An antenna device for an aircraft

Abstract

This utility model discloses an antenna device for an aircraft. The antenna device includes: a rotating shaft disposed at the bottom of the aircraft, an antenna mast radially distributed along the rotating shaft, a driving component disposed inside the aircraft, and a connecting rod assembly connecting the driving component and the rotating shaft. The driving component drives the rotating shaft to rotate based on the connecting rod assembly. When the connecting rod assembly is in a first self-locking position, the antenna mast is parallel to the bottom surface of the aircraft; when the connecting rod assembly is in a second self-locking position, the antenna mast is perpendicular to the bottom surface of the aircraft. By setting the driving component in conjunction with the connecting rod assembly, the lowering and retraction operations of the antenna mast are realized, ensuring the communication stability of the aircraft, and improving the stability and safety of the antenna mast structure.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to an antenna device for aircraft. Background Technology

[0002] When aircraft are in flight, communication signals are easily unstable due to the influence of the flight environment. In order to improve the communication stability between the antenna and the ground base station, the antenna is usually set at the bottom of the aircraft. Existing UAVs equipped with cylindrical antennas are prone to antennas touching the ground before the landing gear because the antennas are vertically installed at the bottom of the fuselage and their length exceeds the height of the landing gear. This can lead to damage to the antenna structure. During the flight mission, the antenna structure is continuously exposed, generating additional aerodynamic drag and reducing the endurance efficiency. Utility Model Content

[0003] The purpose of this invention is to overcome the shortcomings of the prior art. This invention provides an antenna device for aircraft, which, by setting up a driving component in conjunction with a connecting rod assembly, enables the lowering and retraction of the antenna mast, ensuring the communication stability of the aircraft, and improving the stability and safety of the antenna mast structure.

[0004] This utility model provides an antenna device for an aircraft, the antenna device comprising: a rotating shaft disposed at the bottom of the aircraft, an antenna mast radially distributed along the rotating shaft, a driving component disposed inside the aircraft, and a connecting rod assembly connecting the driving component and the rotating shaft;

[0005] The drive component drives the rotating shaft to rotate based on the linkage assembly, and when the linkage assembly is in the first self-locking position, the antenna mast is parallel to the bottom surface of the aircraft;

[0006] When the linkage assembly is in the second self-locking position, the antenna mast is perpendicular to the bottom surface of the aircraft.

[0007] Furthermore, the aircraft is provided with landing gear at the bottom, and a fixed bushing is provided on the landing gear, with the rotating shaft rotatably disposed within the fixed bushing.

[0008] Furthermore, the aircraft is provided with a shell, the landing gear is disposed outside the shell, and the drive components are installed inside the shell.

[0009] Furthermore, the linkage assembly includes a drive linkage disposed at the middle position of the rotating shaft, an actuating linkage disposed at the output end of the drive component, and a transmission linkage disposed between the drive linkage and the actuating linkage;

[0010] One end of the transmission link is rotatably connected to the drive link, and the other end of the transmission link is rotatably connected to the actuation link.

[0011] Furthermore, the transmission link includes: a first section, a second section, and an arc transition section disposed between the first section and the second section;

[0012] The transmission link forms an arc-shaped plate structure based on the first section, the second section, and the arc transition section.

[0013] Furthermore, when the linkage assembly is in the first self-locking position, the first segment of the actuating linkage and the transmission linkage are in a folded state.

[0014] Furthermore, when the linkage assembly is in the second self-locking position, the first segment of the actuating linkage and the transmission linkage are aligned in a straight line.

[0015] Furthermore, the rotating shaft is provided with a plurality of antenna bases, and each of the antenna bases is provided with a mounting slot adapted to the antenna rod.

[0016] This utility model provides an antenna device for an aircraft, which is based on a drive component and a linkage assembly to control the rotation of the rotating shaft, thereby driving the antenna mast to rotate. According to the flight communication requirements of the aircraft, the antenna mast can be lowered to improve the signal connection stability between the aircraft and the ground base station.

[0017] The antenna mast can be retracted in flight environments where the antenna is not required, reducing the overall wind resistance of the aircraft and ensuring good flight efficiency.

