Supporting mechanism and satellite communication terminal equipment

Abstract

The utility model provides a supporting mechanism and satellite communication terminal equipment, the supporting mechanism is symmetrically arranged on two sides of a lower box body of the satellite communication terminal equipment, and the supporting mechanism comprises a supporting rod, the upper part of the supporting rod is hinged to the side part of the lower box body, the supporting rod is provided with an accommodating groove, and a guide column is arranged on the side wall of the accommodating groove in a penetrating manner; the upper portion of the connecting rod is hinged to the side of the lower box body, a strip-shaped hole is formed in the connecting rod, the containing groove is used for containing the connecting rod, and the guide column is matched with the strip-shaped hole; a preset distance is reserved between the hinged position of the supporting rod and the lower box body and the hinged position of the connecting rod and the lower box body. The upper portion of the supporting rod is provided with a limiting table used for abutting against the bottom wall of the side portion of the lower box body so as to limit the maximum rotating unfolding angle of the supporting rod. The supporting mechanism can provide stable support when being unfolded, and is folded on two sides of the equipment when being folded; the equipment comprises a lower box body, an antenna rotationally connected to one end of the lower box body and a supporting mechanism, can be unfolded and stored, and is small in size, convenient to carry and high in practicability when being wholly stored.

Description

Technical Field

[0001] The present application relates to satellite communication technology, and particularly to a support mechanism and a satellite communication terminal device. Background Art

[0002] In order to facilitate single-person carrying and use, satellite communication terminal devices need to be designed as small as possible and have good portability functions. At the same time, they also need to be easy to deploy during use and fold and store when not in use. During display, a satellite alignment operation is performed, and the satellite alignment operation requires high support stability. Therefore, it is necessary to develop a support mechanism that can be integrated into the device body and is easy to retract and deploy to meet the use requirements. Summary of the Utility Model

[0003] To solve the above-mentioned deficiencies of the prior art, the present application provides a support mechanism and a satellite communication terminal device. When the support mechanism is deployed, it can provide stable support, and when retracted, it folds on both sides of the device; the antenna of the device can be deployed and stored, and the overall size of the device is small when stored, which is convenient for carrying and has strong practicability.

[0004] To achieve the above object, the present utility model adopts the following technologies:

[0005] A support mechanism is symmetrically arranged on both sides of the lower box body of the satellite communication terminal device, and includes:

[0006] A support rod, the upper part of which is hinged to the side of the lower box body. A receiving groove is provided on the support rod, and a guiding column is penetrated through the side wall of the receiving groove;

[0007] A connecting rod, the upper part of which is hinged to the side of the lower box body. A strip-shaped hole is provided on the connecting rod, and the receiving groove is used to receive the connecting rod, and the guiding column is fitted in the strip-shaped hole;

[0008] There is a predetermined distance between the hinge joint of the support rod and the lower box body and the hinge joint of the connecting rod and the lower box body.

[0009] Further, the upper end of the support rod has a hinge head, and the hinge head is hinged to the side of the lower box body. A limiting platform is provided on the upper part of the support rod, and the limiting platform is located on both sides of the hinge head and is used to abut against the bottom wall of the side of the lower box body to limit the maximum rotation and deployment angle of the support rod.

[0010] Further, a concave cavity is provided inside the support rod for accommodating the control keys on the side of the lower box body when the support rod rotates and retracts to the side of the lower box body.

[0011] A satellite communication terminal device includes a lower box body, an antenna connected to one end of the lower box body, and the support mechanism.

[0012] The beneficial effects of the present utility model are as follows:

[0013] 1. Through the structural design of the support rod and the connecting rod, a support structure can be formed when unfolded to provide stable support for the satellite communication terminal device. When folded, it can be folded on the side of the lower box body to avoid occupying space.

[0014] 2. The antenna of the device can be unfolded and folded. When the device is folded as a whole, its size is small, making it convenient to carry and highly practical. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a schematic diagram of the support mechanism of the embodiment of the present application installed on the satellite communication terminal device and in the unfolded state.

[0016] Figure 2 is Figure 1 the enlarged view of part A in

[0017] Figure 3 is a schematic diagram of the support rod structure of the embodiment of the present application.

[0018] Figure 4 is a schematic diagram of the support rod from another perspective of the embodiment of the present application.

[0019] Figure 5 is a schematic diagram of the overall folded state structure of the satellite communication terminal device of the embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0020] To make the objectives, technical solutions, and advantages of the embodiments of the present utility model clearer, the following will describe the embodiments of the present utility model in detail with reference to the drawings. However, the described embodiments are only a part of the embodiments of the present utility model, not all of them.

[0021] In one aspect of the embodiments of the present application, a support mechanism applied to a satellite communication terminal device is provided. As Figures 1-5 shown, the support mechanisms are symmetrically arranged on both sides of the lower box body 11 of the satellite communication terminal device. The support mechanism includes a support rod 2, a connecting rod 3, etc.

[0022] The upper part of the support rod 2 is hinged to the side of the lower box body 11, and the upper part of the connecting rod 3 is hinged to the side of the lower box body 11. There is a predetermined distance between the two hinge points, and both are close to one end of the lower box body 11 for connecting to the antenna 12.

