CN108897305A - A kind of three-dimensional test platform of control system system integration delivery - Google Patents
A kind of three-dimensional test platform of control system system integration delivery Download PDFInfo
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- CN108897305A CN108897305A CN201810695931.6A CN201810695931A CN108897305A CN 108897305 A CN108897305 A CN 108897305A CN 201810695931 A CN201810695931 A CN 201810695931A CN 108897305 A CN108897305 A CN 108897305A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
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Abstract
The present invention relates to a kind of control system system integrations to deliver three-dimensional test platform, including main body frame, power supply-distribution system, static electricity releasing system, visual identity and execution system, inertia device shielding system；Main body frame is three-decker, and supporting plate is arranged in upper layer, and supporting plate is for arranging flight control system single machine；Middle layer is for arranging flight control system cable system main structure；Lower layer is used to arrange Test launch and control system single machine, test equipment and the power supply-distribution system of test flight control system；Power supply-distribution system is three-dimensional test platform power supply.Main body frame of the invention is three-decker, and by flight control system single machine, flight control system cable system, partial test launch control system single machine layered arrangement, layout is clear, convenient for the connection, lookup and replacement of cable, avoids the maloperation of personnel；Effectively reduce the risk damaged in cable system test process；Variety classes cable juxtaposition is effectively reduced, testing efficiency is improved.
Description
Technical field
The present invention relates to a kind of control system system integrations to deliver three-dimensional test platform, belongs to space flight and integrates survey field.
Background technique
Control system integration test refers to that carrier space vehicle control system product, will be each in system on the basis of unit testing
Component units carry out integrated assembling, connection, debugging according to design requirement, and are tested according to the method for agreement, are to verify
The harmony that soft and hardware of uniting works, the correctness of function, and whether reach the activity of relevant art index and requirement.
The product for needing to deliver includes Test launch and control system and flight control system, control system cable system and control
Each stand-alone device of system is the integrated important component delivered, and the occupied area the best part in integration testing.It surveys
Examination launch control system and flight control system respectively include cable system and a variety of single machines, and cable system distribution is intricate, use
Easily there is occupant system, and operating difficulties in the connection procedure of Test launch and control system test flight control system, connection.
It is integrated that the purpose of trace management is that in integration testing, a large amount of test product is deployed in test equipment concentration
Testing laboratory, equipment room need a large amount of cables to be attached, need during the test according to integration testing equipment itself
The demands such as characteristic, test purpose, quality restriction condition, mark off test site appropriate.To be conducive to the combination of people, object,
More effectively carry out integration testing activity.Promote test site management standardization, scientific, reaches efficient, high-quality, safety test
Purpose.
Each single machine trace planning of system in industry relies primarily on tester's experience at present, according to previous test layouts
Cable system and each equipment are unfolded in laboratory, the platform of equipment test generally uses according to control system scale several
The wooden table is opened to be spliced.But control system cable system bundlees in actual use and tube, is multiple-limb solid type
Structure is difficult to smoothly be deployed in it on wooden table splicing platform of plane during the test.
Laboratory generallys use the placement position that technological procedure provides each single machine and cable system at present, uses technical papers pair
Expansion process carries out trace management.But because cable system self structure is complicated, part-structure is not pliable, plug interface is fragile easily
The features such as damage, it is difficult to according to technological procedure require spread out on the test platform of plane, and by force to cable system into
Row expansion easily causes to damage to cable system.
And cable system and stand-alone device because using position and function difference, it is cable size, cable material, bent
Degree is different, it is uniformly deployed on the same test platform, it is difficult to make the smooth orderly expansion of cable system, different structure
Test cable intersect reciprocal, overlap each other, seriously affect the integrated testing efficiency of test, test quality is difficult to ensure.
How the three-dimensional test platform of integrated form a kind of is provided, convenient for expansion layout and the system electricity of flight control system
Cable connection is this field technical problem urgently to be resolved.
Summary of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of control system system integrations to deliver three-dimensional survey
Platform is tried, solves the problems, such as that control system cable system and equipment are difficult to orderly fixation expansion, avoids electricity during cable net unfolding
Cable bending angle is excessive, and the time of cable plug need to be looked for by shortening tester, avoids variety classes cable juxtaposition.
