CN217848294U - Aircraft and antenna boom device thereof - Google Patents

Abstract

The embodiment of the application provides an aircraft and an antenna support device thereof. The antenna bracket device comprises a steering structure, wherein the steering structure comprises a body, two first adjusting surfaces which are arranged in parallel relatively and two second adjusting surfaces which are arranged in parallel relatively, and the first adjusting surfaces are vertically connected with the second adjusting surfaces; each first adjusting surface is provided with m rows and n columns of first fixing pieces, each second adjusting surface is provided with i rows and j columns of second fixing pieces, wherein m, n, i and j are natural numbers not less than 2; the position of the antenna connecting piece is unchanged, and the antenna connecting piece is connected with the first fixing piece or the second fixing piece on different straight lines and used for adjusting the pitching angle or the azimuth angle of the body of the steering structure. This application embodiment can select to be connected with first mounting or with the second mounting through antenna connection spare, is favorable to turning to the structure and carries out one-way adjustment, can do benefit to reduce cost and reduce the operation degree of difficulty.

Description

Aircraft and antenna boom device thereof

Technical Field

The application relates to the technical field of aircrafts, in particular to an aircraft and an antenna support device thereof.

Background

The antenna support device of the aircraft is a device for supporting and positioning an antenna, the radiation direction of the antenna is an important index of a communication antenna system, and a servo turntable system or a multi-antenna technology is required to be added to improve the coverage area of the antenna in the conventional antenna support device.

However, the antenna support device adds a servo turntable system or uses a multi-antenna technology, which may increase the cost or cause the control difficulty to be increased to a greater extent.

SUMMERY OF THE UTILITY MODEL

The application provides an aircraft and an antenna support device thereof aiming at the defects of the existing mode, and aims to solve the technical problem that the cost is increased or the control difficulty is increased to a greater extent by adding a servo turntable system or using a multi-antenna technology in the existing antenna support device.

In a first aspect, an embodiment of the present application provides an antenna mounting apparatus for an aircraft, including: the steering structure is used for being connected with two antenna connecting pieces of the aircraft and comprises a body, two first adjusting surfaces which are arranged on the body in a relatively parallel mode and two second adjusting surfaces which are arranged on the body in a relatively parallel mode, and the first adjusting surfaces are vertically connected with the second adjusting surfaces; each first adjusting surface is provided with m rows and n columns of first fixing pieces, each second adjusting surface is provided with i rows and j columns of second fixing pieces, and m, n, i and j are natural numbers not less than 2;

the antenna connecting piece is connected with at least two first fixing pieces or at least two second fixing pieces, and the at least two first fixing pieces or the at least two second fixing pieces are on the same straight line; the antenna connecting piece is connected with the first fixing piece or the second fixing piece on different straight lines and used for adjusting the pitching angle or the azimuth angle of the body of the steering structure.

Optionally, a first distance between adjacent first fixtures is equal and/or a second distance between adjacent second fixtures is equal.

Optionally, the turning structure is a regular hexahedron structure, and m, n, i, and j are all equal.

Optionally, the first fixing piece is a stud protruding outwards, and one side of each stud, which is far away from the body, is on the same plane;

the second fixing piece is of a through hole structure, and the through hole structure is communicated with the two opposite second adjusting surfaces.

Optionally, the first fixing piece and the second fixing piece are both outward protruding studs, and one side of each stud, which is far away from the body, is on the same plane.

Optionally, the steering structure is a hexahedral structure, and further includes two connecting surfaces arranged in parallel;

the antenna support device further comprises a mounting platform structure, the mounting platform structure comprises a first mounting platform surface, and the first mounting platform surface is connected with the connecting surface.

Optionally, the mounting platform structure further includes a second mounting platform surface, the second mounting platform surface is opposite to the first mounting platform surface, and the second mounting platform surface is used for being connected with an antenna.

Optionally, the mounting platform structure and the steering structure are a unitary structure.

