CN103218292B - A kind of aerospace satellite-borne software Auto-Test System - Google Patents
A kind of aerospace satellite-borne software Auto-Test System Download PDFInfo
- Publication number
- CN103218292B CN103218292B CN201310108724.3A CN201310108724A CN103218292B CN 103218292 B CN103218292 B CN 103218292B CN 201310108724 A CN201310108724 A CN 201310108724A CN 103218292 B CN103218292 B CN 103218292B
- Authority
- CN
- China
- Prior art keywords
- test
- computer
- module
- dynamics
- script
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Debugging And Monitoring (AREA)
Abstract
The invention discloses a kind of aerospace satellite-borne software Auto-Test System, comprise main control computer, dynamics computer, remote control computer, remote measurement computing machine and test data memory module; Described main control computer comprises and can perform script generation module, and automatic testing execution module and test result output module formed; Dynamics computer carries out parameter to the parameter bag received and unpacks, and carries out dynamics calculation acquisition dynamics data, and dynamics data is sent to spaceborne computer and test data memory module according to the data after unpacking; The telecommand of reception is sent to spaceborne computer by remote control computer; Remote measurement computing machine receives the telemetry of the satellite transit that spaceborne computer sends; And telemetry is sent to test data memory module.Auto-Test System of the present invention is a kind of real-time Auto-Test System of semi physical closed loop towards spaceborne control software design Test Application, can strengthen the reusability of test case, the repeatability of test process, improves test coverage.
Description
Technical field
The present invention relates to a kind of spaceborne control software design Auto-Test System.
Background technology
At present, the existing test for spaceborne control software design has manual testing and test two kinds automatically, and order first two mode is all in use.
Existing spaceborne control software design test case, be generally the describing mode adopted based on natural language, usually describe in test case: the step of test case, required condition is performed in each step of test case, the variable operated is needed in test execution, to the required concrete numerical value arranging variable set up, in requisition for observing and the data of comparison, the operations such as drafting correlation curve.
Manual test, these test cases are performed by hand mainly through test operation personnel, the method requires higher to tester, need the implication can understood completely described by test case, and operation that can be correct, along with being on the increase of satellite control software design development task, the working strength adopting this mode work to bring is large, and the impact that the defect of the situations such as test execution difference is large is brought is increasing.
Automatic test, mainly drives based on business-like automatic test execution at present, realizes automatically performing of test by performing certain specific scripting language (such as: the script description that VBScript, JavaScript etc. are special).Main Problems existing is: selected test script describing mode and a large amount of control software design test case existed based on space flight feature natural language description mode incompatible, existing test resource directly cannot be applied in such Auto-Test System, and adopt the workload natural descriptive language being converted to particular script huge, and standard disunity between different Auto-Test Systems, by once changing and meeting the executable demand of Auto-Test System, cannot cause and automatically test many extra works at spaceborne control software design.
The automatic test execution of existing spaceborne control software design performs based on time series order often, cannot by the cycle tests executable operations caused due to Parameters variation or the triggering of other event in test operation, there is limitation in the method, cannot need the test execution carrying out judging triggering based on the condition produced in test process in coverage test execution.
Summary of the invention
Technical matters to be solved by this invention is to provide a kind of real-time Auto-Test System of semi physical closed loop towards spaceborne control software design Test Application, strengthens the reusability of test case, the repeatability of test process, improves test coverage.
The present invention includes following technical scheme:
A kind of spaceborne control software design Auto-Test System, comprises main control computer, dynamics computer, remote control computer, remote measurement computing machine and test data memory module;
Described main control computer comprises and can perform script generation module, and automatic testing execution module and test result output module formed;
Script generation module can be performed the test case of the natural language description based on On-board software characterizing definition tested towards spaceborne control software design is automatically converted into and can performs test script, and the described test script that performs is sent to automatic testing execution module;
Test automatically performs module and imports the performed test script sequence that can perform script generation module and generate, and realizes cycle tests order and performs and real time monitoring; Test automatically performs module and the parameter bag in test script sequence is sent to dynamics computer, the telecommand in cycle tests is sent to remote control computer, and the test data in read test data memory module;
Test result output module receives the test result exported by automatic testing execution module, and test result is outputted to test report;
Dynamics computer carries out parameter to the parameter bag received and unpacks, and carries out dynamics calculation acquisition dynamics data, and dynamics data is sent to spaceborne computer and test data memory module according to the data after unpacking;
The telecommand of reception is sent to spaceborne computer by remote control computer;
Remote measurement computing machine receives the telemetry of the satellite transit that spaceborne computer sends; And telemetry is sent to test data memory module.
