CN101799505A - Electric simulator of gyro - Google Patents
Electric simulator of gyro Download PDFInfo
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- CN101799505A CN101799505A CN 201010152801 CN201010152801A CN101799505A CN 101799505 A CN101799505 A CN 101799505A CN 201010152801 CN201010152801 CN 201010152801 CN 201010152801 A CN201010152801 A CN 201010152801A CN 101799505 A CN101799505 A CN 101799505A
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Abstract
The invention provides an electric simulator of a gyro, and relates to an electric simulator of a satellite facility, which aims at solving the problem that an electric simulator of a gyro and the gyro can not be simultaneously connected to a satellite test system in an existing facility or device. The electric simulator comprises a functional simulation module, a simulator data interface circuit, a power supply input interface circuit, a data driven interface circuit, a signal processing module, a satellite facility data interface circuit and a power supply output interface circuit, wherein simulation sensitive data signals output by the functional simulation module and gyro signals output by the satellite facility data interface circuit are isolated and synthesized in the signal processing module, the processed signal output end of the signal processing module is connected with the processed signal input end of the simulator data interface circuit, and the voltage output end of the power supply input interface circuit is connected with the voltage input end of the power supply output interface circuit. The invention realizes that the electric simulator of a gyro and the gyro can be simultaneously connected to a satellite test system, and is used for the satellite attitude control system or the whole-satellite test.
Description
Technical field
The present invention relates to a kind of electric simulator of on-board equipment.
Background technology
The electrical property test of satellite process comprises unit test, subsystem test and the test of whole star, in subsystem test and whole star test process or some stage of test process, need some auxiliary equipment or devices, be used for on-board equipment that is virtually reality like reality to reach the purpose of subsystem or whole star electric performance test, the utility appliance or the device of these simulation real equipment are called electric simulator.Electric simulator is mainly simulated the structure of true on-board equipment electrical interface, processing, data stream and the temporal characteristics etc. of communication protocol.
The electrical interface of the electric simulator of on-board equipment is in full accord with the electrical interface of the on-board equipment that simulated, in order to correctness, matching and the rationality of check on-board equipment external interface.Electric simulator and corresponding on-board equipment are monopolized the electrical interface on the star in test process, and promptly electric simulator and corresponding on-board equipment can not be linked in the satellite test system simultaneously, can only select one to be connected into the satellite test system.Can realize auxiliary detection by electric simulator on-board equipment, as electrical interface detection, protocol detection, data stream detection, sequential detection etc., but electric simulator can't be simulated the status information of on-board equipment: such as power supply state, temperature, current/voltage remote measurement.
In satellite attitude control system, gyro is the most frequently used on-board equipment.In the test process, gyro and gyro electric simulator can only select one to be connected into test macro, can't satisfy gyro data stream and the simultaneously-measured requirement of gyro work state information under ground environment.At present, the electric simulator and the gyro of gyro can't be connected into the satellite test system simultaneously in existing equipment or the device.
Summary of the invention
The objective of the invention is to solve in existing equipment or the device and can't satisfy the electric simulator of gyro and the problem that gyro is connected into the satellite test system simultaneously, a kind of electric simulator of gyro is provided.
The present invention is achieved by following proposal: a kind of electric simulator of gyro, it comprises the functional simulation module, the simulator data interface circuit, power supply input interface circuit and data-driven interface circuit, the driving data output terminal of data-driven interface circuit links to each other with the driving data input end of functional simulation module, the control signal output ends of simulator data interface circuit links to each other with the signal input end of functional simulation module, the voltage output end of power supply input interface circuit links to each other with the voltage input end of functional simulation module, it also comprises signal processing module, on-board equipment data interface circuit and power supply output interface circuit, the control signal output ends of simulator data interface circuit links to each other with the signal input end of on-board equipment data interface circuit, the simulation sensitive data signal output part of functional simulation module links to each other with the first processing signals input end of signal processing module, the gyro signal output terminal of on-board equipment data interface circuit links to each other with the second processing signals input end of signal processing module, the processing signals output terminal of signal processing module links to each other with the processing signals input end of simulator data-interface, and the voltage output end of power supply input interface circuit links to each other with the voltage input end of signal processing module and the voltage input end of power supply output interface circuit respectively.
The invention provides a kind of electric simulator of gyro, compare it with traditional gyro electric simulator and increased signal processing module, on-board equipment data interface circuit and power supply output interface circuit, the described electric simulator power supply signal that input interface circuit introduces of will powering is powered for the electric simulator internal circuit, and simultaneously this power supply signal being exported to the power supply output interface circuit is the gyro power supply; The simulator data interface circuit receives from the order of the spaceborne computer input as electric simulator, simultaneously this input signal is sent to gyro by the on-board equipment data interface circuit; Electric simulator receives the gyro signal of gyro by the on-board equipment data interface circuit, and carries out Signal Spacing with simulation sensitive data signal that the functional simulation module generates in signal processing module and data are synthetic handles; Data after the processing send to spaceborne computer by the simulator data interface circuit, realize that electric simulator and gyro are connected into the satellite test system simultaneously.
