CN220934381U

CN220934381U - Antenna control assembly suitable for low orbit satellite to star

Info

Publication number: CN220934381U
Application number: CN202323059297.2U
Authority: CN
Inventors: 罗文彬; 顾海燕; 阳灿; 何建; 奉鸣; 旷小兵; 赵为民
Original assignee: Sichuan Netop Telecom Co ltd
Current assignee: Sichuan Netop Telecom Co ltd
Priority date: 2023-11-10
Filing date: 2023-11-10
Publication date: 2024-05-10
Anticipated expiration: 2033-11-10

Abstract

The utility model discloses an antenna control assembly suitable for low orbit satellite-to-satellite, which comprises an ephemeris resolving module and further comprises: an integrated board I which is used for integrally arranging the ephemeris resolving module and the main control ARM module; an integrated board II and an integrated board III for carrying out split design on the network exchange module and the Modem module; a back plate connected to each integrated board; the back plate supplies power for the integrated boards I and III through +24V input provided by the outside, and the Modem module supplies power to the network switching module through the back plate. The utility model provides an antenna control assembly suitable for satellite alignment of a low-orbit satellite, which integrates an independent MODEM module, a control ARM module and an ephemeris resolving module into one control assembly by adopting an onboard design, so that satellite alignment work of one control assembly suitable for a plurality of sets of low-orbit antennas can be realized.

Description

Antenna control assembly suitable for low orbit satellite to star

Technical Field

The utility model relates to the field of satellite pairs. More particularly, the present utility model relates to an antenna control assembly suitable for low-orbit satellite pairs.

Background

With the development of iridium satellite planning, star chain planning and rainbow cloud engineering, low-orbit satellites are from abroad to domestic, the low-orbit satellites have short transmission delay and small path loss due to low orbit height, can provide high-speed internet service, can meet the requirement that users can enjoy the same internet access experience at home wherever they are located, such as deserts, high mountains and oceans, and can ensure that better signals can be provided in beam coverage moment when the low-orbit satellites bypass from the sky, and the ground low-orbit satellite antennas are required to be aligned to keep up with the low-orbit satellites.

In practical applications, in order to realize the above functions, the antenna control module is usually used to realize the functions, but in the prior art, the control module of the low-rail antenna itself cannot be used to combine the ephemeris resolving module and the MODEM module, so that the components can only be matched with each other by using the corresponding components, and the split design of the components is inconvenient for integrated management, so that an integrated on-board antenna control module is required to be designed to realize the functions of ephemeris introduction and ephemeris resolving.

Disclosure of utility model

It is an object of the present utility model to address the above problems and/or disadvantages and to provide advantages which will be described below.

To achieve these objects and other advantages and in accordance with the purpose of the utility model, as embodied and broadly described herein, there is provided an antenna control assembly for a low orbit satellite pair, comprising an ephemeris resolving module, further comprising:

An integrated board I which is used for integrally arranging the ephemeris resolving module and the main control ARM module;

An integrated board II and an integrated board III for carrying out split design on the network exchange module and the Modem module;

A back plate connected to each integrated board;

the back plate supplies power for the integrated boards I and III through +24V input provided by the outside, and the Modem module supplies power to the network switching module through the back plate.

Preferably, the main control ARM module is respectively connected with the Modem module and the network switching module through an RS422 interface and a network port;

the integrated board I is also provided with a GPS module connected with the Modem module;

And the integrated board I is also provided with an interface conversion module so as to provide a second pulse signal for the Modem module through an external GPS antenna.

Preferably, the integrated board I is provided with an ephemeris resolving and debugging serial port, a main control ARM debugging serial port and a GPS antenna interface;

the integrated board II is provided with a TX interface, an RX interface, a 20M interface and a service interface;

And the integrated board III is provided with a LAN interface, a WAN interface and a WIFI antenna interface.

Preferably, the integrated board i is further provided with a DC/DC conversion module, so as to provide an operating voltage of 5V to 3.3V and 3.3V to 1.5V for the corresponding module on the integrated board i.

