CN1982863B - Universal micro-satellite comprehensive testing platform based on PXI system - Google Patents
Universal micro-satellite comprehensive testing platform based on PXI system Download PDFInfo
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Abstract
A universal micro-satellite integrated test platform based on PXI system is formed by interconnecting tested object, direct measurement-control layer, central control management layer and terminal monitoring layer to each other.
Description
Technical field
The present invention relates to a kind of micro-satellite comprehensive testing platform that is applied to make up, particularly based on the universal micro-satellite comprehensive testing platform of PXI system, this test platform by make up a cover intelligence, flexibly, the satellite Auto-Test System of complete function, can finish in the satellite development process from the scheme emulation testing to facing the whole star of penetrating each stage of test and the excitation emulation and the test of unit.
Background technology
The reduction in satellite development cost and cycle not only depends on the development of satellite technology itself, also relies on the raising of satellite developing instrument to a great extent.The satellite test technology is an indispensable equipment in the satellite R﹠D process, is accompanied by the overall process of satellite research and development, and the level of testing apparatus is represented the level of satellite research and development to a certain extent, and research and development testing apparatus and research and development satellite itself are of equal importance.Characteristics have determined that its integrated test system should be different with conventional satellite and the microsatellite construction cycle is short, cost is low, measuring control signal is less relatively etc.
But there is following shortcoming in the microsatellite testing apparatus at present:
1) versatility is not strong
Mainly continue to use the method for testing of large satellite, testing apparatus comprises that unit self-checking equipment, integral test system etc. all have very strong specific aim, testing apparatus is various but unrelated, the unitarity of TT﹠C task and globality shortage system are supported, satellite of every development will be developed a cover integral test system again.
2) robotization and intelligent degree are not high
In the current test process, the test data managerial ability is not strong, and test operation does not have daily record, and the low manually-operated intensity of intelligent degree is bigger, has increased human operational error's incidence.
3) opening and dirigibility are not enough
Testing apparatus in the past is conceived to the moment of the research and development of satellite, and specificity is stronger, causes the testing apparatus flexibility ratio not enough, does not reserve the space of upgrading and expansion.
For this reason, develop the satellite intelligence test platform open, that versatility is stronger, be used for the test macro of satellite unit and whole each test phase of star, can improve satellite efficiency of research and development and reliability, also can reduce development cost, great value and significance be arranged for the development of China's moonlet cause.
Current, measuring technology develops to virtual technology rapidly in recent years.With virtual instrument form Auto-Test System reliability height, dirigibility is strong, can be transplanted to another system under test (SUT) to system from a system under test (SUT) by software arrangements.VXI, PXI are the representatives of virtual instrument, but the VXI assembly mostly is high-end product, and system is comparatively huge; PXI is the module instrument system that America NI company proposes in recent years and promotes, and has obtained the widespread use of domestic and international every field, and the virtual software language LABVIEW and the LABWINDOWS/CVI of NI development make PXI hardware obtain strong support.
Summary of the invention
The object of the present invention is to provide and a kind ofly mainly make up a cover than more comprehensive test macro by the software and hardware of selecting NI company for use, and utilize original VXI assembly to finish the universal micro-satellite comprehensive testing platform based on the PXI system of the test of high requirement, the collaborative work at all levels of this test platform has constituted broad applicability, that can reuse, easy to operation, the automaticity intelligence test platform high, unattended duty of having of the test, each unit performance and the functional test that integrate each technological phase of satellite together.
Purpose of the present invention can be achieved through the following technical solutions:
Universal micro-satellite comprehensive testing platform based on the PXI system is characterized in that: this test platform is interconnected by measurand, direct observing and controlling layer, center control and management layer and terminal monitoring layer and forms.
Described terminal monitoring layer comprises GPS terminal, Star Service terminal, appearance control terminal, communication terminal, power terminal and the thermal control terminal corresponding to six satellite subsystems; Described GPS terminal, Star Service terminal, appearance control terminal, communication terminal, power terminal and thermal control terminal connect with described center control and management layer by hub; The handled data difference of this six station terminal, but function is identical with software configuration.At different test phases, according to the difference of tested object, number of terminals can have corresponding variation.Fly test phase at whole star closed loop mould, each terminal is moved simultaneously, finishes the test assignment of each subsystem of satellite respectively; In whole star open loop experimental stage, only staying Star Service terminal and power terminal can finish the work; And in the single machine test stage, then only need to get final product by the pairing subsystem terminal of unit.
