CN205427516U - Ring testing system closes star based on bus - Google Patents
Ring testing system closes star based on bus Download PDFInfo
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- CN205427516U CN205427516U CN201521087529.8U CN201521087529U CN205427516U CN 205427516 U CN205427516 U CN 205427516U CN 201521087529 U CN201521087529 U CN 201521087529U CN 205427516 U CN205427516 U CN 205427516U
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Abstract
The utility model relates to a ring testing system closes star based on bus for equipment on the star of test appearance rail accuse branch system. Including a N detecting device, controller, a M final controlling element, bus and dynamics computer, the sensor is used for detecting flight attitude information, the sensor is handled the circuit and is used for handling sensor output flight attitude information, the control signal that actuating mechanism drive circuit reception control unit sent to it carries out the operation to generate drive signal drive actuating mechanism, the controller passes through the bus and receives line output 's signal is handled to the sensor to send control signal based on this signal through the bus and give actuating mechanism drive circuit, status signal through bus receiving actuating equipment feedback, through bus and dynamics computer both -way communication. Through the very big star ground interface kind of having simplified of setting up of bus, reduced star ground number of interfaces, reduced test equipment's volume greatly.
Description
Technical field
This utility model relates to a kind of star based on bus ground closed loop test system, belongs to field tests.
Background technology
Closed loop test system is for the test of rail control subsystem, under rail control subsystem running status, detect each parts and system the key technical indexes；Rail control subsystem is used for measuring attitude information, completes gesture stability and the orbits controlling of satellite.
In traditional closed loop test system, on star, unit arranges on the inspection of independent ground interface, and star communication interface between product and does not shares, and carries out information by ground inspection interface mutual, be also based on this reason with causing star complex interfaces between star ground.In system, each circuit has independent ground inspection interface, and accordingly, ground installation needs to arrange corresponding interface.And different systems constitutes the signal condition equipment the most necessarily causing needing to go into operation different, cause the wasting of resources and overlapping investment.
Utility model content
The purpose of this utility model is to overcome the above-mentioned deficiency of prior art, reduces kind of interface, quantity, reduces the volume of test equipment, it is provided that a kind of based on bus closed loop test system.
Above-mentioned purpose of the present utility model is achieved by following technical solution:
A kind of closed loop test system, including N number of detection device, controller, M performs device, bus and dynamics computer；N number of detection device, controller, M execution device and dynamics computer are all connected to described bus；
Each detection device includes sensor and sensor process circuit, and described sensor is used for detecting flight attitude information；Described sensor process circuit processes for sensor is exported flight attitude information, and the signal after processing is sent to controller by described bus, and the pumping signal received is sent to sensor；
Each execution device includes actuator and actuator driver circuit, actuator driver circuit receives the control signal that controller sends, and generate driving signal drive actuator perform operation, the status information of actuator feedback self is to actuator driver circuit, and status information is sent to controller and dynamics computer by actuator driver circuit；
Described controller receives the signal of described sensor process circuit output by bus, and sends control signal to actuator driver circuit based on this signal by bus；The status signal fed back by bus receiving actuating equipment；By bus and dynamics computer both-way communication；
Described dynamics computer includes: CPU, bus board, serial port board；Described CPU sends pumping signal extremely described sensor process circuit by serial port board or bus board, is connected to described bus by bus board card, by bus and controller both-way communication.
Wherein, described controller is by bus and dynamics computer both-way communication, particularly as follows: the status information of self is sent to described CPU, described CPU through bus by controller sends control instruction to controller.
Wherein, described bus is 1553B bus, and described bus board is 1553B bus board.
Wherein, dynamics computer is by network and server, printer communication.
Wherein, described serial port board realizes the output of the pumping signal to middle-size and small-size detection device.
Wherein, described 1553B bus board reserved part EBI；Described serial port board reserved part serial ports.
Wherein, described dynamics computer includes: also includes that display, CPU receive the signal that controller sends, is sent to display and shows after process.
Wherein, described flight attitude information is angle information or angular velocity information.
Wherein, if detection device is designed with EBI, then CPU sends the pumping signal of sensor by bus board；If detection device only serial ports does not has EBI, then CPU sends the pumping signal of sensor by serial port board.
This utility model compared with prior art provides the benefit that:
(1) the ground inspection interface not in use by customization gathers product information, using test equipment as a remote terminal (RT) of 1553B bus in system and watch-dog (MT), gather the communication data on internal bus, as the input of dynamics computer.Greatly simplify star ground kind of interface, decrease star ground interface quantity.Simultaneously because the minimizing of kind of interface, quantity, substantially reduce the volume of test equipment.Make equipment scale little, it is simple to carry, convenient transportation.
(2) product that signal encourages is needed, difference according to product scale, its pumping signal is designed as serial ports or the 1553B bus communication interface of standard, directly by serial ports or bus communication, pumping signal is exported to circuit, without repeating to arrange multiple interface, it is not necessary to be separately provided signal condition equipment output drive signal.
(3) this equipment leaves the communication interface with existing equipment, can be applied in combination with existing equipment, forms Full Featured test and verification platform.
