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CN103218451A - Automatic spacecraft test data interpreting method - Google Patents

Automatic spacecraft test data interpreting method Download PDF

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CN103218451A
CN103218451A CN2013101529179A CN201310152917A CN103218451A CN 103218451 A CN103218451 A CN 103218451A CN 2013101529179 A CN2013101529179 A CN 2013101529179A CN 201310152917 A CN201310152917 A CN 201310152917A CN 103218451 A CN103218451 A CN 103218451A
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interpretation
telemetry
data
spacecraft
execution engine
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CN103218451B (en
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王效楠
何晓宇
向永清
白少华
薛亮
罗光辰
曹宇
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Beijing Institute of Spacecraft System Engineering
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Beijing Institute of Spacecraft System Engineering
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Abstract

本发明公开了一种航天器测试数据自动判读方法，通过在现有遥测测试系统中建立判读规则库、判读结论数据库以及执行引擎，完成遥测数据或指令的自动判读，并将判读结论发送给综合测试监视终端，实现航天器测试数据的自动判读和显示，能够大大提高遥测数据判读工作效率，同时提高航天器可靠性；将判读结论推送给判读结论数据库进行存储，能够对遥测数据的历史判读结论进行分析并形成报表，增强了遥测数据的可分析性；通过在执行引擎中建立黑板区，存储所有需要测试的遥测数据，在实时测试过程中，只需要根据当前遥测数据更新遥测数据中的一种或多种数据参数值，避免内存不断加载遥测数据，节省时间，提高判断效率。

Figure 201310152917

The invention discloses an automatic interpretation method of spacecraft test data. By establishing an interpretation rule base, an interpretation conclusion database and an execution engine in the existing telemetry test system, the automatic interpretation of telemetry data or instructions is completed, and the interpretation conclusion is sent to the comprehensive Test the monitoring terminal to realize the automatic interpretation and display of spacecraft test data, which can greatly improve the efficiency of telemetry data interpretation and improve the reliability of spacecraft; push the interpretation conclusion to the interpretation conclusion database for storage, and can make historical interpretation conclusions of telemetry data Analyze and form reports to enhance the analyzability of telemetry data; by establishing a blackboard area in the execution engine to store all telemetry data that needs to be tested, in the real-time test process, only one part of the telemetry data needs to be updated according to the current telemetry data One or more data parameter values to avoid continuous loading of telemetry data in the memory, save time and improve judgment efficiency.

