CN202158845U - Airplane crack real-time monitoring system based on Beidou navigation satellites - Google Patents
Airplane crack real-time monitoring system based on Beidou navigation satellites Download PDFInfo
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- CN202158845U CN202158845U CN 201120252677 CN201120252677U CN202158845U CN 202158845 U CN202158845 U CN 202158845U CN 201120252677 CN201120252677 CN 201120252677 CN 201120252677 U CN201120252677 U CN 201120252677U CN 202158845 U CN202158845 U CN 202158845U
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Abstract
The utility model relates to safety monitoring systems, and particularly discloses an airplane crack real-time monitoring system based on Beidou navigation satellites, which includes more than two monitoring equipment mounted on an airplane, more than two Beidou navigation satellites and an earth station, wherein monitoring equipment is connected with the earth station through the Beidou navigation satellites; the monitoring equipment includes displacement sensors; every monitoring point includes two displacement sensors that are mounted in the two directions of horizontal X axis and Y axis of the monitoring point respectively; and the monitoring points are arranged on a fuselage and wings of the airplane. The displacement sensors mounted on the fuselage and the wings of the airplane are used for monitoring the displacement in the two directions of the horizontal X axis and the Y axis of the monitoring points, so as to determine whether the airplane cracks, and detects the safety condition of the airplane in real-time and transmits the signal to the earth station; and the earth station processes the received signal, so as to determine the safety condition of the airplane.
Description
Technical field
The utility model relates to safety monitoring systems, relates in particular to a kind of aircraft crackle real-time monitoring system based on Big Dipper Navsat.
Background technology
In recent years; Many types of civilian, the military aircraft in countries in the world uses maintenance by given life-span, proof cycle; But still the catastrophic failure of midair disintegration constantly takes place; Its main cause is exactly to aircraft crackle insufficient recognition, and the technological means that lacks structural crack monitoring in the aircraft utilization process.
At present; International airline bound pair aircraft structural damage detects has 2 points: the one, and expose the tired dangerous position of aircaft configuration, provide proof cycle and safe life or carry out the unit Payload Monitoring And Control through test; Adopt the method control damage of grasp macroscopical; The 2nd, shorten the time between overhauls(TBO), enlarge inspection area, when advancing factory's overhaul and daily servicing, adopt Non-Destructive Testing or visual means, with the method control damage of strengthening inspection.But facts have proved in a large number, aircraft is actual use in the loss of structure more than complicated many in the test.And do not have a kind of effective aircraft crackle real-time monitoring system in the prior art.
The utility model content
To there not being a kind of system that security is monitored in real time to the aircraft crackle in the prior art, therefore be necessary to provide a kind of aircraft crackle security system of monitoring in real time.
The utility model discloses a kind of aircraft crackle real-time monitoring system based on Big Dipper Navsat; Comprise installation monitoring equipment, two above Big Dipper Navsats, the land station of two above monitoring points aboard; Said monitoring equipment connects land station through Big Dipper Navsat; Said monitoring equipment comprises displacement transducer; There are two displacement transducers each monitoring point, is installed in the horizontal X axle and the Y axle both direction of monitoring point respectively, and the monitoring point on the said aircraft is separately positioned on fuselage and the wing.
Preferably; Above-mentioned land station comprises that ground control centre, power subsystem, communication monitoring subsystem, emission receive subsystem, antenna; Said ground control centre connects power subsystem, communication monitoring subsystem, emission reception subsystem respectively, and said emission receives subsystem and is connected with Navsat through antenna.
Preferably, above-mentioned monitoring equipment comprises wave filter, amplifier, ARM plate, and said displacement transducer connects wave filter, amplifier, ARM plate in regular turn.
Preferably, on the above-mentioned ARM plate warning device is set.
Preferably, above-mentioned aircraft crack monitoring system comprises Big Dipper Navsat time dissemination system.
To sum up above-mentioned, owing to adopted technique scheme, the utlity model has following beneficial effect: said installation monitoring equipment is aboard monitored the security information of aircraft and is transferred to land station through Big Dipper Navsat.Through being installed in the displacement that displacement transducer on fuselage and the wing monitors the horizontal X axle and the Y axle both direction of monitoring point; Confirm whether aircraft crackle occurs; Detect the safety case of aircraft in real time and be transferred to land station; Land station handles to the received signal, confirms the safety case of aircraft in real time.