[0023] The support rod 2 is provided with a receiving groove 23 for receiving the connecting rod 3, and a guiding post 24 is penetrated through the side wall of the receiving groove 23; a strip-shaped hole 30 is formed on the connecting rod 3, and the guiding post 24 is fitted into the strip-shaped hole 30.

[0024] Specifically, the support rod 2 is hinged to the side of the lower box body 11 through a hinge head 21 formed at its upper end.

[0025] AsFigures 2-4 As shown, the upper part of the support rod 2 has a limit platform 22, and the limit platform 22 is located on both sides of the hinge joint 21, and is used to abut against the bottom wall of the side part of the lower box body 11 to limit the maximum rotation and deployment angle of the support rod 2.

[0026] The inner side of the support rod 2 has a concave cavity 20, which is used to accommodate the control keys on the side part of the lower box body 11 when the support rod 2 rotates and retracts to the side part of the lower box body 11, such as Figure 4 and Figure 5 shown.

[0027] During application, by rotating the support rod 2, the support rod 2 drives the connecting rod 3 to rotate, and the guiding column 24 moves in the strip-shaped hole 30. When rotating to the limit platform 22 abuts against the bottom wall of the side part of the lower box body 11, the support rod 2 is at the maximum rotation and deployment angle. At this time, the guiding column 24 also moves to the other end of the strip-shaped hole 30. Thus, the connecting rod 3 also limits the rotation of the support rod 2 at this time, improving the stability of the support rod 2 in the deployed state. When in the deployed state, the inclination of the support rod 2 and the lower box body 11 as a whole are inclined, forming a stable support for the satellite communication terminal device, such as Figure 1 shown. When it needs to be retracted, rotate the support rod 2 in reverse, driving the connecting rod 3 to rotate in the opposite direction. As it rotates, a part of the main body of the connecting rod 3 can be received in the receiving groove 23. Finally, when the support rod 2 rotates to be parallel to the lower box body 11, that is, when rotating and retracting to the side part of the lower box body 11, the concave cavity 20 on the inner side of the support rod 2 is just used to accommodate the control keys on the side part of the lower box body 11 to avoid interference, and also plays a role in protecting the control keys, such as Figure 5 shown.

[0028] Another aspect of the embodiment of the present application provides a satellite communication terminal device, such as Figure 1 and Figure 5 shown, including a lower box body 11, an antenna 12 connected to one end of the lower box body 11, and the support mechanism described in the previous embodiment. Specifically, the antenna 12 is rotatably connected to the lower box body 11, so that it can have an antenna 12 deployed state as shown in Figure 1 and an antenna retracted state as shown in Figure 5 shown.

[0029] Specifically, the antenna 12 is rotatably connected to the lower box body 11 through a transmission mechanism 13. The rotation of the antenna 12 is controlled through the transmission mechanism 13.

[0030] The above are only the preferred embodiments of the present application and are not used to limit the present application. Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application.

Claims

1. A support mechanism, characterized in that: Symmetrically arranged on both sides of the lower box (11) of the satellite communication terminal equipment, comprising: A support rod (2), the upper portion of which is hinged to the side of the lower box body (11), the support rod (2) is provided with a receiving groove (23), and a guide column (24) is provided through the side wall of the receiving groove (23); A connecting rod (3), the upper portion of which is hinged to the side of the lower box body (11), a strip hole (30) is provided on the connecting rod (3), the receiving groove (23) is used to receive the connecting rod (3), and the guide column (24) is matched with the strip hole (30); There is a predetermined distance between the hinged joint between the support rod (2) and the lower box body (11) and the hinged joint between the connecting rod (3) and the lower box body (11).

2. The support mechanism according to claim 1, characterized in that: The upper end of the support rod (2) is provided with a hinged joint (21), and the hinged joint (21) is hinged to the side of the lower box body (11).

3. The support mechanism according to claim 2, characterized in that: The upper portion of the support rod (2) is provided with a limit platform (22), which is located on both sides of the hinge joint (21) and is used to abut against the bottom wall of the side portion of the lower box body (11) to limit the maximum rotation and deployment angle of the support rod (2).

4. The support mechanism according to claim 1, characterized in that: The inner side of the support rod (2) is provided with a concave cavity (20) for accommodating a control key on the side of the lower box body (11) when the support rod (2) is rotated and retracted to the side of the lower box body (11).

5. The support mechanism according to claim 1, characterized in that: The hinged joint between the support rod (2) and the lower box (11) and the hinged joint between the connecting rod (3) and the lower box (11) are located at one end of the lower box (11) connected to the antenna (12) of the satellite communication terminal equipment.

6. A satellite communication terminal device, characterized in that: It comprises a lower box (11), an antenna (12) connected to one end of the lower box (11), and a supporting mechanism as claimed in any one of claims 1 to 5.

7. The satellite communication terminal device according to claim 6, characterized in that: The antenna (12) is rotationally connected to the lower box body (11) via a transmission mechanism (13).

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