In a second aspect, an embodiment of the present application provides an aircraft, including: two antenna connection members and the antenna mounting apparatus of the first aspect;

one of the antenna connectors is connected with one first adjusting surface of the antenna bracket device, and the other antenna connector is connected with the other first adjusting surface; or, one of the antenna connecting pieces is connected with one second adjusting surface of the antenna support device, and the other of the antenna connecting pieces is connected with the other second adjusting surface.

Optionally, the aircraft further comprises a horizontal testing device, the horizontal testing device being arranged on one side of the steering structure.

The beneficial technical effects brought by the technical scheme provided by the embodiment of the application comprise:

each first adjusting surface is provided with m rows and n columns of first fixing pieces, the antenna connecting piece is connected with at least two first fixing pieces, the at least two first fixing pieces are arranged on the same straight line, and when the position of the antenna connecting piece is unchanged, the antenna connecting piece is connected with the first fixing pieces on different straight lines, namely, the pitching angles of the first fixing pieces on the different straight lines and the horizontal line are different, so that the pitching angle of the body of the steering structure can be favorably adjusted; each second adjustment face is equipped with i row j and is listed as a second mounting, and the antenna connecting piece is connected with two at least second mountings, and two at least second mountings are on same straight line, and when the position of antenna connecting piece was unchangeable, the antenna connecting piece was connected with the second mounting on the different straight lines, and because of the position angle difference of the second mounting on the different straight lines promptly, the department can do benefit to the position angle at adjustment steering structure's body place from this.

Therefore, two antenna connection spare of aircraft can select to be connected with first mounting, perhaps are connected with the second mounting, can do benefit to and turn to the structure and carry out one-way adjustment, adjust pitch angle or azimuth angle promptly, and the antenna boom device of this application need not additionally set up servo revolving stage system or use many antennas technique, can do benefit to reduce cost and reduce the operation degree of difficulty.

Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.

Drawings

The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a schematic front view of an antenna mounting apparatus according to an embodiment of the present disclosure;

fig. 2 is a schematic structural diagram of a steering structure according to an embodiment of the present disclosure;

fig. 3 is a schematic structural diagram illustrating an antenna connection element connected to a first fixing element according to an embodiment of the present disclosure;

fig. 4 is a schematic structural diagram of an antenna connection member and a second fixing member according to an embodiment of the present disclosure;

FIG. 5 is a schematic left side view of the structure of FIG. 1;

FIG. 6 is a schematic diagram of the right-side view of FIG. 1;

fig. 7 is a schematic representation of a pitch angle and an azimuth angle provided in an embodiment of the present application.

Description of reference numerals:

1-an antenna mount device;

11-mounting the platform structure; 111-a second mounting platform face;

12-a steering structure; 121-a first conditioning surface; 122-a second conditioning surface; 123-a first fixing piece; 124-a second fixing piece; 125-connecting surface;

2-antenna connection element.

Detailed Description

Embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the embodiments set forth below in connection with the drawings are exemplary descriptions for explaining technical solutions of the embodiments of the present application, and do not limit the technical solutions of the embodiments of the present application.

As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of other features, information, data, steps, operations, elements, components, and/or groups thereof, that may be implemented as required by the art. The term "and/or" as used herein refers to at least one of the items defined by the term, e.g., "a and/or B" may be implemented as "a", or as "B", or as "a and B".

To make the objects, technical solutions and advantages of the present application more clear, embodiments of the present application will be described in further detail below with reference to the accompanying drawings.

The research and development idea of the application comprises: the antenna support device of the aircraft is a supporting and positioning device of the antenna, and the radiation direction of the antenna is influenced, so that communication can be interrupted. The tracking range of the antenna support device is limited by the radiation range of the antenna, a tracking blind area can be formed near the top of the antenna, namely, the antenna system cannot be aligned to a target in the blind area range, and communication is interrupted. In order to overcome the tracking blind area, improve the coverage area and improve the antenna gain, the common solutions are: the servo turntable system is added and the multi-antenna technology is used, but the antenna support device adds the servo turntable system or uses the multi-antenna technology, so that the cost is greatly increased and the control difficulty is increased.

The following describes the technical solutions of the present application and how to solve the above technical problems with specific embodiments. It should be noted that the following embodiments may be referred to, referred to or combined with each other, and the description of the same terms, similar features, similar implementation steps, etc. in different embodiments is not repeated.