Description of drawings
The utility model will explain through example and with reference to the mode of accompanying drawing, wherein:
Fig. 1 is the positioning principle figure of the Big Dipper Navsat of the utility model.
Fig. 2 is a big-dipper satellite communication subsystem theory diagram.
Embodiment
Disclosed all characteristics in this instructions, or the step in disclosed all methods or the process except mutually exclusive characteristic and/or the step, all can make up by any way.
The utility model discloses a kind of aircraft crackle real-time monitoring system based on Big Dipper Navsat; Comprise installation monitoring equipment, two above Big Dipper Navsats, the land station of two above monitoring points aboard; Said monitoring equipment connects land station through Big Dipper Navsat; Said monitoring equipment comprises displacement transducer, and there are two displacement transducers each monitoring point, is installed in the horizontal X axle and the Y axle both direction of monitoring point respectively; Obtain the signal of horizontal crackle respectively, the monitoring point on the said aircraft is separately positioned on fuselage and the wing.Said installation monitoring equipment is aboard monitored the security information of aircraft and is transferred to land station through Big Dipper Navsat.Through being installed in the displacement that displacement transducer on fuselage and the wing monitors the horizontal X axle and the Y axle both direction of monitoring point; Confirm whether aircraft crackle occurs; Detect the safety case of aircraft in real time and be transferred to land station; Land station handles to the received signal, confirms the safety case of aircraft in real time.
Preferably; Said land station comprises that ground control centre, power subsystem, communication monitoring subsystem, emission receive subsystem, antenna; Said ground control centre connects power subsystem, communication monitoring subsystem, emission reception subsystem respectively, and said emission receives subsystem and is connected with Navsat through antenna.
The positioning principle figure of the Big Dipper Navsat of the utility model as shown in Figure 1, the realization principle of the utility model is following: triones navigation system is active bidirectional ranging two dimensional navigation, and the ground control centre system is resolved, and supplies aircraft monitoring point three-dimensional localization data.At first send interrogating signal simultaneously to satellite 1 and satellite 2, broadcast to each aircraft monitoring point through satellite repeater by the ground control centre system.The response of aircraft monitoring point is the interrogating signal of a satellite wherein, and simultaneously to two satellite transmission response signals, after Big Dipper Navsat is transmitted, goes back to the system of control center.The signal that the system of control center receives and send demodulation aircraft monitoring point carries out corresponding data processing according to the application service content of aircraft monitoring point then.To location application, central control system is measured two time delays: promptly send interrogating signal from central control system, transmit through a certain satellite and arrive the user, the user sends the location response signal, the delay of transmitting back central control system through same satellite; Send interrogating signal with controlling from the center, arrive the user through above-mentioned same satellite, the user sends response signal, transmits back the delay of central control system through another satellite.Because the position of system of control center and two satellites all is known; Therefore can calculate the distance of user's to the first satellite by top two retardations; And user's to two satellite distance sum; Thereby know that it is a sphere of the centre of sphere with first satellite that the user is in one, with on the intersection between two satellites ellipsoid that is focus.The system of control center searches user's height value from the digital terrain figure that is stored in the computing machine in addition; Know that again the user is on a certain ellipsoid parallel with the earth reference ellipsoid, thereby the system of control center can finally calculate the three-dimensional coordinate of aircraft loca.
Preferably, said monitoring equipment comprises wave filter, amplifier, ARM plate, and said displacement transducer connects wave filter, amplifier, ARM plate in regular turn.When displacement takes place, sensor acquisition arrival horizontal X axle, horizontal Y axis signal, sensor is with the low-pass filter of the signal of exporting through 1KHz, and the high frequency interference in signal is mixed in filtering; Send filtered signal to amplifier then, amplifier is amplified to 1V with the signal of input
PpDeliver to the ARM plate and change, because the signal that collects is a simulating signal, at this moment, the AD translation function that ARM9 is last converts model signals to digital signal, and sends data processing centre (DPC) to.