In addition, for the ease of observation satellite running status directly perceived, described terminal monitoring layer also comprises an appearance rail presentation terminal, and this appearance rail presentation terminal also connects with described center control and management layer by hub.This appearance rail presentation terminal shows the satellite orbit and the attitude data of control center's distribution with three dimensional form emulation.
Described center control and management layer comprises control center and database server, and this center control and management layer connects alternately with direct observing and controlling layer, and connects with the terminal monitoring layer with above-mentioned hub.To finish the straight survey and the wire-link telemetry of satellite are controlled, and finished the comparison of test data, automatically generated data library test record is gone into the system works journal function; Response terminal supervisory layers request simultaneously realizes the inquiry and the announcement of test data, and each terminal control command request is verified, handing over has direct observing and controlling end to carry out, and final execution result is returned to each terminal.
Described direct observing and controlling layer is to be designed to direct one deck that links to each other with satellite on network structure.Simultaneously, on physical function it also as direct observing and controlling end.This direct observing and controlling layer comprises interface box on observing and controlling front end rack and the star, between the two by star ground; Connect signal cable and connect, observing and controlling front end rack connects alternately with the control center of center control and management layer; Interface box connects with spaceborne computer and each signal measurement apparatus by threeway socket or star ground serial ports and wire-link telemetry terminal on the described star.
This direct observing and controlling layer both can have been realized direct wired straight survey of drawing from pull-off plug, finished the preceding direct test job of satellite encapsulation.Directly by the threeway socket satellite is carried out immediate data during test and adopt control, i.e. centralized control to spaceborne computer plays supervisory function bit, and all signal measurement parameters are with observing and controlling parameter on the star, and compares with the real-time measuring data of surveying serial ports from ground.And provide normal working power for satellite.
Can realize wire-link telemetry by star ground serial ports again, gather all information that pass to ground on the star in real time by star ground serial ports during remote measurement: as the working condition of autonomous telemetry, software operation state, each subsystem on the star; Also support the data on ground are passed on the star: indirect remote control instruction, program are injected, data are injected, to make things convenient for the interactive mode debugging in the test process.
Of the present inventionly directly adopt the major equipment that control end can be used as unit and pylon test, cooperate wired telemetry terminal system to finish pylon test satellite by directly adopting the control end.
Above-mentioned star ground serial ports adopts the asynchronous 485 communication standard patterns of standard.
The above-mentioned front end of directly adopting the control layer as satellite intelligence test platform, use the PXI bus system, under the complete situation of hardware configuration, only need test and control that software (virtual instrument) is made amendment and just can be realized different tested objects, strengthen configurability, the reconfigurability of system, shortened system development cycle; Demonstrate fully the intelligent characteristics of system.
Described observing and controlling front end rack is by PXI data acquisition (DAQ) cabinet, signal condition (SCXI) cabinet, the signal converting cabinet, the equivalent load cabinet, the power supply cabinet is formed, the power supply cabinet is responsible for to PXI data acquisition (DAQ) cabinet, signal condition (SCXI) cabinet, the signal converting cabinet, the power supply of equivalent load cabinet, connect alternately between described PXI data acquisition (DAQ) cabinet and signal condition (SCXI) cabinet, connect alternately between signal condition (SCXI) cabinet and the signal converting cabinet, connect alternately between signal converting cabinet and equivalent load cabinet and the measurand.
Dispose the system controller, input and output (DI/O), simulation output (DA), high speed analog input (AD), the RS-485 serial port board module that are coupled to each other in described PXI data acquisition (DAQ) cabinet, system controller is installed Microsoft Windows2000 operating system, use the control program of adopting of the different tested objects of Measurement Studio software development, and set up local data base (realizing) with MS Access.
Dispose analog signal conditioner module and digital signal conditioning module in described signal condition (SCXI) cabinet, processing such as filtering, isolation amplification are carried out in in-site modeling or digital signal.