The electric simulator structural design of a kind of gyro of the present invention is simple, can realize that the electric simulator of gyro and gyro are connected into the satellite test system simultaneously, satisfies on-board equipment time of day and closed-loop simulation and carries out simultaneously, simplifies the satellite system test.
Description of drawings
Fig. 1 is the structural representation of a kind of gyro electric simulator described in the embodiment one; Fig. 2 is the structural representation of embodiment five.
Embodiment
Embodiment one: specify present embodiment below in conjunction with Fig. 1.A kind of electric simulator of gyro, it comprises functional simulation module 1, simulator data interface circuit 2, power supply input interface circuit 5 and data-driven interface circuit 7, the driving data output terminal of data-driven interface circuit 7 links to each other with the driving data input end of functional simulation module 1, the control signal output ends of simulator data interface circuit 2 links to each other with the signal input end of functional simulation module 1, the voltage output end of power supply input interface circuit 5 links to each other with the voltage input end of functional simulation module 1, it also comprises signal processing module 3, on-board equipment data interface circuit 4 and power supply output interface circuit 6, the control signal output ends of simulator data interface circuit 2 links to each other with the signal input end of on-board equipment data interface circuit 4, the simulation sensitive data signal output part of functional simulation module 1 links to each other with the first processing signals input end of signal processing module 3, the gyro signal output terminal of on-board equipment data interface circuit 4 links to each other with the second processing signals input end of signal processing module 3, the processing signals output terminal of signal processing module 3 links to each other with the processing signals input end of simulator data-interface 2, and the voltage output end of power supply input interface circuit 5 links to each other with the voltage input end of signal processing module 3 and the voltage input end of power supply output interface circuit 6 respectively.
The electric simulator of a kind of gyro described in the present embodiment is powered by power supply, the voltage output end of power supply links to each other with the voltage input end of power supply input interface circuit 5, power supply input interface circuit 5 is the electric simulator power supply, and the output interface circuit 6 that passes through to power is the gyro power supply, wherein, the interface type of power supply input interface circuit 5 is consistent with the interface type of power supply output interface circuit 6, and the power supply described in the present embodiment adopts accumulator to realize;
The electric simulator of a kind of gyro described in the present embodiment is controlled by spaceborne computer, the instruction output end of spaceborne computer links to each other with the instruction input end of simulator data interface circuit 2, and the test data output terminal of simulator data interface circuit 2 links to each other with the test data input end of spaceborne computer.Spaceborne computer sends to the gyro electric simulator by simulator data interface circuit 2 with instruction, and by on-board equipment data interface circuit 4 this instruction is transmitted to gyro;
Data-driven interface circuit 7 in the electric simulator of a kind of gyro described in the present embodiment links to each other with the driving data input end of functional simulation module 1 according to kinetic model output data drive signal;
Functional simulation module 1 in the electric simulator of a kind of gyro described in the present embodiment is the circuit and the handling procedure of simulator simulation on-board equipment communication protocol, data stream, sequential etc., is similar to the electric simulator of traditional sense;
The electric simulator of a kind of gyro described in the present embodiment links to each other with gyro by on-board equipment data interface circuit 4, be used to transmit the instruction that simulator receives, the status data that receives gyro, the described electric simulator of present embodiment can be connected into the electric simulator and the gyro of traditional sense in the satellite test system simultaneously;
The electric simulator of a kind of gyro described in the present embodiment, when gyro and electric simulator are linked into the satellite test system simultaneously, signal processing module 3 is circuit and the programs that are used for gyro is carried out Signal Spacing and data processing, send to spaceborne computer after can be with the status data of the data of electric simulator and gyro synthetic, the time of day and the closed-loop simulation that satisfy gyro carry out simultaneously.
The invention provides a kind of electric simulator of gyro, it has increased signal processing module 3, on-board equipment data interface circuit 4 and power supply output interface circuit 6 on the basis of traditional gyro electric simulator, the described electric simulator power supply signal that input interface circuit 5 introduces of will powering is powered for the electric simulator internal circuit, simultaneously this power supply signal is exported to power supply output interface circuit 6 and powers for gyro; Simulator data interface circuit 2 receives from the order of the spaceborne computer input as electric simulator, simultaneously this input signal is sent to gyro by on-board equipment data interface circuit 4; Electric simulator receives the gyro signal of gyros by on-board equipment data interface circuit 4, and carries out Signal Spacing with simulation sensitive data signal that functional simulation module 1 generates in signal processing module 3 and data are synthetic handles; Data after the processing send to spaceborne computer by simulator data interface circuit 2, realize that electric simulator and gyro are connected into the satellite test system simultaneously.
