CN203720558U - Ground acquisition aircraft data backup system - Google Patents
Ground acquisition aircraft data backup system Download PDFInfo
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- CN203720558U CN203720558U CN201320843131.7U CN201320843131U CN203720558U CN 203720558 U CN203720558 U CN 203720558U CN 201320843131 U CN201320843131 U CN 201320843131U CN 203720558 U CN203720558 U CN 203720558U
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- 238000005259 measurement Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
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Abstract
A ground acquisition aircraft data backup system belongs to the aviation field. The system comprises a ground station, an airborne link system, and a flight control center and further comprises a laser wind-measurement radar and a data combination computer. The laser wind-measurement radar measures aircraft periphery wind field information in a self-centered mode and transmits the measurement information to the data combination computer. The data combination computer combines the wind field information with aircraft posture information to calculate and obtain an aircraft flight state, and transmits the aircraft flight state to the ground station. The ground station transmits the aircraft posture information to the flight control center on an aircraft through the airborne link system. The ground acquisition aircraft data backup system ensures the promptness, correctness, and effectiveness of operation parameters of an aircraft atmosphere system and guarantees the safety of the aircraft. Moreover, the ground acquisition aircraft data backup system is simple in structure, convenient to operate, and suitable for civil and military manned aircrafts and all unmanned aircrafts. Besides, the ground acquisition aircraft data backup system has a wide application range and a high market application value.
Description
Technical field
The utility model belongs to aviation field, is 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, send back land station as what manipulate according to will or air speed information exchange being crossed to airborne chain-circuit system by preset program operation, manipulated by land station.In the time of 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, in the time that the larger environment of wind speed flies, be breakneck behavior according to ground velocity flight, in the time of aircraft landing, no matter fly according to ground velocity, or carry out Landing Control by artificial terrestrial operation, cause most probably the accident of air crash.
In prior art, the way that solves airborne Atmosphere System fault is that airborne large institute system for subsequent use 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.
Utility model content
Manipulate for solving the aircraft that may cause because of the mechanical Atmosphere System fault of aircraft in prior art the problem having no basis, the utility model 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 utility model 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 taking ground survey as aircraft provides backup, has ensured the timely, correct and effective of aircraft Atmosphere System operating parameter.Ensure the flight safety of aircraft.And the utility model 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.
Brief description of the drawings
The drawing of the utility model accompanying drawing is described as follows:
Fig. 1: fundamental diagram of the present utility model when airborne atmosphere, inertial navigation system fault;
Fig. 2: aircraft image data fundamental diagram when non-fault;
Fig. 3: aircraft image data fundamental diagram while using utility model fault
Embodiment
Below in conjunction with accompanying drawing, the utility model is further described, 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.
Also when breaking down as the inertial navigation system of aircraft, the utility model 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, represent 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, show that in conjunction with computing machine the information of aircraft sends back land station again by data, 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320843131.7U CN203720558U (en) | 2013-12-19 | 2013-12-19 | Ground acquisition aircraft data backup system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320843131.7U CN203720558U (en) | 2013-12-19 | 2013-12-19 | Ground acquisition aircraft data backup system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203720558U true CN203720558U (en) | 2014-07-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320843131.7U Expired - Fee Related CN203720558U (en) | 2013-12-19 | 2013-12-19 | Ground acquisition aircraft data backup system |
Country Status (1)
| Country | Link |
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| CN (1) | CN203720558U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103744285A (en) * | 2013-12-19 | 2014-04-23 | 中航贵州飞机有限责任公司 | Ground acquisition plane data backup system |
-
2013
- 2013-12-19 CN CN201320843131.7U patent/CN203720558U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103744285A (en) * | 2013-12-19 | 2014-04-23 | 中航贵州飞机有限责任公司 | Ground acquisition plane data backup system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140716 |