Electromagnetic receiving device for aircraft and aircraft

Abstract

The utility model discloses an electromagnetic receiving device for an aircraft. The electromagnetic receiving device comprises a connecting main body, an extension part, a carrying platform and a receiving coil, the connecting body is suitable for being connected with an aircraft. The multiple extension parts are arranged, one end of each extension part is connected with the connecting body and extends in the direction away from the connecting body, and the extension parts are suitable for deforming in the extension direction of the extension parts; the carrying platform is respectively connected with the plurality of extension parts, and a plurality of fixing points are formed on the carrying platform; the receiving coil is arranged on the carrying platform and is fixed with the carrying platform through a plurality of fixing points. The receiving coil of the electromagnetic receiving device can keep the stability in the electromagnetic exploration process, deviation during signal receiving is avoided, and the accuracy of the exploration result is guaranteed.

Description

Technical Field

[0001] The utility model relates to the technical field of semi-aerial geophysical exploration, in particular to an electromagnetic receiving device for an aircraft and an aircraft. Background Art

[0002] In the fields of geological surveys, mineral resource exploration, and environmental monitoring, the use of manned or unmanned aircraft equipped with electromagnetic exploration equipment is common. During exploration, the aircraft must be equipped with a receiver for the electromagnetic exploration equipment, primarily consisting of a receiving host for collecting and storing data and a receiving coil for receiving electromagnetic signals. The receiving coil is typically suspended below the aircraft. However, during flight, the receiving coil exhibits significant instability. Under the influence of wind and its own vibrations, it cannot maintain a horizontal operating state and may even spin and deflect, causing motion noise. This can lead to deviations in the received electromagnetic signal, affecting the accuracy of the exploration results. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, one object of the present invention is to provide an electromagnetic receiving device for an aircraft, which can keep the receiving coil of electromagnetic exploration in a stable working state during exploration, thereby ensuring the accuracy of the exploration results.

[0004] The utility model proposes an electromagnetic receiving device for an aircraft, comprising: a connecting body, an extension component, a carrying platform and a receiving coil; the connecting body is suitable for being connected to the aircraft; the extension component is constructed in a plurality of ways, and one end of each extension component is connected to the connecting body and extends in a direction away from the connecting body, and the extension component is suitable for being deformed in its extending direction; the carrying platform is respectively connected to the plurality of extension components, and a plurality of fixing points are formed on the carrying platform; the receiving coil is arranged on the carrying platform and is fixed to the carrying platform through the plurality of fixing points.

[0005] According to the electromagnetic receiving device of the embodiment of the present application, since the extended component can be deformed, the receiving coil can be kept horizontal relative to the ground; since the receiving coil is connected to the carrying platform at multiple points, the receiving coil can be effectively prevented from spinning or deflecting; the receiving coil of the electromagnetic receiving device of the present application can maintain its own stability during the electromagnetic exploration process, avoiding deviations in the received signal, thereby ensuring the accuracy of the exploration results.

[0006] According to some embodiments of the present application, the extension component includes: a fixed rod and a movable rod, one end of the fixed rod is connected to the connecting body; the movable rod is sleeved or accommodated in the fixed rod and moves relative to the fixed rod in its extension direction to adjust the length of the extension component, and the end of the movable rod is connected to the mounting platform.

[0007] According to some embodiments of the present application, one end of the fixed rod is hingedly connected with the connecting body, and the end of the movable rod is hingedly connected with the mounting platform.

[0008] According to some embodiments of the present application, the mounting platform is configured as a polygon or a circle, and a plurality of hingedly connected portions corresponding to the plurality of extension members are formed on the mounting platform and are arranged at intervals on the outer periphery of the mounting platform.

[0009] According to some embodiments of the present application, the mounting platform comprises an outer frame portion and a grid portion, the outer frame portion is provided with a plurality of hingedly connected portions on the outer periphery thereof, and the grid portion is arranged in the outer frame portion and fixedly connected with the outer frame portion, and a plurality of fixed points are formed on the grid portion.