The embodiment of the present application provides an antenna support device 1 of an aircraft, as shown in fig. 1 to 7, including: a steering structure 12, the steering structure 12 being intended to be connected to two antenna connections 2 of an aircraft.

The steering structure 12 comprises a body, two first adjusting surfaces 121 arranged in parallel relatively and two second adjusting surfaces 122 arranged in parallel relatively, wherein the first adjusting surfaces 121 are vertically connected with the second adjusting surfaces 122; each first adjusting surface 121 is provided with m rows and n columns of first fixing pieces 123, each second adjusting surface 122 is provided with i rows and j columns of second fixing pieces 124, wherein m, n, i and j are natural numbers not less than 2.

The antenna connecting member 2 is connected to at least two first fixing members 123 or at least two second fixing members 124, and the at least two first fixing members 123 or the at least two second fixing members 124 are located on the same straight line; the position of the antenna connecting element 2 is fixed, and the antenna connecting element 2 is connected with the first fixing element 123 or the second fixing element 124 on different straight lines, so as to adjust the pitch angle or the azimuth angle of the body of the steering structure 12.

In this embodiment, set up first regulation face 121 and two second regulation faces 122 of relative parallel arrangement on the body of structure 12 turns to, first regulation face 121 is connected perpendicularly with second regulation face 122, then antenna connecting piece 2 and first regulation face 121 or second regulation face 122 of aircraft are connected, can do benefit to the angle that the body equidirectional of adjustment structure 12 turned to, when antenna connecting piece 2 and the first regulation face 121 of aircraft are connected promptly, can do benefit to the pitch angle that the body of adjustment structure 12 is located, when antenna connecting piece 2 and the second regulation face 122 of aircraft are connected, can adjust the azimuth angle that the body of structure 12 is located.

Each first adjusting surface 121 is provided with m rows and n columns of first fixing pieces 123, the antenna connecting piece 2 is connected with at least two first fixing pieces 123, the at least two first fixing pieces 123 are on the same straight line, and when the position of the antenna connecting piece 2 is unchanged, the antenna connecting piece 2 is connected with the first fixing pieces 123 on different straight lines, that is, because the pitching angles of the first fixing pieces 123 on different straight lines and a horizontal line are different, the pitching angle of the body of the steering structure 12 can be adjusted conveniently; each second adjusting surface 122 is provided with i rows and j columns of second fixing members 124, the antenna connecting member 2 is connected with at least two second fixing members 124, the at least two second fixing members 124 are on the same straight line, and when the position of the antenna connecting member 2 is not changed, the antenna connecting member 2 is connected with the second fixing members 124 on different straight lines, that is, the azimuth angles of the second fixing members 124 on different straight lines are different, so that the adjustment of the azimuth angle of the body of the steering structure 12 can be facilitated.

Therefore, two antenna connecting pieces 2 of aircraft can select to be connected with first mounting 123, perhaps are connected with second mounting 124, can do benefit to steering structure 12 and carry out one-way adjustment, adjust pitch angle or azimuth angle promptly, and the antenna boom device of this application need not additionally set up servo turntable system or use many antennas technique, can do benefit to reduce cost and reduce the operation degree of difficulty.

It should be noted that a to F, 2 to 6, and B2 to F6 in fig. 1 to 3 all represent a first fixing member 123; the antenna connecting member 2 in fig. 3 is connected to six first fixing members 123, wherein the six first fixing members 123 are 6, B5, C4, D3, E2 and F; in fig. 4, the antenna connector 2 is connected to two second fixing elements 124, namely a first column of the second fixing element 124 in the sixth row and a sixth column of the second fixing element 124 in the first row.

Alternatively, the distance between the adjacent first fixing elements 123 may be equal or may vary regularly, which can facilitate to obtain the size of the pitch angle between the first fixing elements 123 and the horizon on different straight lines, thereby facilitating to determine the first fixing elements 123 to which the antenna connecting element 2 is connected. The second distances between the adjacent second fixing elements 124 are equal, equal or regularly variable, which can facilitate to obtain the size of the orientation angle of the second fixing elements 124 on different straight lines from the horizontal line, thereby being capable of facilitating to determine the second fixing elements 124 connected with the antenna connector 2.