The object of the invention is achieved by following technical solution：
A kind of three-dimensional test platform of control system system integration delivery, including main body frame and power supply-distribution system are provided；
Main body frame is three-decker, and supporting plate is arranged in upper layer, and supporting plate is for arranging flight control system single machine；Middle layer is used for
Arrange flight control system cable system main structure；Lower layer is used to arrange the Test launch and control system of test flight control system
Single machine, test equipment and power supply-distribution system；Power supply-distribution system is three-dimensional test platform power supply.
Preferably, supporting plate setting in upper layer is for the line outlet of cable connection, the trace slot of branch cable cabling and flight
Control system single machine locating slot.
Preferably, middle layer supporting plate includes multiple trace blocks for cable system positioning, and trace slot, row are formed around trace block
Mark block is arranged at the key feature points position of cable system.
Preferably, lower layer includes fixed part and multiple removable frames, and fixed part is more for arranging power supply-distribution system
The Test launch and control system single machine and test equipment of a removable frame arrangement test flight control system.
Preferably, every layer of the three-decker multilevel structure zoning according to carrier rocket, the upper and lower cable connection
Position up and down be correspondingly arranged.
It preferably, further include visual identity and execution system, including image capture module, control module and execution machine
Structure, the traffic light system state of image capture module collecting test launch control system single machine, and it is sent to control module, it controls
Module judges the work shape of Test launch and control system single machine according to the display state of the signal lamp of launch control system single machine
State, control executing agency execute the flight of corresponding actions simulated rocket.
Preferably, executing corresponding actions includes plug between separation grade, sliding magneto stroke switch and overturning password unlocking
Module.
Preferably, image capture module, control module are arranged in a removable frame of lower layer, and executing agency places
Near the component that upper layer needs to operate.
Preferably, lower layer also has separate space, and for placing inertia device shielding system, inertia device shielding system is used
In placing inertial sensor part, inertia device shielding system and main body frame physical isolation are arranged.
It preferably, further include along the one week multiple Electro-static Driven Comb module being arranged in middle layer periphery, Electro-static Driven Comb module includes quiet
Electricity release bracelet.
Preferably, lower layer includes that fixed part is divided into upper and lower two layers of wiring, the forceful electric power power distribution unit setting of power supply-distribution system
In the trace slot of the bottom of lower layer, the upper layer of lower layer is arranged in the data transmission unit between the test equipment of power supply-distribution system
In trace slot.
The assemble method that three-dimensional test platform is delivered in the control system system integration described in one kind, power supply-distribution system weldering are provided
It connects in lower layer, makes control system integration and deliver test platform stage body, middle layer supporting plate is assembled on testboard stage body, upper layer support
Plate is placed on trace block in middle level.
The application method that three-dimensional test platform is delivered in the control system system integration described in one kind, power supply-distribution system weldering are provided
It connects as follows the lower layer, use the step of：
(1) by Test launch and control system single machine, test equipment, visual identity and execute system image capture module,
Control module is placed in the removable frame of lower layer, by power supply-distribution system and Test launch and control system single machine, test equipment,
The image capture module of visual identity and execution system, control module are connected；
(2) main body of cable system is placed into supporting plate in middle level, by the key feature points of cable system by cable trace block into
Row positioning；Test launch and control system single machine is connected with cable system；
(3) flight control system single machine is placed in the relevant device locating slot of upper layer supporting plate, by cable system plug from
Line outlet takes out, and is connected by cable connector with flight control system single machine, and cable connector is placed on supporting plate desktop
On；
(4) inertia device is placed on inertia device shielding system, and be connected with power supply-distribution system；Executing agency places
Near the pending component of upper tabletop, and it is connected with power supply-distribution system；
(5) open power supply-distribution system, Test launch and control system single machine and test equipment to flight control system single machine into
Row is tested, and passes through the traffic light system state of image capture module collecting test launch control system single machine in test process, and
It is sent to control module, control module judges test hair according to the display state of the signal lamp of Test launch and control system single machine
The working condition for penetrating control system single machine executes phase according to the working state control executing agency of Test launch and control system single machine
Action simulation rocket flight state is answered, flight control system single machine is completed and is tested.
The present invention has the following advantages that compared with prior art：
(1) main body frame of the invention be three-decker, by flight control system single machine, flight control system cable system,
Partial test launch control system single machine layered arrangement, layout is clear, convenient for the connection, lookup and replacement of cable, avoids personnel
Maloperation.