Test data memory module may operate on independent data server and also may operate on main control computer.
The present invention compared with prior art tool has the following advantages:
The test case that this Auto-Test System uses is the test case based on space flight feature natural language description, can make full use of the abundant On-board software test case that long term accumulation gets up to greatest extent;
This Auto-Test System not only based on the time order and function order of test event, can also be triggered the execution of test event, improve the dirigibility that automatic cycle tests performs and the test coverage changed various state by the change of comparison variable;
This Auto-Test System operates in real-time semi physical closed loop test environmentally, has the true environment that limit simulation spaceborne computer control software design runs, guarantees the high emulation of software test result.This Auto-Test System has good Interface Expanding ability, adapts to the diversity of spaceborne control test assignment.
Accompanying drawing explanation
Fig. 1 is Auto-Test System structural representation of the present invention.
Fig. 2 is Auto-Test System data flow diagram of the present invention.
Fig. 3 carries out pretreated process flow diagram to the test case of natural language description.
Fig. 4 carries out processing the process flow diagram obtaining and can perform script to pretreated test case.
Fig. 5 is order execution thread process flow diagram.
Fig. 6 is real-time monitoring thread process flow diagram.
Fig. 7 is that test result exports process flow diagram.
Embodiment
Just by reference to the accompanying drawings the present invention is described further below.
One, Auto-Test System
As shown in Figure 1, 2, Auto-Test System of the present invention is the distributed real-time testing system of semi physical, comprises main control computer, dynamics computer, remote control computer, remote measurement computing machine, and test data memory module.The concrete process path of each ingredient data stream is shown in Figure 2.
Main control computer is the control carrier of test automatically, is furnished with and dynamics computer, the interface of remote control computer, remote measurement computing machine.Described main control computer comprises and can perform script generation module, and automatic testing execution module, test result output module formed.Script generation module can be performed the test case of the natural language description based on On-board software characterizing definition tested towards spaceborne control software design is automatically converted into and can performs test script, and the described test script that performs is sent to automatic testing execution module; Test automatically performs module and imports the performed test script sequence that can perform script generation module and generate, and realizes cycle tests order and performs and real time monitoring; Test automatically performs module and the parameter bag in test script sequence is sent to dynamics computer, the telecommand in cycle tests is sent to remote control computer, and the test data in read test data memory module.The described test script that performs comprises multiple cycle tests block, and each cycle tests block comprises multiple operating block.Automatic testing execution module can realize the importing that can perform test script, the real-time control of test process, and cycle tests performs, real time data supervision, interpretation and comparison.
Test result output module receives the test result exported by automatic testing execution module, to be tested be finished after take out each Output rusults in turn, in a standardized format test result is outputted to test report, in output, have the data and the required test curve drawn of test script that comprise and judge variable.
Test data memory module may operate on independent data server and also may operate on main control computer, its Main Function is that the remote control produced in On-board test process is injected, dynamics data is arranged, the related data run in the real-time Auto-Test System such as telemetry.
Dynamics computer carries out parameter to the parameter bag received and unpacks, and carries out dynamics calculation acquisition dynamics data, and dynamics data is sent to spaceborne computer and test data memory module according to the data after unpacking.Dynamics computer is connected with the interface of spaceborne computer by various regulation, simulates the communication of all kinds of sensor and the topworks be connected with spaceborne computer.Can be implemented in Interruption the serial data receiving spaceborne computer and send, parallel port data, various signal such as position mouth data and 1553B data etc., obtain and various state in test macro is set, level, the information such as pulse, the operation of the peripheral components such as the sensor that analog satellite controls and topworks, the satellite dynamics information such as analog satellite posture position when orbital motion in addition, by dynamics computer simulation calculation, and direct fault location data when sending to each sensor needed for spaceborne computer control software design and parts data and On-board software to run by respective channel.Dynamics computer also can gather the topworks's data sent by spaceborne computer, and dynamics computer combines the environment constituted needed for spaceborne control software design operation with closed ring with spaceborne computer by above-mentioned simulation.