The electric simulator structural design of a kind of gyro of the present invention is simple, can realize that the electric simulator of gyro and gyro are connected in the satellite test system simultaneously, and the time of day and the closed-loop simulation that satisfy on-board equipment carry out simultaneously, simplifies the satellite system test.
Embodiment two: the difference of the electric simulator of present embodiment and embodiment one described a kind of gyro is that described simulation sensitive data by 1 output of functional simulation module is meant the angular velocity data of satellite gyro output when space motion of electric simulator analog configuration gyro.
Embodiment three: the difference of the electric simulator of present embodiment and embodiment one described a kind of gyro is, described gyro signal by 4 outputs of on-board equipment data interface circuit is meant that gyro is linked into the signal data that obtains in the test macro, by satellite sensitive data, satellitosis data and verification with form, described satellitosis data are meant temperature information data, power supply information data and command reception status data.
One frame of the gyro signal described in the present embodiment is made up of four bytes, and wherein, first byte and second byte are deposited the satellite sensitive data, and the space motion state that is in that gyro is inreal is so the satellite sensitive data is invalid; The 3rd byte is deposited the satellitosis data, nybble deposit verification and, verification and be used for one group of data item of verification with because the satellite sensitive data is invalid, so verification and also be invalid.
Embodiment four: the difference of the electric simulator of present embodiment and embodiment one described a kind of gyro is that the processor of described signal processing module 3 is FPGA, DSP or single-chip microcomputer.
Embodiment five: specify present embodiment below in conjunction with Fig. 2.The difference of the electric simulator of present embodiment and embodiment one or four described a kind of gyros is, described signal processing module 3 is isolated conversion with the gyro signal that the second processing signals input end receives, and synthesize processing from the simulation sensitive data that the first processing signals input end receives with signal processing module 3
Described isolation conversion is meant that the gyro signal with 4 outputs of on-board equipment data interface circuit carries out the photoelectricity isolation by the photoelectricity coupled circuit 3-1 in the signal processing module 3,
Described synthetic processing is meant the satellitosis data of extracting a byte from the gyro signal after the isolation, and the simulation sensitive data of two bytes that receive from the first processing signals input end with signal processing module 3 merges, add the verification of a byte again and be combined into the complete data of a frame, one frame is made up of four bytes, wherein, first byte, second byte are deposited the simulation sensitive data, and the 3rd byte is deposited the satellitosis data, nybble deposit verification and.
After receiving the instruction of spaceborne computer, functional simulation module 1 generates the simulation sensitive data, gyro generates gyro signal, the gyro signal of on-board equipment data interface circuit 4 outputs is carried out the photoelectricity isolation by the photoelectricity coupled circuit 3-1 in the signal processing module 3, signal after the isolation is consistent with original signal, but does not link to each other on electric.
The frame data that signal processing module 3 described in the present embodiment will be finished after synthesizing send to spaceborne computer by simulator data interface circuit 2.
Claims (5)
1. the electric simulator of a gyro, it comprises functional simulation module (1), simulator data interface circuit (2), power supply input interface circuit (5) and data-driven interface circuit (7), the driving data output terminal of data-driven interface circuit (7) links to each other with the driving data input end of functional simulation module (1), the control signal output ends of simulator data interface circuit (2) links to each other with the signal input end of functional simulation module (1), the voltage output end of power supply input interface circuit (5) links to each other with the voltage input end of functional simulation module (1), it is characterized in that: further comprising signal processing module (3), on-board equipment data interface circuit (4) and power supply output interface circuit (6), the control signal output ends of simulator data interface circuit (2) links to each other with the signal input end of on-board equipment data interface circuit (4), the simulation sensitive data signal output part of functional simulation module (1) links to each other with the first processing signals input end of signal processing module (3), the gyro signal output terminal of on-board equipment data interface circuit (4) links to each other with the second processing signals input end of signal processing module (3), the processing signals output terminal of signal processing module (3) links to each other with the processing signals input end of simulator data-interface (2), and the voltage output end of power supply input interface circuit (5) links to each other with the voltage input end of signal processing module (3) and the voltage input end of power supply output interface circuit (6) respectively.
2. the electric simulator of a kind of gyro according to claim 1 is characterized in that: described simulation sensitive data by functional simulation module (1) output is meant the angular velocity data of satellite gyro output when space motion of electric simulator analog configuration gyro.