(2) middle layer of the invention is used to arrange the main structure of cable system, and by cable system connector as upper layer, comparison is former
Some plane testboards have a bigger cabling space, and double-layer structure is more suitable the control system cable of solid type, multiple-limb
Screen cloth line reduces the stress in control system cable system test process, reduces the risk of cable system damage in test process；Pass through
Middle layer cable trace slot and cable trace block realize the fixation equipotential of leader cable, avoid main cable in wire casing from design level
A possibility that excessively bending, can effectively reduce the risk damaged in cable system test process；
(3) present invention is positioned in superstructure by fixation of the cover plate of upper layer to cable plug, and it is flat to compare original test
Platform cable cloth is more clear, and tester's connecting cable plug time is shorter.Superstructure is priming system cable and ground test
The dedicated cabling channel of cable design, compares original testboard and effectively reduces variety classes cable juxtaposition, improve survey
Try efficiency.
(4) the control system system integration of the present invention delivers three-dimensional test platform and compares original testboard, and table top selection is anti-
Special frosted wearing plate again, upper table surface cable and equipment placement are regular, and cabling is straight, and laboratory's test environment is obviously improved.
(5) present invention setting inertia device shielding system, inertia device is physically separated, avoid inertia device by
Interference, influences to test.
(6) present invention setting visual identity and execution system, according to the working condition of Test launch and control system single machine, certainly
It is dynamic to execute corresponding actions, realize the simulation of the live flying situation to carrier rocket.
Detailed description of the invention
Fig. 1 is platform structure schematic diagram of the present invention；
Fig. 3 is media layer damage figure of the present invention；
Fig. 2 is the upper trace cover board of the present invention；
Fig. 4 is land cable cabling channel of the present invention.
Specific embodiment
The specific implementation method of the invention is introduced below
Three-dimensional test platform, including main body frame, power supply-distribution system, Electro-static Driven Comb system are delivered in the control system system integration
System, visual identity and execution system, inertia device shielding system.
Main body frame is three-decker, and supporting plate is arranged in upper layer 1, and supporting plate for arranging flight control system single machine, use by middle layer 2
In arrangement flight control system cable system, lower layer 3 is used to arrange the Test launch and control system single machine of test flight control system
And test equipment.
The supporting plate on upper layer has multiple line outlets 4, cable when connecting for cable system with each single machine of flight control system
It is interspersed, and cable connector is placed in upper tabletop, convenient for cable seeking and patches.
The cable tray that middle layer 2 includes, for placing the main body of cable system, every level-one cable of carrier rocket is correspondingly arranged
Cable trace slot and cable trace block 23, cable trace slot are matched with the topological shape of corresponding cable, and cable trace slot is around electricity
The setting of cable trace block, cable trace block is used for positioning cable main body, and supports upper layer supporting plate.
Lower layer 31 includes fixed part and multiple removable frames 8, and removable frame places the tooling device of carrier rocket
And Test launch and control system single machine, tooling device needed for the test of each are respectively provided with independent removable frame.Three
The landscape layout of layer structure is according to carrier space vehicle control system topology layout, and according to the quaternary structure of carrier rocket, every level-one is only
Vertical layout, it is longitudinally opposed to answer.
Power supply-distribution system is integrated between the forceful electric power power distribution unit and test equipment of test equipment executing agency power supply and distribution
Data transmission unit, setting is fixed on the fixed part of lower layer.
Static electricity releasing system is used for tester's release electrostatic, the one week multiple Electro-static Driven Comb mould of setting in periphery along middle layer
Block 5 provides multiple Electro-static Driven Comb bracelets worn for personnel.
Visual identity and execution system, including image capture module, control module and executing agency, image capture module
The traffic light system data of collecting test launch control system single machine, and it is sent to control module, control module is controlled according to transmitting
The display situation of the signal lamp of system single machine processed, judges the working condition of Test launch and control system single machine, according to working condition
It controls executing agency and executes plug between corresponding actions, such as separation grade, sliding magneto stroke switch and overturning password unlocking mould
Block.Such as when separation indicator light is lighted, plug between separation grade is demonstrated the need for, control system controls the automatic executive level of executing agency
Between separate, simulate the live flying situation of carrier rocket.Image capture module, control module are arranged in a removable frame 7
In.Executing agency is placed near the component that upper layer needs to operate.
Lower layer has separate space, for placing inertia device shielding system 6, the inertia device shielding system 6 and main body
Frame physical isolation, to guarantee inertial sensor part not by the interference of other equipment.
Main body frame of the invention selects carbon steel square tubes soldering steel skeleton.
