CN103744285A - Ground acquisition plane data backup system - Google Patents
Ground acquisition plane data backup system Download PDFInfo
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- CN103744285A CN103744285A CN201310703696.XA CN201310703696A CN103744285A CN 103744285 A CN103744285 A CN 103744285A CN 201310703696 A CN201310703696 A CN 201310703696A CN 103744285 A CN103744285 A CN 103744285A
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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
The invention provides a ground acquisition plane data backup system, and belongs to the field of aviation. The system comprises a ground station, an onboard link system and a flight control center. The system also comprises a laser wind-measuring radar and a data combination computer. The laser wind-measuring radar measures information including wind field information around a plane with the laser wind-measuring radar as the center. The laser wind-measuring radar transmits the measured information to the data combination computer. The data combination computer combines the wind field information and attitude information of the plane and calculates the flight state of the plane. Then the flight state of the plane is transmitted to the ground station which transmits the attitude information of the plane to the flight control center on the plane via the onboard link system. Operation parameters of an air system of the plane are ensured to be timely, correct and effective so that flight safety of the plane is ensured. Besides, the system is simple in structure, convenient to operate and applicable to manned planes like civil planes, military planes, etc. and all the unmanned planes. Therefore, the system is wide in application and relatively high in market application value.
Description
Technical field
The invention belongs to aviation field, be specifically related to a kind of ground acquisition airplane data standby system.
Background technology
Aircraft, in flight course, flies to be called air speed with respect to the speed of the wind field of periphery, and the measurement of the air speed of aircraft is to be provided by the mechanical Atmosphere System of aircraft, and the air speed information on aircraft sends the aircraft control center on aircraft to.There is man-machine aircraft control center that air speed is shown to the manipulation foundation as pilot, the aircraft control center of unmanned plane is directly computing machine, aircraft control computer is received air speed information, as what manipulate, according to will or air speed information exchange being crossed to airborne chain-circuit system by preset program operation, send back land station, by land station, manipulated.When airborne Atmosphere System fault, man-machine to having, need pilot to go to judge air speed according to the experience of oneself, and then operating aircraft, once the error of pilot's decision operation may cause fatal crass's accident.And to unmanned plane, airborne Atmosphere System is slipped up, unmanned plane has not just had the parameter foundation of manipulation, and conventional solution is to allow unmanned plane constantly accelerate, and uses ground velocity (the GPS speed etc.) control of flying, when the larger environment of wind speed flies, according to ground velocity flight, be breakneck behavior, when aircraft landing, no matter according to ground velocity, fly, or by artificial terrestrial operation, carry out Landing Control, cause most probably the accident of air crash.
In prior art, the way that solves airborne Atmosphere System fault is that standby airborne large institute system is installed aboard.If but in the situation about also losing efficacy of backup: as power supply goes wrong, when the equal fault of airborne Atmosphere System itself, the Atmosphere System data solver system failure, data transmission system fault, the flight safety of aircraft just can not ensure.
Equally, the flight attitude information of aircraft is to be provided by the inertial navigation system of aircraft, and flight attitude information is also one of requisite parameter in aircraft manipulation process, if inertial navigation system breaks down, what aircraft was same can not safe flight.
Summary of the invention
For solving the aircraft that may cause because of the mechanical Atmosphere System fault of aircraft in prior art, manipulate the problem having no basis, the invention provides a kind of ground acquisition airplane data standby system.
Ground acquisition airplane data standby system, comprise land station, airborne chain-circuit system, flight control center, land station transmits mutually data by the flight control center on airborne chain-circuit system and aircraft, it is characterized in that: also comprise that laser windfinding radar and data are in conjunction with computing machine, described laser windfinding radar is measured and is comprised aircraft periphery wind field information centered by self, laser windfinding radar sends metrical information to data in conjunction with computing machine, and data are combined wind field information in conjunction with computing machine and are calculated the state of flight of aircraft with the attitude information of aircraft; Send the state of flight of aircraft to land station again, land station sends the attitude information of aircraft to flight control center on aircraft by airborne chain-circuit system.
The present invention is by laser windfinding radar, by aircraft wind field information measurement around out, use again data in conjunction with computing machine, the attitude information of aircraft is combined to the air speed information that draws with wind field information, air speed take ground survey as aircraft provides backup, has guaranteed the timely, correct and effective of aircraft Atmosphere System operating parameter.Guaranteed the flight safety of aircraft.And the present invention is simple in structure, easy to operate, being applicable to civil aircraft, military secret etc. has man-machine and all unmanned planes.Applied range, has higher market using value.
Accompanying drawing explanation
The drawing of accompanying drawing of the present invention is described as follows:
Fig. 1: fundamental diagram of the present invention when airborne atmosphere, inertial navigation system fault;
Fig. 2: aircraft image data fundamental diagram during non-fault;
Fig. 3: aircraft image data fundamental diagram while using invention fault
Embodiment
Below in conjunction with accompanying drawing, the present invention is further illustrated, embodiment part is just described as an example of the concrete structure of the ground acquisition airplane data standby system of unmanned plane example, and have man-machine theory structure identical with the structure of unmanned plane, the just ground control station of unmanned plane, referred to as land station, corresponding to there being man-machine ground control centre, the flight control center on the aircraft of unmanned plane is flight-control computer, therefore no longer repeat statement.
