CN202339497U - Verification system of satellite-bone integrated service unit - Google Patents

Verification system of satellite-bone integrated service unit Download PDF

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Publication number
CN202339497U
CN202339497U CN 201120355755 CN201120355755U CN202339497U CN 202339497 U CN202339497 U CN 202339497U CN 201120355755 CN201120355755 CN 201120355755 CN 201120355755 U CN201120355755 U CN 201120355755U CN 202339497 U CN202339497 U CN 202339497U
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CN
China
Prior art keywords
integrated service
service unit
host computer
inspection equipment
verification system
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Expired - Lifetime
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CN 201120355755
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Chinese (zh)
Inventor
郝燕艳
李威
安卫钰
王雷
王涛
李明峰
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China Academy of Space Technology CAST
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China Academy of Space Technology CAST
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Priority to CN 201120355755 priority Critical patent/CN202339497U/en
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Publication of CN202339497U publication Critical patent/CN202339497U/en
Anticipated expiration legal-status Critical
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Abstract

The utility model discloses a verification system of a satellite-bone integrated service unit, which is used for verification of the integrated service unit. The verification system comprises an upper computer, special inspection equipment and power supply equipment. The upper computer serves as a master control machine to control the special inspection equipment and the integrated service unit. The verification system improves comprehensiveness and automation degree of comprehensive verification of the integrated service unit of a high-rail communication satellite.