Optionally, the first distance between adjacent first fixing members 123 is equal and/or the second distance between adjacent second fixing members 124 is equal.

In this embodiment, the first distance between the adjacent first fixing members 123 is equal and/or the second distance between the adjacent second fixing members 124 is equal, which includes the following three cases: the first distances between the adjacent first fixing pieces 123 are equal, the second distances between the second fixing pieces 124 are not equal, or the first distances between the adjacent first fixing pieces 123 are equal and the second distances between the second fixing pieces 124 are equal, or the first distances between the first fixing pieces 123 are not equal and the second distances between the second fixing pieces 124 are equal. When the first distances between the adjacent first fixing pieces 123 are equal, the pitch angle values of the first fixing pieces 123 of different straight lines and the horizontal line can be calculated conveniently according to the specific values of the first distances; when the second distances between the adjacent second fixing elements 124 are equal, it is possible to advantageously calculate the azimuth angle values of the second fixing elements 124 in different straight lines from the horizontal line according to specific values of the second distances. From this, this application equals and/or the second distance between the adjacent second mounting 124 is equal through setting up the first distance between the adjacent first mounting 123, can do benefit to and calculate the angle value according to the distance between first mounting 123 and the second mounting 124, does not need additionally to use measuring tool, is favorable to reduce cost and reduces the control degree of difficulty, can do benefit to and solve the problem of the communication interrupt that the antenna pointed angle blind area caused.

Optionally, the turning structure 12 is a regular hexahedron structure, and m, n, i, and j are all equal.

In this embodiment, the steering structure 12 is a regular hexahedron structure, that is, the lengths and widths of the first adjusting surface 121 and the second adjusting surface 122 are equal, and when m, n, i, and j are equal, the first distance between the adjacent first fixing members 123 is equal to the second distance between the adjacent second fixing members 124, which further facilitates determining the pitch angle and the azimuth angle according to the positions of the first fixing members 123 and the second fixing members 124, and further facilitates reducing the operation difficulty.

In the present application, the first fixing element 123 and the second fixing element 124 may be connected to the antenna connector 2, and the specific structures of the first fixing element 123 and the second fixing element 124 may be selected according to actual situations.

Optionally, in a practicable manner, the first fixing element 123 is a stud protruding outwards, and one side of each stud away from the body is on the same plane; the second fixing member 124 is a through hole structure, the through hole structure communicates with the two second adjusting surfaces 122, and the through hole structure is connected with the antenna connector 2 through a through-pin.

In this embodiment, the first fixing element 23 is a stud protruding outward, and when the antenna connector 2 is connected to the stud, because one side of each stud away from the body is on the same plane, the antenna connector 2 can be connected to the stud conveniently, and the connection surface 125 can be ensured to be a plane. The second fixing member 124 is a through hole structure, and the second fixing member 124 and the antenna connector 2 can be connected by a through pin. Therefore, the double-screw bolt or the through hole structure is fixedly connected with the antenna connecting piece 2, the stability of the connection of the antenna bracket device and the antenna connecting piece 2 can be guaranteed, and the problem of directional offset caused by vibration in work can be avoided.

Optionally, a threaded hole is formed in the center of the stud, and the antenna connection member 2 and the first fixing member 23 may be connected by a screw.

Alternatively, it is practicable that the first fixing member 123 and the second fixing member 124 are both outwardly protruding studs, and a side of each stud away from the body is on the same plane.

In this embodiment, the first fixing member 123 and the second fixing member 124 are both outwardly protruding studs, which can facilitate cost reduction, simplify installation manner, and facilitate operation.

Alternatively, as shown in fig. 5 and 6, the steering structure 12 is a hexahedral structure, and further includes two connecting surfaces 125 disposed in parallel; the antenna mounting device 1 further comprises a mounting platform structure 11, the mounting platform structure 11 comprising a first mounting platform face, the first mounting platform face being connected with a connection face 125.

