CN102801435B - A kind of C being applicable to moonlet launching site and using 3i system - Google Patents

Abstract

The invention discloses a C ³ I system suitable for use in small satellite launch sites, including: a launch site C ³ I system, a main test processor, a parameter forwarding module, a parameter subscription module, a first data return module, a second Data return module. Before the satellite launch, the parameter subscription module receives the telemetry parameter engineering value by the main test computer according to the telemetry parameter number of each satellite, and sends it to the parameter forwarding module; the parameter forwarding module transmits the received telemetry parameter engineering value The value is forwarded to the launch site C ³ I system. After the satellite is launched, the first data return module receives the original telemetry code values of different satellites from the C3I system ^of the launch site, and converts the original telemetry code values into telemetry frames used by the satellite test network and sends them to the second A data return module; the second data return module sends the original frame to the main test processor for analysis by the main test processor. The invention can solve the problem of communication between a plurality of satellites and the launching site at the same time.

Description

A C3I system suitable for small satellite launching sites

technical field

The invention relates to a C ³ I system suitable for use in small satellite launch sites.

Background technique

The C ³ I (Command, Control, Communications & Intelligence) system of the small satellite launch site is mainly used to complete the command, control and coordination of the launch site and the satellite system, and make decisions at the same time. Before the satellite is launched, the satellite C ³ I system sends the pre-agreed satellite telemetry decoding value to the launch site C ³ I system to provide the operating status of each subsystem of the satellite, and the launch site C ³ I system sends the satellite C ³ I system weather and command information to the satellite C 3 I system. and other information; after the satellite is launched, the C ³ I system of the launching site sends the original code information of the satellite telemetry to the satellite C ³ I system in the format of the satellite measurement and transmission information frame, and the satellite C ³ I system processes the satellite measurement and transmission information frame The format of the original telemetry code is sent to the satellite test network. The satellite test network analyzes the telemetry source code information, obtains the in-orbit operation data of the satellite, and sends the parsed data to the test network.

At present, the C ³ I system of the small satellite launch site is mainly applicable to the single satellite mode, and the C ³ I system in the single satellite mode communicates with the launch site by means of point-to-point and group broadcasting. Figure 1 shows a typical small satellite C ³ I Schematic diagram of the composition of the system and the launch site C ³ I system. In Figure 1, the system includes the interface computer between the satellite network and the C ³ I system, and the satellite network switch, which are mainly responsible for the acquisition of satellite test data, data analysis, data storage, data exchange, and data display.

With the development of small satellites, a multi-satellite launch mode has gradually appeared at the launch site. ^The existing C3I system in the single ^- satellite mode can only provide the communication function between the test network of a single satellite and the C3I system at the launch site. , In addition, due to the limitations of its logical structure, the performance of the system is affected, and it can no longer meet the requirements of multiple satellites communicating with the C ³ I system of the launch site at the same time.

Contents of the invention

The problem solved by the technology of the present invention is to provide a C ³ I system suitable for use in small satellite launch sites in view of the deficiencies of the prior art. Adopting the present invention can solve the communication problem between multiple satellites and the launching site at the same time.

Technical solution of the present invention is:

A C ³ I system suitable for small satellite launching sites, comprising: a launching site C ³ I system, a main test processor, a parameter forwarding module, a parameter subscription module, a first data return module, and a second data return module ,

Before the satellite is launched, the parameter subscription module receives the telemetry parameter engineering value corresponding to the telemetry parameter number of each satellite returned by the main test computer according to the telemetry parameter numbers of multiple satellites, and sends it to the parameter forwarding module; the parameter forwarding module forwards the received telemetry parameter engineering value to the launch site C ³ I system;

After the satellite is launched, the first data return module receives the original telemetry code values of different satellites from the C3I system ^of the launch site, and converts the original telemetry code values into telemetry frames used by the satellite test network and sends them to the second A data return module; the second data return module sends the original frame to the main test processor for analysis by the main test processor.

