CN102175899B - Automatic test safety control method of satellite interface - Google Patents
Automatic test safety control method of satellite interface Download PDFInfo
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- CN102175899B CN102175899B CN 201110005615 CN201110005615A CN102175899B CN 102175899 B CN102175899 B CN 102175899B CN 201110005615 CN201110005615 CN 201110005615 CN 201110005615 A CN201110005615 A CN 201110005615A CN 102175899 B CN102175899 B CN 102175899B
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Abstract
The invention relates to an automatic test safety control method of an satellite interface, comprising the steps of: (1) mounting a signal switching circuit between a satellite contact and a measuring port, namely a piece of measuring equipment, wherein the connection between the satellite contact and the measuring equipment is a passage, and two ends of each protective resistor are connected to a static measuring switch in parallel; (2) performing static interface measurement when the satellite is not electrified, switching on the static measuring switch in the step (1) and a bypass protection resistor; (3) before the satellite is electrified, switching off the static measuring switch, accessing the protection resistor, monitoring the state of each passage by FPGA (field programmable gate array), and realizing the exclusive logic with the FPGA, so as to avoid the switch error of the passages; and (4) electrifying the satellite, and performing the tests of other low-frequency interface signals on the satellite with the exception of the static interface measurement. The method provided by the invention enables the automatic test equipment to be work safely and reliably, and still can ensure that the safety of the single machine on the satellite is not influenced by the faults of the device under the condition that the automatic test equipment is faulted, so that the safety of the whole satellite low-frequency interface test is ensured.
Description
Technical field
The present invention relates to a kind of automatic test safety control method of satellite interface, belong to the satellite test field.
Background technology
The satellite low frequency interface contains polytype interfaces such as 100V bussed supply interface, secondary power supply power supply interface, instruction interface, telemetry interface, and has high pressure.If improper use causes the contact handoff error, and the safeguard measure imperfection, the interface that this should may do not linked together couple together, and light test result mistake is heavy damage unit on star.For avoiding the generation of above situation, guarantee improper use or send out wrong still can avoid in the switching command situation channel errors action, protection satellite test safety must be studied the control method that channel security switches.This patent is according to interface circuit principle on star and channel switching device principle, by analyzing on its star Primary Component characteristic in characteristics of signals and channel switching device, work out the state-detection for channel switching device, method and the steering logic that break-make is controlled, and realized this control method by software and hardware.This technology is the secret main points of the major technique of this patent.By using this technology, can effective monitoring passage switching state, avoid handoff error, unit on the protection star.
Summary of the invention
The technical matters that the present invention solves is: according to existing methodical deficiency, provide a kind of automatic test safety control method of satellite interface, the method can ensure the safety of whole star low frequency interface test.
Technical solution of the present invention is: a kind of automatic test safety control method of satellite interface, and step is as follows:
(1) be that signal switching circuit is installed between measuring equipment at star upper contact and measurement port, described signal switching circuit is: inner in testing apparatus, each star upper contact is divided into two paths, switch through two parallel connections, a protective resistance is installed before the positive and negative terminal that connects respectively measuring equipment, each switch; When carrying out between the star upper contact signal measurement, the closed measurement in star upper contact path and the plus end of measuring equipment, the switch that negative terminal is connected respectively, rest switch all disconnects; Being connected between star upper contact and measuring equipment is called a passage, each protective resistance two ends static measurement switch in parallel;
Carry out static interface when (2) satellite does not power up and measure, connect all the static measurement switches described in step (1), bypass protection resistance;
(3) before satellite powers up, disconnect the static measurement switch, access protective resistance, utilize the state of each passage in FPGA control panel monitoring step (1), use FPGA to realize the mutual exclusion logic, avoid the passage handoff error;
(4) satellite powers up, and removes the test that static interface is measured extraterrestrial upper other low frequency interface signal.
The resistance 10K Ω of described protective resistance ± 1K Ω.
The invention has the advantages that:
(1) the present invention utilizes protective resistance, state detection circuit, FPGA control panel and static measurement switch; realized the security control of test automatically of whole star satellite interface; make ATE (automatic test equipment) can safety, reliably working; and in the situation that ATE (automatic test equipment) fault; the fault that still can guarantee this device can not affect the safety of unit on star, thereby ensures the safety of whole star low frequency interface test.
(2) safe and reliable, even in the situation that the ATE (automatic test equipment) fault can guarantee that still the fault of this device can not affect the safety of unit on star, thereby ensure the safety that whole star low frequency interface is tested.
