnetic transmitting coil. The underground mineral resources are excited to generate an induced current, and the magnetic field generated by the induced current is called the secondary electromagnetic field. During the on-time and off-time, the receiving coil synchronously collects the primary electromagnetic field in the air, the natural electromagnetic field on the ground, and the secondary electromagnetic field generated by the underground mineral substances. Since the secondary electromagnetic field will have different directions and different time decay characteristics due to the differences in underground mineral substances, and its resource information (such as magnetic permeability, dielectric) can be used to perform inversion calculations on the data to obtain the state characteristics and distribution of underground resources.

[0004] To achieve the purpose of surveying large depths, it is necessary to continuously increase the magnetic moment of the transmitting coil. Due to the limited load-bearing capacity and endurance of the aircraft, the weight of the transmitting coil and the electrical connection device cannot be increased infinitely. Therefore, while controlling the weight of the coil, it is necessary to reduce the volume of the electrical connection device, improving the efficiency of the transmitting system and the transmitted magnetic moment. Currently, abroad, the transmitting coil and the electrical device are separated, resulting in poor system integration and reduced efficiency of the entire electromagnetic exploration system. Therefore, independently developing an electrical connection device with a small volume, light weight, and integrated mechanical and electrical structure is a key technical issue for improving the system efficiency and transmitted magnetic moment in the field of airborne electromagnetic exploration. Summary of the Invention

[0005] To solve the above problems of the limited load-bearing capacity and endurance of the aircraft, the present invention proposes an electrical connection device with integrated mechanical and electrical functions for the transmitting coil of the time-domain airborne electromagnetic method, which has the characteristics of small volume, light weight, and strong stability. This electrical connection device has two major functions. One is that the electrical components of the transmitting circuit part of the airborne electromagnetic transmitting system are installed inside the electrical connection device, and the electrical components include a resonant capacitor bank, thyristors, a thyristor drive circuit board, a communication circuit board, a power supply battery, and switches, etc.; the other is that the head and tail of the airborne electromagnetic transmitting coil are connected through this electrical connection device to form a closed loop, playing the role of integrated mechanical and electrical functions. Without changing the assessment indicators, the weight of the electromagnetic detection coil is greatly reduced. Abroad, the resonant capacitor and the transmitting coil are installed separately, resulting in problems such as instability, large vibration, and uneven stress during lifting and flight. The present invention proposes an installation method with integrated mechanical and electrical functions for the transmitting coil and the electrical device. Compared with abroad, the transmitting efficiency and magnetic moment have been improved.

[0006] The specific technical solutions are as follows:

[0007] An electromechanical integrated electrical connection device for a time-domain airborne electromagnetic method transmitting coil includes seven parts: an installation barrel (2), a hub (3), multiple electrode plates (4), multiple capacitors (5), a device support frame (6), an electrode plate connecting rod (7), and a thyristor radiator (8). Among them, the installation barrel (2) is a hollow cylinder, and both ends of the hollow cylinder are obliquely cut by inclined planes between 30° and 45° with the axis of the hollow cylinder. The hub (3) is provided with three first fixing holes (3-1), a groove (3-2), three limiting holes (3-3), and three second fixing holes (3-4). Among them, the first fixing holes (3-1) are used for assembling with the installation barrel (2), and the three second fixing holes (3-4) are used for assembling the connecting objects installed in the limiting holes (3-3). The electrode plate (4) is provided with an electrode plate fixing hole (4-1) and an electrode plate limiting hole (4-2). The capacitor (5) is a cylinder (5-2), and fixing screw holes (5-1) are respectively provided at the centers of both ends along the axis. The device support frame (6) is provided with three support frame top fixing holes (6-1), a support frame base fixing hole (6-2), and a support frame arc surface (6-3). The electrode plate connecting rod (7) is provided with a connecting rod fixing hole (7-1). The thyristor radiator (8) is provided with four radiator fixing holes (8-1) and two fan fixing holes (8-2). The hub (3), the electrode plate (4), the electrode plate connecting rod (7), and the device support frame (6) form a connector. The specific connection relationship is as follows: The capacitors (5) are evenly distributed along the semicircular contour of the electrode plate (4). The fixing screw holes (5-1) at the left and right ends of the capacitor (5) are respectively assembled with the electrode plate limiting holes (4-2) on both sides of the electrode plate (4). Two electrode plates (4) form a group to fix the capacitors (5) evenly distributed along their semicircular contours. Two electrode plates (4) and the multiple capacitors (5) evenly distributed along their contours form a structure body, and this structure body is axially distributed at both ends inside the installation barrel (2). The right electrode plate (4) of the left structure body and the left electrode plate (4) of the right structure body are assembled through three electrode plate connecting rods (7). The left electrode plate (4) of the left structure body and the right electrode plate (4) of the right structure body are assembled through the electrode plate connecting rod (7). Two device support frames (6) are connected side by side through the electrode plate connecting rod (7) to form an integral body, constituting a group of annular fixing pieces. There are two groups of annular fixing pieces located between the two structure bodies, and the two groups of annular fixing pieces are symmetrically and fixedly connected to the top and bottom of the installation barrel (2).