The utility model at least comprises the following beneficial effects: the utility model integrates the independent MODEM module, the control ARM module and the ephemeris resolving module into one control component by adopting the on-board design, so that the satellite matching work of one control component applicable to a plurality of sets of low-rail antennas can be realized;

Furthermore, the board card type design adopted by the utility model is beneficial to recycling, realizes the control of a plurality of sets of low-orbit satellite antennas by one set of antenna control assembly, saves the cost and is convenient to install and debug.

Additional advantages, objects, and features of the utility model will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the utility model.

Drawings

FIG. 1 is a schematic diagram of a layout of an antenna control assembly for a low-orbit satellite pair according to an embodiment of the present utility model;

FIG. 2 is a schematic diagram of a low-orbit satellite-to-satellite operational relationship;

FIG. 3 is a schematic diagram of the communication relationship between the ephemeris resolving module and the control ARM module.

Detailed Description

The present utility model is described in further detail below with reference to the drawings to enable those skilled in the art to practice the utility model by referring to the description.

It will be understood that terms, such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.

It should be noted that, in the description of the present utility model, the orientation or positional relationship indicated by the term is based on the orientation or positional relationship shown in the drawings, which are merely for convenience of describing the present utility model and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present utility model. Furthermore, the terms "I", "II" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "configured to," "engaged with," "connected to," and the like are to be construed broadly, and for example, "connected" may be a fixed connection, may be a detachable connection, or may be integrally connected, may be mechanically connected, may be electrically connected, may be directly connected, may be indirectly connected through an intermediate medium, may be communication between two members, and may be understood in a specific manner by those skilled in the art.

Furthermore, in the present utility model, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be a direct contact of the first and second features, or an indirect contact of the first and second features through an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.

Example 1

The working block diagram of the low-orbit satellite pair is shown in figure 2, and relates to an aerial low-orbit satellite, a low-orbit satellite antenna of a ground user side, an antenna control component, a MODEM module, an ephemeris resolving module and an ARM control module, so that different functions of the low-orbit satellite pair can be realized, two ephemeris acquisition modes can be provided, and manual ephemeris introduction and automatic ephemeris acquisition can be realized;

in practical application, the MODEM module is used for automatically receiving the ephemeris file and sending the ephemeris file to the ephemeris resolving module;

The control ARM module is used for realizing the function of manually importing the ephemeris module, receiving the resolving result output by the ephemeris resolving module, and executing manual star-to-star and automatic star-to-star operations;

Ephemeris resolving module: the method is used for realizing the calculation of the input ephemeris file, outputting the ephemeris calculation result to the control ARM module, wherein the data interaction relation between the ephemeris calculation module and the control ARM module is shown in figure 3, and a path for introducing ephemeris is provided through the ephemeris calculation module; realizing real-time calculation of the ephemeris of the low-orbit satellite by an ephemeris calculation module;

Further, as shown in fig. 1, the antenna control assembly suitable for low-orbit satellite-to-satellite further includes:

an integrated board I3 which is integrally arranged with the ephemeris resolving module 1 and the main control ARM module 2;

An integrated board II 6 and an integrated board III 7 which are used for carrying out split design on the network exchange module 4 and the Modem module 5;

A back plate 8 connected to each integrated board;

Working principle: in practical application, the scheme consists of 3 integrated boards and a backboard, wherein an ephemeris resolving module and a main control ARM module are arranged on the same board (1#), a Modem module is a single board (3#) and a 2# board for providing network exchange and WIFI.

The antenna control assembly of this scheme is through the +24V that the backplate outside provided as the power supply input, provides the electric energy for three integrated boards, and wherein the power supply of network switching module is by modem through the direct 5V/3A power supply that provides of bottom plate, other two integrated boards are through the direct power supply of bottom plate.