Description

A kind of spaceborne integrated service unit verification system
Technical field
The utility model relates to a kind of spaceborne integrated service unit verification system, is applicable to the test and validation of high rail telstar remote measuring and controlling equipment.
Background technology
High rail telstar integrated service unit is spaceborne remote measuring and controlling equipment, mainly comprises temperature amount acquisition module, analogue collection module, two level amount acquisition module, matrix instruction management and driver module, matrix telemetry-acquisition module, loading device remote measuring and controlling secondary bus etc.This equipment has two kinds of mode of operations, and a kind of is normal mode, and under normal mode, equipment is accomplished data interaction through 1553B bus and other satellite borne equipments; Another kind is a contingency mode, and under contingency mode, equipment is accomplished data interaction through self-defined synchronous serial interface and other equipment.
For whether function, the performance of checking the integrated service unit satisfies technical requirement, need validation test equipment that it is carried out comprehensive function and performance verification.Traditional Authentication devices is independent equipment; Respectively each module and function are tested; Comprise temperature amount collection Authentication devices, analog acquisition Authentication devices and two level amount collection Authentication devices etc., each equipment is tested a few functional parameters of equipment under test respectively.Mainly there are following 2 problems in the stand alone type Authentication devices: 1, each Authentication devices is just tested to a few functional parameters, accomplish whole tests, and the time and efforts that needs is more; Whether 2, separately test can not verify whether the multinomial performance index exists incidence relation, can produce a few remote measurement values and disturb as not testing the process that sends instructions, and therefore the spreadability of test is not enough, and the relevance problem of function has been left to whole star test phase.
At present, the integrated service unit has adopted the integration module design philosophy, and function concentrates complicacy high, so traditional Authentication devices can not adapt to the testing authentication of current device.
The utility model content
The technology of the utility model is dealt with problems and is: overcome the deficiency of prior art, a kind of spaceborne integrated service unit verification system is provided.Adopt the utility model to improve comprehensive and automaticity to the comprehensive verification of high rail telstar integrated service unit.
The technical solution of the utility model is:
A kind of spaceborne integrated service unit verification system is used for realizing the integrated service unit is verified, comprising: host computer, specially examine equipment and power-supply unit;
Host computer and special inspection equipment interaction are provided with data to special inspection equipment transmission; Receive the detection data that special inspection equipment sends;
Host computer and integrated service unit interaction send telecommand to the integrated service unit; Receive the telemetry intelligence (TELINT) that the integrated service unit collects;
Specially inspection equipment and integrated service unit interaction send test simulation amount data to the integrated service unit, and receive the telecommand return data that is sent by the integrated service unit;
Power-supply unit is given the power supply of integrated service unit and host computer.
Said special inspection equipment comprises: CSB interface emulation module, matrix instruction load simulator, matrix instruction fault simulator module, matrix remote measurement driving source, analog quantity driving source, temperature amount driving source, two level amount driving source, discrete command load simulator, emergent telemetry interface simulator, emergent Remote Control Interface simulator, direct instruction interface simulator, direct telemetry interface simulator and RS422 interface simulator.
Said host computer carries out with special inspection equipment utilization ICP/IP protocol alternately.
Said host computer is through 1553B bus and integrated service unit interaction.
Said host computer is confirmed the data that are provided with to special inspection equipment transmission through the read test script.
The utility model compared with prior art has following advantage:
(1) the utility model has adopted the verification system framework based on master-slave mode; As the host computer of total control computer through the 1553B bus to the integrated service unit send telecommand, through special inspection equipment reception telecommand feedback data, and compare passing back on the host computer; Host computer is provided with the remote measurement driving source through special inspection equipment, receives telemetry-acquisition information through the 1553B bus, and in the enterprising line data comparison of total control computer.Above-mentioned two processes constitute the closed loop proof procedure of telemetry-acquisition, telecommand.
(2) the utility model adopts script to realize automatic test.Original Authentication devices test is adopted the customization modes more, builds when verification system to finish, and the automatic test flow process is just fixing, or comprises the dirigibility in very little Chengdu, can not realize the cycle tests of high complexity.The utility model adopts and sets up cycle tests based on the mode of script to this problem, has improved the dirigibility of test, and the cycle tests of high complexity can be provided.
Description of drawings
Fig. 1 is the utility model synoptic diagram;
Fig. 2 is the utility model embodiment connection layout.
Embodiment
The utility model provides a kind of spaceborne integrated service unit verification system, is applicable to the test and validation of high rail telstar remote measuring and controlling equipment.Be illustrated in figure 1 as the system architecture diagram of the utility model, by host computer, specially examine equipment, power-supply unit is formed, and accomplishes the checking to integrated service unit on the star.
Host computer carries out data interaction through ICP/IP protocol and special inspection equipment, carries out data interaction through 1553B integrated circuit board and integrated service unit, is connected with power-supply unit through gpib interface, reads the current/voltage value.
Special inspection equipment comprises CSB interface emulation module, matrix instruction load simulator, matrix instruction fault simulator module, matrix remote measurement driving source, analog quantity driving source, temperature amount driving source, two level amount driving source, discrete command load simulator, emergent telemetry interface simulator, emergent Remote Control Interface simulator, direct instruction interface simulator, direct telemetry interface simulator and RS422 interface simulator.Specially each equipment completion in the inspection equipment and the instruction and the telemetry intelligence (TELINT) transmission of integrated service unit are promptly sent test simulation amount data to the integrated service unit, and are received the telecommand feedback data that the integrated service unit sends; Power-supply unit is through main 100V bus and be equipped with the 100V bus to the power supply of integrated service unit.
In the special inspection equipment, the transmission of the telemetry and telecommand command information of CSB bus module on completion of CSB interface emulation module and the star; Matrix instruction load simulator receives the matrix instruction that the matrix instruction circuit sends on the star, and instruction is responded and record; Matrix instruction fault simulator module is through being provided with the fault of open circuit and short circuit, the working condition of matrix instruction circuit on the star under the test failure situation; Matrix remote measurement driving source provides the on off state amount to supply on the star matrix telemetry module to gather; The analog quantity driving source provides the analog quantity voltage value to supply on the star analogue collection module to gather; Temperature amount driving source provides the resistance of thermistor to supply on the star temperature amount acquisition module to gather; Two level amount driving sources provide two level amounts to supply on the stars two level amount acquisition modules to gather; The discrete command load simulator receives the discrete command that the discrete command sending module sends on the star, and instruction is responded and record; Emergent telemetry interface simulator is accomplished the collection of remote measurement amount on the star under the contingency mode; Emergent Remote Control Interface simulator is used under contingency mode, sending instruction to on-board equipment; Direct instruction interface simulator is used for sending direct instruction to on-board equipment, the switching on and shutting down of control on-board equipment; The bus communication function of RS422 module on completion of RS422 interface simulator and the star.
Test assignment is accomplished by PC control, and all test data and test result all can be accomplished at host computer and show and processing.
Host computer sends to special inspection equipment data are set, and the said data that are provided with comprise: analog quantity setting, the setting of temperature amount, directly discrete command, CSB bus are provided with and 422 bus settings.Receive the telemetry command feedback data that comes from the integrated service unit that special inspection equipment returns, said telemetry command feedback data comprises: the discrete command of number pipe, direct remote measurement amount, CSB bus data and 422 bus datas.
Specially inspection equipment sends test simulation amount data according to the data that are provided with of host computer to the integrated service unit, and the integrated service unit turns back to host computer after test simulation amount data are gathered.
The data message in general 1553B communication card transmission of host computer and integrated service separate room utilizes the 1553B communication card to send telecommand information to the integrated service unit, and receives the telemetry intelligence (TELINT) that the integrated service unit collects through the 1553B integrated circuit board.
In order to realize the cycle tests of high complexity, adopt the mode of generic script to carry out multitasking in the dispatcher software.Write the multinomial test that needs carry out as script, called the each task program of verification system, accomplished test automatically, reduced manually-operated, improved the real-time of test.Behind the EOT,, repeatedly measure the back data are compared in real time, therefore can test and find whether the multinomial performance index exists incidence relation, and whether the operation of a certain function can exert an influence to other indexs test gained data storage.
Be illustrated in figure 2 as the utility model test and connect synoptic diagram, dual mode is arranged.First kind of connected mode is: the connector of specially examining EM equipment module 1 links to each other with the connector of transfer box 1 through cable; In the transfer box signal wire is redistributed; Make and to mate that the connector of transfer box 1 passes through that corresponding connector is connected on cable and the star with the connector that is connected on-board equipment (integrated service unit).Second kind of connected mode is: the connector of specially examining EM equipment module 2 links to each other with transfer box 1 through bus cable; In the transfer box signal wire is redistributed; Make and to mate that the connector of transfer box 2 passes through that corresponding connector is connected on cable and the star with the connector that is connected on-board equipment.The test connected mode is stored in database; Comprise corresponding connector title and remarks on connector title, affiliated module, connector type, corresponding transfer box title, the corresponding transfer box, be convenient to describe the connected mode of Authentication devices and spaceborne integrated service unit.
The unspecified part of the utility model belongs to general knowledge as well known to those skilled in the art.

