CN106595760A - Design method for carrier rocket telemetry data automatic processing system - Google Patents
Design method for carrier rocket telemetry data automatic processing system Download PDFInfo
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- CN106595760A CN106595760A CN201611121808.0A CN201611121808A CN106595760A CN 106595760 A CN106595760 A CN 106595760A CN 201611121808 A CN201611121808 A CN 201611121808A CN 106595760 A CN106595760 A CN 106595760A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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Abstract
The invention provides a design method for carrier rocket telemetry data automatic processing system, comprising: using the type and name of the rocket, the sending time name, the flight time sequence name, the source file address and the database address provided by a task information card to classify the measuring points according to the parameter types through the point measurement card; listing the measuring points according to the cabin under each classification type; using the time domain processing parameter cards to classify the various measuring points according to the work condition; configuring different processing parameters for each measuring point. Each database is name as type of rocket-parameter type with the table named by cabin section and work condition. The running program writes the telemetry data automatically from the source file to the database. When a plurality of telemetry data are accumulated, historical record is used to write a document.
Description
Technical field
The present invention relates to carrier rocket mechanical environment technical field, more particularly to a kind of launch vehicle telemetry data are located automatically
The method for designing of reason system.
Background technology
Launch vehicle telemetry parameter is the important motivity data in flight course, be judge rocket flight state normally with
No important indicator.The flight mechanics environment being likely encountered to ensure each unit, subsystem and satellite to bear, in its development
Key link to carry out corresponding mechanical test, mainly including sine vibration test, random vibration test, noise fest and punching
Hit test etc..Experimental condition design level directly determines the reliability of the effectiveness of test and in-orbit execution task.In mechanics
In Environment Design work, the side for typically being combined using multiple means such as simulation analysis, telemetry statistics, ground experiment checkings
Formula, such as sinusoidal and random vibration test often carry out amplitude limit with reference to satellite and the rocket interface telemetry with regard to Jing to condition.Therefore, mechanical ring
The Trend of Environmental Change that border works firstly the need of product on quick or periodic analysises arrow, on the basis of it have accumulated mass data,
Also need to that experimental condition is carried out to improve and iteration, including under the states such as different satellite quality, height, interface size, layout
Telemetry parameter carry out statistical analysiss, conclude response pattern, provide foundation for product design optimization.
Carrier rocket has a variety of models, and every kind of model all has respective telemetry station distribution scheme, quantity and life
Name；Every time launch mission all can fly according to set timing instructions, and telemetry mainly includes that each bay section measuring point flies different
When low-frequency vibration, dither, impact, noise of row period etc., frequency domain parameter；Corresponding telemetry file also can be by " survey
Call the roll. when segment number " naming, represent rumble spectrum of certain measuring point within certain period.The situation of level of confidentiality transmitting needs foundation badly simultaneously
Unified data processing and management platform, solidification operational module and flow process are improved, to tackle the requirement of cost efficiency, and for automatic
The senior application such as analysis, machine learning, data mining provides strong support.
The content of the invention
It is an object of the invention to provide a kind of method for designing of launch vehicle telemetry action data automation, to solve
Unified data processing and management platform are how set up and improved, solidifies the problem of operational module and flow process.
In order to solve above-mentioned technical problem, the technical scheme is that：There is provided a kind of launch vehicle telemetry data automatic
The method for designing of processing system, including：Using mission bit stream card the model name of rocket is provided, time title, flight time sequence name is sent out
Title, source file address and database address, press parameter type and measuring point are sorted out, in the measuring point parameter card with measuring point parameter card
All measuring point is enumerated by bay section subclass below each class parameter type, with time domain processing parameter card to each measuring point by operating mode point
Class, to the time domain data of each measuring point collection different processing parameters are configured；Each data base is with " rocket model _ parameter type "
List is set up in name, each data base the inside by the bay section or operating mode；Operation program takes out telemetry from source file automatically
Take out process and write into Databasce；After have accumulated the telemetry of multiple times, closed with history transmitting log sheet input
The history of the heart sends out time title, and operation program is realized multiple automatic comparisons, draws and write document.
Further, operation program, program reads in first the mission bit stream card with, measuring point parameter card and Time Domain Processing
Information on parameter card, by the frequency spectrum of different parameters type different data bases are write, by bay section classification write list and by column
Storage, " sending out time name _ measuring point name " name of each row frequency spectrum.