[0010] According to some embodiments of the present application, the mounting platform is configured as a plurality of mounting platforms arranged at intervals in the height direction, and the electromagnetic receiving device further comprises an electromagnetic receiving unit, the electromagnetic receiving unit is detachably arranged on one of the mounting platforms, and the electromagnetic receiving unit is electrically connected with the receiving coil.

[0011] According to some embodiments of the present application, the connecting body comprises a support frame and a connecting rod, the support frame is connected with the plurality of extension members respectively, and the connecting rod is arranged on the support frame and is provided with a connecting piece for connecting with the aircraft.

[0012] According to some embodiments of the present application, the connecting rod is configured as a plurality of connecting rods arranged at intervals, and at least one of the connecting rods is movable relative to the support frame to adjust the distance between two adjacent connecting rods.

[0013] According to some embodiments of the present application, the connecting piece is slidably arranged in the extension direction of the connecting rod.

[0014] The utility model also proposes an aircraft, include: aircraft body and electromagnetic receiving device, electromagnetic receiving device is configured as any above -mentioned electromagnetic receiving device and is detachably connected with aircraft body through connecting body.

[0015] The additional aspects and advantages of the utility model will be partly given in the following description, some will become obvious from the following description, or be understood through the practice of the utility model. BRIEF DESCRIPTION OF DRAWINGS

[0016] The above and / or additional aspects and advantages of the utility model will become apparent and more readily appreciated from the following description of the embodiments, with reference to the following drawings, in which:

[0017] Figure 1 It is the structure schematic diagram of electromagnetic receiving device for aircraft according to some embodiments of the present application.

[0018] REFERENCE NUMERALS

[0019] Connecting body 10; supporting frame 11; connecting rod 12; connecting member 13;

[0020] Carrying platform 20; outer frame 21; grid portion 22; fixing point 221; fence 23;

[0021] Extension part 30. DETAILED DESCRIPTION

[0022] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0023] Reference below Figure 1 An electromagnetic receiving device for an aircraft according to an embodiment of the present invention is described.

[0024] The present invention proposes an electromagnetic receiving device for an aircraft, comprising: a connecting body 10, an extension component 30, a carrying platform 20 and a receiving coil; the connecting body 10 is suitable for being connected to the aircraft; the extension component 30 is constructed in plurality, and one end of each extension component 30 is connected to the connecting body 10 and extends in a direction away from the connecting body 10, and the extension component 30 is suitable for being deformed in its extension direction; the carrying platform 20 is respectively connected to the plurality of extension components 30, and a plurality of fixing points 221 are formed on the carrying platform 20; the receiving coil is arranged on the carrying platform 20 and fixed to the carrying platform 20 through the plurality of fixing points 221.

[0025] According to the electromagnetic receiving device of the embodiment of the present invention, the extension member 30 is connected to the connecting body 10 and extends in a direction away from the connecting body 10. In combination with the actual application scenario of the electromagnetic induction device, under normal conditions, the extension direction of the extension member 30 is perpendicular to the ground, the connecting body 10 is connected to the top of the extension member 30, and the carrying platform 20 is connected to any position of the extension member 30. Because the extension member 30 is constructed in multiples, and each extension member 30 is suitable for deformation in its extension direction, adjusting the deformation of each extension member 30 so that they cooperate with each other can make the connection point of each extension member 30 and the carrying platform 20 located in the same horizontal plane, thereby keeping the carrying platform 20 horizontal and the receiving coil horizontal relative to the ground. In addition, because the carrying platform 20 is formed with multiple fixing points 221 with the receiving coil, it can effectively prevent the receiving coil from spinning or offsetting.

[0026] According to the electromagnetic receiving device of the embodiment of the present application, since the extension component 30 can be deformed, the receiving coil can be kept horizontal relative to the ground; since the receiving coil is connected to the carrying platform 20 at multiple points, the receiving coil can be effectively prevented from spinning or deflecting; the receiving coil of the electromagnetic receiving device of the present application can maintain its own stability during the electromagnetic exploration process, avoiding deviations in the received signal, thereby ensuring the accuracy of the exploration results.