Figure 201310152917

Description

A kind of spacecraft test data automatic interpretation method
Technical field
The present invention relates to the data interpretation technical field, be specifically related to a kind of spacecraft test data automatic interpretation method.
Background technology
The interpretation of spacecraft integration test telemetry is meant in spacecraft integration test process, meet some requirements or state under, the telemetry descending to spacecraft monitors, analyzes a kind of work whether descending telemetry satisfies design objective.For example under the data handling subsystem powering state, the scope of A parameter should be [a, b], if under data handling subsystem powers up situation, the A parameter is not at scope [a, b] in, so in this state, A parameter and design objective are not inconsistent, and need according to circumstances unit, the subsystem of A parameter correlation to be analyzed, be that what reason causes A parameter and design objective not to be inconsistent, thus the fault and the defective of location spacecraft.The automatic interpretation of current spacecraft integration test telemetry comprises the work of following three aspects:
The telemetry parameter interpretation: the telemetry parameter interpretation refers to add in the electric process at spacecraft, and the real-time telemetry data of spacecraft are carried out continuous, continual supervision, under specific state, judges whether telemetry parameter satisfies the design objective requirement.
The telecommand interpretation: the telecommand interpretation refers to add in the electric process at spacecraft, send a certain or a few instructions after, instruct caused telemetry parameter to change to this and monitor, judge whether the telemetry parameter relevant with this instruction satisfies design objective.
Remote measurement saltus step interpretation: remote measurement saltus step interpretation refers to add in the electric process at spacecraft, amplitude of variation to parameter monitors, if amplitude of variation has exceeded the maximum magnitude that parameter can be accepted amplitude of variation, then think the telemetry parameter saltus step has taken place, need analyze its reason.
In spacecraft model integration test before, data interpretation is mainly based on artificial interpretation, and artificial interpretation has three deficiencies: one, and artificial interpretation cost is very high; Its two, the artificial interpretation related data of might misjudging and fail to judge; Its three, artificial interpretation can't form the interpretation historical record, is unfavorable for the telemetry analysis.In order to improve the reliability of spacecraft, must improve the interpretation efficient of telemetry.
Summary of the invention
In view of this, the invention provides a kind of spacecraft test data automatic interpretation method, can carry out automatic interpretation, demonstration and storage, increase work efficiency, promote spacecraft reliability telemetry.
A kind of spacecraft test data automatic interpretation method of the present invention comprises the steps:
Step 1, set up the interpretation rule base,, the telemetry parameter interpretation rule of each subsystem of spacecraft is entered into described interpretation rule base then according to the spacecraft design document; Set up and carry out engine, be used for telemetry is carried out interpretation; Set up interpretation findings data storehouse, be used to store the interpretation conclusion; Main test handler, each integration test monitoring terminal in described execution engine and described interpretation rule base, interpretation findings data storehouse and the existing telemetry test macro are coupled together;
Step 2, described execution engine connect the interpretation rule base, load the interpretation rule and the interpretation rule is resolved from the interpretation rule base;
Step 3, described execution engine portion are within it created the blackboard district, and deposit the telemetry parameter that each subsystem of spacecraft institute tests possibly in the blackboard district;
Step 4, described execution engine set up with main test handler between network be connected, and from main test handler reception real-time telemetry data; And judge whether current telemetry data stream interrupts, and if interrupt, finish the automatic interpretation process, quit a program, if do not interrupt, carry out next step;
Step 5, described execution engine are judged the telemetry type:
If telemetry is telemetry parameter data or device status data, then:
1) described execution engine refreshes the data parameters in the blackboard district and returns this data parameters value with the real-time telemetry or the device status data that receive;
2) carry out engine with 1) in real-time data parameters value and corresponding interpretation rule mate;
3) carry out engine with 2) in matching result form telemetry parameter interpretation conclusion information;
If telemetry is telecommand or device directive, then:
1) described execution engine reads this telecommand or device directive to the moment that spacecraft sends from main test handler, reads interpretation criterion and interpretation time delay of this instruction from the interpretation rule base;
2) from delivery time, carry out engine continuous telemetry parameter value in the inquiry blackboard district in interpretation time delay, and the telemetry parameter value mated with corresponding instruction interpretation criterion: if in interpretation time delay correct coupling, instruction is carried out correct, judges that then conclusion is that the match is successful; If correct coupling in interpretation time delay, instruction execution error or do not carry out judges that then conclusion is that it fails to match;
3) described execution engine forms matching result the interpretation conclusion information of telecommand or device directive;
Step 6, the interpretation conclusion information that step 5 is obtained push in each integration test monitoring terminal and the interpretation findings data storehouse according to communication protocol packing between the electric equipment of integration test ground;
Step 7, integration test monitoring terminal show the interpretation conclusion, and execution in step 4-7 finishes telemetry interpretation order up to receiving.
The present invention has following beneficial effect:
1) by in existing remote measurement test macro, setting up interpretation rule base, interpretation findings data storehouse and carrying out engine, finish the automatic interpretation of telemetry or instruction, and the interpretation conclusion sent to the integration test monitoring terminal, realize the automatic interpretation and the demonstration of spacecraft test data, can improve telemetry interpretation work efficiency greatly, improve spacecraft reliability simultaneously; The interpretation conclusion is pushed to interpretation findings data storehouse stores, can analyze and form form, strengthened the analyticity of telemetry the historical interpretation conclusion of telemetry;
