A transmit coil frame structure

Abstract

The utility model discloses a kind of transmitting coil frame structures, belong to transmitting coil technical field, comprising: frame structure, the frame structure is polygonal solid frame, is connected by insulating light pipe material;Electromagnetic sensor, the electromagnetic sensor is spherical coil assembly, is set in the frame structure inside;Hanging assembly;This transmitting coil frame structure is by limiting frame structure as polygonal solid frame and with insulating light pipe material integral connection, make whole while maintaining high stiffness significantly reduce weight, binding groove is along edge interval arrangement, hanging rope and connecting rope can be directly embedded and fixed with turn, without additional metal connecting piece, both simplify assembly process, and avoid the additional weight and electromagnetic interference risk brought by metal piece, multiple hanging ropes are gathered into concentrated hanging point in transmitting line frame, and connect with aircraft single point, gravity center concentrates and facilitate quick disassembly and assembly, reduce the number of hanging point, reduce air swing probability.

Description

Technical Field

[0001] This utility model specifically relates to a transmitting coil frame structure, belonging to the field of transmitting coil technology. Background Technology

[0002] The transmitting coil frame structure is a spherical cone-shaped suspension frame specifically designed for transmitting coils in time-domain airborne electromagnetic methods. It consists of fiberglass tubes and polymer suspension ropes, forming a "well"-shaped support frame. Each tube is fixed by a nested adhesive joint through a central cross connector, eliminating the need for bolts or metal fittings. All forces are borne by the suspension ropes that converge at the top point, ensuring the coil maintains geometric stability during flight and preventing electromagnetic interference.

[0003] Existing transmitting coil frame structures generally adopt a planar frame structure made of PVC round pipes or engineering plastic rings, and the transmitting coil frame and receiving coil frame are suspended in layers by metal connectors such as pipe clamps and screws. Due to the limited rigidity of the rings themselves, when the aircraft is in crosswind or maneuvering flight, the frame is prone to significant torsion and swaying, which causes the relative position between the transmitting coil and the receiving coil to change in real time. As a result, the acquired electromagnetic signals drift and become distorted. At the same time, the metal connectors may generate induced current in the magnetic field environment, introducing additional noise and reducing the detection depth and resolution. Utility Model Content

[0004] The purpose of this invention is to address the shortcomings of existing technologies by providing a transmitting coil frame structure to solve the problems mentioned in the background section.

[0005] A transmitting coil frame structure, comprising: The frame structure is a polygonal three-dimensional frame made of insulated lightweight tubing. An electromagnetic sensor, wherein the electromagnetic sensor is a spherical coil assembly disposed inside the frame structure; A suspension assembly, which is connected to the frame structure via connection points, is used to suspend the frame structure below the aircraft. A positioning component, one end of which is connected to the frame structure and the other end of which is connected to the electromagnetic sensor, so that the electromagnetic sensor is suspended and positioned at the center inside the frame structure.

[0006] Furthermore, the frame structure is a triangular prism-shaped emitting wire frame, and the insulating lightweight tubing is a glass fiber hollow tube.

[0007] Furthermore, the connection point is a binding groove spaced along the edge of the transmitting frame, and the binding groove is used for binding connection of the hanging component and the positioning component.

[0008] Furthermore, the electromagnetic sensor includes an internal electromagnetic coil and an external insulating protective ring.

[0009] Furthermore, the insulating protective ring is a hoop ring used to fix the cable; The electromagnetic coil is a receiving coil used to receive signals.

[0010] Furthermore, the positioning component consists of multiple connecting ropes arranged in a ring. One end of each connecting rope is connected to the binding groove on the transmitting frame, and the other end is connected to a slot adapted to be opened on the hoop.

[0011] Furthermore, the suspension assembly consists of multiple suspension ropes, one end of which is connected to the launch frame, and the other end extends upward and converges at the same point to form a centralized suspension point connected to the lower part of the aircraft.