Description of drawings
Fig. 1 is the theory diagram of the inventive method;
Fig. 2 is state detection circuit schematic diagram of the present invention;
Fig. 3 is FPGA control panel initialization flowchart of the present invention;
Fig. 4 is that on star of the present invention, any two contact a, b measure passage connection flow process;
Fig. 5 is combined-voltage amplitude measurement process flow diagram of the present invention;
Fig. 6 be the present invention rise negative edge measurement procedure figure;
Fig. 7 is static impedance measurement procedure figure of the present invention.
Embodiment
Introduce in detail implementation procedure of the present invention below in conjunction with accompanying drawing, concrete steps are as follows:
(1) be that signal switching circuit is installed between measuring equipment at star upper contact and measurement port, described signal switching circuit is illustrated in figure 1 as: inner in testing apparatus, each star upper contact is divided into two paths, switch (being signal switched path switch) through two parallel connections, a protective resistance is installed before the positive and negative terminal that connects respectively measuring equipment, each switch; When carrying out between the star upper contact signal measurement, the closed measurement in star upper contact path and the plus end of measuring equipment, the switch that negative terminal is connected respectively, rest switch all disconnects; Being connected between star upper contact and measuring equipment is called a passage, each protective resistance two ends static measurement switch in parallel;
Carry out static interface when (2) satellite does not power up and measure, connect all the static measurement switches described in step (1), bypass protection resistance;
More because measuring passage, the static measurement switch can adopt the mode of short circuit plug to realize, plugs short circuit plug and can connect the static measurement switch, pulls up short circuit plug and can disconnect the static measurement switch.When static impedance between the star upper contact is surveyed in satellite outage, be the correctness of guaranteeing to test, need to connect the static measurement switch, bypass protection resistance makes the resistance value that records more accurate.Before after satellite powers up, must disconnect the static measurement switch.
The static impedance measurement procedure is as shown in Figure 7: under the satellite powering-off state, at first confirm that the static measurement switch connects, then connect the switch (this step is referring to Fig. 4) of corresponding measurement passage, start the resistance measurement function of measuring equipment (multimeter), and reading out data.
(3) before satellite powers up, disconnect the static measurement switch, access protective resistance, utilize the state of each passage in FPGA control panel monitoring step (1), use FPGA to realize the mutual exclusion logic, avoid the passage handoff error; Be connected by cable between FPGA control panel and signal switching circuit.
Before satellite powers up, must disconnect the static measurement switch, protective resistance is come into force.During the measurement interface voltage signal, because of the existence of protective resistance, even the passage handoff error does not return unit on the harm star yet, thereby contain that this fault spreads on star.And the input resistance of surveying instrument is large (generally greater than 1M Ω) enough, selects the protective resistance of certain resistance 10K Ω ± 1K Ω (generally selecting 10K Ω), both can guarantee the correctness measured can guarantee again the security of measuring.
The state detection circuit principle is: as shown in Figure 2, on star, signal all adopts the dpdt double-pole double-throw (DPDT) signal relay to connect, a path of signal relay (signal measurement path on star) is used for signal on the break-make star, and another path (state-detection path) is for detection of the on off operating mode of signal measurement path on star.When signal measurement path on star was closed, the state-detection path was also closed, and the IO port of FPGA measures+the 5V signal, thereby judges the path closure state.When signal measurement path on star disconnected, the state-detection path also disconnected, and the IO port of FPGA measures low level, thereby judges the path off-state.
Fig. 3 is the initialization flow process of FPGA, and in initialization procedure, FPGA sends instructions and disconnects all passages, and the sense channel state, as finding, the passage that does not disconnect is arranged, provide corresponding miscue, signal switching apparatus enters the fault disable mode, no longer accepts any instruction.
Fig. 4 is that on the monitoring star of FPGA, any two contact a, b measure passage and connect flow process, the FPGA control panel sends control signal, disconnect the signal switched path switch of measuring equipment positive and negative terminal, and sense channel state, detect as FPGA and still have the passage that is connected to the equipment positive and negative terminal, provide corresponding miscue and enter error handler.Detecting as FPGA the passage that is connected to the equipment positive and negative terminal all disconnects, send instructions and connect corresponding measurement channel switch, and the channel switch state is measured in detection, as the rear corresponding measurement channel switch that sends instructions does not move, provide corresponding miscue, signal switching circuit enters the fault disable mode, no longer accepts any instruction.