The scheme provides a manual and automatic ephemeris acquisition mode through a MODEM module and a control ARM module; the acquired ephemeris file is sent to an ephemeris resolving module, real-time longitude and latitude information per second is obtained through the ephemeris resolving function of the ephemeris resolving module, the information is sent to a control ARM module, and two modes of manual control for satellites or automatic control for satellites are adopted on a web upper computer of the control ARM module, so that the purposes of controlling manual alignment of a low-orbit satellite antenna and automatically tracking a low-orbit satellite in an alignment sky by a program are achieved;

The integrated operation is adopted, the ephemeris file is obtained manually and automatically through the control ARM module and the modulation-demodulation module, the obtained ephemeris file is sent to the ephemeris resolving module, real-time longitude and latitude height information per second is obtained through resolving and sent to the control ARM module, two modes of manual control for satellites or automatic control for satellites are adopted on a web upper computer of the control ARM module, and a low-orbit satellite antenna is controlled to realize manual alignment and program automatic tracking for low-orbit satellites in an aligned sky.

Example 2

Embodiment 2, which is a preferred embodiment of the present utility model, has a specific structure as shown in fig. 1-2, and the following modifications are disclosed on the basis of embodiment 1:

The main control ARM module is respectively connected with the Modem module and the network switching module through an RS422 interface and a network port;

The integrated board I is also provided with a GPS module 9 connected with the Modem module;

The integrated board I is also provided with an interface conversion module 10 for providing a second pulse signal to the Modem module through an external GPS antenna;

The integrated board I is also provided with a DC/DC conversion module I11 for providing working voltages of 5V to 3.3V and 3.3V to 1.5V for corresponding modules on the integrated board I, and the integrated board II is provided with a DC/DC conversion module II 12;

An ephemeris resolving and debugging serial port, a main control ARM debugging serial port and a GPS antenna interface are arranged on the integrated board I;

Working principle: in the scheme, a No. 1 board is provided with an ephemeris resolving debugging serial port, a main control ARM debugging serial port and a GPS antenna interface; the 2# board is provided with three interfaces, namely a LAN port, a WAN port and a WIFI antenna; the 3# board is provided with four interfaces of TX, RX, 20M and a service port; the board 1 is a core board, provides interface conversion, provides a second pulse signal for the modem module through an external GPS antenna, provides DC/DC and power supply conversion functions, and has the advantages that through the design of the board interface, each board card is independent in function, so that the problem searching is facilitated; meanwhile, the antenna control assembly is physically separated from the low-rail antenna, so that one antenna control assembly is suitable for the star alignment of multiple sets of low-rail antennas, and the cost is saved.

The above embodiments are merely illustrative of a preferred embodiment, but are not limited thereto. In practicing the present utility model, appropriate substitutions and/or modifications may be made according to the needs of the user.

The number of equipment and the scale of processing described herein are intended to simplify the description of the present utility model. Applications, modifications and variations of the present utility model will be readily apparent to those skilled in the art.

Although embodiments of the utility model have been disclosed above, they are not limited to the use listed in the specification and embodiments. It can be applied to various fields suitable for the present utility model. Additional modifications will readily occur to those skilled in the art. Therefore, the utility model is not to be limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.

Claims

1. An antenna control assembly for low orbit satellite-to-satellite comprising an ephemeris resolution module, further comprising:

A back plate connected to each integrated board;

2. The antenna control assembly for low-orbit satellite pair as claimed in claim 1, wherein the main control ARM module is respectively connected with the Modem module and the network switching module through an RS422 interface and a network port;

3. The antenna control assembly for low-orbit satellite pair satellites according to claim 2, wherein an ephemeris resolving and debugging serial port, a master ARM debugging serial port and a GPS antenna interface are arranged on the integrated board i;

4. The antenna control assembly for a low-orbit satellite according to claim 2, wherein the integrated board i is further provided with a DC/DC conversion module for providing the corresponding module on the integrated board i with an operating voltage of 5V to 3.3V and 3.3V to 1.5V.