[0012] Beneficial effects: This invention significantly reduces weight while maintaining high rigidity by defining the frame structure as a polygonal three-dimensional frame and connecting it integrally with insulated lightweight tubing. Binding grooves are spaced along the edges, allowing the hanging ropes and connecting ropes to be directly embedded and wound around for fixation, eliminating the need for additional metal connectors. This simplifies the assembly process and avoids the added weight and electromagnetic interference risks associated with metal components. Multiple hanging ropes converge at the transmitting frame to form a centralized suspension point, connecting to the aircraft at a single point. This centralized center of gravity facilitates quick assembly and disassembly, reducing the number of suspension points and lowering the probability of in-flight swaying. The clamp ring acts as an insulating protective ring, maintaining a ring gap fit with the receiving coil. This ensures the cable is orderly fixed and tensioned along the outer peripheral slots, preventing the cable from loosening or swinging during flight. This ensures the receiving coil maintains a spherically symmetrical posture, significantly improving signal consistency and reducing noise. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of this utility model; Figure 2 This is a schematic diagram of the structure of the hanging rope of this utility model; Figure 3 This is a schematic diagram of the structure of the transmitting wire frame of this utility model; Figure 4 This is a partially enlarged structural diagram of the transmitting wire frame of this utility model; Figure 5 This is a schematic diagram of the connecting rope of this utility model; Figure 6 This is a schematic diagram of the receiving coil of this utility model.

[0014] In the diagram: 1. Suspension rope; 2. Transmitter frame; 3. Binding groove; 4. Connecting rope; 5. Receiving coil; 6. Hoop. Detailed Implementation

[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0016] Please see Figures 1-6 As shown, a transmitting coil frame structure includes: The frame structure is a polygonal three-dimensional frame made of insulated lightweight tubing. An electromagnetic sensor, wherein the electromagnetic sensor is a spherical coil assembly disposed inside the frame structure; A suspension assembly, which is connected to the frame structure via connection points, is used to suspend the frame structure below the aircraft. A positioning component, one end of which is connected to the frame structure and the other end of which is connected to the electromagnetic sensor, so that the electromagnetic sensor is suspended and positioned at the center inside the frame structure.

[0017] In this embodiment, the frame structure is a polygonal three-dimensional frame, connected by insulated lightweight tubing, forming a load-bearing skeleton that can hover stably in the air. Multiple connection points are set on the outside of the frame structure, and the suspension assembly forms a reliable suspension system with the frame structure through these connection points, suspending the entire frame structure below the aircraft and maintaining its balance. The electromagnetic sensor, as a spherical coil assembly, is placed inside the frame structure. Its spherical shape maintains a clearance fit with the inner wall of the frame structure, which avoids rigid collisions and allows airflow to pass through to reduce wind resistance. One end of the positioning assembly is fixed to the inner wall or edge of the frame structure, and the other end is connected to the outer wall of the electromagnetic sensor. Through multi-directional tension, the electromagnetic sensor is always located in the center of the frame structure, suppressing swaying and maintaining relative positional stability during flight.

[0018] Please see Figures 1-4 As shown, as a technical optimization of this utility model, the frame structure is a triangular prism-shaped emitting wire frame 2, and the insulating lightweight tube is a glass fiber hollow tube.

[0019] In this embodiment, the launch frame 2 is a triangular prism, which is continuously spliced ​​together from glass fiber hollow tubes along the edges. The tubes are locked at the intersection to form a closed frame that is both lightweight and has sufficient torsional stiffness. The three side edges of the triangular prism frame and the base triangle together form a stable three-dimensional structure, which can effectively resist lateral wind loads and torsional moments when the aircraft is in flight, ensuring overall attitude stability.

[0020] Please see Figures 1-5 As shown, as a technical optimization of this utility model, the connection point is a binding groove 3 spaced along the edge of the transmitting frame 2, and the binding groove 3 is used for binding connection of the hanging component and the positioning component.

[0021] The positioning component consists of multiple connecting ropes 4 arranged in a ring. One end of each connecting rope 4 is connected to the binding groove 3 on the transmitting frame 2, and the other end is connected to a slot in the hoop 6.