Such as: the controlled quentity controlled variables such as the thruster jet pulse after spaceborne computer collection is calculated by spaceborne computer, the output of wheel control-torque, by the real-time orbital motion state of mathematical model computing analog satellite when space motion and attitude of satellite state, and pass through satellite sun sensor by these states calculated, the data transfer mode that earth sensor and gyro specify according to it passes to spaceborne computer, constitutes the closed loop test verification system verifying spaceborne control software design attitude orbits controlling.
Real-time is mainly reflected in simulation sensor that dynamics computer runs, the mathematical operation simulation part such as topworks and satellite dynamics of orbits in orbit divides and operates in real time operating system, strictly need carry out according to time specific with the data communication of spaceborne computer.
The telecommand of reception is sent to spaceborne computer by remote control computer; Realize remote control injecting data to send.So-called remote control injecting data sends namely to be sent to spaceborne computer by the passage of specifying uply has specific meanings according to agreement regulation, can by the bit data flow of the length-specific of On-board software identification.
Remote measurement computing machine is for receiving the remote measurement downlink data of spaceborne computer transmission and remote measurement downlink data being sent to test data memory module.So-called remote measurement downlink data is to the generation of spaceborne computer software and by particular physical interface passage, according to the sequential of regulation, the bit data flow with the specified length of specific meanings of cyclical transmission.
Measurand is spaceborne computer control software design, and this running software is on spaceborne computer, and by the dynamics computer in the external physical channel interface of spaceborne computer and testing apparatus, remote control computer, remote measurement computing machine carries out data interaction.
Two, script generation module can be performed
Step generation module can be performed On-board software test case is automatically converted into and can performs script.Described test case adopts the relevant behavior of a kind of natural language set pair or operation to be described, and test script is the executable cycle tests of computing machine; And process test case being converted into the test script that can automatically perform resolves to test case the process obtaining the cycle tests that computing machine can automatically perform, the automatic test of the spaceborne control software design to spaceborne computer operation can be realized by running described cycle tests.The component of test case comprises annotation, separator, operation key word etc.Test case performs the separator of sequence using " branch " as one section, and " comma ", as the separator between at the same level operation, such as to be arranged, drawing etc., and " pause mark " is as the separator between the inner multiple object of a certain operation; " colon " is the further explanation of a certain object.
Can performing step generation module, that On-board software test case is converted into the concrete grammar that can perform script is automatically as follows:
The first step, first carry out pre-service to the test case of natural language description, preprocessing process as shown in Figure 3;
(1) carry out character reading to the test case of natural language description, carry out cutting obtain each cycle tests block by branch to test case, each jumper indicator to understand in test a concrete cycle tests block; Cycle tests block is the set once performing content operation with clear and definite operation executive condition.
(2) by comma, segmentation is carried out to each cycle tests block and obtain operating block, and obtain the specific descriptions character string of each operating block in each cycle tests block; Test operation block is the test operation unit with clear and definite meaning.
(3) compare to process to the specific descriptions character string of each operating block in each cycle tests block and predefined file and obtain the character string after processing.Character string after described process at least comprises the character string with tagged word; Also change character string to be operated and variable parameter value character string to be operated, passage keyword strings can according to circumstances be comprised.Until terminate the pretreatment work of test case after completing the extraction of all characters.The described character string with tagged word comprises routine operation key word, special operational key word and annotation key word.
Described step (3) concrete grammar is as follows: described predefined file comprises syntactic data defined file, parameter definition data file and test system configurations file.So-called syntactic data defined file contains all key words and it processes description accordingly; Title and the data layout of needed assigned variable and variable to be compared is contained in so-called parameter definition data file; So-called test system configurations file contains the characteristic information relevant to current test system state, and this characteristic information can there are differences along with the difference of concrete test system environment.
The specific descriptions character string of each operating block in obtained each cycle tests block and predefined syntactic data defined file are carried out search comparison, obtains the character string with tagged word; The specific descriptions character string of each operating block in obtained each cycle tests block and parameter are defined data file to carry out search comparison and obtain change character string to be operated; Digital quantity character string is obtained by set concrete digital quantity search; The specific descriptions character string of each operating block in obtained each cycle tests block and Auto-Test System configuration file are compared and obtains passage keyword strings.