Dispose the interconnecting module and the handover module that the on-the-spot test Signal Separation are become the sets of signals of same type in the described signal converting cabinet to switching between satellite and the equivalent load cabinet, interconnecting module can be with on-the-spot test signal such as digital signal, be separated into the sets of signals of same type and the signal of unlike signal group is sent into corresponding signal condition module as digital signal, simulating signal, rs 232 serial interface signal, and the circuit that handover module can be finished simultaneously to satellite and simulator switches.
Described equivalent load cabinet comprises load equivalent device, signal simulator, integrated linear power supply and the interface that is connected with the interior surface power supply module of interconnecting module and power supply cabinet in the described signal converting cabinet, and wherein load equivalent is only done in the power supply equivalence.
The purpose of above-mentioned equivalent load cabinet equivalence is: guarantee the reliability of testing apparatus self before test, the test confidence level of Authentication devices.Therefore, equivalence requires on load capacity different tested objects to be carried out equivalence, uses the safe reliability of verification system for the system equipment self check.This equivalence load machine case in fact can not real equivalent satellite.It only is part measurement and the control signal that analog satellite passes through umbilical connector.Its major function is to carry out power supply equivalence and function equivalent, and power supply equivalence one is to check correctness and the harmony of ground power supply to satellite power supply and distribution physical interface and electric interfaces; The 2nd, simulation power supply process condition produces analog power and status signal.Function equivalent is load on the simulation star, the correctness of access control instruction; Checkout device control equipment is soft, the correctness and the rationality of the every function of hardware and technical requirement.
Described measurand layer comprises measurands such as spaceborne computer, sun sensor, momenttum wheel, magnetic torquer, and measurands such as described spaceborne computer, sun sensor, momenttum wheel, magnetic torquer all can be connected on the above-mentioned star on the interface box by cable on the star.
Reliability is the life of Space Science and Technology, be that spacecraft or ground checkout equipment all must take into full account the Design in Reliability requirement, do not allow because the fault of test macro or human error are sent wrong control signal, so that cause the carrying out of fault delayed test even satellite is damaged.
Owing to adopted technical scheme as above, test platform of the present invention is compared with existing microsatellite test platform, has following advantage aspect reliability:
A) function modoularization, the system assembles design makes system failure judgement and easy to maintenance;
B) star ground system electrical is isolated: test macro and on-board equipment ground wire are all isolated, and are mainly isolated by the light lotus root and relay isolation realization;
For the input of simulating signal, select suitable voltage by connection terminal earlier, isolate through signal regulating panel again, send at last in the A/D capture card, realize the isolation of satellite and test macro.
C), guarantee the accuracy that signal connects by simulator system autodiagnosis and carry out effective self check;
D) to the power supply of telecommand module, adopt relay control, relay disconnects when not sending out telecommand, and the telecommand module is in off position, can guarantee not have the generation of any misoperation, thereby guarantees the safeguard protection to satellite;
E) take into full account safeguard protection to satellite on software design, especially the limiting means of outrange has been taked in output to control signal, and promptly Shu Chu value can not surpass the maximal value and the minimum value of system's permission.Thereby the value that has guaranteed control output can not influence the safety of satellite.
In addition, test platform provided by the invention is compared with existing microsatellite test platform, also has following advantage:
A) highly versatile: as long as test platform of the present invention is just can be from a system transplantation to another system under test (SUT) by software (virtual instrument) configuration.
B) robotization and intelligent degree height, test platform of the present invention mainly is made up of virtual instrument, each terminal is done the operation daily record, with the startup of program own, network connect situation, send the instruction situation, test data is crossed the border alarm condition, quit a program etc., and that action writes the local data library database is for future reference.But each terminal is unattended duty at program start and after linking test network, and data are stored automatically, data are out-of-limit or test makes mistakes can report to the police with the form of sound, electricity, literary composition automatically.In end of test (EOT) or test process, the terminal user can require the test data form in fixed time zone and print.
C) have stronger exploration and dirigibility: the present invention adopts virtual instrument to set up test platform, and each hardware all leaves extending space.
Description of drawings
Further specify the present invention below in conjunction with the drawings and specific embodiments.
Fig. 1 is the network structure that the present invention is based on the universal micro-satellite comprehensive testing platform of PXI system.