Middle layer cable tray material uses cold-rolled steel sheet, forms cable trace slot by bending.Cable trace slot has anti-
The characteristics of burn into intensity height, anti-scratch.
Upper layer supporting plate selects anti-times of special frosted wearing plate, this material plate itself has insulation, fire-retardant, anti-corrosion and waterproof, prevents
Damp function.
1) middle layer cable tray makes
The present invention is according to cable web frame production middle layer trace slot and trace block on bullet, and the specific structure is shown in FIG. 3, bracket
21 are bent by cold-rolled steel sheet, and trace block is bent by cold-rolled steel sheet, and is welded on cable tray, formed trace block and
Trace slot 22 around trace block.The roomy cable trough for placing cable system main structure is produced, cable groove depth is
200mm, entire cable system can be divided into 4 parts according to its design feature, make 4 pieces of trace groove body structures altogether, have been spliced into
Whole cable tray.Trace block is arranged on the key feature points of cable system, such as in cable inflection point, cable isolation point, cable
Relay bearing.
Control system cable backbone is laid in cable trace slot, according to the difference of the construction of cable, makes cable trace block
23, shape is determined by cable mesh-shaped, and packet expands but is not limited to ellipse, round, square.Wherein round locating piece radius is not small
In 300mm.It is welded on supporting plate after determining position, reaches fixed control system cable system position, determine cable system row
The purpose of mark.
The periphery of the setting of Electro-static Driven Comb module 5 in middle level one week, is set as drawer structure, and Electro-static Driven Comb is arranged in drawer
Whether equipment can detecte tester's electrostatic surplus in accordance with test request, and provide tester's Electro-static Driven Comb hand of wearing
Ring.Multiple heat release holes are provided in cable trace slot 22.
2) upper layer supporting plate makes
The present invention is according to the structure and control system single machine feature of control system cable system branch cable according to Fig. 2 pattern system
Make upper layer supporting plate 1, upper layer supporting plate is also classified into 4 each sections, and supporting plate area is identical with the area of middle layer trace slot, supporting plate according to
Cable appearance position opens line outlet 11, and line outlet size is not less than 150mm*150mm, according to control system branch cable on supporting plate
Walk the corresponding control system branch cable net trace slot 12 of line position turnning and milling, wire casing depth 3mm places wire clamp in trace slot 12
Guarantee that cable system cabling is straight, while according to the connection relationship of control system single machine and cable system, position is put in planning on supporting plate
It sets, in corresponding position turning and milling equipment locating slot, clamping slot depth 3mm.
3) power supply-distribution system trace slot makes
In conjunction with Fig. 4, bottom 3 divides for upper layer and lower layer cabling, for arranging power supply-distribution system of the invention, forceful electric power power distribution unit
33 are arranged in the trace slot of bottom, and the data transmission unit 32 between test equipment is arranged in the trace slot of upper layer.Bottom
Frame 31 is used to support middle layer cable tray.
Cable trace slot, trace slot structure feature are shown in that Fig. 4, frame 31 are the support of metal folding part, are each in trace slot
Root cable isolates corresponding ground test cableway 32, and cabling channel is located at lower trace plate according to ground test cable feature
Lower section.
4) platform assembles
Using carbon steel square tubes soldering steel main body frame, power supply-distribution system is welded on main body frame, makes control system collection
At test platform stage body is delivered, middle layer supporting plate is assembled on testboard stage body, and upper layer supporting plate is placed on trace block in middle level.
It is as follows that three-dimensional test platform application method is delivered in the control system system integration：
(1) by Test launch and control system single machine, test equipment, visual identity and execute system image capture module,
Control module is placed in the removable frame of lower layer, by power supply-distribution system and Test launch and control system single machine, test equipment,
The image capture module of visual identity and execution system, control module are connected；
(2) main body of cable system is placed into supporting plate in middle level, by the key feature points of cable system by cable trace block into
Row positioning；Test launch and control system single machine is connected with cable system；
(3) flight control system single machine is placed in the relevant device locating slot of upper layer supporting plate, by cable system plug from
Line outlet takes out, and is connected by cable connector with flight control system single machine, and cable connector is placed on supporting plate desktop
On.
(4) inertia device is placed on inertia device shielding system, and be connected with power supply-distribution system；Executing agency places
It is connected near upper tabletop execution unit, and with power supply-distribution system.