Optionally, the mounting platform structure 11 further includes a second mounting platform surface 111, the second mounting platform surface 111 is disposed opposite to the first mounting platform surface, and the second mounting platform surface 111 is configured to be connected to the antenna.

In this embodiment, the second mounting platform surface 111 is connected to an antenna, and the second mounting platform surface 111 is an antenna surface, i.e. a radiation direction.

Alternatively, the mounting platform structure 11 and the steering structure 12 are of unitary construction.

In this embodiment, the mounting platform structure 11 and the steering structure 12 are integrated, which can facilitate to enhance the connection strength between the mounting platform structure 11 and the steering structure 12, and simplify the manufacturing process.

Based on the same inventive concept, the embodiment of the application provides an aircraft, which comprises: two antenna connection members 2 and the antenna mounting apparatus 1 provided in the above-described embodiment.

One antenna connection element 2 is connected to one first adjustment surface 121 of the antenna mounting device 1, and the other antenna connection element 2 is connected to the other first adjustment surface 121; alternatively, one antenna connection element 2 is connected to one second adjustment surface 122 of the antenna mounting device 1, and the other antenna connection element 2 is connected to the other second adjustment surface 122.

In this embodiment, the antenna connection element 2 of the aircraft is connected to the first adjustment surface 121 or the second adjustment surface 122, and can be used for adjusting the angles of the body of the steering structure 12 in different directions, that is, when the antenna connection element 2 of the aircraft is connected to the first adjustment surface 121, the adjustment of the pitch angle of the body of the steering structure 12 can be used for facilitating, and when the antenna connection element 2 of the aircraft is connected to the second adjustment surface 122, the azimuth angle of the body of the steering structure 12 can be adjusted.

It should be noted that the vehicle may be a rocket vehicle.

Optionally, the aircraft further comprises a level testing device, which is arranged on one side of the turning structure 12.

In this embodiment, the horizontal testing device is disposed at one side of the steering structure 12, and is used for indicating a horizontal reference plane, that is, a pitch angle between a straight line where the antenna connection member 2 is connected to the at least two first fixing members 123 of the first adjusting surface 121 and the horizontal reference plane, and an azimuth angle between a straight line where the antenna connection member 2 is connected to the at least two second fixing members 124 of the second adjusting surface 122 and the horizontal reference plane.

It should be noted that, as shown in fig. 7, if the pointed target is located at point B, XY is a horizontal reference plane, and the projection of point B on the horizontal reference plane is point B', the azimuth angle is α, and the pitch angle is β.

By applying the embodiment of the application, at least the following beneficial effects can be realized:

1. the two antenna connecting pieces of aircraft that this application embodiment provided can select to be connected with first mounting, perhaps are connected with the second mounting, can do benefit to and turn to the structure and carry out one-way adjustment, adjust pitch angle or position angle promptly, and the antenna boom device of this application need not additionally set up servo revolving stage system or use many antennas technique, can do benefit to reduce cost and reduce the operation degree of difficulty.

2. The first distance between the adjacent first fixing pieces is equal and/or the second distance between the adjacent second fixing pieces is equal, the angle value can be calculated according to the distance between the first fixing pieces and the second fixing pieces, measuring tools do not need to be additionally used, cost reduction and control difficulty reduction are facilitated, and the problem of communication interruption caused by antenna pointing angle blind areas can be solved.

3. The first fixing part that this application embodiment provided is outside convex double-screw bolt, and the second fixing part is the through-hole structure, adopts double-screw bolt or through-hole structure and antenna connection spare to be connected fixedly promptly, can guarantee the stability that antenna boom device and antenna connection spare are connected to can avoid causing the problem of directional skew because of taking place the vibration at work.

Those of skill in the art will appreciate that the various operations, methods, steps in the processes, acts, or solutions discussed in this application can be interchanged, modified, combined, or eliminated. Further, other steps, measures, or schemes in various operations, methods, or flows that have been discussed in this application can be alternated, altered, rearranged, broken down, combined, or deleted. Further, steps, measures, schemes in the prior art having various operations, methods, procedures disclosed in the present application may also be alternated, modified, rearranged, decomposed, combined, or deleted.

