Phased array satellite communication antenna beam high-frequency control device

Abstract

The utility model discloses a phased array satellite communication antenna beam high-frequency control device, which comprises an inertial measurement unit, a Beidou compass module and a main control unit, the inertial measurement unit and the Beidou compass module are communicated with the main control unit; the utility model relates to the technical field of phased array satellite communication antennas, an inertial measurement unit directly captures and analyzes three-dimensional angular velocity and three-dimensional linear acceleration signals of a carrier, and combines positioning information provided by a Beidou compass module at the same time, and the real-time and high-precision data streams are directly transmitted to a main control unit, so that the calculation of the attitude of the carrier is realized, and the accuracy of the attitude of the carrier is improved. According to the technical scheme, the traditional method of integrating an inertial measurement unit, a Beidou compass module and a signal processing and settlement unit into a single inertial navigation system module is abandoned, and the problem that the data updating rate is limited due to integration is effectively avoided.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of phased array satellite communication antenna, concretely is a kind of phased array satellite communication antenna beam high frequency control device. BACKGROUND

[0002] Satellite communication has become a very competitive communication means today with its extensive coverage, ultra-long transmission distance, huge communication capacity, excellent transmission quality, flexible networking capability and high confidentiality. With the continuous development of technology, phased array antennas are gradually replacing traditional parabolic antennas to realize communication connection with satellites. Phased array antennas can quickly adjust beam pointing by using electrically controlled beam scanning, realize accurate tracking of different satellites, and thus have been more and more widely used in satellite communication.

[0003] The design principle of the beam pointing of the phased array antenna is to calculate the phase value corresponding to each antenna channel through the angle to be pointed, and then write the phase value corresponding to each channel into the phase shifter of the corresponding channel to realize the pointing of the beam in the expected direction. In this process, the inertial navigation system component needs to measure the attitude (tilt, pitch and yaw) of the carrier in the spatial coordinate system in real time. Therefore, the update frequency of the attitude data provided by the inertial navigation system and the ability of the main control module to calculate the attitude data directly determine the accuracy and response speed of the beam control of the phased array satellite communication antenna, which are the two core elements to ensure the efficient and stable operation of satellite communication.

[0004] Under normal circumstances, shipborne satellite communication phased array antennas rely on the attitude data provided by the ship to calculate and adjust the pointing of the antenna to the satellite in real time, to ensure that the ship can accurately point to the satellite to complete the communication business in the moving state. These ship attitude data are calculated by IMU (Inertial Measurement Unit) real-time data. The inertial navigation system used by the traditional shipborne satellite communication phased array antenna is often limited by the integrated design of the internal inertial navigation system module, resulting in a relatively low data update frequency, usually hovering between 50-100 Hz. Due to the low update frequency of the attitude data provided by the integrated inertial navigation system of the ship, the ship is always in a state of continuous shaking under the sea wave, and the attitude data such as tilt angle, pitch angle and yaw angle of the ship are changing all the time. When the phased array antenna is tracking the satellite, it cannot ensure that the antenna beam is always pointing to the satellite. The low update rate of the attitude data leads to the lag of the calculated phased array antenna beam pointing to the change of the ship attitude, which causes the phased array antenna to fail to effectively track the satellite, resulting in the decline or even interruption of the communication signal quality, and thus greatly affecting the communication performance of the phased array antenna.

[0005] In view of the above problems, there may be technical means to solve them in the prior art, but the present case wants to provide an alternative or replacement technical solution. Practical new type content

[0006] To solve the problems presented in the background art, the utility model discloses a kind of phased array satellite communication antenna beam high frequency control devices, including inertial measurement unit, compass module of big dipper and host computer unit;

[0007] The inertial measurement unit and compass module of big dipper are interconnected with the host computer unit;

[0008] The inertial measurement unit, compass module of big dipper and host computer unit are provided with mounting structure;

[0009] The mounting structure includes base, and the base is provided with three protective connection components, and the base is provided with a buckle cover component outside the three protective connection components;

[0010] The inertial measurement unit, compass module of big dipper and host computer unit are respectively mounted on the three protective connection components.

[0011] Preferably, each protective connection component includes a mounting groove seat, a support is provided on the outer side wall surface of the mounting groove seat, the lower wall surface of the support is located below the lower wall surface of the mounting groove seat, the support is mounted on the inner side bottom surface of the mounting groove seat by first bolt, a heat dissipation hole is formed in the center part of the bottom surface of the mounting groove seat, a recess is formed in the lower wall surface of the mounting groove seat coaxially with the heat dissipation hole, a heat-conducting block is filled between the recess and the mounting groove seat, and L-shaped air holes are formed in the heat-conducting block in a circular array.