Syntactic data defined file: the key word defining operational processes, operation key word is that the symbolism in the test case of concrete mode of operation describes, have found key word, just can be mapped concrete disposal route by key word in process subsequently.Usually have in the primary key comprised in syntactic data defined file: routine operation key word comprise direction state of operation key word, mapping operation key word, setting operation key word, compare operation key word, polling message operation key word, prompting message operation key word and etc. key word to be operated.Special operational key word can be such as " performing this operation ", " dynamics computer initialization ".Annotation key word is comments feature symbol, such as " // " or "/* */".
Parameter definition data file: parameter defined file mainly comprises that the computing of a. dynamics can be changed, the name variable of the test operation of the parameter of remote control up wait assignment is corresponding with the discernible name variable of computing machine shows and the data format definition of these variablees, b. remote measurement pass down data name, dynamics computing export data name and the corresponding data layout of these variablees, these data are variable to be compared in test process.
Test system configurations file: the definition mainly comprising each back end on distributed test system that this test macro defines, this definition is configured according to the concrete condition of test macro.The Main Function of CONFIG.SYS is to provide the definition description of the Data flow direction of data stream on test macro.
Second step, after pre-service, extract through script information, resolve and the Mapping implementation conversion that can automatically perform test script, processing procedure is see shown in accompanying drawing 4.
(1) remove the annotation in test case according to comments feature symbol " // " or "/* */", remove the script annotation in test case;
(2) obtain cycle tests block number K, by obtained cycle tests block composition cycle tests block array, sequence blocks operation count value sets to 0;
(3) cycle tests block is extracted from cycle tests block array; Sequence blocks process count value adds 1;
(4) obtain the operating block number M of current cycle tests block, by the test operation block composition test operation block array in current cycle tests block, operating block process Counter Value sets to 0;
(5) from this test operation block array, extract operating block content, operating block process count value adds 1; Key word in operating block is mapped, carries out mapping to variable to be operated in operating block and resolve; Variable to be operated comprises treats assigned variable and variable to be compared; The Mapping Resolution completing above-mentioned variable with associate after, form executable single-step operation;
(6) judge whether all operations block of current cycle tests block maps/resolve complete (by judging whether operating block process count value equals M to realize), if do not map/resolve complete (if being not equal to M), then return step (5), continue to extract next operating block; If all map/resolve complete (if equaling M), then form executable single step sequence, and proceed to step (7);
(7) judging whether all cycle tests blocks are disposed (by judging whether sequence blocks process count value equals K to realize), if be not disposed (if being not equal to K), then return step (3), continuing to extract next cycle tests block; If all cycle tests blocks are disposed (if equaling K), then terminate.
The concrete grammar that described step (5) key word maps is as follows: the key word in operating block and the key word preset are compared, call the handling function corresponding with this key word and form executable operation.
Three, automatic testing execution module
Automatic testing execution module is according to performing test script sequence dynamic creation order execution thread and real-time monitoring thread, can perform test script sequence and import to order execution thread, the real-time monitor task that can perform in test script sequence imports in real-time monitoring thread and forms real-time aligned sequences; The described test script sequence that performs comprises multiple script sequence blocks, and each script sequence blocks comprises multiple operating block;
As shown in Figure 5, the step of order execution thread is as follows:
(1) script is waited for that counting variable resets, obstruction is waited for Flag Reset, the extraction pointed of script sequence blocks and operating block can be performed test script sequence beginning;
(2) whether can perform test script sequence described in judgement is empty,
If script sequence is empty, be then invalid by thread execution traffic sign placement, end order execution thread;
If step sequence non-NULL, then take out first script sequence blocks in step sequence, go to step (3);
(3) judge whether there is untreated operating block in current script sequence blocks, if having, take out first operating block, and proceed to step (4), if without, judge that script waits for whether counting variable is 0, if 0, then returns step (2), otherwise goes to step (7);
(4) the executive condition classification of current operation block is judged,
If executive condition classification is instant judgement condition, then compare currency and the expectation value of instant judgement conditional-variable, if consistent, go to step (5), otherwise go to step (6);
If executive condition classification is continuation Rule of judgment, then this continuation decision condition is injected into the comparison task sequence of real-time monitoring thread, script is waited for that counting variable adds 1 simultaneously, then judge that current operation block waits for returning results of monitoring thread the need of in obstruction mode, if desired then wait mark is blocked in set, go to step (7), if do not need, directly go to step (7);
If executive condition classification is current operation block do not have executive condition, then go to step (5);
(5) read the destination address of instruction in current operation block, then binding instructio parameter, perform current operation block;
(6) judge whether there is instantaneous expected results comparison operation in current operation block, if having, export instantaneous comparison result, then go to step (7), otherwise directly go to step (7);
(7) judge whether implant operation block sequence is empty, if not sky then takes out first injection enter operating block, reads the destination address of instruction in current implant operation block, binding instructio parameter, then perform current operation block, and script is waited for that counting variable subtracts 1, then go to step (8); If " operating block injection sequence " is empty, then go to step (9);
(8) judge whether block wait mark is set,
Wait for that mark is set if block, then judge the operating block of current implant operation block whether corresponding to continuation decision condition in step (4), wait for mark, if not then go to step (7) if then reset to block;
If it is invalid that obstruction wait is masked as, then go to step (7);
(9) the operating block whether interface buffer of order execution thread and real-time monitoring thread has real-time monitoring thread to inject is judged, if have, then the operating block that real-time monitoring thread is injected is added to implant operation block sequence end, and goes to step (10), if no, then directly go to step (10);
(10) judge to block and wait for mark whether set, if set, go to step (7), otherwise go to step (3).