(4) satellite powers up, and removes the test that static interface is measured extraterrestrial upper other low frequency interface signal.
Low frequency interface signal on star comprised combined-voltage amplitude, rising the aspects of contents such as negative edge, static impedance, dissimilar signal must adopt different measure setups and method.
Combined-voltage amplitude measurement flow process is as shown in Figure 5: at first after disconnecting the static measurement switch under the satellite powering-off state and confirming, satellite powers up, then connect the switch (this step is referring to Fig. 4) of corresponding measurement passage, start the voltage measurement function of measuring equipment (multimeter), and reading out data.
Rising the negative edge measurement procedure as shown in Figure 6: at first after disconnecting the static measurement switch under the satellite powering-off state and confirming, satellite powers up, the triggering level of setting measurement equipment (oscillograph), control oscillograph and enter the triggering waiting status, then connect the switch (this step is referring to Fig. 4) of corresponding measurement passage, rising after negative edge arrives, trigger to carry out and measure, and reading out data.
The content that is not described in detail in instructions of the present invention belongs to those skilled in the art's known technology.
Claims (2)
1. automatic test safety control method of satellite interface is characterized in that step is as follows:
(1) be that signal switching circuit is installed between measuring equipment at star upper contact and measurement port, described signal switching circuit is: inner in testing apparatus, each star upper contact is divided into two paths, switch through two parallel connections, a protective resistance is installed before the positive and negative terminal that connects respectively measuring equipment, each switch; When carrying out between the star upper contact signal measurement, the closed measurement in star upper contact path and the plus end of measuring equipment, the switch that negative terminal is connected respectively, rest switch all disconnects; Being connected between star upper contact and measuring equipment is called a passage, each protective resistance two ends static measurement switch in parallel;
Carry out static interface when (2) satellite does not power up and measure, connect all the static measurement switches described in step (1), bypass protection resistance;
(3) before satellite powers up, disconnect the static measurement switch, access protective resistance, utilize the state of each passage in FPGA control panel monitoring step (1), use FPGA to realize the mutual exclusion logic, avoid the passage handoff error; The described state step of each passage in FPGA control panel monitoring step (1) of utilizing is as follows:
The FPGA control panel sends control signal, disconnect the signal switched path switch of measuring equipment positive and negative terminal, and the sense channel state, detect as FPGA and still have the passage that is connected to the equipment positive and negative terminal, provide corresponding miscue and enter the fault disable mode, no longer accept any instruction; Detecting as FPGA the passage that is connected to the equipment positive and negative terminal all disconnects, send instructions and connect corresponding measurement channel switch, and the channel switch state is measured in detection, as the rear corresponding measurement channel switch that sends instructions does not move, provide corresponding miscue, signal switching circuit enters the fault disable mode, no longer accepts any instruction;
(4) satellite powers up, and removes the test that static interface is measured extraterrestrial upper other low frequency interface signal.
2. a kind of automatic test safety control method of satellite interface according to claim 1, is characterized in that: the resistance 10K Ω of described protective resistance ± 1K Ω.
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| CN104569697B (en) * | 2015-01-30 | 2017-07-28 | 航天东方红卫星有限公司 | A kind of power supply interface detection method for moonlet integration test |
| CN110247696B (en) * | 2019-05-27 | 2021-11-16 | 中国空间技术研究院 | Communication satellite remote control instruction interface detection circuit and method |
| CN110568307A (en) * | 2019-09-12 | 2019-12-13 | 中国科学院微小卫星创新研究院 | Automatic testing device and method for satellite single-machine interface |
| CN111487443B (en) * | 2020-04-30 | 2021-08-13 | 电子科技大学 | Measuring instrument channel expansion, physical isolation and automatic electrostatic protection system |
| CN113933566B (en) * | 2020-12-31 | 2024-01-26 | 中国科学院微小卫星创新研究院 | Program controlled junction box |
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| CN2833714Y (en) * | 2005-10-19 | 2006-11-01 | 甘肃省计量研究院 | Multi-path programmed switch |
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| JP2010112764A (en) * | 2008-11-04 | 2010-05-20 | Toyota Boshoku Corp | Device for conducting experiment on application of overcurrent to electric wire |
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| CN2833714Y (en) * | 2005-10-19 | 2006-11-01 | 甘肃省计量研究院 | Multi-path programmed switch |
| CN201177662Y (en) * | 2008-03-14 | 2009-01-07 | 安徽省电力公司六安供电公司 | Remote on-line detection system for electric energy metering error |
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