CN103218451A - Automatic spacecraft test data interpreting method - Google Patents
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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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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
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. a spacecraft test data automatic interpretation method is characterized in that, 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.
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