3. the electric simulator of a kind of gyro according to claim 1, it is characterized in that: described gyro signal by on-board equipment data interface circuit (4) output is meant that gyro is linked into the signal data that obtains in the test macro, by gyro sensitive data, gyro status data and verification with form, described gyro status data is meant temperature information data, power supply state data and command reception status data.
4. the electric simulator of a kind of gyro according to claim 1, it is characterized in that: the processor of described signal processing module (3) is FPGA, DSP or single-chip microcomputer.
5. according to the electric simulator of claim 1 or 4 described a kind of gyros, it is characterized in that: described signal processing module (3) is isolated conversion with the gyro signal that the second processing signals input end receives, and synthesize processing from the simulation sensitive data that the first processing signals input end receives with signal processing module (3)
Described isolation conversion is meant that the gyro signal with on-board equipment data interface circuit (4) output carries out the photoelectricity isolation by the photoelectricity coupled circuit (3-1) in the signal processing module (3),
Described synthetic processing is meant the satellitosis data of extracting a byte from the gyro signal after the isolation, and the simulation sensitive data of two bytes that receive from the first processing signals input end with signal processing module (3) merges, add the verification of a byte again and be combined into the complete data of a frame, one frame is made up of four bytes, wherein, first byte, second byte are deposited the simulation sensitive data, and the 3rd byte is deposited the gyro status data, nybble deposit verification and.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101528011A CN101799505B (en) | 2010-04-22 | 2010-04-22 | Electric simulator of gyro |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010101528011A CN101799505B (en) | 2010-04-22 | 2010-04-22 | Electric simulator of gyro |
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| CN101799505A true CN101799505A (en) | 2010-08-11 |
| CN101799505B CN101799505B (en) | 2011-10-19 |
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| CN2010101528011A Expired - Fee Related CN101799505B (en) | 2010-04-22 | 2010-04-22 | Electric simulator of gyro |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101937031A (en) * | 2010-07-01 | 2011-01-05 | 哈尔滨工业大学 | Electric simulator for star sensor |
| CN102540908A (en) * | 2012-02-20 | 2012-07-04 | 哈尔滨工业大学 | General simulator for satellite attitude and track control subsystem closed-loop tests and method for general simulator |
| CN104457784A (en) * | 2013-09-16 | 2015-03-25 | 刘危 | Simulator capable of simulating function and fault of TC-9A vertical gyro |
| CN106895832A (en) * | 2017-02-20 | 2017-06-27 | 上海航天控制技术研究所 | A kind of angular velocity signal analogy method of Gyro |
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| US4646255A (en) * | 1983-05-02 | 1987-02-24 | The Boeing Company | Gyro simulator |
| CN2179981Y (en) * | 1992-09-30 | 1994-10-19 | 上海市电子物理研究所 | Digital gyrosimulator |
| US20070050139A1 (en) * | 2005-04-27 | 2007-03-01 | Sidman Adam D | Handheld platform stabilization system employing distributed rotation sensors |
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2010
- 2010-04-22 CN CN2010101528011A patent/CN101799505B/en not_active Expired - Fee Related
Patent Citations (3)
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| US4646255A (en) * | 1983-05-02 | 1987-02-24 | The Boeing Company | Gyro simulator |
| CN2179981Y (en) * | 1992-09-30 | 1994-10-19 | 上海市电子物理研究所 | Digital gyrosimulator |
| US20070050139A1 (en) * | 2005-04-27 | 2007-03-01 | Sidman Adam D | Handheld platform stabilization system employing distributed rotation sensors |
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| 《仪器仪表学报》 20090630 赵光权等 "小卫星通用模拟器设计" 357-360 1-5 第30卷, 第6期 2 * |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101937031A (en) * | 2010-07-01 | 2011-01-05 | 哈尔滨工业大学 | Electric simulator for star sensor |
| CN101937031B (en) * | 2010-07-01 | 2012-07-04 | 哈尔滨工业大学 | Electric simulator for star sensor |
| CN102540908A (en) * | 2012-02-20 | 2012-07-04 | 哈尔滨工业大学 | General simulator for satellite attitude and track control subsystem closed-loop tests and method for general simulator |
| CN102540908B (en) * | 2012-02-20 | 2014-10-15 | 哈尔滨工业大学 | General simulator for satellite attitude and track control subsystem closed-loop tests and method for general simulator |
| CN104457784A (en) * | 2013-09-16 | 2015-03-25 | 刘危 | Simulator capable of simulating function and fault of TC-9A vertical gyro |
| CN106895832A (en) * | 2017-02-20 | 2017-06-27 | 上海航天控制技术研究所 | A kind of angular velocity signal analogy method of Gyro |
| CN106895832B (en) * | 2017-02-20 | 2019-05-31 | 上海航天控制技术研究所 | A kind of angular velocity signal analogy method of Gyro |
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| CN101799505B (en) | 2011-10-19 |
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