Further, the history time title that log sheet input is concerned about is launched with the history, program is according to described
The document template of business release opening correspondence model, correspondence is inquired about inside each data base and sends out secondary, according to the measuring point parameter
Card is compared the spectral line of each measuring point by bay section or producing condition classification, is drawn picture or is compared maximum etc., writes the result into document mould
Plate shape is into analysis report.
Further, sound pressure level is recorded by flight time sequence during noise parameter is processed, a line in each sequential correspondence list,
Row name presses " flight time sequence name " labelling, and the mission bit stream card is arranged in order flight time sequence, and program is using in Data Filename
Flight when segment number inquire corresponding sequential title, result is finally inserted the corresponding row in list.
Further, deposit impact parameter data base by flight time sequence record shock response spectrum peak, each when ordered pair
The a line in list, row name is answered to press " flight time sequence name " labelling, the mission bit stream card is arranged in order flight time sequence, and program is read
After entering data file, sequential title is inquired about in the mission bit stream card by segment number during flight in filename, finally will knot
Fruit inserts the corresponding row in list.
Further, time-domain signal is processed successively by the order of intercepting period, pretreatment, calculating frequency spectrum, the used time
Domain processing parameter card configures different processing parameters to each time-domain signal, and the Time Domain Processing parameter card is by " operating mode " to measuring point
Classification, program is read in by the Time Domain Processing parameter card and will be named with " operating mode " in result write into Databasce after measuring point data
List.
Further, the operating mode to take off, transonic speed, the moment such as stage separation.
The method for designing of the launch vehicle telemetry action data automation that the present invention is provided, using configuration file by measuring point
Arranged by parameter type big class, affiliated bay section subclass, and rocket model is provided, the information such as secondary, flight time sequence, program is sent out
After reading in configuration card, just the telemetry of different times can automatically be pressed parameter type and sort out, arrange and by flight by bay section
Period is counted, and is common to each carrier rocket model.Under the situation of level of confidentiality transmitting, the launch vehicle telemetry data
The method for designing of automated processing system can set up unified data processing and management platform, solidification operational module and flow process, with
The requirement of reply cost efficiency, and to automatically analyze, machine learning, the senior application such as data mining provide strong support.
Further, the method for designing of launch vehicle telemetry action data automation can also be by the parameter on configuration card
Spectrum analyses are carried out to time-domain signal, and writes the result into data base automatically.
Description of the drawings
Invention is described further below in conjunction with the accompanying drawings：
The step of Fig. 1 is the method for designing of launch vehicle telemetry action data automation provided in an embodiment of the present invention flow process is shown
It is intended to；
Fig. 2 is low-frequency vibration frequency domain data handling process schematic diagram provided in an embodiment of the present invention；
Fig. 3 is dither frequency domain data handling process schematic diagram provided in an embodiment of the present invention；
Fig. 4 is noise frequency domain data handling process schematic diagram provided in an embodiment of the present invention；
Fig. 5 is impact frequency domain data handling process schematic diagram provided in an embodiment of the present invention；
Fig. 6 is Time Domain Processing parameter card field structure schematic flow sheet provided in an embodiment of the present invention；
Fig. 7 is time domain data handling process schematic diagram provided in an embodiment of the present invention；
Fig. 8 writes schematic flow sheet automatically for telemetry analysis report provided in an embodiment of the present invention.
Specific embodiment
Below in conjunction with the drawings and specific embodiments to launch vehicle telemetry action data automation proposed by the present invention
Method for designing is described in further detail.According to following explanation and claims, advantages and features of the invention will become apparent from.
It should be noted that, accompanying drawing in the form of simplifying very much and uses non-accurately ratio, only conveniently, lucidly to aid in
Illustrate the purpose of the embodiment of the present invention.
The present invention core concept be, the present invention provide launch vehicle telemetry action data automation design side
Method, is arranged measuring point by parameter type big class, affiliated bay section subclass using configuration file, and is provided rocket model, sent out
The information such as secondary, flight time sequence, program is read in after configuration card, just can be returned the telemetry of different times by parameter type automatically
Class, arrange by bay section and counted by the flight period, and be common to each carrier rocket model.In the shape of level of confidentiality transmitting
Under gesture, the method for designing of the launch vehicle telemetry action data automation can set up unified data processing and manage flat
Platform, solidification operational module and flow process, to tackle the requirement of cost efficiency, and to automatically analyze, machine learning, data mining it is contour
Level application provides strong support.
