CN103303503A - Portable spacecraft ground simulation test platform - Google Patents
Portable spacecraft ground simulation test platform Download PDFInfo
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- CN103303503A CN103303503A CN2013102678306A CN201310267830A CN103303503A CN 103303503 A CN103303503 A CN 103303503A CN 2013102678306 A CN2013102678306 A CN 2013102678306A CN 201310267830 A CN201310267830 A CN 201310267830A CN 103303503 A CN103303503 A CN 103303503A
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Abstract
The invention discloses a portable spacecraft ground simulation test platform which comprises a crate, a support plate, a zero slot controller, a function expansion board and an ATX (AT extended) power supply, wherein, a front panel and a rear panel are arranged on the crate, the test platform further comprises the support plate vertically mounted in the middle inside the crate and connected with the front panel through cables, the zero slot controller arranged inside the crate and connected with the support plate through a connector, the function expansion plate fixed between the support plate and the rear plate and connected with the support plate circuit, the ATX power supply arranged on one side of the rear panel of the crate, and an external 220 V alternating current powering the ATX power supply, and the ATX power supply outputs direct current with a plurality of voltage amplitudes and supplies power to the zero slot controller and the function expansion plate through the support plate. The test platform is small and light, can build the test environment of the spacecraft model, solves the test conflict caused by model increasing, decreases the connecting cable between test systems, and effectively decreases the complexity of the system.
Description
Technical field
The present invention relates to simulation test platform, particularly a kind of portable spacecraft ground simulation test platform.
Background technology
Space flight model ground simulation test at present is general to be adopted and builds large-scale test macro and carry out, and no matter is each single machine test or system level testing, and the product of space flight model all has its particularity, is mainly reflected in that signal is various, complex interfaces, reliability requirement be high.In addition, test environment is often carried, changed to the product needed of space flight model, the requirement of test macro is convenient in addition mobile.Large-scale emulation test system can satisfy test request, but no matter from the commonality between carrying convenience, extensibility, each system inborn deficiency is arranged all.Under some environment, the large artificial test macro is subject to bigger volume and can not finishes, and when particularly carrying out some small-sized confirmation testings, can not finish to fast and reliable building of test environment.
Summary of the invention
The purpose of this invention is to provide a kind of portable spacecraft ground simulation test platform, this test platform small portable, test environment that can fast construction space flight model, test conflict when the solution model is increasing, and the connecting cable between the minimizing test macro, effectively reduce the complexity of system.
In order to realize above purpose, the present invention is achieved by the following technical solutions:
A kind of portable spacecraft ground simulation test platform comprises cabinet, and this cabinet is provided with front panel and rear panel, be characterized in,
Also comprise:
Support plate, it is vertically mounted on the cabinet inside midway location, and links to each other with front panel by cable;
Zero greeve controller, it is arranged in the cabinet, and links to each other with support plate by connector;
Expansion board, it is fixed between support plate and the rear panel, and is connected with the support plate circuit;
The ATX power supply, it is arranged on a side of cabinet rear panel, and outside 220V exchanges and is the power supply of ATX power supply, the direct current (DC) of simultaneously described ATX power supply output multiple voltage amplitude and be that Zero greeve controller and expansion board are powered by support plate.
Described support plate is respectively equipped with some first connectors and some second connectors;
Described first connector linkage function expansion board and the Zero greeve controller;
Described second connector is used for outer signal output.
Described cabinet adopts aluminum design and is provided with reinforcement;
In described cabinet bottom some tube axial fans are installed;
The top of described cabinet and bottom offer louvre respectively.
This test desk also comprises LCDs, and it is installed on the described front panel, and links to each other with support plate.
Described rear panel is respectively equipped with PXI zero groove and some expansion slot, and described expansion slot comprises PXI protocol extension groove and self-defined expansion slot.
The present invention compared with prior art has the following advantages:
(1) this simulation test platform make up simple, flexibly, by being equipped with different standards and the nonstandard supporting corresponding cable of bus integrated circuit board can be finished building of platform, highly versatile;
(2) the simulation test platform volume of building is little, has reduced a lot of interface circuit occupation space resources and transit cable net, and is portable strong, is convenient to carrying;
(3) reliable in structure, anti-seismic performance is strong, can be fit to use under the various harsies environment.
Description of drawings
Fig. 1 is a kind of portable spacecraft ground simulation test platform structural representation of the present invention;
Fig. 2 is the structure principle chart of a kind of portable spacecraft ground simulation test platform of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing, by describing a preferable specific embodiment in detail, the present invention is further elaborated.