In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like are for convenience of description or simplicity of describing the embodiments of the present application based on the exemplary directions or positional relationships shown in the drawings, and do not indicate or imply that the devices or components referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, are not to be construed as limiting the present application.

The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, the meaning of "a plurality" is two or more unless otherwise specified.

In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in this application will be understood to be a specific case for those of ordinary skill in the art.

The particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.

It should be understood that, although the steps in the flowcharts of the figures are shown in sequence as indicated by the arrows, the order in which the steps are performed is not limited to the sequence indicated by the arrows. In some implementations of embodiments of the present application, the steps in the various flows may be performed in other sequences as desired, unless explicitly stated otherwise herein. Moreover, some or all of the steps in each flowchart may include multiple sub-steps or multiple stages, depending on the actual implementation scenario. Some or all of the sub-steps or phases may be executed at the same time, or may be executed at different times in a scenario where the execution time is different, and the execution order of the sub-steps or phases may be flexibly configured according to the requirement, which is not limited in this embodiment of the application.

The foregoing is only a part of the embodiments of the present application, and it should be noted that, for those skilled in the art, other similar implementation means based on the technical idea of the present application may be adopted without departing from the technical idea of the present application, and the scope of protection of the embodiments of the present application also belongs to the embodiments of the present application.

Claims (10)

1. An antenna mounting apparatus for an aircraft, comprising: the steering structure is used for being connected with two antenna connecting pieces of the aircraft and comprises a body, two first adjusting surfaces which are arranged on the body in a relatively parallel mode and two second adjusting surfaces which are arranged on the body in a relatively parallel mode, and the first adjusting surfaces are vertically connected with the second adjusting surfaces; each first adjusting surface is provided with m rows and n columns of first fixing pieces, each second adjusting surface is provided with i rows and j columns of second fixing pieces, and m, n, i and j are natural numbers not less than 2;

the antenna connecting piece is connected with at least two first fixing pieces or at least two second fixing pieces, and the at least two first fixing pieces or the at least two second fixing pieces are on the same straight line; the antenna connecting piece is connected with the first fixing piece or the second fixing piece on different straight lines and used for adjusting the pitching angle or the azimuth angle of the body of the steering structure.

2. The antenna mounting apparatus according to claim 1, wherein a first distance between adjacent first fixing members is equal and/or a second distance between adjacent second fixing members is equal.

3. The antenna mounting apparatus of claim 1, wherein the turning structure is a regular hexahedron structure, and m, n, i, and j are all equal.

4. The antenna mounting apparatus according to any one of claims 1-3, wherein the first fixing member is an outwardly protruding stud, and a side of each stud away from the body is in the same plane;

the second fixing piece is of a through hole structure, the through hole structure is communicated with the two opposite second adjusting surfaces, and the through hole structure is connected with the antenna connecting piece through a through nail.

5. The antenna mounting apparatus according to any one of claims 1-3, wherein the first fixing member and the second fixing member are outwardly protruding studs, and a side of each stud away from the body is in a same plane.

6. The antenna mounting apparatus of claim 1, wherein the turning structure is a hexahedral structure, further comprising two connection faces disposed in parallel with each other;

the antenna support device further comprises a mounting platform structure, wherein the mounting platform structure comprises a first mounting platform surface, and the first mounting platform surface is connected with the connecting surface.

7. The antenna mounting apparatus of claim 6, wherein the mounting platform structure further comprises a second mounting platform surface, the second mounting platform surface being disposed opposite the first mounting platform surface, the second mounting platform surface being configured to interface with an antenna.

8. An antenna mounting apparatus according to claim 6 or 7, wherein the mounting platform structure and the steering structure are a unitary structure.

9. An aircraft comprising two antenna connection members and an antenna mount apparatus as claimed in any one of claims 1 to 8;

one of the antenna connectors is connected with one first adjusting surface of the antenna bracket device, and the other antenna connector is connected with the other first adjusting surface; or, one of the antenna connecting pieces is connected with one second adjusting surface of the antenna support device, and the other of the antenna connecting pieces is connected with the other second adjusting surface.

10. The aircraft of claim 9, further comprising a level testing device disposed on one side of the turning structure.

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