As shown in Figure 6, the step of real-time monitoring thread is as follows:
(1) set thread execution mark, by real-time for the extraction pointed of real-time aligned sequences aligned sequences starting position;
(2) judge the whether set of thread execution mark, if set, then go to step (3), if non-set, then terminate thread;
(3) judge whether real-time aligned sequences is empty, if not empty, then goes to step (4), if it is empty, then goes to step (5);
(4) take out real-time comparison task by the extraction pointer of real-time aligned sequences, judge whether current real-time comparison task meets comparison condition, if so, goes to step (6), if not, goes to step (3);
(5) judge whether the comparison task sequence that order execution thread injects is empty, if not empty, the comparison task sequence that described order execution thread injects be added to real-time aligned sequences, if it is empty, then go to step (2);
(6) comparison is performed according to the concrete comparison logic of comparison task; Described concrete comparison logic comprises the comparison of logical relation between the comparison of the parameter ranges in the comparison of value of consult volume, preset time section and multiple parameter;
(7) judge that whether comparison result is corresponding and have pending operating block, if then inject corresponding operating block to described interface buffer, then go to step (8), otherwise, directly go to step (8);
(8) judging that comparison result is the need of outputting in test report, if then export current comparison result, then going to step (9), otherwise, directly go to step (9);
(9) judge that the expected results of current comparison task upgrades the need of according to the actual value of current parameter, if desired upgrade, then according to the expected results that current parameter calculated with actual values makes new advances, then proceed to step (3), otherwise, directly go to step (3).
Four, test result output module
As shown in Figure 7, implementation step is as follows for the flow chart of data processing of test result output module:
Operation steps (1): judge whether " script performs sequence and whether is finished " is finished, if be finished, then proceeds to step (7), if be not finished, then proceeds to operation steps (2);
Operation steps (2): receive the test result exported by automatic testing execution module, and stored in test result output sequence;
Operation steps (3): if test result output sequence is empty, then proceed to operation steps (1), if test result output sequence is not empty, then proceeds to operation steps (4);
Operation steps (4): take out each Output rusults in turn, proceeds to operation steps (5);
Operation steps (5): according to the Output rusults of standardized form expection variable, proceed to operation steps (6);
Operation steps (6): test result is exported and forms test report, proceed to operation steps (3);
Operation steps (7): terminate.
Utilize Auto-Test System of the present invention can realize following test:
Test case is as follows:
Run On-board software and test procedure;
When satellite time is 100 seconds, send to dynamics computer passage 1, arranging SS61 solar angle is 40 degree, SS61 is set and sees that sun strobe is 0, arranging SS62 solar angle is 0 degree, SS62 is set and sees that sun strobe is 0, perform this operation/* sun sensor can not see the sun should carry out sun search operation */; After waiting for 2880 second time, judge whether satellite transit pattern is 0x11(XX safe mode): perform this operation;
When satellite time is 3000 seconds, terminate this test;
" satellite rate of roll ", " satellite rate of pitch " during drafting satellite time 0s->3000s, the time curve of " satellite yaw rate " variable.