2) by in carrying out engine, setting up the blackboard district, store the telemetry that all need be tested, in the real-time testing process, only need be according to one or more data parameters values in the current telemetry renewal telemetry, avoid internal memory constantly to load telemetry, save time, improve judging efficiency.
Description of drawings
Fig. 1 is the annexation figure of interpretation rule base, execution engine and interpretation findings data storehouse and existing telemetry system among the present invention;
Fig. 2 is an automatic interpretation process flow diagram of the present invention.
Embodiment
Below in conjunction with the accompanying drawing embodiment that develops simultaneously, describe the present invention.
As shown in Figure 1, in existing spacecraft integration test process, generally speaking, each telemetry parameter all has certain variation range or Changing Pattern under identical state of the art, and this scope or rule generally can embody in the spacecraft design document.Spacecraft produces a large amount of descending telemetries, descending telemetry receives through main test handler, the staff handles telemetry according to the variation range or the Changing Pattern of telemetry parameter then, at last result is distributed to each integration test monitoring terminal.Because the data volume of telemetry is very big, kind is a lot, and staff's work of treatment is extremely heavy, also occurs erroneous judgement easily and wait error in processing procedure, brings negative effect can for the spacecraft integration test, finally influences the reliability of spacecraft probably.Therefore, in view of the drawback of artificial treatment telemetry parameter, the present invention provides a kind of spacecraft test data automatic interpretation method according to this characteristics of telemetry parameter, and this method comprises the steps:
Step 1, set up the interpretation rule base,, the telemetry parameter interpretation rule of each subsystem of spacecraft is entered into the interpretation rule database then according to the variation range and the Changing Pattern of the telemetry of spacecraft design document record; Set up and carry out engine, be used for telemetry is carried out interpretation; Set up interpretation findings data storehouse, be used to store the interpretation conclusion; As shown in Figure 1, main Test Host, each integration test monitoring terminal of carrying out in engine and described interpretation rule database, interpretation findings data storehouse and the existing telemetry test macro coupled together;
Step 2, is as shown in Figure 2 carried out engine and is connected the interpretation rule database, loads the interpretation rule and the interpretation rule is resolved from the interpretation rule base;
Step 3, carry out engine within it portion create the blackboard district, and in the blackboard district, deposit the telemetry parameter that each subsystem of spacecraft institute tests possibly; Because spacecraft telemetry kind is many, quantity is big, the telemetry parameter that execution engine of the present invention will be tested all earlier is loaded in the internal memory in blackboard district, after receiving real-time telemetry, can only upgrade several telemetries of receiving, and needn't internal memory repeatedly be read and write, thus, can save the time of whole interpretation process, raise the efficiency.
Step 4, carry out engine set up with main test handler between network be connected, and from main test handler reception real-time telemetry data; And judge whether current telemetry data stream interrupts, and if interrupt, finish the automatic interpretation process, quit a program, if do not interrupt, carry out next step;
Step 5, judgement telemetry type:
Generally speaking, the test to spacecraft mainly comprises: judge that 1, whether within the limits prescribed or meet set rule telemetry or device status data; 2, the ground turn-key system sends telecommand or device directive to spacecraft, spacecraft receives the back and carries out this instruction, then some telemetries of spacecraft correspondence will change, telemetry system judges that whether within the limits prescribed or meet set rule the above-mentioned telemetry that changes, determine the instruction that whether spacecraft is carried out or whether correct execution receives, the duty of testing spacecraft thus.
Among the present invention, if telemetry is telemetry parameter data or device status data, then:
1) refreshes the data parameters in the blackboard district and return this data parameters value with the real-time telemetry or the device status data that receive;
2) with 1) in real-time data parameters value and corresponding interpretation rule mate;
3) form telemetry parameter interpretation conclusion information;
If telemetry is telecommand or device directive, then:
1) the ground turn-key system sends telecommand or device directive to spacecraft, sends the delivery time of this instruction and this instruction simultaneously to main test handler; Carry out engine and read this telecommand or device directive to the moment that spacecraft sends, read interpretation criterion and interpretation time delay of this instruction from the interpretation rule base from main test handler;
2) from delivery time, carry out engine continuous telemetry parameter value in the inquiry blackboard district in interpretation time delay, and the telemetry parameter value mated with corresponding instruction interpretation criterion: if in interpretation time delay correct coupling, the instruction of spacecraft is carried out correct, judges that then conclusion is that the match is successful; If correct coupling in interpretation time delay, the instruction execution error of spacecraft or do not carry out judges that then conclusion is that it fails to match;
3) the interpretation conclusion information of formation telecommand or device directive;
Step 6, the interpretation conclusion information that step 5 is obtained push in each integration test monitoring terminal and the interpretation findings data storehouse according to communication protocol packing between the electric equipment of integration test ground;
Step 7, integration test monitoring terminal show the interpretation conclusion, and execution in step 4-7 finishes telemetry interpretation order up to receiving.Each integration test monitoring terminal receives from the telemetry result who carries out engine, analyzes current spacecraft state according to sentence read result, location spacecraft fault.Simultaneously, can historical interpretation conclusion be carried out query analysis and be formed analytical statement according to the integration test needs.
In sum, more than be preferred embodiment of the present invention only, be not to be used to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.