Fig. 2 is that the universal micro-satellite comprehensive testing platform that the present invention is based on the PXI system is combined simulated flight device extension figure when surveying.
Fig. 3 is the theory diagram of observing and controlling front end rack that the present invention is based on the universal micro-satellite comprehensive testing platform of PXI system.
Fig. 4 is that the hardware that the present invention is based on the universal micro-satellite comprehensive testing platform of PXI system is formed synoptic diagram.
Fig. 5 is the synoptic diagram of a kind of equivalent way of equivalent load cabinet that the present invention is based on the universal micro-satellite comprehensive testing platform of PXI system.
Fig. 6 is the principle schematic when the present invention is based on the universal micro-satellite comprehensive testing platform system extension of PXI system.
Embodiment
Referring to Fig. 1, based on the universal micro-satellite comprehensive testing platform of PXI system, by measurand, directly observing and controlling layer, center control and management layer and terminal monitoring layer interconnect and form.
Because measuring technology develops to virtual technology rapidly in recent years.With virtual instrument form Auto-Test System reliability height, dirigibility is strong, can be transplanted to another system under test (SUT) to system from a system under test (SUT) by software arrangements.VXI, PXI are the representatives of virtual instrument, but the VXI assembly mostly is high-end product, and system is comparatively huge; PXI is the module instrument system that America NI company proposes in recent years and promotes, obtained the widespread use of domestic and international every field, the virtual software language LABVIEW and the LABWINDOWS/CVI of NI development make PXI hardware obtain strong support, therefore test platform of the present invention mainly makes up a cover than more comprehensive test macro by the software and hardware of selecting NI company for use, and utilizes original VXI assembly to buy the test that a small amount of accessory is finished high requirement.
Constitute the measurand of whole test platform, directly collaborative work between observing and controlling layer, center control and management layer and the terminal monitoring layer, constituted broad applicability, that can reuse, easy to operation, the automaticity intelligence test platform high, unattended duty of having of the test, each unit performance and the functional test that integrate each technological phase of satellite together.
The terminal monitoring layer comprises GPS terminal, Star Service terminal, appearance control terminal, communication terminal, power terminal and the thermal control terminal corresponding to six satellite subsystems; Described GPS terminal, Star Service terminal, appearance control terminal, communication terminal, power terminal and thermal control terminal connect with described center control and management layer by hub; The handled data difference of this six station terminal, but function is identical with software configuration.At different test phases, according to the difference of tested object, number of terminals can have corresponding variation.Fly test phase at whole star closed loop mould, each terminal is moved simultaneously, finishes the test assignment of each subsystem of satellite respectively; In whole star open loop experimental stage, only staying Star Service terminal and power terminal can finish the work; And in the single machine test stage, then only need to get final product by the pairing subsystem terminal of unit
In addition, for the ease of observation satellite running status directly perceived, described terminal monitoring layer also comprises an appearance rail presentation terminal, and this appearance rail presentation terminal also connects with described center control and management layer by hub.This appearance rail presentation terminal shows the satellite orbit and the attitude data of control center's distribution with three dimensional form emulation.
The general function of terminal monitoring layer is as follows:
Each terminal is in charge of the test assignment of own subsystem, finishes demonstration, storage and the management of subsystem test data.Under the situation of authorizing, tested object is sent out direct steering order various or steering order indirectly by control center.
Two kinds of instructions all are pooled to control center earlier, by the validity of control center's analysis instruction, carry out safe examination, if success then sends to number and adopts the control front end, adopt sub-category two kinds of instructions are adopted equipment via pumping signal generator or number being sent to measurand of control front end by number again.
Simultaneously, each terminal is done the operation daily record, with the startup of program own, network connect situation, send the instruction situation, test data is crossed the border alarm condition, quit a program etc., and that action writes the local data library database is for future reference.But each terminal is unattended duty at program start and after linking test network, and data are stored automatically, data are out-of-limit or test makes mistakes can report to the police with the form of sound, electricity, literary composition automatically.In end of test (EOT) or test process, the terminal user can require the test data form in fixed time zone and print.