[0027] According to some embodiments of the present application, the extension member 30 includes a fixed rod and a movable rod. One end of the fixed rod is connected to the connecting body 10. The movable rod is sleeved or accommodated within the fixed rod and moves relative to the fixed rod in its extension direction to adjust the length of the extension member 30. The end of the movable rod is connected to the mounting platform 20. In this embodiment, the extension member 30 includes the fixed rod and the movable rod. The fixed rod and the movable rod cooperate to form a telescopic rod. When the movable rod moves relative to the fixed rod, the telescopic rod extends or contracts to change the length of the extension member 30.

[0028] In this embodiment, a locking member may be provided between the fixed rod and the movable rod. After adjusting the relative position of the fixed rod and the movable rod, the locking member is used to restrict further movement of the fixed rod relative to the movable rod, thereby maintaining the length of the extension member 30. A limit member may also be provided between the fixed rod and the movable rod in this embodiment to limit the range of relative movement of the fixed rod and the movable rod, thereby limiting the length range of the telescopic rod. In actual use, the extension member 30 is suspended below the aircraft via the connecting body 10. During installation, the telescopic rod can naturally extend to its maximum length due to gravity. At the same time, gravity can maintain the same length during exploration flight. Manual adjustment and locking of the extension member 30 are no longer required, simplifying the installation process of the extension member 30, improving assembly efficiency, and facilitating the use of the electromagnetic receiving device.

[0029] It should be noted that in actual applications, to prevent interference from the aircraft with the receiving coil, a certain distance must be maintained between the receiving coil and the aircraft. This places a considerable length requirement on the extension member 30, reaching 20 meters or longer in some embodiments. This requires the fixing rod to be at least 10 meters long, making the extension member 30 difficult to manufacture and assemble during use. To address this issue, in some embodiments, the extension member 30 can be constructed as a combination of multiple telescopic rods, which can be detachably connected in sequence to achieve a wide range of length adjustment for the extension member 30 and facilitate storage and transportation of the extension member 30 after exploration.

[0030] Furthermore, the extension component 30 of the present application may be constructed as a carbon fiber structure to ensure that the extension component 30 has strong ductility and high hardness while avoiding being affected by electromagnetic signals.

[0031] According to some embodiments of the present application, one end of the fixed rod is hingedly connected to the connecting body 10, and the end of the movable rod is hingedly connected to the carrying platform 20. In this embodiment, the connection points of the extension component 30 with the connecting body 10 and the carrying platform 20 are all hinged, allowing the extension component 30 to rotate through a certain angle relative to the connecting body 10, giving the electromagnetic induction device a certain degree of freedom and greater adaptability to different flight environments during aircraft takeoff and flight. At the same time, because the carrying platform 20 is connected to multiple extension components 30, when the extension components 30 rotate relative to the carrying platform 20 and the connecting body 10, the carrying platform 20 can always remain parallel to the plane of the connecting body 10, maintaining the stability of the receiving coil's posture.

[0032] In some embodiments, one end of the fixed rod can also be configured to be fixedly connected to the connecting body 10, and the end of the movable rod can be configured to be fixedly connected to the carrying platform 20. In this embodiment, the extension member 30 can always remain relatively stationary relative to the aircraft, and the carrying platform 20 always remains parallel to the plane where the connecting body 10 is located. The electromagnetic receiving device of this embodiment has strong stability under normal working conditions, avoiding shaking that affects electromagnetic signal reception and affects the normal flight of the aircraft. Furthermore, the fixed connection between the extension member 30 and the connecting body 10 and the carrying platform 20 can be achieved by providing a locking member at the hinge. In this way, the degree of freedom of connection between the extension member 30 and the connecting body 10 and the carrying platform 20 can be selectively adjusted to adapt to more working environments and working conditions.