Ground acquisition airplane data standby system, comprise land station, airborne chain-circuit system, flight control center, land station transmits mutually data by the flight control center on airborne chain-circuit system and aircraft, it is characterized in that: also comprise that laser windfinding radar and data are in conjunction with computing machine, described laser windfinding radar is measured and is comprised aircraft periphery wind field information centered by self, laser windfinding radar sends metrical information to data in conjunction with computing machine, and data are combined wind field information in conjunction with computing machine and are calculated the state of flight of aircraft with the attitude information of aircraft; Send the state of flight of aircraft to land station again, land station sends the attitude information of aircraft to flight control center on aircraft by airborne chain-circuit system.
In aforesaid operations process, the attitude information of described aircraft is not have out of order aircraft to be used to layer system to provide, and aircraft inertial navigation information exchange is crossed airborne chain-circuit system and sent land station to, and land station sends the attitude information of aircraft to data in conjunction with computing machine again.
When also breaking down as the inertial navigation system of aircraft, the present invention also comprises range finding survey appearance velocity radar, range finding is surveyed appearance velocity radar with from as initial point, the information of measuring directly sends data in conjunction with computing machine, calculate again the attitude information of aircraft, and be combined with the air speed information of aircraft, calculate the status information of aircraft.
In Fig. 1, represented data transfer relationship when laser windfinding radar is all worked with range finding survey appearance velocity radar.If again in conjunction with the relation of the data acquisition under aircraft reference performance in Fig. 2 and transmission, draw in Fig. 3, when in the situation that airborne atmosphere, Airborne Inertial Navigation System all break down, ground acquisition airplane data standby system is as worked in Fig. 1, by data, in conjunction with computing machine, show that the information of aircraft sends back land station again, carry out sending the data of simulated atmosphere system, simulation inertial navigation system to aircraft control computer by airborne chain-circuit system, as the parameter foundation of aircraft manipulation.
Claims (3)
1. ground acquisition airplane data standby system, comprise land station, airborne chain-circuit system, flight control center, land station transmits mutually data by the flight control center on airborne chain-circuit system and aircraft, it is characterized in that: also comprise that laser windfinding radar and data are in conjunction with computing machine, described laser windfinding radar is measured and is comprised aircraft periphery wind field information centered by self, laser windfinding radar sends metrical information to data in conjunction with computing machine, and data are combined wind field information in conjunction with computing machine and are calculated the state of flight of aircraft with the attitude information of aircraft; Send the state of flight of aircraft to land station again, land station sends the attitude information of aircraft to flight control center on aircraft by airborne chain-circuit system.
2. ground acquisition airplane data standby system according to claim 1, it is characterized in that: the attitude information of described aircraft is not have out of order aircraft to be used to layer system to provide, aircraft inertial navigation information exchange is crossed airborne chain-circuit system and is sent land station to, and land station sends the attitude information of aircraft to data in conjunction with computing machine again.
3. ground acquisition airplane data standby system according to claim 1, it is characterized in that: also comprise range finding survey appearance velocity radar, range finding is surveyed appearance velocity radar with from as initial point, the information of measuring directly sends data in conjunction with computing machine, calculate again the attitude information of aircraft, and be combined with the air speed information of aircraft, calculate the status information of aircraft.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310703696.XA CN103744285A (en) | 2013-12-19 | 2013-12-19 | Ground acquisition plane data backup system |
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| CN201310703696.XA CN103744285A (en) | 2013-12-19 | 2013-12-19 | Ground acquisition plane data backup system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104501836A (en) * | 2014-12-22 | 2015-04-08 | 中国人民解放军海军航空工程学院青岛校区 | Wireless device for calibration of flight data |
| CN105867416A (en) * | 2016-04-20 | 2016-08-17 | 北京博瑞爱飞科技发展有限公司 | Flying control method and device of unmanned aerial vehicle and unmanned aerial vehicle |
| CN113126528A (en) * | 2019-12-30 | 2021-07-16 | 北京华航无线电测量研究所 | Remote control system and method for hanging and flying acquisition equipment |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104501836A (en) * | 2014-12-22 | 2015-04-08 | 中国人民解放军海军航空工程学院青岛校区 | Wireless device for calibration of flight data |
| CN104501836B (en) * | 2014-12-22 | 2018-01-05 | 中国人民解放军海军航空工程学院青岛校区 | A wireless device for flight parameter calibration |
| CN105867416A (en) * | 2016-04-20 | 2016-08-17 | 北京博瑞爱飞科技发展有限公司 | Flying control method and device of unmanned aerial vehicle and unmanned aerial vehicle |
| CN113126528A (en) * | 2019-12-30 | 2021-07-16 | 北京华航无线电测量研究所 | Remote control system and method for hanging and flying acquisition equipment |
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Application publication date: 20140423 |