Center control and management layer comprises control center and database server, and this center control and management layer connects alternately with direct observing and controlling layer, and connects with the terminal monitoring layer with above-mentioned hub.Be responsible for the collaborative work of whole test platform, formulation and distribution, test data storage and management, the system works daily record etc. of test assignment.
Center control and management layer is the core of the control and the management of whole intelligence test platform, it should be mutual with direct observing and controlling layer, to finish the straight survey and the wire-link telemetry of satellite controlled, and finished the comparison of test data, automatically generated data library test record is gone into the system works journal function; Response terminal supervisory layers request again realizes the inquiry and the announcement of test data, and request is verified to the terminal control command, and handing over has direct observing and controlling end to carry out, and final execution result is returned to terminal.
Directly the observing and controlling layer is to be designed to direct one deck that links to each other with satellite on network structure.Simultaneously, on physical function it also as direct observing and controlling end.
This direct observing and controlling layer comprises interface box on observing and controlling front end rack and the star, between the two by star ground; Connect signal cable and connect, observing and controlling front end rack connects alternately with the control center of center control and management layer; Interface box connects with spaceborne computer and each signal measurement apparatus by threeway socket or star ground serial ports and wire-link telemetry terminal on the described star.
Directly the functional task of observing and controlling layer is:
1, wired straight survey (control)----is directly drawn from pull-off plug;
Mainly finish the preceding direct test job of satellite encapsulation.This part is carried out immediate data by the threeway socket to satellite and is adopted control, i.e. centralized control to spaceborne computer plays supervisory function bit, and all signal measurement parameters are with observing and controlling parameter on the star, and compares with the real-time measuring data of surveying serial ports from ground.And provide normal working power for satellite.Mainly comprise:
1) provides normal working power for satellite;
2) provide power supply to control needed various hardware signal, comprise the charge and discharge of accumulator and the operations such as open and close of communication power supply;
3) be the control of spaceborne computer, operations such as comprising open and close, switch and reset provides satisfactory control signal;
4) measure the direct various simulating signals of measuring (0-35V) of needs that pull-off plug provides;
After the satellite encapsulation, this part just no longer works, and promptly gets in touch with satellite dropping.
2, wire-link telemetry----is by star ground serial ports (survey serial ports);
Star ground communication serial port adopts the asynchronous 485 communication standard patterns of standard, gathers all information that pass to ground on the star in real time by star ground serial ports: the working condition of autonomous telemetry, software operation state, each subsystem on the star; Also support the data on ground are passed on the star: indirect remote control instruction, program are injected, data are injected, to make things convenient for the interactive mode debugging in the test process.Concrete star ground communication protocol is undetermined.
Directly adopt the major equipment that control end can be used as unit and pylon test, cooperate wired telemetry terminal system to finish pylon test satellite by directly adopting the control end.
Referring to Fig. 2, in the comprehensive survey stage, the very important point is will carry out mould to fly, and can both carry out under various patterns to guarantee spaceborne software and each subsystem.Finish this task and be with the special inspection equipment of appearance control and GPS specially inspection equipment include this system in.The special inspection equipment of appearance control mainly is to comprise a dynamics simulation machine, control output by dynamics simulation algorithm model and orbital data, reach change solar simulator, earth simulator for earth, the purpose of magnetic simulator state, simulate various patterns in the practical flight process with this.The GPS analog machine can be simulated actual track ruuning situation, makes GPS on the satellite receive function and obtains orbital data under the simulation status.By network, control center sends the output and the orbital data of appearance control performer to the dynamics simulation machine, carries out mould by the dynamics simulation machine and flies, and control center also can issue control command to dynamics simultaneously, changes existing operational mode, convenient debugging.
More than the partial content of two classes design input repeat, be that some measurement or control signal both can be finished by wire-link telemetry, also can finish by wired straight survey, the part signal of pull-off plug is also inconvenience test on pylon, therefore, in the stage of pylon test, according to the emphasis and the characteristics of test, partial test is not done requirement in the pylon test.
Referring to Fig. 3, the above-mentioned front end of directly adopting the control layer as satellite intelligence test platform, use the PXI bus system, under the complete situation of hardware configuration, only need test and control that software (virtual instrument) is made amendment and just can be realized different tested objects, strengthen configurability, the reconfigurability of system, shortened system development cycle; Demonstrate fully the intelligent characteristics of system.