[0018] The antenna mast can be retracted during aircraft descent and landing, reducing the risk of collision damage and thus improving the stability and safety of the antenna mast structure. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the antenna device of an aircraft in an embodiment of this utility model;

[0021] Figure 2 This is a schematic diagram of the antenna device of the aircraft in the lowered state in an embodiment of this utility model;

[0022] Figure 3 This is a structural cross-sectional view of the aircraft's antenna device in the retracted state according to an embodiment of this utility model;

[0023] Figure 4 This is an example of the embodiments of this utility model. Figure 3 Enlarged schematic diagram of the structure at point A;

[0024] Figure 5 This is a structural cross-sectional view of the aircraft's antenna device in the lowered state according to an embodiment of this utility model;

[0025] Figure 6 This is an example of the embodiments of this utility model. Figure 5 Enlarged schematic diagram of the structure at point B. Detailed Implementation

[0026] 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 skilled in the art without creative effort are within the protection scope of the present utility model.

[0027] refer to Figures 1 to 6 This utility model provides an antenna device for an aircraft. The antenna device includes: a rotating shaft 4 disposed at the bottom of the aircraft, an antenna mast 5 radially distributed along the rotating shaft 4, a drive component 6 disposed inside the aircraft, and a connecting rod assembly 3 connecting the drive component 6 and the rotating shaft 4. The aircraft is provided with a shell 1, and a landing gear 2 is disposed at the bottom of the shell 1. The drive component 6 is disposed inside the shell 1 to avoid the drive component 6 being exposed to the outside of the aircraft and to reduce the risk of damage to the drive component 6. The bottom of the shell 1 is provided with a slot so that the drive component 6 can be driven and connected to the rotating shaft 4 based on the connecting rod assembly 3.

[0028] Furthermore, the driving component 6 can be configured as a servo motor, which drives and controls the movement of the linkage assembly 3, thereby causing the rotating shaft 4 and the antenna rod 5 on the rotating shaft 4 to deflect.

[0029] The driving component 6 drives the rotating shaft 4 to rotate based on the connecting rod assembly 3. When the connecting rod assembly 3 is in the first self-locking position, the antenna mast 5 is parallel to the bottom surface of the aircraft, so that the antenna mast 5 can be close to the bottom surface of the aircraft, avoiding damage caused by the antenna mast 5 colliding with the ground when the aircraft lands.

[0030] When the linkage assembly 3 is in the second self-locking position, the antenna mast 5 is perpendicular to the bottom surface of the aircraft, that is, the antenna mast 5 can extend downward from the aircraft, so that during the flight of the aircraft, the antenna mast 5 can point to the ground signal base station, so as to improve the aircraft's ability to obtain signals during flight, thereby improving the aircraft's flight stability.

[0031] Furthermore, the linkage assembly 3 is provided with a first self-locking position and a second self-locking position, so that when the driving component 6 drives the linkage assembly 3 to move in linkage, the working state of the linkage assembly 3 can be locked based on the first self-locking position and the second self-locking position. When the aircraft is in flight and the antenna mast 5 is in the lowered state based on the movement of the linkage assembly 3, the self-locking structure of the linkage assembly 3 can improve the structural rigidity of the antenna mast 5, avoid the antenna mast 5 from shaking or deflecting due to external wind pressure, and ensure the stability of signal transmission and reception during the flight of the aircraft. When the aircraft is parked on the ground and the antenna mast 5 is in the retracted state, the self-locking structure of the linkage assembly 3 can improve the structural stability of the antenna mast 5 in the retracted state.

[0032] Specifically, a fixed bushing 21 is provided at the bottom of the aircraft, and the rotating shaft 4 is rotatably disposed within the fixed bushing 21. The bottom of the aircraft is provided with two or more fixed bushings 21 to improve the installation stability of the rotating shaft 4. A lubricant is provided between the fixed bushing 21 and the rotating shaft 4 to effectively reduce the friction between the rotating shaft 4 and the fixed bushing 21, thereby improving the ease of rotation of the rotating shaft 4 within the fixed bushing 21.

[0033] Specifically, the linkage assembly 3 includes a drive linkage 31 located at the center of the rotating shaft 4, an actuating linkage 33 located at the output end of the drive component 6, and a transmission linkage 32 located between the drive linkage 31 and the actuating linkage 33.

[0034] One end of the transmission link 32 is rotatably connected to the drive link 31, and the other end of the transmission link 32 is rotatably connected to the actuation link 33.

[0035] Specifically, the transmission link 32 includes a first section, a second section, and an arc transition section disposed between the first section and the second section. The transmission link 32 forms an arc plate structure based on the arc transition section. The transmission link 32, based on the arc plate structure, can meet the self-locking requirements of the linkage component, so that the transmission link 32 can cooperate with the action link 33 and the drive link 31 to form a self-locking structure.