[0008] The electromagnetic emission coil uses multiple metal conductive pipes to enclose a regular polygon instead of a circle, and the electromagnetic emission coil and the electrical connection device are simple Figure 1 as shown

[0009] This electrical connection device has the advantages of small size, light weight, and strong stability, realizing an integrated electrical and mechanical connection method, and greatly improving the efficiency of the aviation electromagnetic detection system. Description of the Drawings

[0010] Figure 1 Schematic diagram of a 12-sided electromagnetic emission coil and an electrical connection device;

[0011] Figure 2a Front view of the installation barrel;

[0012] Figure 2b Side view of the installation barrel;

[0013] Figure 3 Schematic diagram of the wheel hub;

[0014] Figure 4 Schematic diagram of the electrode plate;

[0015] Figure 5 Schematic diagram of the capacitor;

[0016] Figure 6 Schematic diagram of the device support frame;

[0017] Figure 7 Schematic diagram of the electrode plate connecting rod;

[0018] Figure 8 Schematic diagram of the thyristor radiator;

[0019] Figure 9 Installation diagram of the electrical connection device;

[0020] Figure 10, Metal straight pipe of the electromagnetic emission coil;

[0021] Among them, installation barrel (2), wheel hub (3), first fixing hole (3-1), groove (3-2), limit hole (3-3), second fixing hole (3-1), electrode plate (4), fixing hole (4-1), limit hole (4-2), capacitor (5), fixing screw hole (5-1), cylinder (5-2), device support frame (6), fixing hole at the top of the support frame (6-1), fixing hole at the bottom of the support frame (6-2), arc surface of the support frame (6-3), electrode plate connecting rod (7), connecting rod fixing hole (7-1), thyristor radiator (8), radiator fixing hole (8-1), fan fixing hole (8-2). Detailed Implementation Manner

[0022] An electromechanical connection device for a time-domain airborne electromagnetic method transmitting coil, comprising seven parts: an installation barrel, a hub, an electrode plate, a capacitor, a device support frame, an electrode plate connecting rod, and a thyristor radiator. Among them, the hub, the electrode plate, the electrode plate connecting rod, and the device support frame form a connector. The hub is provided with a through hole, three fixing holes, three limiting holes, an arc surface, and a rope groove; the electrode plate is provided with fixing holes and limiting holes; the capacitor is provided with a cylinder and fixing screw holes; the device support frame is provided with fixing holes and an arc surface; the electrode plate connecting rod is provided with fixing holes; the thyristor radiator is provided with fixing holes, fan fixing holes, and a concave surface. The connector fixes the electrical components in the installation cylinder through assembly.

[0023] The selected installation barrel and hub are made of an alloy material, with both ends cut at an oblique angle of 30° - 45°. The electrode plate and the electrode plate connecting rod are made of copper. Other types of metals can also be selected for the materials used. Attached Figure 3 In the hub, there are three limiting holes for placing three turns of the coil. When the number of turns of the coil changes, the number of limiting holes should also change accordingly according to the number of turns of the coil used.

[0024] Specific connection method: The transmitting coil of the airborne electromagnetic method transmitting system has a total of three turns, and each turn is a regular dodecagon structure composed of 12 metal conductive tubes (such as Figure 1 )). The beginning and end of the three turns of the coil are connected through this electromechanical connection device. The connection relationship of the connector includes three parts: crimping, positioning, and hoisting. First, connect the electrical components to the connector, and then install them in the installation barrel. The electrical components refer to the devices used in the transmitting circuit part of the airborne electromagnetic method transmitting system, including a resonant capacitor bank, thyristors, a thyristor drive circuit board, a communication circuit board, a power supply battery, and a switch, etc.; then embed the hub into both sides of the installation barrel, and then place the coil into the limiting hole 3 - 3 in the hub and connect it to the wire led out from the corresponding pin of the electrical component in the installation barrel. The coil, the hub, the connector, and the installation barrel are fixed by screws. On the outer side of the hub, there is a groove for fastening other equipment after tying a rope. The supporting circuit is installed inside the supporting structure through the connector to support the operation of the capacitor and the thyristor; the symmetrically installed device support frames are fastened and supported by multiple support rods; the metal conductive straight tubes are made of hollow metal tubes.