[0033] According to some embodiments of the present application, the carrying platform 20 is constructed in a polygonal or circular shape, and is formed with hinged connection portions corresponding one-to-one with multiple extension components 30. The multiple hinged connection portions are arranged at intervals around the periphery of the carrying platform 20. In this embodiment, the carrying platform 20 is connected to the multiple extension components 30 via the multiple hinged connection portions arranged at intervals around the periphery, so that the multiple extension components 30 surround the carrying platform 20 in the middle, providing a certain degree of protection for the structure supported by the carrying platform 20 without affecting the structural layout of the carrying platform 20.

[0034] According to some embodiments of the present application, the carrying platform 20 includes an outer frame 21 and a mesh portion 22. The outer periphery of the outer frame 21 is provided with multiple hinged connection portions; the mesh portion 22 is disposed within the outer frame 21 and fixedly connected to the outer frame 21, and multiple fixing points 221 are formed on the mesh portion 22. In this embodiment, the carrying platform 20 is hingedly connected to the extension member 30 via the outer frame 21 and connected to the supported structure via the mesh portion 22. In specific applications, the receiving coil can be fixed to the mesh portion 22 using structures such as cable ties, making the installation method of the receiving coil diverse and arbitrary, and simplifying its installation process. In addition, the main structure of the carrying platform 20 is the mesh portion 22, which can effectively reduce the deadweight of the carrying platform 20, reduce the load-bearing pressure of the aircraft, and improve the stability of the electromagnetic receiving device. At the same time, it can provide a large number of fixing points 221 for selection, which can accommodate receiving coils of different sizes.

[0035] In addition, the extension component 30 of the present application is constructed as a rod, and the main body of the carrying platform 20 is constructed as a grid component, which can effectively reduce the contact area with the air and reduce the air resistance during flight, thereby making the overall structure more stable.

[0036] Furthermore, the carrying platform 20 may also be constructed as a carbon fiber structure to ensure that the carrying platform 20 has strong ductility and high hardness while avoiding being affected by electromagnetic signals.

[0037] Furthermore, in some embodiments, the carrying platform 20 further includes a fence 23. The fence 23 is disposed on the outer frame 21 and connected to the outer frame 21 and each extension member 30. The fence 23 extends in the same direction as the extension member 30 and surrounds the grid portion 22 of the carrying platform 20. The provision of the fence 23 in this embodiment prevents the structure carried by the carrying platform 20 from loosening and sliding, thereby improving the safety of the device.

[0038] According to some embodiments of the present application, the mounting platforms 20 are configured as a plurality of platforms spaced apart in the height direction. The electromagnetic receiving device further includes an electromagnetic receiving unit, which is detachably mounted on one of the mounting platforms 20 and electrically connected to the receiving coil. In this embodiment, the electromagnetic receiving unit refers to a host device or apparatus capable of collecting and storing electromagnetic signal data. In specific applications, the receiving coil generates an instantaneous response in a changing magnetic field and transmits the responsive electrical signal to the electromagnetic receiving unit, which collects, records, and processes the signal for subsequent analysis. In practice, the electromagnetic receiving unit is generally directly fixed to the aircraft. In this embodiment, by mounting the electromagnetic receiving unit on the mounting platform 20, the electromagnetic receiving unit and the receiving coil can be integrally mounted on the aircraft, simplifying the installation process of the electromagnetic receiving unit. Furthermore, the compatibility of the connection structure between the electromagnetic receiving unit and the aircraft need not be considered. The electromagnetic induction device of the present application is highly adaptable to different aircraft.

[0039] It should be noted that the mounting platform 20 for mounting the receiving coil should be constructed as the lowest one among the multiple mounting platforms 20 so that the receiving coil can receive the electromagnetic signal reflected by the ground without any obstruction.