The step of Fig. 1 is the method for designing of launch vehicle telemetry action data automation provided in an embodiment of the present invention is flowed
Journey schematic diagram.With reference to Fig. 1, there is provided a kind of method for designing of launch vehicle telemetry action data automation, including following step
Suddenly：
S11, the model name that rocket is provided using mission bit stream card, time title, flight time sequence title, source file address sum
According to storehouse address, press parameter type with measuring point parameter card and measuring point is sorted out, under each class parameter type of the measuring point parameter card
Measuring point is all enumerated in face by bay section subclass, and producing condition classification is pressed to each measuring point with time domain processing parameter card, to each measuring point collection
Time domain data configure different processing parameters；
, with " rocket model _ parameter type " name, the list inside each data base presses " bay section " for S12, each data base
Or " operating mode " is named, telemetry is extracted process and write into Databasce by operation program from source file automatically；
S13, after have accumulated the telemetry of multiple times, launch the history that log sheet input is concerned about with history and send out time name
Claim, operation program is realized multiple time automatic comparisons, draws and write document.
Every time all in rocket body, each bay section arranges sensor to flight test, and these sensors will during boosting flight
Sampled, and passed back measurement and control center, telemetry is divided into frequency domain data and the big class of time domain data two.Automatic treatment software according to
Mission bit stream card, measuring point parameter card and Time Domain Processing parameter card carry out data processing.
In embodiments of the present invention, operation program, program reads in first the mission bit stream card, measuring point parameter card with timely
Information on the processing parameter card of domain.Mission bit stream card provide source file address, database address, rocket model, rocket send out time with
And flight time sequence name, each flight time sequence name is arranged in order, and correspond to respectively flight when segment number 1, when segment number 2 ...,
Frequency domain data is divided into several parameter types such as high frequency, low frequency, noise, impact by measuring point parameter card, below parameter type big class again
Measuring point is divided into into several subclasses, including bay section 1, bay section 2 ... according to bay section, includes measuring point 1, measuring point wherein in bay section 1 again
2…….Time Domain Processing parameter card configures different processing parameters, the Time Domain Processing parameter card to the time-domain signal of each measuring point
Measuring point is classified by operating mode 1, operating mode 2 ....The moment such as the operating mode is to take off, transonic speed, stage separation.
Source file by " measuring point name. when segment number " name, program reads in these source files, and sticks into by above three information
Row is processed.To high frequency frequency domain data, subdivision section is calculated power spectrum by program；To low frequency frequency domain data, program calculates subdivision section
Equivalent sine is composed；Subdivision section is extracted the impact spectrum peak of each flight time sequence to impacting frequency domain data；To trouserss noise frequency
Numeric field data will calculate the sound pressure level of each flight time sequence and calculate total spectra of sound pressure；To time domain data, program will be according to configuration parameter
It is converted into frequency spectrum.The frequency spectrum of different parameters type is written column-wise as different data bases by program, and data base presses " rocket type
Number _ parameter type " name, the list in each data base by " bay section " or " operating mode " name, use and " send out secondary by each row frequency spectrum
Name _ measuring point name " is named.
Fig. 2 is low-frequency vibration frequency domain data handling process schematic diagram provided in an embodiment of the present invention.With reference to Fig. 2, read and appoint
Business release in rocket model and send out time, read measuring point parameter card in rocket bay section name, bay section in each measuring point name and
Its measurement each when segment number, certain measuring point is read accordingly with the remote measurement shock response spectrum of " measuring point name+when segment number " name（SRS）
And power spectrum（PSD）, it takes envelope after the spectrum of each period for traversal reading, calculates equivalent sine spectrum.In low-frequency data storehouse
In press rocket model name and open corresponding data library file, it is newly-built by " send out time+measuring point name+SRS/PSD " by bay section name inquiry form
Field, will just calculated spectral line write.According to all measuring points of each bay section of above principle traversal processing.
Fig. 3 is dither frequency domain data handling process schematic diagram provided in an embodiment of the present invention.With reference to Fig. 3, read and appoint
Business release in rocket model and send out time, read measuring point parameter card in rocket bay section name, bay section in each measuring point name and
Its measurement each when segment number, certain measuring point is read accordingly with the remote measurement power spectrum of " measuring point name+when segment number " name, traversal
Read it and take envelope after the spectrum of each period.Rocket model name is pressed in high-frequency data storehouse and opens corresponding data library file,
By bay section name inquiry form, by " sending out secondary+measuring point name " newly-built field, will just calculated spectral line write.According to above principle
All measuring points of traversal processing each bay section.