(5) open power supply-distribution system, Test launch and control system single machine and test equipment to flight control system single machine into
Row is tested, and passes through the traffic light system state of image capture module collecting test launch control system single machine in test process, and
It is sent to control module, control module judges test hair according to the display state of the signal lamp of Test launch and control system single machine
The working condition for penetrating control system single machine executes phase according to the working state control executing agency of Test launch and control system single machine
Action simulation rocket flight state is answered, flight control system single machine is completed and is tested.
The present invention has the cable for being difficult to bend originally bigger by the dimension of three layers of platform structure expanding test platform
Expansive space.Tester can be quickly found out cable plug according to different cable outlet holes, and be attached with single machine,
Shorten the time that need to look for cable plug.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (13)
1. three-dimensional test platform is delivered in a kind of control system system integration, which is characterized in that including main body frame and power supply and distribution
System；
Main body frame is three-decker, and supporting plate is arranged in upper layer, and supporting plate is for arranging flight control system single machine；Middle layer is for arranging
Flight control system cable system main structure；Lower layer is used to arrange the Test launch and control system list of test flight control system
Machine, test equipment and power supply-distribution system；Power supply-distribution system is three-dimensional test platform power supply.
2. three-dimensional test platform is delivered in the control system system integration as described in claim 1, which is characterized in that upper layer supporting plate is set
Set the line outlet for cable connection, the trace slot of branch cable cabling and flight control system single machine locating slot.
3. three-dimensional test platform is delivered in the control system system integration as claimed in claim 2, which is characterized in that middle layer supporting plate packet
Multiple trace blocks for cable system positioning are included, form trace slot around trace block, the key that cable system is arranged in trace block is special
At sign point position.
4. three-dimensional test platform is delivered in the control system system integration as claimed in claim 3, which is characterized in that lower layer includes solid
Fixed part and multiple removable frames, fixed part is for arranging that power supply-distribution system, multiple removable frames arrange test flight
The Test launch and control system single machine and test equipment of control system.
5. three-dimensional test platform is delivered in the control system system integration as claimed in claim 4, which is characterized in that three-decker is every
According to the multilevel structure zoning of carrier rocket, the position of the upper and lower cable connection is correspondingly arranged layer up and down.
6. three-dimensional test platform is delivered in the control system system integration as claimed in claim 4, which is characterized in that further include vision
Identification and execution system, including image capture module, control module and executing agency, the transmitting of image capture module collecting test
The traffic light system state of control system single machine, and it is sent to control module, control module is according to launch control system single machine
The display state of signal lamp, judges the working condition of Test launch and control system single machine, and control executing agency executes corresponding actions
Simulated rocket flight.
7. three-dimensional test platform is delivered in the control system system integration as claimed in claim 6, which is characterized in that execute corresponding dynamic
Make to include separating plug between grade, sliding magneto stroke switch and overturning password unlocking module.
8. three-dimensional test platform is delivered in the control system system integration as claimed in claim 6, which is characterized in that Image Acquisition mould
Block, control module are arranged in a removable frame of lower layer, and executing agency is placed near the component that upper layer needs to operate.
9. three-dimensional test platform is delivered in the control system system integration as claimed in claim 8, which is characterized in that lower layer also has
Separate space, for placing inertia device shielding system, inertia device shielding system is for placing inertial sensor part, inertia device
Part shielding system and main body frame physical isolation are arranged.
10. three-dimensional test platform is delivered in the control system system integration as claimed in claim 9, which is characterized in that further include edge
Multiple Electro-static Driven Comb modules of middle layer periphery setting in one week, Electro-static Driven Comb module includes Electro-static Driven Comb bracelet.
11. three-dimensional test platform is delivered in the control system system integration as claimed in claim 9, which is characterized in that lower layer includes
Fixed part is divided into upper and lower two layers of wiring, and the forceful electric power power distribution unit of power supply-distribution system is arranged in the trace slot of the bottom of lower layer,
Data transmission unit between the test equipment of power supply-distribution system is arranged in the upper layer trace slot of lower layer.
12. the assemble method of three-dimensional test platform is delivered in a kind of control system system integration as claimed in claim 9, feature exists
In power supply-distribution system is welded on lower layer, and production control system integration delivers test platform stage body, and middle layer supporting plate is assembled in testboard
On stage body, upper layer supporting plate is placed on trace block in middle level.