[0040] According to some embodiments of the present application, the connection body 10 includes: a support frame 11 and a connecting rod 12, wherein the support frame 11 is respectively connected to a plurality of extension components 30; the connecting rod 12 is disposed on the support frame 11, and a connecting member 13 for connecting to an aircraft is formed on the connecting rod 12. In this embodiment, the connection body 10 includes the support frame 11, which facilitates connection with the extension components 30 through the support frame 11; further, the hinge points between the support frame 11 of the connection body 10 and the extension components 30 and the hinge points between the outer frame portion 21 and the extension components 30 correspond one-to-one to enable connection between the extension components 30, the connection body 10, and the mounting platform 20. The connection body 10 of this embodiment also includes the connecting rod 12 and the connecting member 13 to provide a specific connection and fixing mechanism for connecting the connection body 10 to the aircraft.

[0041] According to some embodiments of the present application, the connecting rods 12 are constructed to be multiple and spaced apart from each other, and at least one connecting rod 12 can be moved relative to the support frame 11 to adjust the distance between two adjacent connecting rods 12. In this embodiment, by providing multiple connecting rods 12 to provide multiple connecting members 13 connected to the aircraft, the spacing of the connecting rods 12 can be adjusted to accommodate different aircraft. In this embodiment, since multiple connecting members 13 cooperate with each other to achieve the connection between the connecting body 10 and the aircraft, the connection method is diverse, such as a snap-on method, where the connecting members 13 are correspondingly constructed as mutually cooperating claws; or a fixed connection method, where the connecting members 13 are correspondingly constructed as bolts or other structures; or a combination structure with a certain degree of freedom and a locking member that limits the degree of freedom is adopted. The electromagnetic induction device of this embodiment has a high adaptability to different aircraft.

[0042] In some embodiments, the support frame 11 is composed of a plurality of support beams connected end to end in sequence, and the two ends of the connecting rod 12 are respectively connected to the two support beams of the support frame 11. At least two support beams of the support frame 11 connected to the connecting rod 12 are constructed as slide rails, and the two ends of the connecting rod 12 are constructed as sliders that cooperate with the slide rails to enable the connecting rod 12 to move relative to the support frame 11. Furthermore, the connecting body 10 also includes a locking mechanism that can selectively limit the movement of the connecting rod 12 relative to the support frame 11 to achieve the fixation of the position of the connecting rod 12. It should be noted that the key to connecting with the aircraft lies in the connecting member 13. The aircraft has requirements for the specific position of the connecting member 13, but there is no absolute restriction on the relative position between the connecting rods 12. The connecting rods 12 can be constructed to be parallel to each other or to be intersecting.

[0043] According to some embodiments of the present application, the connecting member 13 is slidably arranged in the extension direction of the connecting rod 12. In this embodiment, the sliding of the connecting member 13 in the extension direction of the connecting rod 12 can adapt to the specific connection structure of the aircraft and improve the adaptability of the connecting body 10. Furthermore, the connecting body 10 also includes a locking mechanism that can selectively limit the movement of the connecting member 13 relative to the connecting rod 12 to achieve the fixation of the position of the connecting member 13. Furthermore, a plurality of connecting members 13 can be provided on a connecting rod 12 to cooperate with each other to connect to the aircraft. The plurality of connecting members 13 can slide along the extension direction of the connecting rod 12 to adjust the position of the connection point between the connecting body 10 and the aircraft, thereby adjusting the relative position of the connecting body 10 and the aircraft so that the center of the plurality of connecting members 13 is close to or located on the centerline of the center of gravity of the overall structure of the electromagnetic receiving device, so that the electromagnetic receiving device is stabilized by the tension of the connecting body 10 and is not easily deformed or unstable due to eccentric force.

[0044] Furthermore, Figure 1The specific structure of the electromagnetic receiving unit and the receiving coil is not shown. When installing the electromagnetic receiving unit and the receiving coil, they should be installed in the center of the mounting platform 20 as much as possible to ensure that the structure is evenly and stably stressed.