Observing and controlling front end rack is made up of PXI data acquisition (DAQ) cabinet, signal condition (SCXI) cabinet, signal converting cabinet, equivalent load cabinet, power supply cabinet, the power supply cabinet is responsible for to PXI data acquisition (DAQ) cabinet, signal condition (SCXI) cabinet, signal converting cabinet, the power supply of equivalent load cabinet, connect alternately between described PXI data acquisition (DAQ) cabinet and signal condition (SCXI) cabinet, connect alternately between signal condition (SCXI) cabinet and the signal converting cabinet, connect alternately between signal converting cabinet and equivalent load cabinet and the measurand.
In PXI data acquisition (DAQ) cabinet, dispose the system controller, input and output (DI/O), simulation output (DA), high speed analog input (AD), the RS-485 serial port board module that are coupled to each other, system controller is installed Microsoft Windows 2000 operating systems, use the control program of adopting of the different tested objects of Measurement Studio software development, and set up local data base (realizing) with MS Access.
In signal condition (SCXI) cabinet, dispose analog signal conditioner module and digital signal conditioning module, processing such as filtering, isolation amplification are carried out in in-site modeling or digital signal.
In the signal converting cabinet, dispose the interconnecting module and the handover module that the on-the-spot test Signal Separation are become the sets of signals of same type to switching between satellite and the equivalent load cabinet, interconnecting module can be with on-the-spot test signal such as digital signal, be separated into the sets of signals of same type and the signal of unlike signal group is sent into corresponding signal condition module as digital signal, simulating signal, rs 232 serial interface signal, switches the circuit that can finish simultaneously soon satellite and simulator and switches.
Described equivalent load cabinet comprises load equivalent device, signal simulator, integrated linear power supply and the interface that is connected with the interior surface power supply module of interconnecting module and power supply cabinet in the described signal converting cabinet, and wherein load equivalent is only done in the power supply equivalence.
The purpose of above-mentioned equivalent load cabinet equivalence is: guarantee the reliability of testing apparatus self before test, the test confidence level of Authentication devices.Therefore, equivalence requires on load capacity different tested objects to be carried out equivalence, uses the safe reliability of verification system for the system equipment self check.
During the design of equivalent load cabinet, the technical requirement of following is:
1, the satellite simulator is to the interface of ground distributor and the relevant testing apparatus in ground and the interface unanimity of the relevant testing apparatus of ground distributor and ground;
2, the command reception relay and the on-board equipment of Shi Yonging is basic identical, the relevant indication of steering order executing state.
Its major function should comprise power supply equivalence and function equivalent, and power supply equivalence one is to check correctness and the harmony of ground power supply to satellite power supply and distribution physical interface and electric interfaces; The 2nd, simulation power supply process condition produces analog power and status signal.Function equivalent is load on the simulation star, the correctness of access control instruction; Checkout device control equipment is soft, the correctness and the rationality of the every function of hardware and technical requirement.
Above-mentioned equivalent load cabinet can have two kinds of design proposals:
Scheme one: traditional method be the design special measurand " simulator " as equivalent load; This scheme requires simulator itself to have " equivalence " function of appropriateness, and design is complicated, and versatility is not enough; Advantage is: as functional checking, reliability is higher; Specific design is as follows:
Simulator mainly comprises load equivalent device and signal simulator.In fact can not real equivalent satellite.It only is part measurement and the control signal that analog satellite passes through umbilical connector.
Wherein load equivalent is only done in the power supply equivalence; Control unit satellite equivalence design simulator
In view of above requirement and consideration, simulator mainly comprises:
1) integrated linear power supply: simulator drive circuitry and imitated storage battery (DC/DC) power supply;
2) imitated storage battery voltage: mainly form storage battery power supply part on the simulation star by the DC/DC transducer;
3) step switch on the simulation star:, disappear anti-and protection, current-limiting circuit composition mainly by magnetic latching relay; Discharge switch on the simulation star, spaceborne computer switch motion etc.
4) analog bus pull-up resistor: (purpose) is at the satellite ground test phase, and be to the satellite power supply, normal for guaranteeing surface power supply by ground power supply (comprising square formation simulator and ground electric analogy power supply), need test the load capacity of ground power supply; (composition) forms equivalent bus pull-up resistor according to satellite load power by the high-power resistance parallel-series, determines the load capacity of ground power supply by current monitoring.