Further, the parameter subscription module distinguishes the satellites through a form, and the form corresponding to each satellite records the telemetry parameter name and telemetry parameter number subscribed to the main test computer.

Further, the parameter forwarding module organizes the telemetry parameter engineering values on the list of each satellite into an information frame and sends it to the launch site C ³ I system.

Compared with the prior art, the present invention has the following advantages:

(1) The present invention adopts a modular design, with functional modules such as the parameter forwarding module, the parameter subscription module, the first data return module, and the second data return module as the main functional modules. Post-launch workflow. At the same time, it is applicable to the launch site mission of a single satellite or multiple satellites;

(2) The present invention adopts an object-oriented analysis and design method, follows the principle of component design, clarifies and optimizes the data structure and processing flow of modules, ensures the hierarchy and calling relationship between modules, and can improve the operating efficiency of the system;

(3) Compared with the existing C ³ I system, the present invention can carry out the system setting of multiple satellites through the page configuration item to meet the configuration requirements of different tasks. At the same time, use the form to distinguish the subscription parameters of multiple satellites, the configuration form can be changed flexibly, and only need to be re-imported after the change. The system is flexible and reusable, and the same version of the program can complete the work of launching sites for multiple satellites;

(4) Each module of the present invention is divided according to task requirements, and has clear and independent functions, and can respectively complete functions such as data analysis, data format processing, data display, and data storage. At the same time, the modules are closely connected, and the data reception and data transmission between the modules are completed through the corresponding external interfaces. Such as: the parameter forwarding module and the first data return module need to complete data processing, and at the same time complete the data exchange with the launch site ^C3I ; the subscription parameter module needs to pass through different port numbers to complete the reading and verification of the form Subscribe the corresponding telemetry parameters to the main test processor; the second data return module needs to be responsible for communicating with the main test processor after launch, and transmit the data to the test network.

Description of drawings

Figure 1 is a schematic diagram of the composition of the small satellite C ³ I system and the launch site C ³ I system;

Fig. 2 is a schematic diagram of the present invention;

Figure 3 is a parameter subscription module;

Fig. 4 is a schematic diagram of a parameter forwarding module;

Fig. 5 is a schematic diagram of receiving and sending data by the first data return module;

Fig. 6 is a schematic diagram of data sent by the second data return module;

Figure 7 is a flow chart before launch;

Figure 8 is a post-launch flow chart.

Detailed ways

The present invention will be further introduced below in conjunction with the accompanying drawings.

As shown in Figure ² , the C3I system applicable to the small satellite launch site according to the present invention includes: the launch site ^C3I system, the main test processor, the parameter forwarding module, the parameter subscription module, and the first data return module, a second data return module, a display module, and a data storage module.

Before launching, the subscribing parameter module is responsible for subscribing parameters to the main test processor (MTP, Main Test Processor), and the MTP returns corresponding telemetry engineering value to the subscribing parameter module according to the telemetry parameter number corresponding to each satellite sent by the subscribing parameter module . The subscription parameter module outputs the obtained telemetry engineering value to the parameter forwarding module, and the parameter forwarding module packs the telemetry engineering value into an information frame according to the communication protocol format, and forwards the information frame to the C ³ I system of the launch site, and outputs it to the launch site C ³ The telemetry engineering value of the I system can also be used to output the display module for display.

As shown in Figure 3, in the parameter subscription module, the telemetry parameter number of each satellite sent to the MTP distinguishes different satellites through a form. For example, for three satellites A, B, and C, use the single table pick point_A, single table pick point_B, and single table pick point_C to record the telemetry parameter numbers of the corresponding satellites that need to be subscribed. The parameter subscription module sends the telemetry parameter number to the MTP by reading the three telemetry parameter tables, and the three processes MTP_A, MTP_B, and MTP_C corresponding to the satellites A, B, and C in the MTP return corresponding information to the parameter subscription module according to the telemetry parameter number. The engineering value of the telemetry parameter. In the parameter subscription module, data exchange with multiple MTPs can be supported at the same time, which can meet the mission requirements of multiple satellites with one arrow.