As shown in Figure 1, 2, a kind of portable spacecraft ground simulation test platform, it is wide to comprise 310mm() * 360mm(is dark) * the 180mm(height) cabinet 1, this cabinet is provided with front panel 11 and rear panel 12, at the place, base angle of this cabinet binding post 14 is housed, and also comprises: support plate 2, it is vertically mounted on cabinet 1 bosom position, and link to each other with front panel 11 by switching, the point-to-point cable of transit cable employing standard carries out, and colligation is firm in cabinet; Zero greeve controller 3, it is arranged in the cabinet 1, and links to each other with support plate 2 by connector, and Zero greeve controller 3 can external telltale and mouse-keyboard; Expansion board 4, it is fixed between support plate 2 and the rear panel 12, and is connected with support plate 2 circuit, and expansion board 4 mainly is applicable to each unit of space flight model and the interface definition of system, satisfies control and the test of function; The ATX power supply 5 of two 250W standard cPCI, it is arranged on a side of cabinet rear panel 12, realize that two redundant states backup each other, and has a characteristic of plug and pull, outside 220V interchange is 5 power supplies of ATX power supply, and the direct current (DC) of simultaneously described ATX power supply 5 output 3.3V, 5V, 12V is Zero greeve controller 3 and expansion board 4 power supplies by support plate 2 also.
Described support plate 2 is respectively equipped with several A25 series first connectors and several J30 series second connector; The described first connector linkage function expansion board 4, Zero greeve controller 3; Described second connector is used for outer signal output.
Described cabinet 1 adopts aluminum design and is provided with reinforcement, can guarantee the stable degree of cabinet self; In described cabinet 1 bottom some tube axial fans 13 are installed; The top of described cabinet 1 and bottom offer louvre respectively, provide more heat-dissipating space guaranteeing that cover plate does not produce under the prerequisite of deformation, form the structure of ventilating up and down, accelerate heat radiation by tube axial fan, guarantee that by optimal design foreign matter (comprising water droplet) can not enter cabinet 1 by louvre simultaneously.
This test platform also comprises LCDs 6, and it is installed on the described front panel 11, and links to each other with support plate 2, and LCDs 6 is used for showing the operating system of Zero greeve controller, and writes corresponding emulation testing software.Simultaneously front panel is installed various monitoring points according to demand, can be according to the layout of the different self-defined front panels of demand, and various power supplys and signal all can be drawn from the connector on the support plate 2.
Described rear panel 12 is respectively equipped with PXI zero groove and some expansion slot, the compatible PXI bus standard in this expansion slot position, expansion slot comprises PXI protocol extension groove, self-defined expansion slot, and each self-defined expansion slot is equipped with a J30 connector and namely is used for the output of support plate 2 outer signals.
Above-mentioned ATX power supply 5, Zero greeve controller 3 and expansion board 4 all have special-purpose drawing-aid device and latching device.
Support plate directly links to each other to the part nonstandard signal according to actual needs, can change corresponding support plate to the analogue system of having relatively high expectations that links to each other, and increases interconnected signal location.Also can be by the connection of transferring of the J30 connector of each groove position, alerting ability is stronger.Expansion board is powered by the PXI bus after inserting corresponding slot position in the corresponding cabinet, can design accordingly according to the requirement of analogue system, and fast construction goes out the test emulation environment.Under the characteristic demand, according to the corresponding expansion slot of PXI bus protocol bridge joint, make that expansion slot quantity is 14 grooves or 18 grooves, extensibility is stronger, has taken full advantage of the advantage of PXI bus simultaneously, can carry out Synchronization Design by increasing one or several cabinet, has higher flexibility, in actual process of building, dwindle space and the complexity of emulation test system, reduced the research and development time of test macro, had higher value of service.
According to the actual emulation testing requirement, generally to test macro possess for distribution, set up realistic model, send various control signals, function such as monitoring in real time, because various product functions and the interface tested all have very big difference, by demand is put in order, the functional cards that inserts supporting design links to each other with corresponding product, simultaneously according to monitoring function can insertion portion standard P XI bus integrated circuit board, can fast construction go out hardware environment.Because the general PXI integrated circuit board of part has had relevant standard in the industry, and the functional cards relevant with emulation testing also universalization gradually on spacecraft, a lot of functional circuits can share under multiple environment.After connecting by support plate, hardware environment is built and is become simple unusually.
Building under the hardware environment that finishes, develop corresponding test software according to the demand of emulation testing, set up concrete realistic model in test software, reach the purpose of test and monitoring.
In sum, a kind of portable spacecraft ground simulation test platform of the present invention, this test platform small portable, test environment that can fast construction space flight model, test conflict when the solution model is increasing, and the connecting cable between the minimizing test macro, effectively reduce the complexity of system.