5) voltage and current is measured and is shown: the imitated storage battery voltage of measurement and demonstration satellite simulator and analog bus equivalent load electric current etc.
6) with the interface of miscellaneous equipment: the main realization and signal converting module of " directly adopt and control front end " and being connected of surface power supply module.
Scheme two: referring to Fig. 5, adopt high reliability, standardized functional module to form the closed loop equivalent way, this scheme is utilized the functional module of high reliability, versatility, also can realize the self check to the front equipment end test channel reliably, simplicity of design, convenience; Shortcoming is that functional self check reliability is not as " simulator ".
According to simplifying principle, the satellite simulator does not comprise the equivalence of RS-422 star ground communication, and load equivalent is only done in the equivalence of power supply equivalent source.
Referring to Fig. 4, hardware in above-mentioned PXI data acquisition (DAQ) cabinet, signal condition (SCXI) cabinet is all selected product (the National Instruments of American National instrument company for use, hereinafter to be referred as NI company), each module meets the PXI bus specification at aspects such as electric, structures.
System controller is selected the embedded Zero greeve controller of PXI-8186 PIV2.2G of the up-to-date release of NI for use, has guaranteed the travelling speed of system.The SCXI-1327 terminal module that 32 tunnel simulating signals at first enter SCXI-1120D signal condition module front end amplifies through the SCXI-1120D module filtered after decay again, is gathered by the PXI-6052E module at last; 8 road analog output signals are finished by the D/A of PXI-6733 module, and the PXI-6052E module also has 2 road D/A output in addition, and these analog output signals can enter self-made signal modulate circuit plate and isolate amplification, reach the requirement of system to output signal; Output of 24 way words and 8 way word input signals are finished by PXI-6527 numeral I/O module, and this module is input as 24 road light and isolates 0～28VDC signal, is output as to isolate solid-state relay 0～60VDC or 0～30Vrms signal.PXI-8423/2 is 2 mouthfuls of RS-485 serial communication interface modules, is used for the Communication Control between system and the external unit; By RS-485 serial communication interface module, can finish the wire-link telemetry function directly adopting control end.
Aspect hardware opening and extendability, PXI data acquisition (DAQ) cabinet of test platform of the present invention, signal condition (SCXI) cabinet are selected the PXI data acquisition cabinet of 18 groove and the SCXI signal condition cabinet of 1 18 groove for use, actual putting in order star when test, the PXI cabinet has only taken 6 slots, its middle controller takies 1, capture card takies 5, has 2 slots to use for expansion module; The SCXI cabinet only takies 4 slots, also has 8 slots to use for system extension.
If system also will carry out bigger expansion, then can increase the PXI cabinet, and can couple together by the MXI-3 interface card of NI company between original PXI cabinet.In addition, also can increase signal input channel quantity by increasing conditioning cabinet or SCXI multiplexing module, every capture card can connect the SCXI signal condition cabinet of 8 12 grooves at most, nearly 3072 input channels.
Referring to Fig. 1, the measurand layer comprises measurands such as spaceborne computer, sun sensor, momenttum wheel, magnetic torquer, and measurands such as described spaceborne computer, sun sensor, momenttum wheel, magnetic torquer all can be connected on the above-mentioned star on the interface box by cable on the star.
Certainly,, do not spend performing creative labour, on the basis of the foregoing description, can do multiple variation, can realize purpose of the present invention equally for one of ordinary skill in the art.But above-mentioned various variations obviously should be in the protection domain of claims of the present invention.
Claims (11)
1. based on the universal micro-satellite comprehensive testing platform of PXI system, it is characterized in that: this test platform is interconnected by measurand layer, direct observing and controlling layer, center control and management layer and terminal monitoring layer and forms; Described terminal monitoring layer comprises an appearance rail presentation terminal, and this appearance rail presentation terminal connects with described center control and management layer by hub; This appearance rail presentation terminal shows the satellite orbit and the attitude data of control center's distribution with three dimensional form emulation; Described direct observing and controlling layer comprises interface box on observing and controlling front end rack and the star, connects signal cable by star ground between the two and connects, and observing and controlling front end rack connects alternately with the control center of center control and management layer; Interface box connects with wire-link telemetry terminal, spaceborne computer and each signal measurement apparatus by threeway socket or star ground serial ports on the described star.