[0036] Specifically, the rotating shaft 4 is provided with a plurality of antenna bases, each of which is provided with a mounting slot adapted to the antenna rod 5. The bottom end of the antenna rod 5 is provided with an external connecting thread, and the mounting slot is provided with an internal connecting thread that matches the antenna rod 5, so that the antenna rod 5 can be threadedly connected to the mounting slot based on the external connecting thread.

[0037] Specifically, when the linkage assembly 3 is in the first self-locking position, the first segment of the transmission link 32 and the action link 33 form a folded state, so that the apex of the first segment of the transmission link 32 and the apex of the action link 33 are connected to form an action dead point structure, so that the linkage assembly 3 is in a self-locking state, the driving component 6 stops driving the linkage assembly 3, and the linkage assembly 3 can maintain the retracted state of the antenna mast 5 based on its own self-locking state.

[0038] Furthermore, when the linkage assembly 3 is in the second self-locking position, the first segment of the transmission link 32 and the actuating link 33 are in the same straight direction, and the actuating link 33 and the first segment of the transmission link 32 are connected, so that a dead point structure is formed between the actuating link 33 and the transmission link 32 of the linkage assembly 3. When the driving component 6 stops driving the linkage assembly 3, the linkage assembly 3 can maintain the stability of its own structure.

[0039] This utility model provides an antenna device for an aircraft. Based on a drive component 6 and a connecting rod assembly 3, the rotating shaft 4 is controlled to rotate, driving the antenna mast 5 to rotate. According to the aircraft's flight communication requirements, the antenna mast 5 can be lowered to improve the signal connection stability between the aircraft and the ground base station. In flight environments where the antenna is not needed, the antenna mast 5 can be retracted to reduce the overall wind resistance of the aircraft and ensure good flight efficiency. By setting the drive component 6 and the connecting rod assembly 3 to realize the lowering and retraction operations of the antenna mast 5, the communication stability of the aircraft is ensured. The antenna mast 5 can be retracted during descent and landing, reducing the risk of collision damage to the antenna mast 5, thereby improving the structural stability and operational safety of the antenna mast 5.

[0040] Furthermore, the above description provides a detailed account of an aircraft antenna device provided by the embodiments of this utility model. Specific examples have been used to illustrate the principles and implementation methods of this utility model. The description of the above embodiments is only for the purpose of helping to understand the method and core ideas of this utility model. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this utility model. Therefore, the content of this specification should not be construed as a limitation of this utility model.

Claims

1. An antenna device for an aircraft, characterized in that, The antenna device includes: a rotating shaft disposed at the bottom of the aircraft, an antenna mast radially distributed along the rotating shaft, a drive component disposed inside the aircraft, and a connecting rod assembly connecting the drive component and the rotating shaft; The drive component drives the rotating shaft to rotate based on the linkage assembly, and when the linkage assembly is in the first self-locking position, the antenna mast is parallel to the bottom surface of the aircraft; When the linkage assembly is in the second self-locking position, the antenna mast is perpendicular to the bottom surface of the aircraft.

2. The antenna device for an aircraft as described in claim 1, characterized in that, The aircraft is equipped with landing gear at the bottom, and a fixed bushing is provided on the landing gear. The rotating shaft is rotatably disposed within the fixed bushing.

3. The antenna device for an aircraft as described in claim 2, characterized in that, The aircraft is provided with an outer shell, the landing gear is disposed outside the outer shell, and the drive components are installed inside the outer shell.

4. The antenna device for an aircraft as described in claim 1, characterized in that, The linkage assembly includes a drive linkage located at the middle of the rotating shaft, an actuating linkage located at the output end of the drive component, and a transmission linkage located between the drive linkage and the actuating linkage. One end of the transmission link is rotatably connected to the drive link, and the other end of the transmission link is rotatably connected to the actuation link.

5. The antenna device for an aircraft as described in claim 4, characterized in that, The transmission link includes: a first section, a second section, and an arc transition section disposed between the first section and the second section; The transmission link forms an arc-shaped plate structure based on the first section, the second section, and the arc transition section.

6. The antenna device for an aircraft as described in claim 5, characterized in that, When the linkage assembly is in the first self-locking position, the first segment of the actuating linkage and the transmission linkage are in a folded state.

7. The antenna device for an aircraft as described in claim 5, characterized in that, When the linkage assembly is in the second self-locking position, the first segment of the actuating linkage and the transmission linkage are in the same straight line.

8. The antenna device as claimed in claim 1, characterized in that, The rotating shaft is provided with a plurality of antenna bases, and each of the antenna bases is provided with a mounting slot adapted to the antenna rod.

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