CN103592908B - A kind of aircraft integrated measurement system based on 1553B bus - Google Patents
A kind of aircraft integrated measurement system based on 1553B bus Download PDFInfo
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- CN103592908B CN103592908B CN201310485559.3A CN201310485559A CN103592908B CN 103592908 B CN103592908 B CN 103592908B CN 201310485559 A CN201310485559 A CN 201310485559A CN 103592908 B CN103592908 B CN 103592908B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
Based on an aircraft integrated measurement system for 1553B bus, comprise distribution modular converter, direct supply, DC power control device, AC power, AC power controller, Measurement &control computer, bus controller, test interface adapter, bus protocol modular converter, AD acquisition module, digital multimeter, testing control module, Signal-regulated kinase and data interpretation module.Relevant device in the present invention's abundant integrating traditional Aerospace vehicle test scheme, the general-utility test platform that height of formation is integrated, auxiliary with the software engineering of advanced person, realize the integration of Aerospace Vehicle Shooting Range Test, miniaturization, portability.
Description
Technical field
The present invention relates to a kind of aircraft integrated measurement system based on 1553B bus, be suitable for space flight/aviation aircraft dispatch from the factory before ground test time avionics system parameter characteristic checking.
Background technology
At present, before domestic air mail/aerospacecraft dispatches from the factory, in ground testing system, more employ traditional distributed measuring technology, for function and the performance test of different system inside.
Aviation/aerospacecraft distributed testing technology refers between different subsystem, such as belong to power supply under avionics system and sub power distribution system, navigational guidance and control subsystem, telemetry communication subsystem, data and health control subsystem have a set of independently ground checkout equipment, the function such as power supply, distribution, signal excitation, state parameter control, measurement of each system on complete independently aircraft separately.This test mode, at the initial stage of national defense industry development, according to the actual demand of ground testing system at that time, has certain advantage in the development of system and management aspect.Current, along with improving constantly aircraft avionics system test request, the defects such as distributed testing scheme is fought separately, testing apparatus function repeats, comprehensive utilization rate variance are more obvious, each subsystem test equipment development level is uneven, testing standard disunity, cause whole system poor compatibility, reliability is low, and the maintenance job of testing apparatus also needs the human and material resources of at substantial, cause many wasting of resources phenomenons.Secondly, each subsystem test on-the-spot due to equipment numerous, often cause that place inner cable layout is chaotic, staffing is not in place, test process and state indefinite, be very easy to cause tester's maloperation, the test number of occurrence is many, and mistake searches the outstanding problems such as difficulty.
Along with increasing of aircraft development task, a large amount of accumulation of designer's experience, simultaneously the greatly developing of network technology, constantly bringing forth new ideas of bus test technology, and the active demand to new-type measuring technology, traditional distributed ground measuring technology can not adapt to the test request of current aerospace/aerospacecraft.
Summary of the invention
Technology of the present invention is dealt with problems and is: the deficiency overcoming traditional distributed measuring technology, provides a kind of aircraft integrated measurement system based on 1553B bus, achieve aviation/aerospacecraft dispatch from the factory before test integration, miniaturization, portability.
Technical solution of the present invention is:
Based on an aircraft integrated measurement system for 1553B bus, comprising: distribution modular converter, direct supply, DC power control device, AC power, AC power controller, Measurement &control computer, bus controller, test interface adapter, bus protocol modular converter, AD acquisition module, digital multimeter, testing control module, Signal-regulated kinase and data interpretation module;
Externally fed passes through distribution modular converter to direct supply and ac power supply, DC power control device controls direct supply and provides direct current to test interface adapter, AC power controller controls AC power and provides alternating current to test interface adapter, Measurement &control computer sends test instruction to bus controller, bus controller converts described test instruction to 1553B bus data bag and is sent to testing control module by 1553B bus, testing control module generates corresponding test and excitation signal according to the test instruction in packet, and carry out bus protocol conversion by bus protocol modular converter, by test interface adapter, test and excitation signal is sent to aircraft again, control aircraft and carry out corresponding actions, the analog signals produced during aircraft maneuvers is sent to Signal-regulated kinase by test interface adapter and carries out signal condition, signal after conditioning is sent into AD acquisition module and is carried out analog to digital conversion, also send into digital multimeter simultaneously, the digital quantity signal of generation is sent in data interpretation module and is carried out data interpretation by AD acquisition module, send in Measurement &control computer by 1553B bus and bus controller successively again, measurement result is directly sent in Measurement &control computer by 1553B bus and bus controller by digital multimeter,
The data signal bus produced during aircraft maneuvers is sent to bus protocol modular converter by test interface adapter and carries out bus protocol conversion, then is sent in Measurement &control computer by 1553B bus and bus controller successively.