Fig. 4 is noise frequency domain data handling process schematic diagram provided in an embodiment of the present invention.With reference to Fig. 4, task letter is read
Cease the rocket model in card and send out secondary, each period of measuring point name and its measurement compiles in the trouserss in reading measuring point parameter card
Number, certain measuring point is read accordingly with the remote measurement spectra of sound pressure of " measuring point name+when segment number " name, calculate sound pressure level.In noise database
In press rocket model name and open corresponding data library file, by " send out time+measuring point name " newly-built field, by " when segment number " inquiry row,
Will just calculated sound pressure level write.Traversal reads it and envelope is taken after the spectrum of each period, calculates overall sound pressure level, still writes
Enter the field.According to all measuring points of above principle traversal processing.Sound pressure level is recorded by flight time sequence in noise parameter process, each
A line in period correspondence list, row name presses " flight time sequence name " labelling, and the mission bit stream card successively arranges the sequential of flight
Row, program inquires corresponding sequential title, finally result is inserted in list using the when segment number in Data Filename
Correspondence row.
Fig. 5 is impact frequency domain data handling process schematic diagram provided in an embodiment of the present invention.With reference to Fig. 5, task letter is read
Cease the rocket model in card and send out secondary, each measuring point name in rocket bay section name, bay section and its survey in reading measuring point parameter card
Amount each when segment number, certain measuring point is read accordingly with the remote measurement shock response spectrum of " measuring point name+when segment number " name（SRS）, take peak
Value.Rocket model name is pressed in high-frequency percussion data base and opens corresponding data library file, by bay section name inquiry form, by " send out time+
The newly-built field of measuring point name ", by " when segment number " inquiry row, by the peak value for just having obtained write.It is each according to above principle traversal processing
All measuring points of individual bay section.The data base of storage impact parameter segment record shock response spectrum peak value when pressing rocket flight, each when
A line in section correspondence list, row name presses " flight time sequence name " labelling, and the mission bit stream card provides flight time sequence information, journey
Sequence is read in after data file, sequential title is inquired about in the mission bit stream card by segment number during flight in filename, finally
Result is inserted the corresponding row in list.
Fig. 6 is Time Domain Processing parameter card field structure schematic diagram provided in an embodiment of the present invention.With reference to Fig. 6, Time Domain Processing
Parameter card is used for signal procesing in time domain into frequency domain data, and the processing parameter point of each measuring point intercepts period, pretreatment and calculating
Three parts of frequency spectrum." measuring point code name " is used to read the remote measurement time-domain curve of certain measuring point, by " time started " and " end time "
Intercept one section.The trend term of this section of curve is removed by " centralization method " and " centralization exponent number ", by " sample rate ", " is filtered
Beginning frequency ", " filtering terminates frequency " are filtered, and remove hop by " going hop to switch ", " hop numbering ".Finally with " punching
Hit spectrum initial frequency ", " shock response spectrum exponent number frequency ", " shock response spectrum frequency interval " calculate shock response spectrum.
Fig. 7 is time domain data handling process schematic diagram provided in an embodiment of the present invention.With reference to Fig. 7, mission bit stream card is read
In rocket model and send out time, read Time Domain Processing parameter card in flight operating mode name, each measuring point name and its corresponding process ginseng
Number, reads accordingly the remote measurement time-domain curve of certain measuring point, calculates frequency spectrum.In certain class data base（High frequency, low frequency, noise, impact
Deng）Corresponding data library file is opened by rocket model name, by operating mode name inquiry form, by " sending out secondary+measuring point name " newly-built field, will
Just calculated spectral line write.According to each operating mode of all measuring points of above principle traversal processing.
Fig. 8 writes schematic flow sheet automatically for telemetry analysis report provided in an embodiment of the present invention.With reference to Fig. 8, read
Take the rocket model in mission bit stream card and send out secondary, read the parameter type in measuring point parameter card（High frequency, low frequency, noise, impact
Deng）, rocket bay section name.In certain class data base（High frequency, low frequency, noise, impact etc.）Corresponding data is opened by rocket model name
Library file, by bay section name inquiry form, by " sending out secondary " inquiry field, it would be desirable to which the spectral lines of several times for comparing take out, and write
Enter document template.According to all parameter types of each bay section of above principle traversal processing.Launch log sheet with the history
The history that input is concerned about sends out time title, and program opens the document template of correspondence model according to the mission bit stream card, according to described
Measuring point parameter card inquires about correspondence inside each data base and sends out secondary, and the spectral line of each measuring point is compared by bay section or producing condition classification, paints
Drawing piece compares maximum etc., writes the result into document template and forms analysis report
Obviously, those skilled in the art the present invention can be carried out it is various change and deform without deviating from the present invention spirit and
Scope.So, if these modifications of the present invention and modification belong within the scope of the claims in the present invention and its equivalent technologies,
Then the present invention is also intended to comprising these changes and modification.