[0025] The crimping part is: filling a high-viscosity substance at one end of the copper sleeve for the head and tail of the coil, and then using corresponding instruments to crimp them into one body. The positioning part is: using screws to position and fix the through holes on the copper sleeve and the through holes on the hub, and using screws to position and fix between the mounting barrel and the electrode plate. The hoisting part is that the rope groove on the hub is used to assemble the rope for hoisting. The advantages of this connection method are: good electrical conductivity, convenient installation, not easy to bend at the connection, integration of electrical components and mechanical structures, and improvement of the efficiency of the emission system.

Claims

1. An electromechanical integrated electrical connection device for a time-domain airborne electromagnetic method transmitting coil, characterized in that: It includes seven parts: an installation barrel (2), a hub (3), multiple electrode plates (4), multiple capacitors (5), a device support frame (6), an electrode plate connecting rod (7), and a thyristor radiator (8). Among them, the installation barrel (2) is a hollow cylinder, and both ends of the hollow cylinder are obliquely cut by inclined planes between 30° and 45° with the axis of the hollow cylinder; three first fixing holes (3-1), a groove (3-2), three limiting holes (3-3), and three second fixing holes (3-4) are provided on the hub (3). Among them, the first fixing hole (3-1) is used for assembling with the installation barrel (2), and the three second fixing holes (3-4) are used for assembling the connectors installed in the limiting holes (3-3); an electrode plate fixing hole (4-1) and an electrode plate limiting hole (4-2) are provided on the electrode plate (4); the capacitor (5) is a cylinder (5-2), and fixing screw holes (5-1) are respectively provided at the centers of both ends along the axis; three support frame top fixing holes (6-1), a support frame base fixing hole (6-2), and a support frame arc surface (6-3) are provided on the device support frame (6); a connecting rod fixing hole (7-1) is provided on the electrode plate connecting rod (7); four radiator fixing holes (8-1) and two fan fixing holes (8-2) are provided on the thyristor radiator (8); the hub (3), the electrode plate (4), the electrode plate connecting rod (7), and the device support frame (6) form a connector; the connection relationship is as follows: the capacitors (5) are evenly distributed along the semicircular contour of the electrode plate (4). The fixing screw holes (5-1) at the left and right ends of the capacitor (5) are respectively assembled with the electrode plate limiting holes (4-2) on both sides of the electrode plate (4). Two electrode plates (4) form a group and are used to fix the capacitors (5) evenly distributed along their semicircular contours. Two electrode plates (4) and the multiple capacitors (5) evenly distributed along their contours form a structure body. This structure body is axially distributed at both ends inside the installation barrel (2). The right electrode plate (4) of the left structure body and the left electrode plate (4) of the right structure body are assembled through three electrode plate connecting rods (7). The left electrode plate (4) of the left structure body and the right electrode plate (4) of the right structure body are assembled through the electrode plate connecting rod (7); two device support frames (6) are connected side by side through the electrode plate connecting rod (7) to form a whole, constituting a group of annular fixing parts. There are two groups of annular fixing parts located between the two structure bodies, and the two groups of annular fixing parts are symmetrically and fixedly connected to the top and bottom of the installation barrel (2) respectively; the head and tail of the aviation electromagnetic emission coil are connected through this electrical connection device to form a regular polygon closed loop; the number of turns of the aviation electromagnetic emission coil matches the number of limiting holes (3-3) of the hub (3). When the number of turns of the coil changes, the number of limiting holes also changes accordingly.

2. The electrical connection device for the electromechanical integration of the transmitting coil in the time-domain airborne electromagnetic method according to claim 1, characterized in that: The hubs (3) are respectively installed at both ends of the installation barrel (2) to form a support structure.

3. An electrical connection device for the electromechanical integration of a transmitting coil in time-domain airborne electromagnetic method according to claim 1, characterized in that: The thyristor radiator (8) is placed in the middle of the two groups of annular fixing parts and is assembled with the support frame base fixing hole (6-2) through the radiator fixing hole (8-1).

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