[0022] The suspension assembly consists of multiple suspension ropes 1, one end of which is connected to the launch frame 2, and the other end extends upward and converges at the same point to form a centralized suspension point connected to the lower part of the aircraft. In this embodiment, the binding grooves 3 are evenly spaced along each edge of the launch frame 2, with the groove depth and width remaining consistent. This allows the suspending rope 1 and connecting rope 4 to be directly embedded and wrapped around for secure fixing, achieving a reliable connection without the need for additional metal parts. When the aircraft takes off or maneuvers, the binding grooves 3 limit the slippage distance of the ropes, evenly distribute the tension, and suppress the torsion of the frame structure caused by inertia or airflow disturbances. Multiple connecting ropes 4 are arranged in a circular array. One end of each rope passes through the corresponding binding groove 3 and is then folded back and tightened. Its tension can be finely adjusted on-site by adjusting the number of wraps. The other end passes through a pre-set ring 6. The slots are secured again, ensuring that the receiving coil 5 remains suspended at the geometric center of the triangular prism frame. The ropes remain taut during flight, forming a damping system that significantly reduces the sway amplitude of the electromagnetic sensor. The lower ends of multiple suspension ropes 1 are tied to the binding slots 3 on different edges of the transmitting frame 2, and their upper ends converge at a single point to form a concentrated suspension point. This suspension point is connected to the lower lifting lug of the aircraft via a quick hook. The knot at the convergence point uses a double-loop reverse buckle, which facilitates quick assembly and disassembly while maintaining the center of gravity in the air, preventing the frame structure from tilting, and ensuring signal stability and flight safety during the airborne electromagnetic measurement process.

[0023] Please see Figures 1-6 As shown, as a technical optimization of this utility model, the electromagnetic sensor includes an internal electromagnetic coil and an external insulating protective ring.

[0024] The insulating protective ring is a hoop 6, used to fix the cable; The electromagnetic coil is a receiving coil 5, used to receive signals.

[0025] In this embodiment, the receiving coil 5 is formed by tightly winding a continuous cable along a spherical path. The two ends of the coil are led out through insulating sleeves to form signal lines, and the whole is coaxially surrounded by a hoop 6. The hoop 6 is made of glass fiber composite material and is molded in one piece. Several slots are opened on the outer circumference of the hoop 6. The cable can be wound in an orderly manner along the slots and pressed tightly by cable ties to prevent loosening or swinging. When the aircraft flies at a constant speed on the measuring line, the receiving coil 5 maintains a spherical symmetrical attitude under the constraint of the hoop 6, senses the secondary electromagnetic field generated by the underground medium in real time and converts it into a voltage signal, which is transmitted to the airborne control unit through the lead cable to realize continuous high-precision detection of underground targets.

[0026] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0027] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A transmitting coil frame structure, characterized in that, include: The frame structure is a polygonal three-dimensional frame, which is connected by insulating lightweight tubing. The frame structure is a triangular prism-shaped radiating wire frame (2). An electromagnetic sensor, wherein the electromagnetic sensor is a spherical coil assembly disposed inside the frame structure; A suspension assembly, which is connected to the frame structure via connection points, is used to suspend the frame structure below the aircraft. A positioning component, one end of which is connected to the frame structure and the other end of which is connected to the electromagnetic sensor, so that the electromagnetic sensor is suspended and positioned at the center inside the frame structure.

2. The transmitting coil frame structure according to claim 1, characterized in that: The insulating lightweight tubing is a glass fiber hollow tube.

3. The transmitting coil frame structure according to claim 1, characterized in that: The connection point is a binding groove (3) spaced along the edge of the transmitting frame (2), and the binding groove (3) is used for binding connection of the hanging component and the positioning component.

4. The transmitting coil frame structure according to claim 3, characterized in that: The electromagnetic sensor includes an internal electromagnetic coil and an external insulating protective ring.

5. The transmitting coil frame structure according to claim 4, characterized in that: The insulating protective ring is a hoop (6) used to fix the cable; The electromagnetic coil is a receiving coil (5) used to receive signals.

6. The transmitting coil frame structure according to claim 5, characterized in that: The positioning component consists of multiple connecting ropes (4), which are arranged in a ring. One end of each connecting rope (4) is connected to the binding groove (3) on the transmitter frame (2), and the other end is connected to the slot in the hoop (6).

7. The transmitting coil frame structure according to claim 1, characterized in that: The suspension assembly consists of multiple suspension ropes (1), one end of which is connected to the launch frame (2), and the other end extends upward and converges at the same point to form a centralized suspension point connected to the lower part of the aircraft.

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