Claims (7)
1. a kind of method for designing of launch vehicle telemetry action data automation, it is characterised in that include：
Using mission bit stream card the model name of rocket is provided, time title, flight time sequence title, source file address and data base is sent out
Address, presses parameter type and measuring point is sorted out, below each class parameter type of the measuring point parameter card all with measuring point parameter card
Enumerate measuring point by bay section subclass, producing condition classification pressed to each measuring point with time domain processing parameter card, to the collection of each measuring point when
Numeric field data configures different processing parameters；
Each data base presses " bay section " or " work with " rocket model _ parameter type " name, the list inside each data base
Condition " is named, and telemetry is extracted process and write into Databasce by operation program from source file automatically；
After have accumulated the telemetry of multiple times, with history the history time title that log sheet input is concerned about, fortune are launched
Line program is realized multiple time automatic comparisons, draws and write document.
2. the method for designing of launch vehicle telemetry action data automation as claimed in claim 1, it is characterised in that operation
Program, program reads in first the information on the mission bit stream card, measuring point parameter card and Time Domain Processing parameter card, and program will be each
The frequency spectrum of measuring point is written column-wise as different data bases by parameter type, and each data base is named with " rocket model _ parameter type ",
List inside each data base is named by " bay section " or " operating mode ", " sending out time name _ measuring point name " name of each row frequency spectrum.
3. the method for designing of launch vehicle telemetry action data automation as claimed in claim 1, it is characterised in that use institute
The history time title that history transmitting log sheet input is concerned about is stated, program opens correspondence model according to the mission bit stream card
Document template, correspondence is inquired about inside each data base and sends out secondary, and the spectral line of each measuring point is pressed into bay section according to the measuring point parameter card
Or producing condition classification is compared, draw picture or compare maximum etc., write the result into document template and form analysis report.
4. the method for designing of launch vehicle telemetry action data automation as claimed in claim 1, it is characterised in that noise
Sound pressure level is recorded by flight time sequence in parameter processing, a line in each sequential correspondence list, row name is marked by " flight time sequence name "
Note, the mission bit stream card is arranged in order flight time sequence, and program is inquired using segment number during flight in Data Filename
Corresponding sequential title, result is finally inserted the corresponding row in list.
5. the method for designing of launch vehicle telemetry action data automation as claimed in claim 1, it is characterised in that storage
The data base of impact parameter records shock response spectrum peak by flight time sequence, and a line in each sequential correspondence list, row name is pressed
" flight time sequence name " labelling, the mission bit stream card is arranged in order flight time sequence, and program is read in after data file, by filename
In flight when segment number sequential title is inquired about in the mission bit stream card, result is finally inserted the corresponding row in list.
6. the method for designing of launch vehicle telemetry action data automation as claimed in claim 1, it is characterised in that pair when
Numeric field data is processed successively by the order of intercepting period, pretreatment, calculating frequency spectrum, with time domain processing parameter card to each time domain
The different processing parameter of data configuration, the Time Domain Processing parameter card is classified by operating mode to measuring point, and program presses card reading measuring point
The list that will be named with " operating mode " in result write into Databasce after time domain data.
7. the method for designing of launch vehicle telemetry action data automation as claimed in claim 6, it is characterised in that described
The moment such as operating mode is to take off, transonic speed, stage separation.
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| CN201611121808.0A CN106595760B (en) | 2016-12-08 | 2016-12-08 | A kind of design method of launch vehicle telemetry action data automation |
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| CN108593231A (en) * | 2018-03-28 | 2018-09-28 | 上海宇航***工程研究所 | Carrier rocket random vibration test condition determination method |
| CN110543489A (en) * | 2019-09-02 | 2019-12-06 | 内蒙动力机械研究所 | Solid rocket engine reliability data analysis mining and application software tool |
| CN116450994A (en) * | 2023-06-13 | 2023-07-18 | 东方空间技术(山东)有限公司 | High-frequency telemetry data processing method, computing device and storage medium |
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| Publication number | Publication date |
|---|---|
| CN106595760B (en) | 2019-04-02 |
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