Patent ID: 12259421

DETAILED DESCRIPTION OF THE EMBODIMENTS

In order to make the purposes, technical solutions and beneficial effects of the present invention clearer, the embodiments of the present invention will be described below with reference to the accompanying drawings. It should be noted that the embodiments in the present application and the features in the embodiments may be combined with each other on a non-conflict basis.

As shown inFIG.2, an embodiment of the present invention provides an airborne electromagnetic signal observation device carried by a UAV, including:an inner frame, an outer frame and a flexible support that are connected to each other. The surface of the outer frame is provided with a plurality of mount points for connecting cables; the flexible support is installed under the UAV, the flexible support is of a multi-spoke umbrella-like structure, and the top of each spoke is connected to a mount point of the outer frame by a cable.

The outer frame is of a hollow closed structure, and the inside of a tube of the outer frame is used to install each electronic unit of a receiver; the surface of the outer frame is provided with one or more cable interfaces, and the cable interfaces are used to connect sensor output signal cables; and the inner frame is used to accommodate an inductive magnetic sensor.

In the embodiment of the present invention, the overall shape of the outer frame includes but is not limited to a circle or a square, and the cross-sectional shape of the outer frame tube includes but is not limited to a circle or a square. The inside of the outer frame tube is used to install each electronic unit of the receiver. The surface of the outer frame is provided with cable interfaces, the number of which depends on the number of sensors accommodated in the inner frame, and the cable interfaces are used to connect sensor output signal cables. The surface of the outer frame is provided with a plurality of mount points for connecting cables. The inner frame is functionally to accommodate an inductive magnetic sensor (air core coil).

In the embodiment of the present invention, the flexible support is of a multi-spoke umbrella-like structure composed of a plurality of semi-rigid tubular or columnar materials, and the number of spokes is the same as the number of mount points designed on the outer frame. The whole flexible support is installed on the UAV. One end of the cable is connected to the top of each spoke, and the other end is connected to the mount point designed on the outer frame of the receiver-sensor integrated structure.

In the embodiment of the present invention, the inner frame and the outer frame are horizontally coplanar and concentric.

In the embodiment of the present invention, the overall shape of the outer frame includes a circle or a square, and the cross-sectional shape of the outer frame tube includes a circle or a square.

In the embodiment of the present invention, the inner frame and the outer frame are connected by a shock absorbing material.

In the embodiment of the present invention, an inner frame and an outer frame are included, and the two frames are connected by shock absorbing material.

In the embodiment of the present invention, the number of cable interfaces on the surface of the outer frame is set according to the number of sensors accommodated in the inner frame.

In the embodiment of the present invention, the inner frame accommodates a single inductive magnetic sensor, or a dual-axis inductive magnetic sensor, or a three-axis inductive magnetic sensor.

In the embodiment of the present invention, the number of spokes in the flexible support is the same as the number of mount points on the outer frame, one end of each cable is connected to the top of the spoke, and the other end is connected to the mount point on the outer frame.

In the embodiment of the present invention, when the inner frame is used to accommodate the single inductive magnetic sensor, the overall shape of the inner frame includes a circle or a square, the cross-sectional shape of the inner frame tube includes a circle or a square, the inside of the inner frame tube is used to install each electronic unit of the inductive magnetic sensor, and the surface of the inner frame is provided with a cable interface for connecting a sensor output signal cable.

When the inner frame is used to accommodate the dual-axis inductive magnetic sensor, the inner frame is composed of two orthogonal tubular frames, one of which is used to observe electromagnetic signals in the advancing direction of the UAV, and the other is used to observe electromagnetic signals in the vertical direction: the respective overall shapes of the two orthogonal tubular frames of the inner frame include circles or squares: the cross-sectional shapes of tubes of the two orthogonal tubular frames of the inner frame include circles or squares, the insides of the two orthogonal tubular frames of the inner frame are used to install each electronic unit of the inductive magnetic sensor, and the surfaces of the two orthogonal tubular frames are each provided with a cable interface for connecting a sensor output signal cable.

When the inner frame is used to accommodate the three-axis inductive magnetic sensor, the inner frame is composed of three orthogonal tubular frames, which are respectively used to observe electromagnetic signals in the advancing direction of the UAV, electromagnetic signals in the vertical direction, and electromagnetic signals in the horizontal direction perpendicular to the advancing direction of the UAV: the respective overall shapes of the three orthogonal tubular frames of the inner frame include circles or squares, the insides of the three orthogonal tubular frames of the inner frame are used to install each electronic unit of the inductive magnetic sensor, and the surfaces of the three orthogonal tubular frames are each provided with a cable interface for connecting a sensor output signal cable.

An embodiment of the present invention further provides an airborne electromagnetic signal observation system carried by a UAV, including: a UAV, and an inner frame, an outer frame and a flexible support that are connected to each other. The surface of the outer frame is provided with a plurality of mount points for connecting cables: the flexible support is installed under the UAV, the flexible support is of a multi-spoke umbrella-like structure, and the top of each spoke is connected to a mount point of the outer frame by a cable.

The outer frame is of a hollow closed structure, and the inside of a tube of the outer frame is used to install each electronic unit of a receiver; the surface of the outer frame is provided with one or more cable interfaces, and the cable interfaces are used to connect sensor output signal cables; and the inner frame is used to accommodate an inductive magnetic sensor.

In the embodiment of the present invention, the inner frame and the outer frame are connected by a shock absorbing material.

Example

In this example, an agricultural plant protection UAV is used to carry the electromagnetic signal observation device proposed in the present invention.

As shown inFIG.2, the flexible support is of a multi-spoke umbrella-like structure composed of 4 carbon fiber tubes, and is integrally installed on an undercarriage of the UAV. The selected carbon fiber tubes as a semi-rigid material can provide sufficient support on the one hand, and can suppress the vibration of the UAV on the other hand. A cable is connected to the top of each carbon fiber tube, and the other end of the cable is connected to a mount point on the outer frame of the receiver-sensor integrated structure. Because the cables are of a flexible material, the vibration of the UAV will be further removed, and can thus be prevented from propagating to the receiver-sensor integrated structure. In addition, it should be noted that the diameter of the circumscribed circle of the flexible support should be much larger than the diameter of the circumscribed circle of the inner frame of the receiver-sensor integrated structure, so that the horizontal swing of the receiver-sensor integrated structure during flight can be effectively avoided.

As shown inFIG.2, the receiver-sensor integrated structure is composed of an inner frame and an outer frame, which are connected by an engineering rubber material. The overall shape of the outer frame is square, and the cross-sectional shape of its tube is also square. In the outer frame, various electronic units of the receiver are distributed, including: a circuit board, a battery, a memory card reader, an indicator light, etc. The memory card reader, the battery, etc. have openings on the surface of the outer frame, so as to facilitate the loading and unloading of the battery and a memory card.

As shown inFIG.2, the inner frame of the receiver-sensor integrated structure is of a single Z-axis mode, and the inner and outer frames are horizontally coplanar and concentric. The overall shape of the inner frame is circular, and the cross-sectional shape of the inner frame tube is also circular. The inside of the inner frame tube is used to install each electronic unit of the inductive magnetic sensor. The surface of the inner frame is provided with a cable interface for connecting a sensor output signal cable.