Data interpretation is specially: if conversion generate digital signal in preset range, then the digital signal that generates of conversion is sent in Measurement &control computer by 1553B bus and bus controller successively; If the digital signal that conversion generates exceeds preset range, then generate abnormal data cue, and the digital signal this abnormal data cue and described conversion generated is sent in Measurement &control computer by 1553B bus and bus controller in the lump.
Described digital multimeter comprises digital electronic ammeter and digital voltmeter, and for magnitude of voltage and the current value of test simulation amount signal, and precision is higher than six and half.
The present invention's beneficial effect is compared with prior art:
(1) the present invention can realize the Highgrade integration of ground testing system, Measurement &control computer is articulated on 1553B data bus as a BC terminal, the detecting information that direct acquisition aircraft passes up and down also sends different test instructions according to testing process, also can pass through the external various traditional testing apparatus of test interface adapter simultaneously, expand the test function of self.
(2) detecting information strictly controls according to 1553B bus protocol alternately, can prevent misoperation; Test judgement speed block, direct observation test result on the display screen that can carry at Measurement &control computer, test result can utilize and carry printer and directly print, or data is directly stored in the hard disk of Measurement &control computer self, completes one-stop ground test.
(3) the present invention can adopt test resource to share system, the quantity of effective minimizing testing apparatus, test site cable is made to obtain concentrating constraint, make test site orderliness clear, be convenient to management, also stopped reusing of testing apparatus simultaneously, reduced testing expense, decrease the number of operating personnel.
Accompanying drawing explanation
Fig. 1 is present system block diagram;
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is further described in detail.
As shown in Figure 1, the invention provides a kind of aircraft integrated measurement system based on 1553B bus, comprising: distribution modular converter, direct supply, DC power control device, AC power, AC power controller, Measurement &control computer, bus controller, test interface adapter, bus protocol modular converter, AD acquisition module, digital multimeter, testing control module, Signal-regulated kinase and data interpretation module;
Externally fed passes through distribution modular converter to direct supply and ac power supply, DC power control device controls direct supply and provides direct current to test interface adapter, AC power controller controls AC power and provides alternating current to test interface adapter, Measurement &control computer sends test instruction to bus controller, bus controller converts described test instruction to 1553B bus data bag and is sent to testing control module by 1553B bus, testing control module generates corresponding test and excitation signal according to the test instruction in packet, and carry out bus protocol conversion by bus protocol modular converter, by test interface adapter, test and excitation signal is sent to aircraft again, control aircraft and carry out corresponding actions, the analog signals produced during aircraft maneuvers is sent to Signal-regulated kinase by test interface adapter and carries out signal condition, signal after conditioning is sent into AD acquisition module and is carried out analog to digital conversion, also send into digital multimeter simultaneously, the digital quantity signal of generation is sent in data interpretation module and is carried out data interpretation by AD acquisition module, send in Measurement &control computer by 1553B bus and bus controller successively again, measurement result is directly sent in Measurement &control computer by 1553B bus and bus controller by digital multimeter,
Data interpretation is specially: if conversion generate digital signal in preset range, then the digital signal that generates of conversion is sent in Measurement &control computer by 1553B bus and bus controller successively; If the digital signal that conversion generates exceeds preset range, then generate abnormal data cue, and the digital signal this abnormal data cue and described conversion generated is sent in Measurement &control computer by 1553B bus and bus controller in the lump.Described digital multimeter comprises digital electronic ammeter and digital voltmeter, and for magnitude of voltage and the current value of test simulation amount signal, and precision is higher than six and half.
The data signal bus produced during aircraft maneuvers is sent to bus protocol modular converter by test interface adapter and carries out bus protocol conversion, then is sent in Measurement &control computer by 1553B bus and bus controller successively.
Distribution modular converter, direct supply, DC power control device, AC power, AC power controller unified cooperation powers to a kind of aircraft integrated measurement system based on 1553B bus, wherein, external power source is converted into the interchange required for system by distribution modular converter, DC quantity, and externally exported by direct supply and AC power, when the output voltage values of direct supply or AC power, when current value exceeds the normal range preset, DC power control device or AC power controller control to the output voltage values of direct supply or AC power or current value, increase or reduce corresponding magnitude of voltage, current value, realize integrated measurement system stable power-supplying.