[0045] The present invention also provides an aircraft, comprising: an aircraft body and an electromagnetic receiving device. The electromagnetic receiving device is constructed as any of the aforementioned electromagnetic receiving devices and is detachably connected to the aircraft body via a connecting body 10. Due to the provision of the aforementioned electromagnetic receiving device, the aircraft of this embodiment can reduce exploration errors during electromagnetic exploration, ensuring the accuracy of exploration results. Furthermore, the aircraft is less susceptible to air resistance and wind during the exploration process, thus exhibiting a certain degree of adaptability to the flight environment.

[0046] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation to the present invention.

[0047] In the description of the present invention, "first feature" and "second feature" may include one or more such features.

[0048] In the description of the present invention, “plurality” means two or more.

[0049] In the description of the present invention, a first feature being “above” or “below” a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact via another feature therebetween.

[0050] In the description of the present invention, a first feature “above”, “above” and “above” a second feature includes the first feature being directly above and obliquely above the second feature, or simply means that the first feature is horizontally higher than the second feature.

[0051] Throughout this specification, reference to terms such as "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples" means that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the illustrative use of the above terms does not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0052] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and purpose of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. An electromagnetic receiving device for an aircraft, characterized in that: include: a connecting body, the connecting body being adapted to be connected to the aircraft; an extension component, wherein the extension component is constructed in plurality, and one end of each extension component is connected to the connecting body and extends in a direction away from the connecting body, and the extension component is suitable for deforming in the extension direction thereof; A carrying platform, the carrying platform is connected to the plurality of extension components respectively, and a plurality of fixing points are formed on the carrying platform; A receiving coil is provided on the carrying platform and is fixed to the carrying platform via a plurality of fixing points.

2. The electromagnetic receiving device for aircraft according to claim 1, characterized in that: The extension component comprises: a fixing rod, one end of which is connected to the connecting body; A movable rod is sleeved or accommodated in the fixed rod and moves relative to the fixed rod in its extension direction to adjust the length of the extension component. The end of the movable rod is connected to the carrying platform.

3. The electromagnetic receiving device for aircraft according to claim 2, characterized in that: One end of the fixed rod is hinged to the connecting body, and the end of the movable rod is hinged to the carrying platform.

4. The electromagnetic receiving device for aircraft according to claim 2, characterized in that: The carrying platform is polygonal or circular in structure, and hinge connection parts corresponding to the plurality of extension components are formed on the carrying platform. The plurality of hinge connection parts are arranged at intervals on the periphery of the carrying platform.

5. The electromagnetic receiving device for aircraft according to claim 4, characterized in that: The carrying platform includes: an outer frame portion, wherein a plurality of hinge connection portions are provided on the outer periphery of the outer frame portion; A grid portion is arranged in the outer frame portion and fixedly connected to the outer frame portion, and a plurality of fixing points are formed on the grid portion.

6. The electromagnetic receiving device for aircraft according to claim 5, characterized in that: The carrying platform is configured as a plurality of platforms spaced apart in the height direction; the electromagnetic receiving device further comprises: An electromagnetic receiving unit is detachably disposed on one of the carrying platforms, and is electrically connected to the receiving coil.

7. The electromagnetic receiving device for aircraft according to claim 1, characterized in that: The connecting body includes: a support frame, wherein the support frame is connected to the plurality of extension components respectively; A connecting rod is provided on the support frame, and a connecting piece for connecting with the aircraft is formed on the connecting rod.

8. The electromagnetic receiving device for aircraft according to claim 7, characterized in that: The connecting rods are structured to be multiple and spaced apart from each other, and at least one of the connecting rods can be moved relative to the support frame to adjust the distance between two adjacent connecting rods.

9. The electromagnetic receiving device for aircraft according to claim 8, characterized in that: The connecting member is slidably arranged in the extending direction of the connecting rod.

10. An aircraft, characterized in that: include: Aircraft body; An electromagnetic receiving device, wherein the electromagnetic receiving device is constructed as the electromagnetic receiving device according to any one of claims 1 to 9 and is detachably connected to the aircraft body through the connecting body.

Images