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Automatic spacecraft test data interpreting method

A technology of test data and spacecraft, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as manual interpretation cannot form interpretation history records, unfavorable telemetry data analysis, high cost of manual interpretation, etc., to improve judgment Efficiency, enhanced analyzability, time-saving effects

Active Publication Date: 2013-07-24
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0006] In the previous comprehensive test of spacecraft models, data interpretation was mainly based on manual interpretation, which has three shortcomings: first, the cost of manual interpretation is very high; second, manual interpretation may misjudge or miss relevant data; 3. Manual interpretation cannot form interpretation history records, which is not conducive to telemetry data analysis

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Embodiment Construction

[0029] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0030] Such as figure 1 As shown, in the existing spacecraft comprehensive test process, generally speaking, each telemetry parameter has a certain range or change law under the same technical state, and this range or law is generally listed in the spacecraft design document. reflected in. The spacecraft generates a large amount of downlink telemetry data, and the downlink telemetry data is received by the main test processor, and then the staff processes the telemetry data according to the range or change rule of the telemetry parameters, and finally distributes the processing results to the comprehensive test monitoring terminals. Due to the large amount of telemetry data and many types, the processing work of the staff is extremely heavy, and mistakes such as misjudgments are prone to occur during the processing process, which will have a negative impa...

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Abstract

The invention discloses an automatic spacecraft test data interpreting method. Telemetering data or a telemetering order is automatically interpreted by setting up an interpreting rule base, an interpreting conclusion data base and an executive engine on an existing telemetering measuring system. An interpreting conclusion is transmitted to a compressive testing and monitoring terminal to achieve automatic interpreting and displaying of spacecraft test data. Working efficiency in interpreting the telemetering data is greatly improved and meanwhile, reliability of a spacecraft is improved. The interpreting conclusion is transmitted to the interpreting conclusion data base for storing, analyzing can be performed on historic interpreting conclusions of the telemetering data and then a report is formed. Analyzability of the telemetering data is enhanced. A blackboard zone is set up in the executive engine so as to store all the telemetering data which need testing. In a real-time testing process, an internal storage is prevented from continuously loading telemetering data as long as one or more data parameter values are updated according to current telemetering data. Thus, time is saved and efficiency in judging is improved.

Description

technical field [0001] The invention relates to the technical field of data interpretation, in particular to an automatic interpretation method for spacecraft test data. Background technique [0002] Interpretation of spacecraft comprehensive test telemetry data refers to monitoring the downlink telemetry data of the spacecraft and analyzing whether the downlink telemetry data meets the design indicators under certain conditions or states during the spacecraft comprehensive test process. For example, when the digital control subsystem is powered on, the range of the A parameter should be [a, b]. If the A parameter is not in the range [a, b] when the digital control subsystem is powered on, then in this state If the A parameter does not match the design index, it is necessary to analyze the stand-alone and subsystems related to the A parameter according to the situation, and what causes the A parameter to be inconsistent with the design index, so as to locate the failure and ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/30
Inventor 王效楠何晓宇向永清白少华薛亮罗光辰曹宇
Owner BEIJING INST OF SPACECRAFT SYST ENG
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