The major function of Measurement &control computer is to aircraft sending controling instruction by 1553B bus, receive the response signal from aircraft simultaneously, the function of union display, storage, print data is a kind of based on opertaing device main in the aircraft integrated measurement system of 1553B bus.
Bus controller is realized by bus controller chip design ripe on market, its major function is that the steering order that Measurement &control computer sends is converted into 1553B data bus protocol form by computer bus data layout, and by the 1553B bus protocol data packet back that collects to Measurement &control computer, the data transmission things in 1553B bus is managed.
Test interface adapter provides the electric interfaces between aircraft and integrated measurement system, comprise the various data bus interfaces required for vehicle-borne equipment, such as CAN, RS422 bus, spi bus etc., also have key parameter to direct transfer back analog quantity, the switching value data of Measurement &control computer, unified test interface is the important foundation that integrated measurement system realizes smoothly.
Bus protocol modular converter is changed board design by bus protocol and is realized, bus protocol conversion board is by FPGA, all kinds of bus controller chip, manager chip, electrical level matching circuit hardware implementing, protocol conversion on 1553B bus and aircraft between other data buss is completed by writing hardware description language control FPGA, the data bus of each quasi-tradition is converted to the unified 1553B bus format used of integrated measurement system, the verification mode of 1553B bus is utilized to effectively raise the reliability of data transmission, and because the transfer rate of 1553B data bus is faster than CAN, RS422 bus and spi bus, effectively can improve the transfer rate of bus, promote the whole work efficiency of integrated measurement system.In addition 1553B bus can the simultaneously multiple peripheral hardware of carry, more efficient than traditional data bus point-to-point transmission mode, is conducive to the testing requirement of integrated measurement system miniaturization, portability.
AD acquisition module is responsible for gathering the analog data that aircraft is passed back, and is converted into the digital quantity signal that can be integrated test macro and identify.
The analog data (higher than six and half) that digital multimeter can high-precision collection aircraft be passed back, Measurement &control computer is mail to by after the high-precision analog amount data acquisition after collection, and show in real time on the display interface of Measurement &control computer, for the aircraft each several part duty in test process provides reference.
The standard signal that the operation transformation integralization test macros such as the analog signals passed back by test interface adapter amplification, filtering can be identified by Signal-regulated kinase by aircraft, the industrial signals such as the high pressure that aircraft is passed back, overcurrent, surge correctly can not be identified by system, have to pass through conditioning and remove.
Data interpretation module carries out result interpretation to the aircraft data collected, when collection magnitude of voltage, current value are in the interval range preset, then think that aircraft each system works of being correlated with is normal, and sentence read result is sent to Measurement &control computer, provide the normal information of result in Measurement &control computer display relevant position; If collection magnitude of voltage, current value exceed pre-set interval range, then judge that aircraft related system duty is abnormal, failure message is sent to Measurement &control computer, on Measurement &control computer, display corresponding position is by display report event information, and alert can carry out emergency power off.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. based on an aircraft integrated measurement system for 1553B bus, it is characterized in that comprising: distribution modular converter, direct supply, DC power control device, AC power, AC power controller, Measurement &control computer, bus controller, test interface adapter, bus protocol modular converter, AD acquisition module, digital multimeter, testing control module, Signal-regulated kinase and data interpretation module;
Externally fed passes through distribution modular converter to direct supply and ac power supply, DC power control device controls direct supply and provides direct current to test interface adapter, AC power controller controls AC power and provides alternating current to test interface adapter, Measurement &control computer sends test instruction to bus controller, bus controller converts described test instruction to 1553B bus data bag and is sent to testing control module by 1553B bus, testing control module generates corresponding test and excitation signal according to the test instruction in packet, and carry out bus protocol conversion by bus protocol modular converter, by test interface adapter, test and excitation signal is sent to aircraft again, control aircraft and carry out corresponding actions, the analog signals produced during aircraft maneuvers is sent to Signal-regulated kinase by test interface adapter and carries out signal condition, signal after conditioning is sent into AD acquisition module and is carried out analog to digital conversion, also send into digital multimeter simultaneously, the digital quantity signal of generation is sent in data interpretation module and is carried out data interpretation by AD acquisition module, send in Measurement &control computer by 1553B bus and bus controller successively again, measurement result is directly sent in Measurement &control computer by 1553B bus and bus controller by digital multimeter,
The data signal bus produced during aircraft maneuvers is sent to bus protocol modular converter by test interface adapter and carries out bus protocol conversion, then sends in Measurement &control computer by 1553B bus and bus controller successively;
Data interpretation is specially: if conversion generate digital signal in preset range, then the digital signal that generates of conversion is sent in Measurement &control computer by 1553B bus and bus controller successively; If the digital signal that conversion generates exceeds preset range, then generate abnormal data cue, and the digital signal this abnormal data cue and described conversion generated is sent in Measurement &control computer by 1553B bus and bus controller in the lump.