The meaning of test case is as follows:
Sun search pattern processing capacity, by arranging SS61(rolling solar angle), SS62(pitching solar angle) see that sun strobe is 0 failure condition arranging that run duration in-orbit fails to search out the sun always.In this situation, satellite control software design will carry out enclosing the searching sun around pitch axis with constant speed rotary search one, enclosing the searching sun around the axis of rolling with constant speed rotary search one subsequently, said process total length is 1440 seconds, owing to seeing that sun strobe is set to 0(and shows not see the sun always), On-board software should repeat once along pitch axis with along the search of the axis of rolling to the sun again.Also do not search out solar satellite control model after search and should transfer XX safe mode to, now need to judge whether segment mark becomes 0x11, whether this external demand is correct by the control of curve plotting observe satellites three axis angular rate.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. an aerospace satellite-borne software Auto-Test System, is characterized in that, comprises main control computer, dynamics computer, remote control computer, remote measurement computing machine and test data memory module;
Described main control computer is by performing script generation module, and test automatically performs module and test result output module formed;
Script generation module can be performed the test case of the natural language description based on On-board software characterizing definition tested towards spaceborne control software design is automatically converted into and can performs test script, and the described test script that performs is sent to test and automatically performs module; Script generation module can be performed and first pre-service is carried out to the test case of natural language description, then can perform the automatic conversion of test script through script information extraction, parsing and Mapping implementation;
Test automatically performs module and imports the performed test script sequence that can perform script generation module and generate, and realizes cycle tests order and performs and real time monitoring; Test automatically performs module and the parameter bag in test script sequence is sent to dynamics computer, the telecommand in cycle tests is sent to remote control computer, and the test data in read test data memory module;
Test result output module receives the test result being automatically performed module output by test, and test result is outputted to test report;
Dynamics computer carries out parameter to the parameter bag received and unpacks, and carries out dynamics calculation acquisition dynamics data, and dynamics data is sent to spaceborne computer and test data memory module according to the data after unpacking;
The telecommand of reception is sent to spaceborne computer by remote control computer;
Remote measurement computing machine receives the telemetry of the satellite transit that spaceborne computer sends; And telemetry is sent to test data memory module.
2. aerospace satellite-borne software Auto-Test System according to claim 1, is characterized in that, test data memory module may operate on independent data server and also may operate on main control computer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310108724.3A CN103218292B (en) | 2013-03-29 | 2013-03-29 | A kind of aerospace satellite-borne software Auto-Test System |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310108724.3A CN103218292B (en) | 2013-03-29 | 2013-03-29 | A kind of aerospace satellite-borne software Auto-Test System |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103218292A CN103218292A (en) | 2013-07-24 |
| CN103218292B true CN103218292B (en) | 2015-09-23 |
Family
ID=48816110
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310108724.3A Active CN103218292B (en) | 2013-03-29 | 2013-03-29 | A kind of aerospace satellite-borne software Auto-Test System |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103218292B (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104331035B (en) * | 2014-09-30 | 2017-05-10 | 航天东方红卫星有限公司 | Mini-satellite test remote measurement and remote control monitoring system based on service-oriented architecture and method thereof |
| CN104406618B (en) * | 2014-10-23 | 2017-05-03 | 航天东方红卫星有限公司 | State diagram based test method in small satellite test |
| CN107608874A (en) * | 2016-07-12 | 2018-01-19 | 博彦科技股份有限公司 | Method of testing and device |
| CN106326114A (en) * | 2016-08-16 | 2017-01-11 | 北京控制工程研究所 | Automatic aerospace software testing method for approximately natural language testing case script |
| CN109556652A (en) * | 2017-09-26 | 2019-04-02 | 南京淳泰控制设备有限公司 | A kind of drive dynamic control device test equipment |
| CN108536125B (en) * | 2018-04-03 | 2020-12-29 | 北京航空航天大学 | Automatic detection method for source program written by artificial intelligence programmer for digital aircraft |
