C3I system applicable to small satellite launch site

A launch site, C3I technology, applied in the field of C3I system, to achieve the effect of ensuring the level, improving the operation efficiency, and clear functions

Active Publication Date: 2012-11-28
AEROSPACE DONGFANGHONG SATELLITE
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Adopting the present invention can solve the communication proble

Method used

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  • C3I system applicable to small satellite launch site
  • C3I system applicable to small satellite launch site
  • C3I system applicable to small satellite launch site

Examples

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[0025] The present invention will be further introduced below in conjunction with the drawings.

[0026] Such as figure 2 As shown, the C 3 I system, including: launch site C 3 I system, main test processor, parameter forwarding module, parameter subscription module, first data return module, second data return module, display module, data storage module.

[0027] Before launch, the subscription parameter module is responsible for subscribing to the main test processor (MTP, Main Test Processor). The MTP returns the corresponding telemetry project value to the subscription parameter module according to the telemetry parameter number corresponding to each satellite sent by the subscription parameter module. . The subscription parameter module outputs the obtained telemetry project value to the parameter forwarding module. The parameter forwarding module packages the telemetered project value into an information frame according to the communication protocol format, and forwards the ...

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Abstract

The invention discloses a C3I system applicable to a small satellite launch site, comprising a launch site C3I system, a main testing processor, a parameter transmitting module, a parameter subscription module, a first data returning module and a second data returning module. Before a satellite is launched, the parameter subscription module receives a parameter engineering value which is remotely measured by a main testing computer according to a remotely-measured parameter number of each satellite, and sends the parameter engineering value to the parameter transmitting module; and the parameter transmitting module sends the received remotely-measured parameter value to the C3I system of the launch site. After the satellite is launched, the first data returning module receives remotely-measured original code values of the different satellites from the C3I system of the launch site, converts the remotely-measured original code values into a remotely-measured frames used by a satellite testing net and sends the remotely-measured frames to the second data returning module; and the second data returning module sends the original frames to the main testing computer and are analyzed by the main testing computer. With the adoption of the C3I system applicable to the small satellite launch site disclosed by the invention, the communication problem among a plurality of the satellites and the launch site can be solved.

Description

technical field [0001] The invention relates to a C 3 I system. Background technique [0002] Small Satellite Launch Site C 3 The I (Command, Control, Communications & Intelligence) system 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 satellite launch, satellite C 3 I system to launch site C 3 System I sends the satellite telemetry decoding value agreed in advance to provide the operating status of each subsystem of the satellite. Launch site C 3 I system to satellite C 3 System I sends weather, command and other information; after the satellite is launched, launch site C 3 System I sends the original code information of satellite telemetry to satellite C in the format of satellite telemetry information frame format 3 On system I, satellite C 3 The I system processes the satellite measurement and transmission information frame into the format of the original te...

Claims

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Application Information

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IPC IPC(8): H04B1/38H04B10/105H04B1/44H04B10/118
Inventor 李敬博任光杰马楠李岩戴涧峰
Owner AEROSPACE DONGFANGHONG SATELLITE
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