Although content of the present invention has been done detailed introduction by above preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.After those skilled in the art have read foregoing, for multiple modification of the present invention with to substitute all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (5)
1. a portable spacecraft ground simulation test platform comprises cabinet (1), and this cabinet is provided with front panel (11) and rear panel (12), it is characterized in that,
Also comprise:
Support plate (2), it is vertically mounted on cabinet (1) bosom position, and links to each other with front panel (11) by cable;
Zero greeve controller (3), it is arranged in the cabinet (1), and links to each other with support plate (2) by connector;
Expansion board (4), it is fixed between support plate (2) and the rear panel (12), and is connected with support plate (2) circuit;
ATX power supply (5), it is arranged on a side of cabinet rear panel (12), outside 220V interchange is ATX power supply (5) power supply, and the direct current (DC) of the multiple voltage of described ATX power supply (5) output simultaneously amplitude is Zero greeve controller (3) and expansion board (4) power supply by support plate (2) also.
2. portable spacecraft ground simulation test platform as claimed in claim 1 is characterized in that, described support plate (2) is respectively equipped with some first connectors and some second connectors;
The described first connector linkage function expansion board (4) and Zero greeve controller (3);
Described second connector is used for outer signal output.
3. portable spacecraft ground simulation test platform as claimed in claim 1 is characterized in that, described cabinet (1) adopts aluminum design and is provided with reinforcement;
In described cabinet (1) bottom some tube axial fans (13) are installed;
Top and the bottom of described cabinet (1) offer louvre respectively.
4. portable spacecraft ground simulation test platform as claimed in claim 1 is characterized in that, also comprises LCDs (6), and it is installed on the described front panel (11), and links to each other with support plate (2).
5. portable spacecraft ground simulation test platform as claimed in claim 1 is characterized in that, described rear panel (12) is respectively equipped with PXI zero groove and some expansion slot, and described expansion slot comprises PXI protocol extension groove and self-defined expansion slot.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102678306A CN103303503A (en) | 2013-06-28 | 2013-06-28 | Portable spacecraft ground simulation test platform |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2013102678306A CN103303503A (en) | 2013-06-28 | 2013-06-28 | Portable spacecraft ground simulation test platform |
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| CN103303503A true CN103303503A (en) | 2013-09-18 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104539376A (en) * | 2015-01-04 | 2015-04-22 | 北京军懋国兴科技有限公司 | Portable test equipment for flight data recorder system |
| CN105373114A (en) * | 2015-11-24 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Signal excitation device |
| CN105842564A (en) * | 2015-12-31 | 2016-08-10 | 西安航天精密机电研究所 | CPCI computer based platform unit testing instrument |
| CN111274678A (en) * | 2020-01-13 | 2020-06-12 | 四川华丰企业集团有限公司 | Manufacturing method of space electronic case |
| CN111605741A (en) * | 2020-07-06 | 2020-09-01 | 北京空间技术研制试验中心 | Microminiature space experimental device based on standard cube module |
| CN111831500A (en) * | 2020-08-07 | 2020-10-27 | 深圳市厚物科技有限公司 | Portable multifunctional PXIe measurement and control platform |
| CN114564347A (en) * | 2022-04-28 | 2022-05-31 | 北京中科飞鸿科技股份有限公司 | Low-delay bus test verification platform for avionics system |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104539376A (en) * | 2015-01-04 | 2015-04-22 | 北京军懋国兴科技有限公司 | Portable test equipment for flight data recorder system |
| CN104539376B (en) * | 2015-01-04 | 2023-07-04 | 北京军懋国兴科技股份有限公司 | Portable flight parameter system's test equipment |
| CN105373114A (en) * | 2015-11-24 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Signal excitation device |
| CN105842564A (en) * | 2015-12-31 | 2016-08-10 | 西安航天精密机电研究所 | CPCI computer based platform unit testing instrument |
| CN111274678A (en) * | 2020-01-13 | 2020-06-12 | 四川华丰企业集团有限公司 | Manufacturing method of space electronic case |
| CN111274678B (en) * | 2020-01-13 | 2023-04-11 | 四川华丰科技股份有限公司 | Manufacturing method of space electronic case |
| CN111605741A (en) * | 2020-07-06 | 2020-09-01 | 北京空间技术研制试验中心 | Microminiature space experimental device based on standard cube module |
| CN111831500A (en) * | 2020-08-07 | 2020-10-27 | 深圳市厚物科技有限公司 | Portable multifunctional PXIe measurement and control platform |
| CN114564347A (en) * | 2022-04-28 | 2022-05-31 | 北京中科飞鸿科技股份有限公司 | Low-delay bus test verification platform for avionics system |
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Application publication date: 20130918 |
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