Claims (1)

1.一种航天器测试数据自动判读方法，其特征在于，包括如下步骤：1. A method for automatic interpretation of spacecraft test data, is characterized in that, comprises the steps: 步骤1、建立判读规则库，然后根据航天器设计文件，将航天器各分系统的遥测参数判读规则录入到所述判读规则库；建立执行引擎，用于对遥测数据进行判读；建立判读结论数据库，用于存储判读结论；将所述执行引擎与所述判读规则库、判读结论数据库以及已有遥测数据测试系统中的主测试处理机、各个综合测试监视终端连接起来；Step 1. Establish an interpretation rule base, and then input the interpretation rules of the telemetry parameters of each subsystem of the spacecraft into the interpretation rule base according to the spacecraft design documents; establish an execution engine for interpreting the telemetry data; establish an interpretation conclusion database , for storing the interpretation conclusion; connecting the execution engine with the interpretation rule base, the interpretation conclusion database, the main test processor in the existing telemetry data testing system, and each comprehensive test monitoring terminal; 步骤2、所述执行引擎连接判读规则库，从判读规则库中加载判读规则并对判读规则进行解析；Step 2, the execution engine connects to the interpretation rule base, loads the interpretation rules from the interpretation rule base and analyzes the interpretation rules; 步骤3、所述执行引擎在其内部创建黑板区，并在黑板区内存放航天器各分系统所有可能要测试的遥测数据参数；Step 3, the execution engine creates a blackboard area inside it, and stores all telemetry data parameters that may be tested by each subsystem of the spacecraft in the blackboard area; 步骤4、所述执行引擎建立与主测试处理机间的网络连接，并从主测试处理机接收实时遥测数据；并判断当前遥测数据流是否中断，如果中断，结束自动判读过程，退出程序，如果未中断，执行下一步；Step 4, the execution engine establishes a network connection with the main test processor, and receives real-time telemetry data from the main test processor; and judges whether the current telemetry data flow is interrupted, and if interrupted, ends the automatic interpretation process and exits the program, if Not interrupted, go to the next step; 步骤5、所述执行引擎判断遥测数据类型：Step 5, the execution engine judges the telemetry data type: 如果遥测数据为遥测参数数据或者设备状态数据，则：If the telemetry data is telemetry parameter data or device status data, then: 1）所述执行引擎用接收到的实时的遥测数据或设备状态数据刷新黑板区中的数据参数并返回该数据参数值；1) The execution engine uses the received real-time telemetry data or device status data to refresh the data parameters in the blackboard area and return the data parameter values; 2）执行引擎将1）中的实时的数据参数值与相应判读规则进行匹配；2) The execution engine matches the real-time data parameter values in 1) with the corresponding interpretation rules; 3）执行引擎将2）中的匹配结果形成遥测参数判读结论信息；3) The execution engine forms the matching results in 2) into telemetry parameter interpretation conclusion information; 如果遥测数据为遥控指令或者设备指令，则：If the telemetry data is a remote control command or a device command, then: 1）所述执行引擎从主测试处理机读取该遥控指令或者设备指令向航天器发送的时刻，从判读规则库读取该指令的判读准则和判读延迟时间；1) When the execution engine reads the remote control instruction from the main test processor or sends the equipment instruction to the spacecraft, it reads the interpretation criterion and interpretation delay time of the instruction from the interpretation rule library; 2）从发送时刻起，执行引擎在判读延迟时间内不断查询黑板区中遥测参数值，并将遥测参数值与对应的指令判读准则进行匹配：如果在判读延迟时间内正确匹配，指令执行正确，则判断结论为匹配成功；如果在判读延迟时间内未正确匹配，指令执行错误或者未执行，则判断结论为匹配失败；2) From the time of sending, the execution engine continuously queries the telemetry parameter value in the blackboard area within the interpretation delay time, and matches the telemetry parameter value with the corresponding instruction interpretation criterion: if it matches correctly within the interpretation delay time, the instruction is executed correctly, Then the judgment conclusion is that the matching is successful; if there is no correct match within the interpretation delay time, the instruction is executed incorrectly or not executed, the judgment conclusion is that the matching fails; 3）所述执行引擎将匹配结果形成遥控指令或者设备指令的判读结论信息；3) The execution engine forms the matching result into the interpretation conclusion information of the remote control command or device command; 步骤6、将步骤5得到的判读结论信息依据综合测试地面电器设备间通信协议打包推送至各综合测试监视终端和判读结论数据库中；Step 6. Packing and pushing the interpretation conclusion information obtained in step 5 to each comprehensive testing monitoring terminal and interpretation conclusion database according to the communication protocol between the comprehensive testing ground electrical equipment; 步骤7、综合测试监视终端显示判读结论，执行步骤4-7，直到接到结束遥测数据判读命令。Step 7. The comprehensive test monitoring terminal displays the interpretation conclusion, and executes steps 4-7 until receiving the command to end the interpretation of telemetry data.
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