[0012] Preferably, the buckle cover component includes a top cover, the top cover is mounted on the base by second bolt, and a wire hole is formed in the side wall surface of the top cover.

[0013] Preferably, a plurality of notches are formed in the side wall surface of the mounting groove seat.

[0014] Preferably, one end of the L-shaped air hole is aligned with the heat dissipation hole, and the other end of the L-shaped air hole is aligned with the lower part of the mounting groove seat.

[0015] Preferably, the heat-conducting block is a cylindrical graphene block structure.

[0016] Beneficial effects

[0017] The utility model provides a kind of phased array satellite communication antenna beam high frequency control device, compared with prior art, with the following beneficial effects: inertial measurement unit directly captures and resolves the three-dimensional angular velocity and three-dimensional linear acceleration signal of carrier, while combining the positioning information provided by Beidou compass module, these real-time, high-precision data stream is directly delivered to main control unit, realizes the calculation of carrier attitude, the technical solution discards the traditional inertial measurement unit, Beidou compass module and signal processing and settlement unit are integrated in single inertial navigation system module approach, effectively avoids the data update rate limited problem caused by integration. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is the connection block diagram of the utility model a kind of phased array satellite communication antenna beam high frequency control device.

[0019] Figure 2 It is the overall three-dimensional explosion structure schematic diagram of the utility model a kind of phased array satellite communication antenna beam high frequency control device.

[0020] Figure 3 It is the local upside-down structure structure schematic diagram of the utility model a kind of phased array satellite communication antenna beam high frequency control device.

[0021] Figure 4 It is the local main view section structure schematic diagram of the utility model a kind of phased array satellite communication antenna beam high frequency control device.

[0022] In the figure: 1, inertial measurement unit, 2, Beidou compass module, 3, main control unit, 4, pedestal, 5, installation groove seat, 6, support, 7, first bolt, 8, heat dissipation hole, 9, heat conduction block, 10, L-shaped air hole, 11, top cover, 12, second bolt, 13, wire hole, 14, gap. DETAILED DESCRIPTION

[0023] Based on the embodiment in the utility model, all other embodiments obtained by the person skilled in the art without making creative labor belong to the scope of protection of the utility model.

[0024] Embodiment: please refer to Figures 1-4 A kind of phased array satellite communication antenna beam high frequency control device, including inertial measurement unit 1, Beidou compass module 2 and main control unit 3;

[0025] Specifically, inertial measurement unit 1 and Beidou compass module 2 are all communicated with main control unit 3;

[0026] It should be noted that the inertial measurement unit 1 adopts a high refresh rate inertial measurement unit 1, and the refresh rate is 1000Hz, which directly captures and analyzes the three-dimensional angular velocity and three-dimensional linear acceleration signals of the carrier, and combines the positioning information provided by the Beidou compass module 2, these real-time and high-precision data streams are directly delivered to the main control unit 3, realizing the calculation of the carrier attitude, and the traditional method of integrating the inertial measurement unit 1, the Beidou compass module 2 and the signal processing and settlement unit in a single inertial navigation system module is abandoned, and the problem of limited data update rate caused by integration is effectively avoided.

[0027] By concentrating the core task of data processing in the main control unit 3, the high-frequency output characteristics of the inertial measurement unit 1 are fully utilized, ensuring the immediacy and accuracy of the attitude information, and the main control unit 3 not only quickly calculates the attitude angle and heading angle of the carrier, but also calculates the amplitude and phase change corresponding to the phased array antenna, thereby giving the phased array satellite communication antenna beam high-frequency and flexible control ability, and significantly improving the response speed and stability of the communication system.

[0028] The inertial measurement unit 1, the Beidou compass module 2 and the main control unit 3 are provided with mounting structures;

[0029] Specifically, the mounting structure includes a base 4, and the base 4 is provided with three protective connection assemblies, and the base 4 is provided with a buckle cover assembly outside the three protective connection assemblies; the inertial measurement unit 1, the Beidou compass module 2 and the main control unit 3 are respectively installed on the three protective connection assemblies;

[0030] The inertial measurement unit 1, the Beidou compass module 2 and the main control unit 3 are independently installed on the base 4 through the protective connection assemblies, so as to ensure that other components are not mistakenly touched when the inertial measurement unit 1, the Beidou compass module 2 or the main control unit 3 is installed and maintained, and the safety of other components is ensured;