| CN108710551B (en) * | 2018-04-28 | 2021-12-07 | 北京轩宇信息技术有限公司 | SPARC processor-based single event upset fault injection test method and system |
| CN109245958B (en) * | 2018-09-14 | 2020-07-14 | 中国空间技术研究院 | Communication function testing method and system based on self-adaptive 1553B bus |
| CN110968515B (en) * | 2019-12-03 | 2021-06-15 | 中国科学院软件研究所 | Software testing bed based on software defined satellite |
| CN112181843A (en) * | 2020-10-12 | 2021-01-05 | 中国科学院微小卫星创新研究院 | Development test verification system based on satellite-borne software |
| CN112558624B (en) * | 2020-12-11 | 2023-09-29 | 北京控制工程研究所 | Spacecraft autonomous mission planning verification deployment integrated intelligent computing system |
| CN113835413A (en) * | 2021-09-22 | 2021-12-24 | 交控科技股份有限公司 | Interlocking automation test system, method, device and storage medium |
| CN113821018B (en) * | 2021-11-22 | 2022-03-22 | 星河动力(北京)空间科技有限公司 | Carrier rocket test system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102096627A (en) * | 2009-12-11 | 2011-06-15 | 上海卫星工程研究所 | Device for testing single event upset fault resistance of on-board software |
| CN102508775A (en) * | 2011-10-31 | 2012-06-20 | 彭勇 | Interactive automation test system |
| CN102541730A (en) * | 2011-12-08 | 2012-07-04 | 北京空间飞行器总体设计部 | Semantic identification and automatic generation method for spacecraft test script |
| CN102622234A (en) * | 2012-03-07 | 2012-08-01 | 迈普通信技术股份有限公司 | Development system and method for automatic test case |
| CN102722437A (en) * | 2012-05-29 | 2012-10-10 | 北京空间飞行器总体设计部 | Spacecraft test system and spacecraft test method based on assemblies and scripts |
-
2013
- 2013-03-29 CN CN201310108724.3A patent/CN103218292B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102096627A (en) * | 2009-12-11 | 2011-06-15 | 上海卫星工程研究所 | Device for testing single event upset fault resistance of on-board software |
| CN102508775A (en) * | 2011-10-31 | 2012-06-20 | 彭勇 | Interactive automation test system |
| CN102541730A (en) * | 2011-12-08 | 2012-07-04 | 北京空间飞行器总体设计部 | Semantic identification and automatic generation method for spacecraft test script |
| CN102622234A (en) * | 2012-03-07 | 2012-08-01 | 迈普通信技术股份有限公司 | Development system and method for automatic test case |
| CN102722437A (en) * | 2012-05-29 | 2012-10-10 | 北京空间飞行器总体设计部 | Spacecraft test system and spacecraft test method based on assemblies and scripts |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103218292A (en) | 2013-07-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103218292B (en) | A kind of aerospace satellite-borne software Auto-Test System | |
| CN102541707B (en) | Multiplex JTAG (Joint Test Action Group) interface-based FPGA (Field Programmable Gate Array) on-chip logic analyzer system and method | |
| CN103218290B (en) | A kind of aerospace satellite-borne software can perform the automatic method for transformation of script | |
| CN103529820B (en) | A kind of direct fault location test macro and method of testing being applicable to embedded device | |
| CN105091927A (en) | All-liquid-crystal automobile instrument automatic test platform | |
| CN104850111B (en) | A kind of hardware-in―the-loop test method and system | |
| CN103970121A (en) | Distributed automatic test framework system for satellites | |
| CN104468035B (en) | A kind of distribution POS data reliability transmission system and method | |
| CN103218289B (en) | Satellite-borne software test automatic executing method | |
| CN102707712B (en) | Electronic equipment fault diagnosis method and system | |
| CN110244688A (en) | Meter bus panel automatic generation method and its system based on LabVIEW | |
| KR20050058793A (en) | Satellite simulation modeling system using interface model | |
| CN105045635B (en) | Configure the generation method of list file | |
| WO2012044262A1 (en) | Embedded system design, programming, and simulation architecture | |
| CN104991263A (en) | Method for performing satellite positioning signal resolution | |
| CN113010358B (en) | LTPB (Low temperature pluggable) bus detection device applied to avionics system and method for testing flow description language of LTPB bus detection device | |
| CN106708764A (en) | Universal IO processing system for airborne avionic system | |
| CN105740579A (en) | Building method for connecting UVM verification platform | |
| CN105334756A (en) | Agile satellite mission interpretation closed loop simulation verification system and method | |
| CN102411312A (en) | Sensor simulator and satellite closed loop simulation system | |
| CN107719622A (en) | The stratospheric airship automatic test approach of Behavior-based control logic | |
| CN106776277A (en) | A kind of method of striding course test, device and electronic equipment | |
| CN116796548A (en) | Digital modeling method for electric interface of single integrated management unit of satellite platform | |
| CN104734900A (en) | Sending control method for communication protocol testing | |
| CN104850015B (en) | A kind of software packaging method and a kind of automobile electronic controller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |