CN1393682A - Real-time flight simulation monitor system - Google Patents
Real-time flight simulation monitor system Download PDFInfo
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- CN1393682A CN1393682A CN 01119845 CN01119845A CN1393682A CN 1393682 A CN1393682 A CN 1393682A CN 01119845 CN01119845 CN 01119845 CN 01119845 A CN01119845 A CN 01119845A CN 1393682 A CN1393682 A CN 1393682A
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Abstract
A real-time simulation-monitor system for airplane is disclosed. The flight parameters of an airplane is transmitted via communication controller, data transmission radio station and antenna to a ground station directly or through a nevigation satellite. The preprocessor and main controller can transmit them to multiple terminals for simulatively displaying the flight state, and position of air plane on a digital map, and the states of flight path, rudder and landing chassis are received and displayed with real-time parameters. The signals and related parameters can also be transmitted back to airplane.
Description
The present invention relates to a kind of supervisory system that is used for the flight parameter of aircraft and satellite navigation information real-time Transmission, emulation.
General flight parameter and the information of aircraft in flight course, all be transferred to " aircraft black box " as pilot and ground control person's dialogue, the duty of each system of aircraft etc., getting in touch of aircraft and ground mainly is to lean on pilot and ground control's dialogue to carry out.The flight attitude of aircraft, highly, data such as position are to be obtained by the supervision of ground radar to aerospace plane.When special feelings take place aloft in aircraft, mainly be to carry out vacant lot by the pilot by the radio station to link up, dispose during for the urgency of the flight safety of aircraft, in-flight failure and the monitoring of flight quality, assisting in flying commander etc. all exist a lot of inconvenience, be difficult to satisfy fault analysis and the aloft effective commander reach in-flight after the landing, the position of especially many airplanes, attitude information can not show intuitively, for implementing the flight control scheduling exactly certain difficulty are arranged.United States Patent (USP) 5,9743,94 disclose a kind of " long-range aircraft, long-haul aircraft global monitoring system " " Remote, aircraft, global, paperless maintenance system ", it be by the aircraft sensor with the position of aircraft, highly, data such as speed, chain of command adjustment, engine speed, temperature, stress and fuel are sent to the ground control centre with sound and vision signal, these information of monitor log are also analyzed, and monitor the operational circumstances of aircraft in real time; In addition, also Positioning System (GPS) or GPS (Global Position System) are sent to ground command center and traffic control center to these signals via satellite.The parameters of this system all is to be obtained by various sensors, and vision signal is to be caught by video camera, this equipment more complicated, the interior space of machine that takies aircraft is more, on baby plane, be difficult to realize, and this system can not understand the skyborne attitude of aircraft intuitively, visually.
The purpose of this invention is to provide a kind of real-time flight simulation monitor system that can adapt to the aircraft useful space.
Technical solution of the present invention is, with the flight parameter of aircraft by the communication controller on the aircraft, data radio station, the radio station antenna is real-time transmitted to land station, or be sent on the GPS navigation satellite and re-send to land station, after the receiving antenna of land station receives this signal, pass through pretreater, main control computer demonstrates the attitude of aircraft flight with being defeated by a plurality of terminating machine real-time simulations, the position, terminating machine is respectively with numerical map, the form of real-time parameter shows flight track, the emulation cockpit instrument, the variation of the variation of aspect and each rudder face of aircraft and the folding and unfolding of undercarriage upload to signal on the airborne equipment at any time.With the method for visual angle conversion world coordinate system is converted to view coordinate and is converted to screen coordinate system again.
The present invention has functions such as assisting in flying commander, flight quality monitoring, auxiliary special feelings disposal and aircraft accident evidence obtaining, the attitude information of aircraft can be provided in the administrative area exactly, demonstration synchronously can reach 30 airplanes at most, and with visual in image forms such as real-time flight simulation, parameter demonstration, numerical maps, the important parameter that shows cockpit instrument indication, aspect and each main system of any airplane, the state and the position that help the commander in time to grasp aircraft are implemented the flight control scheduling exactly; Show that in ground synchronous aircraft skids off the cut-off flight attitude of overall process of landing from driving, for aircraft controller, control tower engineering person on duty, commander's staff officer monitoring aircraft navigates.
Native system can utilize touch video screen to watch the flight situation of aerial any airplane at any time, grasp the aircraft present position, according to circumstances pilot's flare maneuver is implemented to instruct, monitoring aircraft and engine dynamic technique performance, and with these information storages in computing machine, be convenient to carry out technical Analysis afterwards; The relevant personnel on duty of control tower utilizes this system can monitor the working condition of aircraft and engine in real time, to the abnormal conditions of aerial appearance, system can judge automatically, and circular ground also proposes caution, the commander can be according to special feelings Disposal Measures, the aerial special feelings of the correct disposal of guidance and help pilot; This system can be with the main information storage of any " accident " aircraft flight overall process in the computing machine of land station of system, have and " black box " similar function, in case generation aircraft accident, even " black box " lost efficacy, also can reappear flying quality, help to analyze and search culprit by land station.
Fig. 1 is a system principle diagram of the present invention;
Fig. 2 is an airborne portion block scheme of the present invention;
Fig. 3 is an above ground portion block scheme of the present invention;
Fig. 4 is a main control computer menu block diagram of the present invention;
Fig. 5 is time slot allocation figure of the present invention;
Fig. 6 is that multifrequency point of the present invention receives land station's block diagram;
Fig. 7 is a communication controller block diagram of the present invention.
System of the present invention is made up of airborne equipment and uphole equipment two parts.Airborne equipment receives the gps satellite navigation signal and gathers the every flight parameter of aircraft, then, by data radio station these information are sent to terrestrial receiving antenna, then pass device and pass to the data processing display system, show the indication of aloft aspect, cockpit instrument etc. with animated image true to nature through ground number biography device by the difference number.
Antenna 1 imports the gps satellite navigation signal that receives into satellite navigation receiver 2 among Fig. 1, the signal that flies ginseng information 3 and satellite navigation receiver 2 imports pre-service control device 4 into, then, pass device 5 through airborne number and send to difference number biography device 7, pass device 6 to data processing display system 8 through the ground number.
The main composition of airborne equipment is among Fig. 2, data radio station 12, communication controller 10, power pack 11, the radio station antenna, frequency selector 13 etc., communication controller 10 is nucleus equipments, communication between its overall coordination each several part, and with GPS information or fly after ginseng information 9 does pre-service, control data radio station 12 transmission information in its channel time slot, be transferred to frequency selector 13 simultaneously, frequency selector 13 is imported data radio station 12 with the change signal feedback of data radio station 12 channels again to communication controller 10, power pack 11 provides the power supply of whole airborne equipments, frequency selector 13 provides the change function of data radio station 12 channels, communication controller 10 is with the GPS locating information, after flight parameter information 9 is carried out pre-service, send ground control tower or command post with the time division multiple access (TDMA) form back to by data radio station, the wireless transmission rate of data radio station 12 is 9600bps, transmitting-receiving switching time is 16ms, and the data that 36 bytes are transmitted in the radio station need the 38ms time approximately.
The uphole equipment of Fig. 3 mainly comprises ground-plane antenna 14, receives radio station 15, land station's pretreater 16, LAN equipment (comprising hub, network interface card, netting twine etc.), main control computer 17, terminating machine 18, ground power supply 19 and ground check device etc.Its monitoring capacity is 30 airplanes, it is 36 bytes (comprising basic navigation information and aircraft state sign indicating number) that single airplane transmits the essential information amount, operating distance is not less than 350km for height when 10000m, bearing accuracy is not more than 10m, message transmission rate is 9600bps, and data updating rate is 0.5 time/second.The uphole equipment of system with the GPS locating information, fly after ginseng information handles with pretreatment unit on the machine 4, send into main control computer 17, main control computer 17 shows real time position, the flight parameter of aircraft on the one hand with the two dimensional surface map, on the other hand data are sent to each terminating machine 18 by network, terminating machine 18 shows flight track, position etc. with the form of numerical map, real-time parameter respectively, the variation of emulation cockpit instrument and aspect realistically simultaneously, in addition, according to real flight conditions, can go up teletype command at any time, the transmission of control data or change order of transmission.
If will reach the assisting in flying commander, flight quality monitoring, aerial special feelings disposal and aircraft accident evidence obtaining etc. can be real-time in land station, show to emulation, by main control computer 17 many station terminals of control machines 18, the master menu of main control computer 17 as shown in Figure 4, according to different needs, click contents of menus and realize data maintenance, Communication Control, network management and partial display function, also can show the position of aircraft on map simultaneously, this map adopts the flying area plane map, the major parameter that shows each aircraft, the aspect of simplifying, analog capsule cabin, flight formation and demonstration civil aviaton passage, distance circle, terminating machine are then realized respectively numerical map, parameter shows, the demonstration of aspect and analog capsule cabin.
The numerical map module is made according to the relevant requirements of air traffic control, the stack that can realize the landform mark with hide, stepless zooming etc.; The parameter display module requires receiving the data demonstration of classifying; The aspect module is background with the flying area, make true three-dimension ground scape model, three-dimensional model aircraft, realize showing in real time undercarriage control, the situation that yaw rudder changes, flaperon changes, flap changes, spout changes, screen-picture shows the main attitude angle and the planimetric position of aircraft in 50～200km scope of aircraft in real time, the amplification of switching seven kinds of visual angles and current aircraft image with dwindle; The layout of passenger cabin module real simulation aircraft cockpit reflects in real time and the situation of change of each flying instruments can realize that the plug-type amplification of instrument is dwindled, screen-picture show aircraft the planimetric position, show the vertical plane flight path and switch side number.
Fig. 5 has shown the time slot allocation that system is concrete, and the full detail refresh cycle of system is 2 seconds, p.s. be one lock in time sheet T
0, upload time slot T for one
1With several communication time slots T
1(i=1 wherein, 2,3 ...), lock in time sheet T
0Take 20ms, upload time slot T
1Be 38ms and each communication time slot T
iTake the time interval of 61.25ms, comprise the transmission time of about 40ms in communication time slot, the transmitting-receiving switching time of 16ms, be no more than the transmission delay of 1.25ms and the time tolerance of 4ms.System receives synchronizing information signal in the GPS information during sheet in lock in time, receives teletype command and information when uploading time slot, sends data when the communication time slot.Application mixes with time division multiple access (TDMA) in system with frequency division multiple access, in an airport scope a plurality of frequencies are set, and each frequency uses for some airplanes, and the wireless transmission between each frequency is not disturbed mutually.
Fig. 6 shows that when a plurality of receiver was set up on ground, radio station 1 to radio station n connected 1 to n CPU respectively, all imported in the master cpu with the signal at GPS difference station by dual port RAM separately separately, and master cpu passes the signal to the ground data processor.
4 CPU that establish in the communication controller on the machine have been shown among Fig. 7, have been respectively MCPU, FCPU, GCPU and BCPU.FCPU and GCPU major function are for collecting flight parameter and gps signal, and BCPU is as the flat processing that shows data, and MCPU receives the data message of other three CPU, and the communication speed in MCPU and radio station is optional from 9.6Kbps～640Kbps; MCPU also can be by adding the radio station (comprising spread spectrum receivers) of adapter cartridge control different model, data transfer between two CPU has multiple mode, consider system data amount and the expansion of function from now on, system has adopted the dual port RAM mode, MCPU has reserved the expansion interface of system, prepare against when increasing data volume again, expansion more data signal, the signal of MCPU sends to ground receiving equipment by data radio station.
System's video data is not only just on main control computer, also data to be sent on other terminating machine simultaneously and show, for making Data Receiving and showing and to carry out synchronously, system creation data receive and processing threads, this thread is responsible for after system start-up from the serial port reading of data and according to sending the format analysis processing data, and data processing finishes and sends into display routine immediately.
Used packet and instruction bag to distinguish flying quality stream and control command stream in land station's data program, but all be considered to data in Network Transmission, therefore the head at packet and instruction bag adds the sign amount to show difference and in the XOR mode data to be carried out verification.
What show on the terminating machine all is separate modular, consider maintainability and reliability, the program code of complexity should not be added these modules, the back-end data exchanger mainly solves the network data problem of transmission, and its principle is characteristics of utilizing the memory access data speed fast, carry out exchanges data at internal memory, after promptly receiving data, put into internal memory earlier, and send a self-defined message from the network port, display module fetches data from internal memory after receiving message again, realizes memory shared.
System is for reaching simulated effect, analog capsule cabin and aspect module all are to adopt three-dimensional model and true three-dimension ground scape to make, model aircraft is made up of 15 sub-models, drive wing flap, aileron, horizontal tail, yaw rudder, undercarriage, the real flight attitude of wake flame motion simulation of aircraft by real data, and can be in the corresponding aircraft number of the anterior change of model aircraft when switching aircraft; Handle different visual angles by the video camera control module in the program, according to normal visual angle scene is handled, by coordinate transform the coordinate of each object in the scene is transformed to the video camera space by world space, by the cutting conversion scene is projected on the screen, carry out the work that hidden surface is eliminated simultaneously.The method of visual angle conversion is: world coordinate system-view coordinate-screen coordinate system.
Claims (5)
1, a kind of by airborne equipment and uphole equipment real-time flight simulation monitor system dimerous, it is characterized in that, airborne equipment comprises: communication controller, data radio station, power pack, radio station antenna, frequency selector etc., antenna will receive the gps satellite navigation signal and the flight parameter on the aircraft that come and be sent to land station by communication controller by data radio station behind frequency selector; Uphole equipment comprises: ground-plane antenna, receive the radio station, land station's pretreater, LAN equipment (comprises hub, network interface card, netting twine etc.), main control computer, terminating machine ground power supply and ground check device etc., the receiving antenna of land station receive on the machine or the signal that transmits on the satellite after, pass through pretreater, main control computer demonstrates the attitude of aircraft flight with being defeated by a plurality of terminating machine real-time simulations, the position, terminating machine is respectively with numerical map, the form of real-time parameter shows flight track, the emulation cockpit instrument, the variation of aspect, and can at any time signal be uploaded to and the variation of each rudder face of aircraft and the folding and unfolding of undercarriage.
2, real-time flight simulation monitor system according to claim 1 is characterized in that, communication controller is sent land station with the time division multiple access (TDMA) form back to by data radio station after GPS locating information, flight parameter information are carried out pre-service; Frequency selector provides the change signal feedback of data radio station channel to import data radio station again to communication controller.
3, real-time flight simulation monitor system according to claim 1, it is characterized in that, the main control computer of uphole equipment shows the real time position of aircraft on the one hand with the two dimensional surface map, flight parameter, on the other hand data are sent to each terminating machine by network, terminating machine is respectively with numerical map, the form of real-time parameter shows flight track, position etc., variation and the variation of each rudder face of aircraft and the folding and unfolding of undercarriage of emulation cockpit instrument and aspect realistically simultaneously, in addition, according to real flight conditions, can go up teletype command at any time, the transmission of control data or change order of transmission.
4, real-time flight simulation monitor system according to claim 1, it is characterized in that the wireless transmission rate of data radio station is 9600bps, transmitting-receiving switching time is 16ms, the data that 36 bytes are transmitted in the radio station need the 38ms time approximately, and data updating rate is 0.5 time/second.
5, real-time flight simulation monitor system according to claim 1 is characterized in that, the method for visual angle conversion is: world coordinate system-view coordinate-screen coordinate system.
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100408433C (en) * | 2006-07-07 | 2008-08-06 | 中国科学院力学研究所 | Real-time prediction method for satellite flight parameter |
| CN1890639B (en) * | 2003-12-12 | 2010-05-26 | 韩国电子通信研究院 | Satellite simulation model system based on interface standard model |
| CN101109794B (en) * | 2007-07-26 | 2010-12-15 | 北京航空航天大学 | Test platform being compatible with GNSS signal processing algorithm |
| CN101533569B (en) * | 2009-03-23 | 2011-01-05 | 民航数据通信有限责任公司 | Flight dynamic monitoring method supporting aircraft four dimensional space-time information |
| CN101989363A (en) * | 2009-07-30 | 2011-03-23 | 中国商用飞机有限责任公司 | System and method for processing digital air data |
| CN101794523B (en) * | 2009-12-15 | 2011-11-16 | 中国民航大学 | Aircraft hardware-in-the-loop simulation device |
| CN102339021A (en) * | 2011-07-21 | 2012-02-01 | 成都西麦克虚拟现实电子技术有限公司 | UAV(unmanned aerial vehicle) visual simulation system and simulation method |
| CN103010485A (en) * | 2012-12-21 | 2013-04-03 | 南京航空航天大学 | Simulation modeling method for tilt-rotor unmanned plane and system thereof |
| CN104267417A (en) * | 2014-07-29 | 2015-01-07 | 西安科远测控技术有限公司 | Beidou-based flight safety real-time monitoring system and method |
| CN104393906A (en) * | 2014-11-04 | 2015-03-04 | 中国航天科工集团第三研究院第八三五七研究所 | Flight parameter ground wireless transmission system |
| CN105182874A (en) * | 2015-09-10 | 2015-12-23 | 中国人民解放军海军航空工程学院青岛校区 | Real-time flight state monitoring system based on returned flight data, and method |
| CN105319049A (en) * | 2014-07-31 | 2016-02-10 | 空中客车运营简化股份公司 | Real-time management of data relative to aircraft's flight test |
| CN105319571A (en) * | 2014-06-04 | 2016-02-10 | 北京嘉兴网泰科技有限公司 | Global high-precision track measurement system |
| CN107256278A (en) * | 2017-03-30 | 2017-10-17 | 南京航空航天大学 | The seamless interventional method of pilot and system under aircraft accident simulated environment |
| WO2018023870A1 (en) * | 2016-08-02 | 2018-02-08 | 湖南星思科技有限公司 | Intelligent low-altitude traffic management and control centre |
| CN108880724A (en) * | 2018-04-18 | 2018-11-23 | 广州市中海达测绘仪器有限公司 | Airborne equipment data transmission method, apparatus and system based on time sharing transmissions technology |
| CN109448158A (en) * | 2018-11-06 | 2019-03-08 | 珠海欧比特宇航科技股份有限公司 | A kind of flight parameter discharge mechanism |
| CN110441802A (en) * | 2019-08-12 | 2019-11-12 | 四川航天系统工程研究所 | A kind of helicopter monitoring system based on Beidou positioning |
| CN112203058A (en) * | 2020-10-10 | 2021-01-08 | 深圳市卓层天气服务有限公司 | Navigation tower monitoring method and device, computer readable medium and electronic equipment |
| CN112578809A (en) * | 2020-11-19 | 2021-03-30 | 一飞(海南)科技有限公司 | Unmanned aerial vehicle cluster communication topology device, method, computer equipment, medium and terminal |
| CN115273559A (en) * | 2022-07-07 | 2022-11-01 | 沈阳飞机工业（集团）有限公司 | Method for performing virtual simulation on head-up display of aircraft cabin |
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2001
- 2001-07-02 CN CN 01119845 patent/CN1393682A/en active Pending
Cited By (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1890639B (en) * | 2003-12-12 | 2010-05-26 | 韩国电子通信研究院 | Satellite simulation model system based on interface standard model |
| CN100408433C (en) * | 2006-07-07 | 2008-08-06 | 中国科学院力学研究所 | Real-time prediction method for satellite flight parameter |
| CN101109794B (en) * | 2007-07-26 | 2010-12-15 | 北京航空航天大学 | Test platform being compatible with GNSS signal processing algorithm |
| CN101533569B (en) * | 2009-03-23 | 2011-01-05 | 民航数据通信有限责任公司 | Flight dynamic monitoring method supporting aircraft four dimensional space-time information |
| CN101989363A (en) * | 2009-07-30 | 2011-03-23 | 中国商用飞机有限责任公司 | System and method for processing digital air data |
| CN101989363B (en) * | 2009-07-30 | 2014-07-16 | 中国商用飞机有限责任公司 | System and method for processing digital air data |
| CN101794523B (en) * | 2009-12-15 | 2011-11-16 | 中国民航大学 | Aircraft hardware-in-the-loop simulation device |
| CN102339021A (en) * | 2011-07-21 | 2012-02-01 | 成都西麦克虚拟现实电子技术有限公司 | UAV(unmanned aerial vehicle) visual simulation system and simulation method |
| CN102339021B (en) * | 2011-07-21 | 2013-07-03 | 成都西麦克虚拟现实电子技术有限公司 | UAV(unmanned aerial vehicle) visual simulation system and simulation method |
| CN103010485A (en) * | 2012-12-21 | 2013-04-03 | 南京航空航天大学 | Simulation modeling method for tilt-rotor unmanned plane and system thereof |
| CN105319571A (en) * | 2014-06-04 | 2016-02-10 | 北京嘉兴网泰科技有限公司 | Global high-precision track measurement system |
| CN104267417A (en) * | 2014-07-29 | 2015-01-07 | 西安科远测控技术有限公司 | Beidou-based flight safety real-time monitoring system and method |
| CN105319049A (en) * | 2014-07-31 | 2016-02-10 | 空中客车运营简化股份公司 | Real-time management of data relative to aircraft's flight test |
| CN105319049B (en) * | 2014-07-31 | 2020-04-17 | 空中客车运营简化股份公司 | System and method for real-time management of data relating to flight tests of an aircraft |
| CN104393906A (en) * | 2014-11-04 | 2015-03-04 | 中国航天科工集团第三研究院第八三五七研究所 | Flight parameter ground wireless transmission system |
| CN105182874A (en) * | 2015-09-10 | 2015-12-23 | 中国人民解放军海军航空工程学院青岛校区 | Real-time flight state monitoring system based on returned flight data, and method |
| WO2018023870A1 (en) * | 2016-08-02 | 2018-02-08 | 湖南星思科技有限公司 | Intelligent low-altitude traffic management and control centre |
| CN107256278A (en) * | 2017-03-30 | 2017-10-17 | 南京航空航天大学 | The seamless interventional method of pilot and system under aircraft accident simulated environment |
| CN107256278B (en) * | 2017-03-30 | 2019-11-12 | 南京航空航天大学 | The seamless interventional method of pilot and system under aircraft accident simulated environment |
| CN108880724B (en) * | 2018-04-18 | 2021-04-27 | 广州市中海达测绘仪器有限公司 | Airborne equipment data transmission method, device and system based on time-sharing transmission technology |
| CN108880724A (en) * | 2018-04-18 | 2018-11-23 | 广州市中海达测绘仪器有限公司 | Airborne equipment data transmission method, apparatus and system based on time sharing transmissions technology |
| CN109448158A (en) * | 2018-11-06 | 2019-03-08 | 珠海欧比特宇航科技股份有限公司 | A kind of flight parameter discharge mechanism |
| CN110441802A (en) * | 2019-08-12 | 2019-11-12 | 四川航天系统工程研究所 | A kind of helicopter monitoring system based on Beidou positioning |
| CN112203058A (en) * | 2020-10-10 | 2021-01-08 | 深圳市卓层天气服务有限公司 | Navigation tower monitoring method and device, computer readable medium and electronic equipment |
| CN112203058B (en) * | 2020-10-10 | 2024-03-01 | 深圳市卓层技术有限公司 | Navigation tower monitoring method and device, computer readable medium and electronic equipment |
| CN112578809A (en) * | 2020-11-19 | 2021-03-30 | 一飞(海南)科技有限公司 | Unmanned aerial vehicle cluster communication topology device, method, computer equipment, medium and terminal |
| CN115273559A (en) * | 2022-07-07 | 2022-11-01 | 沈阳飞机工业（集团）有限公司 | Method for performing virtual simulation on head-up display of aircraft cabin |
| CN115273559B (en) * | 2022-07-07 | 2024-03-08 | 沈阳飞机工业（集团）有限公司 | Method for carrying out virtual simulation on aircraft cabin head-up display |
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