Accompanying drawing explanation
Fig. 1 is this utility model closed loop test system composition frame chart；
Fig. 2 is this utility model closed loop test system schematic diagram.
Detailed description of the invention
With specific embodiment, this utility model is described in further detail below in conjunction with the accompanying drawings:
Closed loop test structure makes full use of the opening of bus, interoperability and interoperability, makes the information of system be simplified alternately, solves the Interface Matching problem between star upper-part.
The on-board equipment that test object is rail control subsystem of closed loop test system, the test equipment of closed loop test system includes: sensor and process circuit, actuator and driver circuit thereof, controller；Sensor is used for the attitude information such as detection angles, angular velocity；Sensor process circuit is for carrying out calculating process by the signal that sensor exports, and the information after processing is sent to controller by 1553B bus；Described controller receives the signal of sensor process circuit output, controls actuator action based on this signal, and receives the status information of actuator feedback；Actuator driver circuit receives the control signal that controller sends, and generates driving signal driving actuator action, and the status information of actuator feedback self is to actuator driver circuit；Described dynamics computer receives the actuator status information for dynamics calculation by bus, sends the pumping signal of sensor.
If detection device is designed with 1553B EBI, then sent the pumping signal of sensor by 1553B bus board；If detection device only has serial ports, then sent the pumping signal of sensor by serial port board.
Dynamics computer specifically includes that CPU, 1553B bus board, serial port board.The action parameter of Content of communciation and status information between 1553B bus board clamping admission controller and actuator driver circuit, send the pumping signal of sensor by serial port board or 1553B bus board.
Apolegamy equipment comprises the steps that the universal network equipment such as server, printer.
For the ease of the debugging of the big system in star ground, reserved part standard 1553B EBI, or standard serial port, for the monitoring of communication on star, it is simple to find communication failure in time, and can quick orientation and communication failure mechanism.
The above; it is only the detailed description of the invention that utility model is optimal; but protection domain of the present utility model is not limited thereto; any those familiar with the art is in the technical scope that this utility model discloses; the change that can readily occur in or replacement, all should contain within protection domain of the present utility model.
The content not being described in detail in this utility model description belongs to the known technology of professional and technical personnel in the field.
Claims (8)
1. a closed loop test system, it is characterised in that: including N number of detection device, controller, M performs device, bus and dynamics computer；N number of detection device, controller, M execution device and dynamics computer are all connected to described bus；
Each detection device includes sensor and sensor process circuit, and described sensor is used for detecting flight attitude information；Described sensor process circuit processes for sensor is exported flight attitude information, and the signal after processing is sent to controller by described bus, and the pumping signal received is sent to sensor；
Each execution device includes actuator and actuator driver circuit, actuator driver circuit receives the control signal that controller sends, and generate driving signal drive actuator perform operation, the status information of actuator feedback self is to actuator driver circuit, and status information is sent to controller and dynamics computer by actuator driver circuit；
Described controller receives the signal of described sensor process circuit output by bus, and sends control signal to actuator driver circuit based on this signal by bus；The status signal fed back by bus receiving actuating equipment；By bus and dynamics computer both-way communication；
Described dynamics computer includes: CPU, bus board, serial port board；Described CPU sends pumping signal extremely described sensor process circuit by serial port board or bus board, is connected to described bus by bus board card, by bus and controller both-way communication.
System the most according to claim 1, it is characterized in that: described controller is by bus and dynamics computer both-way communication, particularly as follows: the signal that the described sensor process circuit received is exported by controller is sent to described CPU, described CPU through bus and sends control instruction to controller.
System the most according to claim 1, it is characterised in that: described bus is 1553B bus, and described bus board is 1553B bus board.
System the most according to claim 1, it is characterised in that: dynamics computer is by network and server, printer communication.
System the most according to claim 3, it is characterised in that: described 1553B bus board reserved part EBI；Described serial port board reserved part serial ports.
System the most according to claim 2, it is characterised in that: described dynamics computer includes: also includes that display, CPU receive the signal that controller sends, is sent to display and shows after process.
System the most according to claim 1, it is characterised in that: described flight attitude information is angle information or angular velocity information.
System the most according to claim 1, it is characterised in that: if detection device is designed with EBI, then CPU sends the pumping signal of sensor by bus board；If detection device only serial ports does not has EBI, then CPU sends the pumping signal of sensor by serial port board.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521087529.8U CN205427516U (en) | 2015-12-23 | 2015-12-23 | Ring testing system closes star based on bus |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521087529.8U CN205427516U (en) | 2015-12-23 | 2015-12-23 | Ring testing system closes star based on bus |
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| CN205427516U true CN205427516U (en) | 2016-08-03 |
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| CN201521087529.8U Active CN205427516U (en) | 2015-12-23 | 2015-12-23 | Ring testing system closes star based on bus |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260886A (en) * | 2019-04-29 | 2019-09-20 | 上海航天控制技术研究所 | A kind of space photoelectric sensor Intelligentized test system |
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2015
- 2015-12-23 CN CN201521087529.8U patent/CN205427516U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260886A (en) * | 2019-04-29 | 2019-09-20 | 上海航天控制技术研究所 | A kind of space photoelectric sensor Intelligentized test system |
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