Claims (5)

1. spaceborne integrated service unit verification system is used for realizing the integrated service unit is verified, it is characterized in that comprising: host computer, specially examine equipment and power-supply unit;
Host computer and special inspection equipment interaction are provided with data to special inspection equipment transmission; Receive the detection data that special inspection equipment sends;
Host computer and integrated service unit interaction send telecommand to the integrated service unit; Receive the telemetry intelligence (TELINT) that the integrated service unit collects;
Specially inspection equipment and integrated service unit interaction send test simulation amount data to the integrated service unit, and receive the telecommand return data that is sent by the integrated service unit;
Power-supply unit is given the power supply of integrated service unit and host computer.
2. a kind of spaceborne integrated service according to claim 1 unit verification system, it is characterized in that: said special inspection equipment comprises: CSB interface emulation module, matrix instruction load simulator, matrix instruction fault simulator module, matrix remote measurement driving source, analog quantity driving source, temperature amount driving source, two level amount driving source, discrete command load simulator, emergent telemetry interface simulator, emergent Remote Control Interface simulator, direct instruction interface simulator, direct telemetry interface simulator and RS422 interface simulator.
3. a kind of spaceborne integrated service according to claim 1 unit verification system is characterized in that: said host computer carries out with special inspection equipment utilization ICP/IP protocol alternately.
4. a kind of spaceborne integrated service according to claim 1 unit verification system is characterized in that: said host computer is through 1553B bus and integrated service unit interaction.
5. a kind of spaceborne integrated service according to claim 1 unit verification system is characterized in that: said host computer is confirmed the data that are provided with to special inspection equipment transmission through the read test script.
CN 201120355755 2011-09-20 2011-09-20 Verification system of satellite-bone integrated service unit Expired - Lifetime CN202339497U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 201120355755 CN202339497U (en) 2011-09-20 2011-09-20 Verification system of satellite-bone integrated service unit

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Application Number Priority Date Filing Date Title
CN 201120355755 CN202339497U (en) 2011-09-20 2011-09-20 Verification system of satellite-bone integrated service unit

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102915029A (en) * 2012-10-15 2013-02-06 中国运载火箭技术研究院 Avionics system automatic test platform based on reusable spacecraft
CN103676657A (en) * 2013-11-22 2014-03-26 中国空间技术研究院 Verification system for satellite integrated electronic system
CN104932358A (en) * 2015-05-29 2015-09-23 上海卫星工程研究所 Large and medium-sized satellite general emission console based on PXI framework
CN111427332A (en) * 2020-03-31 2020-07-17 成都星时代宇航科技有限公司 Space experiment platform and experiment method
CN111857087A (en) * 2019-04-30 2020-10-30 中国空间技术研究院 Configurable remote control and remote measurement simulator with monitoring function and control test method

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102915029A (en) * 2012-10-15 2013-02-06 中国运载火箭技术研究院 Avionics system automatic test platform based on reusable spacecraft
CN102915029B (en) * 2012-10-15 2014-11-19 中国运载火箭技术研究院 Avionics system automatic test platform based on reusable spacecraft
CN103676657A (en) * 2013-11-22 2014-03-26 中国空间技术研究院 Verification system for satellite integrated electronic system
CN103676657B (en) * 2013-11-22 2016-03-30 中国空间技术研究院 A kind of verification system for satellite Integrated Electronic System
CN104932358A (en) * 2015-05-29 2015-09-23 上海卫星工程研究所 Large and medium-sized satellite general emission console based on PXI framework
CN104932358B (en) * 2015-05-29 2018-01-30 上海卫星工程研究所 A kind of big-and-middle-sized Satellite General transmitter control station based on PXI frameworks
CN111857087A (en) * 2019-04-30 2020-10-30 中国空间技术研究院 Configurable remote control and remote measurement simulator with monitoring function and control test method
CN111857087B (en) * 2019-04-30 2021-10-01 中国空间技术研究院 Configurable remote control and remote measurement simulator with monitoring function and control test method
CN111427332A (en) * 2020-03-31 2020-07-17 成都星时代宇航科技有限公司 Space experiment platform and experiment method
CN111427332B (en) * 2020-03-31 2021-02-02 成都星时代宇航科技有限公司 Space experiment platform and experiment method

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Granted publication date: 20120718