In the multi-satellite mode, when sending the telemetry parameter numbers in the form corresponding to different satellites to the MTP, it is necessary to configure the network address and port number of the MTP. For example: satellite A corresponds to MTP network address 192.9.200.10, port 4003; satellite B corresponds to MTP network address 192.9.200.10, port 4103; satellite C corresponds to MTP network address 192.9.200.10, port 4203.

As shown in Figure 4, in the parameter forwarding module, the engineering value of the telemetry parameter stored in the temporary variable is first read out, and then the engineering value of the telemetry parameter is packaged into an information frame according to the communication protocol applicable to the satellite, and then through the multicast method Send to launch site C ³ I system until requested to stop sending

The first data return module receives the weather data and command information sent to the small satellite C ³ I system by the C ³ I system of the receiving launch site, and outputs the antenna data and command information to the display module for display after analyzing the antenna data and command information. As shown in Figure 5, after the first return data module receives the information containing weather data and command data from the C ³ I system of the launching site, it analyzes the information according to the agreement of the communication protocol, and then the obtained weather The data and command data are sent to the display module for display.

After launch, the first data return module receives the telemetry original code values corresponding to different satellites sent back by the C ³ I system of the launch site, and stores the telemetry original code values with the data storage module. At the same time, the first data return module converts the telemetry original code value into the telemetry frame used by the satellite test network and sends it to the second data return module, and the received telemetry frame is sent by the second data return module to MTP.

As shown in Figure 6, the second data return module first connects to the MTP according to the address and port number, sends sign-in information to the MTP, then synchronizes with the MTP, and sends the telemetry frame from the C ³ I system of the launch site to the MTP again. The telemetry frames corresponding to different satellites correspond to different processes sent to the MTP, so as to meet the mission requirements of one arrow with multiple satellites.

As shown in Figure 7, before launching, set the MTP address and port, and load the single-point table made according to the communication protocol. During the loading process, the system checkpoint table format, if the format is wrong, the program will stop and continue to execute and return , until the point table format is modified correctly. If the point table is loaded correctly, subscribe the telemetry parameters in the point table to MTP. If the subscription fails, the program returns. If the subscription is successful, the subscription data will be displayed, and the information frame will be generated according to the communication protocol according to the set sending interval. Send information frames to the launch site C ³ I system until it stops sending.

As shown in Figure 8, after launching, set the address and port of the C ³ I system at the launch site, and start receiving the data sent to the satellite test network by the C ³ I system at the launch site, and if the receiving status is correct, convert the format of the data , send the converted raw frame telemetry to the MTP until it stops sending.

Parts not described in detail in the present invention belong to the common knowledge of those skilled in the art.

Claims (2)

^1. A kind of C3I system that is applicable to the use of small satellite launch site is characterized in that comprising: launch site ^C3I system, main test processor, parameter forwarding module, parameter subscription module, the first data return module, the first Two data return module, Before the satellite is launched, the parameter subscription module receives the telemetry parameter engineering value corresponding to the telemetry parameter number of each satellite returned by the main test processor according to the telemetry parameter numbers of multiple satellites, and sends it to the parameter forwarding module; the parameter forwarding module forwards the received telemetry parameter engineering value to the launch site C ³ I system; After the satellite is launched, the first data return module receives the original telemetry code values of different satellites from the C3I system ^of the launch site, and converts the original telemetry code values into telemetry frames used by the satellite test network and sends them to the second Data return module; the second data return module sends the original frame to the main test processor, which is analyzed by the main test processor; The parameter subscription module distinguishes the satellites through a form, and the form corresponding to each satellite records the telemetry parameter name and telemetry parameter number subscribed to the main test processor. 2. A kind of C ³ I system applicable to the use of small satellite launch sites as claimed in claim 1, characterized in that: said parameter forwarding module organizes the telemetry parameter engineering value on each satellite form into an information frame and sends it to the launch site C ³ I system.