2. test platform as claimed in claim 1 is characterized in that: described terminal monitoring layer comprises GPS terminal, Star Service terminal, appearance control terminal, communication terminal, power terminal and the thermal control terminal corresponding to six satellite subsystems; Described GPS terminal, Star Service terminal, appearance control terminal, communication terminal, power terminal and thermal control terminal connect with described center control and management layer by hub; The handled data difference of this six station terminal, but function is identical with software configuration.
3. test platform as claimed in claim 1, it is characterized in that: described center control and management layer comprises control center and database server, this center control and management layer connects alternately with direct observing and controlling layer, and control and management layer in center also connects with above-mentioned hub and terminal monitoring layer; To finish the straight survey and the wire-link telemetry of satellite are controlled, and finished the comparison of test data, automatically generated data library test record forms the system works journal function; Response terminal supervisory layers request simultaneously realizes the inquiry and the announcement of test data, and each terminal control command request is verified, transfers to direct observing and controlling layer and carries out, and final execution result is returned to each terminal.
4. test platform as claimed in claim 1 is characterized in that: described direct observing and controlling layer is to be designed to direct one deck that links to each other with satellite on network structure, and simultaneously, it is also as direct observing and controlling end on physical function.
5. test platform as claimed in claim 1 is characterized in that: star ground serial ports adopts the asynchronous 485 communication standard patterns of standard.
6. test platform as claimed in claim 1, it is characterized in that: described observing and controlling front end rack is made up of PXI data acquisition cabinet, signal condition cabinet, signal converting cabinet, equivalent load cabinet, power supply cabinet, the power supply cabinet is responsible for to PXI data acquisition cabinet, signal condition cabinet, signal converting cabinet, the power supply of equivalent load cabinet, connect alternately between described PXI data acquisition cabinet and the signal condition cabinet, connect alternately between signal condition cabinet and the signal converting cabinet, connect alternately between signal converting cabinet and equivalent load cabinet and the measurand.
7. test platform as claimed in claim 6, it is characterized in that: dispose the system controller, input and output, simulation output, high speed analog input, the RS-485 serial port board module that are coupled to each other in the described PXI data acquisition cabinet, system controller is installed Microsoft Windows 2000 operating systems, use the control program of adopting of the different tested objects of Measurement Studio software development, and set up local data base.
8. test platform as claimed in claim 6 is characterized in that: dispose analog signal conditioner module and digital signal conditioning module in the described signal condition cabinet, processing such as filtering, isolation amplification are carried out in in-site modeling or digital signal.
9. test platform as claimed in claim 6, it is characterized in that: dispose the interconnecting module and the handover module that the on-the-spot test Signal Separation are become the sets of signals of same type in the described signal converting cabinet switching between satellite and the equivalent load cabinet, interconnecting module becomes the on-the-spot test Signal Separation sets of signals of same type and the signal of unlike signal group is sent into corresponding signal condition module, and the circuit that handover module is finished simultaneously to satellite and equivalent load cabinet switches.
10. test platform as claimed in claim 6, it is characterized in that: described equivalent load cabinet comprises load equivalent device, signal simulator, integrated linear power supply and the interface that is connected with the interior surface power supply module of interconnecting module and power supply cabinet in the described signal converting cabinet, and wherein load equivalent is only done in the power supply equivalence.
11. want 1 described test platform as right, it is characterized in that: the measurand of described measurand layer comprises spaceborne computer, sun sensor, momenttum wheel, magnetic torquer, and described spaceborne computer, sun sensor, momenttum wheel, magnetic torquer are connected on the described star on the interface box by cable on the star.
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Assignee: Shanghai Guthrie Information Technology Co. Ltd. Assignor: Shanghai Engineering Center for Microsatellites Contract record no.: 2011310000239 Denomination of invention: Universal micro-satellite comprehensive testing platform based on PXI system Granted publication date: 20100707 License type: Exclusive License Open date: 20070620 Record date: 20111206 |
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