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Analytic system and analytic method for simulating data information of spacecraft in flight

A data information and analysis system technology, applied in the direction of digital transmission system, transmission system, data exchange network, etc., can solve the problem of low efficiency of the analysis system, and achieve the effects of avoiding system delay, improving work efficiency, and avoiding congestion

Inactive Publication Date: 2018-04-03
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

[0004] The purpose of the present invention is to provide an analysis system and analysis method for spacecraft data information in simulated flight, to solve the problem of low efficiency of the analysis system in the simulated flight test process of spacecraft

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  • Analytic system and analytic method for simulating data information of spacecraft in flight
  • Analytic system and analytic method for simulating data information of spacecraft in flight
  • Analytic system and analytic method for simulating data information of spacecraft in flight

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Embodiment approach

[0066] According to an embodiment of the present invention, the data information includes test information, engineering telemetry data information, and data tube telemetry data information. In this embodiment, the test information is transmitted by the front-end transmission unit 1 to the spacecraft A, where the test information includes file information, remote control command information, and program control command information. In this embodiment, both the engineering telemetry data information and the data tube telemetry data information are transmitted from the spacecraft A to the front-end transmission unit 1.

[0067] Such as figure 1 As shown, according to an embodiment of the present invention, the front-end transmission unit 1 includes a measurement, control and remote control sub-unit 11 and a data tube instruction sub-unit 12. In this embodiment, the front-end transmission unit 1 sends remote control instruction information and file information to the spacecraft A thr...

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Abstract

The invention relates to an analytic system and an analytic method for simulating the data information of a spacecraft in flight, wherein the analytic system comprises a front-end transmission unit, which is used for two-way transmission of data information with the spacecraft; a front-end processing unit, which is used for controlling the front-end transmission unit and collecting the data information in the front-end transmission unit; and a rear-end processing unit, which is used for acquiring the data information in the front-end processing unit and analyzing the data information. The comparison of execution of commands on the spacecraft is quick and accurate, meanwhile, the spacecraft can be interpreted in real time, when abnormality appears, sound or image alarm can be automaticallyand timely performed, so that a user can respond within a short time, and delay is avoided.

Description

Technical field [0001] The invention relates to an analysis system and analysis method of spacecraft information, in particular to an analysis system and analysis method for simulating spacecraft data information in flight. Background technique [0002] During the simulation flight test of the spacecraft, the spacecraft data management sub-system autonomously sends program-controlled commands, while the ground test equipment injects commands and files into the spacecraft. The testers need to monitor the sending and execution of all commands and files. Due to the large number of injected instructions and files, and the small transmission time slot, it is difficult for the interpreter to make timely and accurate interpretation. [0003] For example, the application publication number CN105334756A, titled "A closed-loop simulation and verification system and method for agile satellite mission interpretation", is to use the agile satellite mission interpretation closed-loop simulation ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H04L12/26H04L29/08B64G7/00
CPCB64G7/00H04L43/50H04L67/12
Inventor 杨枫张悦
Owner BEIJING SPACE TECH RES & TEST CENT
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