[0031] Specifically, each protective connection assembly includes a mounting groove seat 5, a support 6 is arranged on the outer side wall surface of the mounting groove seat 5, the lower wall surface of the support 6 is located below the lower wall surface of the mounting groove seat 5, the support 6 is installed on the inner side bottom surface of the mounting groove seat 5 through a first bolt 7, a heat dissipation hole 8 is formed in the center part of the bottom surface of the mounting groove seat 5, a recess is formed in the lower wall surface of the mounting groove seat 5 coaxially with the heat dissipation hole 8, a heat conduction block 9 is filled between the recess and the mounting groove seat 5, and L-shaped air holes 10 are arranged in a circular array on the heat conduction block 9;

[0032] It needs to be explained that the installation groove seat 5 is used for installing the inertial measurement unit 1, the compass module 2 or the master control unit 3, the installation groove seat 5 is fixed on the base 4 through the support 6, at this time, the distance between the lower wall surface of the installation groove seat 5 and the base 4 is used for ventilation, ensuring the heat dissipation of the inertial measurement unit 1, the compass module 2 or the master control unit 3, the heat conduction block 9 is made of high thermal conductivity material, which can absorb and conduct the heat generated by the inertial measurement unit 1, the compass module 2 or the master control unit 3, the L-shaped air hole 10 is used for air circulation to accelerate heat dissipation;

[0033] Specifically, the buckle cover assembly includes a top cover 11, the top cover 11 is installed on the base 4 through the second bolt 12, and the top cover 11 is provided with a wire hole 13 on the side wall surface;

[0034] It needs to be explained that the top cover 11 is used for shielding and protecting the inertial measurement unit 1, the compass module 2 and the master control unit 3, and the wire hole 13 is used for air circulation to ensure heat dissipation and signal transmission line passing;

[0035] As preferred, further, a plurality of notches 14 are arranged on the side wall surface of the installation groove seat 5 for signal transmission line passing;

[0036] As preferred, further, one end of the L-shaped air hole 10 is aligned with the heat dissipation hole 8, and the other end of the L-shaped air hole 10 is aligned with the lower part of the installation groove seat 5;

[0037] As preferred, further, the heat conduction block 9 is a cylindrical graphene block structure for heat conduction without shielding signals.

[0038] Although the embodiments of the utility model have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and spirits of the utility model, the scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. A device for high frequency control of a beam of a phased array satellite communication antenna, characterized in that Including inertial measurement unit (1), compass module (2) and master unit (3); The inertial measurement unit (1) and the compass module (2) are in communication with the master unit (3); The inertial measurement unit (1), the compass module (2) and the master unit (3) are provided with mounting structures; The mounting structure includes a base (4), and the base (4) is provided with three protective connection assemblies, and a buckle cover assembly is arranged on the base (4) and outside the three protective connection assemblies; The inertial measurement unit (1), the compass module (2) and the master unit (3) are respectively mounted on the three protective connection assemblies.

2. The phased array satcom antenna beam high frequency control device of claim 1, wherein, Each protective connection assembly includes a mounting groove seat (5), a support (6) is arranged on the outer side wall surface of the mounting groove seat (5), the lower wall surface of the support (6) is located below the lower wall surface of the mounting groove seat (5), the support (6) is installed on the inner side bottom surface of the mounting groove seat (5) through a first bolt (7), a heat dissipation hole (8) is formed in the center of the bottom surface of the mounting groove seat (5), a recess is formed in the lower wall surface of the mounting groove seat (5) and coaxial with the heat dissipation hole (8), a heat conduction block (9) is filled between the recess and the mounting groove seat (5), and a plurality of L-shaped air holes (10) are formed in the heat conduction block (9) in a circular array.

3. The phased array satcom antenna beam high frequency control device of claim 1, wherein, The buckle cover assembly includes a top cover (11), and the top cover (11) is installed on the base (4) through a second bolt (12); a wire hole (13) is formed in the side wall surface of the top cover (11).

4. The phased array satcom antenna beam high frequency control device of claim 2, wherein, A plurality of notches (14) are formed in the side wall surface of the mounting groove seat (5).

5. The phased array satcom antenna beam HF control apparatus of claim 2, wherein, One end of the L-shaped air hole (10) is aligned with the heat dissipation hole (8), and the other end of the L-shaped air hole (10) is aligned with the lower part of the mounting groove seat (5).

6. The phased array satcom antenna beam high frequency control device of claim 2, wherein, The heat conduction block (9) is a cylindrical graphene block structure.

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