2. a kind of aircraft integrated measurement system based on 1553B bus according to claim 1, it is characterized in that: described digital multimeter comprises digital electronic ammeter and digital voltmeter, for magnitude of voltage and the current value of test simulation amount signal, and precision is higher than six and half.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998055988A1 (en) * | 1997-06-04 | 1998-12-10 | Mcdonnell Douglas Corp. | Universal electrical interface between an aircraft and an associated store providing an on-screen commands menu |
| US6298289B1 (en) * | 1999-04-24 | 2001-10-02 | The Boeing Company | Integrated spacecraft control system and method |
| CN1897404A (en) * | 2005-07-15 | 2007-01-17 | 中国科学院空间科学与应用研究中心 | Small distribution testing control system for satellite |
| CN101216701A (en) * | 2007-01-04 | 2008-07-09 | 北京航空航天大学 | 1553B bus based triplex hot-redundancy digital type actuator controller |
| CN201371945Y (en) * | 2008-12-29 | 2009-12-30 | 中国航天科技集团公司烽火机械厂 | Electric steering engine controller based on FPGA |
| CN101913427A (en) * | 2010-08-04 | 2010-12-15 | 北京航空航天大学 | Avionics system suitable for multi-purpose unmanned aircraft |
| CN102514736A (en) * | 2011-11-15 | 2012-06-27 | 上海卫星工程研究所 | Swing mechanism controller |
| CN202453698U (en) * | 2011-11-15 | 2012-09-26 | 北京宇航系统工程研究所 | Carrier rocket power measurement and control system |
| CN103092633A (en) * | 2011-10-31 | 2013-05-08 | 北京精密机电控制设备研究所 | Servo control software online burning method based on 1553B bus |
| CN103176482A (en) * | 2013-03-01 | 2013-06-26 | 上海卫星工程研究所 | Electric control heat screen controller for aircraft |
-
2013
- 2013-10-16 CN CN201310485559.3A patent/CN103592908B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998055988A1 (en) * | 1997-06-04 | 1998-12-10 | Mcdonnell Douglas Corp. | Universal electrical interface between an aircraft and an associated store providing an on-screen commands menu |
| US6298289B1 (en) * | 1999-04-24 | 2001-10-02 | The Boeing Company | Integrated spacecraft control system and method |
| CN1897404A (en) * | 2005-07-15 | 2007-01-17 | 中国科学院空间科学与应用研究中心 | Small distribution testing control system for satellite |
| CN101216701A (en) * | 2007-01-04 | 2008-07-09 | 北京航空航天大学 | 1553B bus based triplex hot-redundancy digital type actuator controller |
| CN201371945Y (en) * | 2008-12-29 | 2009-12-30 | 中国航天科技集团公司烽火机械厂 | Electric steering engine controller based on FPGA |
| CN101913427A (en) * | 2010-08-04 | 2010-12-15 | 北京航空航天大学 | Avionics system suitable for multi-purpose unmanned aircraft |
| CN103092633A (en) * | 2011-10-31 | 2013-05-08 | 北京精密机电控制设备研究所 | Servo control software online burning method based on 1553B bus |
| CN102514736A (en) * | 2011-11-15 | 2012-06-27 | 上海卫星工程研究所 | Swing mechanism controller |
| CN202453698U (en) * | 2011-11-15 | 2012-09-26 | 北京宇航系统工程研究所 | Carrier rocket power measurement and control system |
| CN103176482A (en) * | 2013-03-01 | 2013-06-26 | 上海卫星工程研究所 | Electric control heat screen controller for aircraft |
Non-Patent Citations (2)
| Title |
|---|
| "卫星通用自动化测试系统体系结构研究";赵瑞峰 等;《信息技术》;20111231(第4期);第65-68、72页 * |
| "基于1553B总线的某测试系统中远程测试模块设计";陈春艳 等;《计算机测量与控制》;20091231;第17卷(第05期);第841-842、846页 * |
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