13. the application method of three-dimensional test platform, power supply and distribution are delivered in the control system system integration described in a kind of claim 11
System is welded on lower layer, which is characterized in that the step of use is as follows：
(1) by image capture module, the control of Test launch and control system single machine, test equipment, visual identity and execution system
Module is placed in the removable frame of lower layer, by power supply-distribution system and Test launch and control system single machine, test equipment, vision
The image capture module of identification and execution system, control module are connected；
(2) main body of cable system is placed into supporting plate in middle level, the key feature points of cable system is determined by cable trace block
Position；Test launch and control system single machine is connected with cable system；
(3) flight control system single machine is placed in the relevant device locating slot of upper layer supporting plate, by cable system plug from outlet
Mouth takes out, and is connected by cable connector with flight control system single machine, and cable connector is placed on supporting plate desktop；
(4) inertia device is placed on inertia device shielding system, and be connected with power supply-distribution system；Executing agency is placed in
Near the layer pending component of desktop, and it is connected with power supply-distribution system；
(5) power supply-distribution system is opened, Test launch and control system single machine and test equipment survey flight control system single machine
It tries, passes through the traffic light system state of image capture module collecting test launch control system single machine in test process, and send
To control module, control module judges test transmitting control according to the display state of the signal lamp of Test launch and control system single machine
The working condition of system single machine processed executes corresponding dynamic according to the working state control executing agency of Test launch and control system single machine
Make simulated rocket state of flight, completes flight control system single machine and tested.
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101263499A (en) * | 2005-07-11 | 2008-09-10 | 布鲁克斯自动化公司 | Intelligent condition monitoring and fault diagnostic system |
| RU2513063C1 (en) * | 2013-02-21 | 2014-04-20 | Открытое акционерное общество Научно-производственное объединение "Искра" | Test bench for rocket engines with thin-wall nozzles |
| CN203965542U (en) * | 2013-08-31 | 2014-11-26 | 成都飞机工业集团电子科技有限公司 | Pylon comprehensive test device |
| CN204116394U (en) * | 2014-10-28 | 2015-01-21 | 惠州市德赛西威汽车电子有限公司 | A kind of function test fixture of automobile electronics |
| CN105892305A (en) * | 2014-12-15 | 2016-08-24 | 北京空间技术研制试验中心 | General spacecraft ground test bed system |
| CN206074636U (en) * | 2016-08-01 | 2017-04-05 | 航天东方红卫星有限公司 | A kind of satellite ground test cable transfer box of multiplexing |
| CN107262184A (en) * | 2017-07-19 | 2017-10-20 | 上海航天控制技术研究所 | A kind of moveable high integration semi physical testing stand |
| RU2651309C1 (en) * | 2017-02-09 | 2018-04-19 | Общество с ограниченной ответственностью "Даурия - спутниковые технологии" | Microclass earth remote probing spacecraft |
-
2018
- 2018-06-29 CN CN201810695931.6A patent/CN108897305B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101263499A (en) * | 2005-07-11 | 2008-09-10 | 布鲁克斯自动化公司 | Intelligent condition monitoring and fault diagnostic system |
| RU2513063C1 (en) * | 2013-02-21 | 2014-04-20 | Открытое акционерное общество Научно-производственное объединение "Искра" | Test bench for rocket engines with thin-wall nozzles |
| CN203965542U (en) * | 2013-08-31 | 2014-11-26 | 成都飞机工业集团电子科技有限公司 | Pylon comprehensive test device |
| CN204116394U (en) * | 2014-10-28 | 2015-01-21 | 惠州市德赛西威汽车电子有限公司 | A kind of function test fixture of automobile electronics |
| CN105892305A (en) * | 2014-12-15 | 2016-08-24 | 北京空间技术研制试验中心 | General spacecraft ground test bed system |
| CN206074636U (en) * | 2016-08-01 | 2017-04-05 | 航天东方红卫星有限公司 | A kind of satellite ground test cable transfer box of multiplexing |
| RU2651309C1 (en) * | 2017-02-09 | 2018-04-19 | Общество с ограниченной ответственностью "Даурия - спутниковые технологии" | Microclass earth remote probing spacecraft |
| CN107262184A (en) * | 2017-07-19 | 2017-10-20 | 上海航天控制技术研究所 | A kind of moveable high integration semi physical testing stand |
Non-Patent Citations (1)
| Title |
|---|
| 赵瑜龙: "屏幕抓取及图像识别技术在电厂数字化仪控系统功能测试中的应用分析", 《黑龙江科技信息》 * |
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