Preferably, on the said ARM plate warning device is set.The LED light alarming device and the hummer sound warning device that are installed on the ARM plate are worked simultaneously, produce warning function.
Preferably, said aircraft crack monitoring system comprises Big Dipper Navsat time dissemination system.The aircraft of satellite and ground control centre, monitoring point can be had with the synchronizing clock signals of homophase frequently, adopt Big Dipper Navsat time dissemination system among the present invention.The time dissemination system frequency that apparatus of the present invention adopted can be 20MHz, 40MHz, 60MHz, 80MHz, and employed frequency is high more, and then precision is high more.
Said ground control centre comprises location, clock, signal transmitting and receiving, information processing, reaches support equipment composition, the Control work pattern of taking main control centre and disposal system to combine.Main control centre is made up of database subsystem, communication subsystem, calls barred subsystem; Disposal system comprises communication subsystem, GIS subsystem main control centre and each monitoring point link composition dedicated network via satellite, intercourses data, shares information, realizes population surveillance, network alarm, the safe high request of absolute assurance.
Big Dipper Navsat is to cover China domestic regional active three-dimensional satnav and communication system, about 70 °-140 ° of coverage east longitude, 5 °-55 ° of north latitude.Said aircraft crackle real-time monitoring system based on Big Dipper Navsat comprises vacant terminal satellite portion, land station's part and terminal, aircraft monitoring point three parts composition.The vacant terminal satellite portion generally is made up of 2 to 3 geostationary satellites, is responsible for carrying out the two-way radio signal relay task between ground control centre and the aircraft monitoring point.The main load of every satellite is frequency translating transponder, and the global beam or the zone beam antenna that cover the positioning and communicating region point.Land station partly accomplish and satellite between the processing of uplink and downlink data; Service request to send the aircraft monitoring point is carried out response process; Accomplish the work of treatment of aircraft monitoring point locator data and the exchange work of communication data; Position, aircraft monitoring point and the Content of Communication that computing machine obtains,, give relevant user respectively through control center through exchanging.
Big-dipper satellite communication subsystem theory diagram as shown in Figure 2, land station comprises ground control centre, antenna, launches and accepts subsystem, communication monitoring subsystem, power subsystem.The antenna subsystem of land station; Towards Big Dipper Navsat; Gather to become a bit it from aerial satellite-signal energy reflection; Become high-frequency electrical energy to the electromagnetism field energy or high-frequency electrical energy changes the device in a magnetic field into, adopting diameter is 2.4 meters parabola antenna, by antenna itself, feed, high frequency is first-class forms.The emission subsystem is that the signal that needs are broadcast is modulated on the carrier wave of service band, after high-power amplification, goes out through a day alignment satellites transmits.Receiving subsystem is the signal that receives from satellite, after amplification, detection, re-sends to terminal system.The communication monitoring subsystem be responsible for to the various device in the land station keep watch on, control and routine test.Power subsystem is for whole earth station equipments power supply to be provided.
The processing of uplink and downlink data between aircraft monitoring point and the satellite is accomplished at terminal, aircraft monitoring point; Send aircraft monitoring point request, receive the aircraft data of monitoring point; Necessary demonstration and data-interface is provided.Adopt the big-dipper satellite airborne equipment, have miniaturization, integrated level is high, facility compact is simple, low-power consumption and characteristics such as simple to operate.
Disclosed arbitrary characteristic in this instructions (comprising any accessory claim, summary and accompanying drawing) is only if special narration all can or have similar purpose alternative features by other equivalence and replace.That is, only if special narration, each characteristic is an example in a series of equivalences or the similar characteristics.
The utility model is not limited to aforesaid embodiment.The utility model expands to any new feature or any new combination that discloses in this manual, and the arbitrary new method that discloses or step or any new combination of process.
Claims (5)
1. aircraft crackle real-time monitoring system based on Big Dipper Navsat; It is characterized in that comprising installation monitoring equipment, two above Big Dipper Navsats, the land station of two above monitoring points aboard; Said monitoring equipment connects land station through Big Dipper Navsat; Said monitoring equipment comprises displacement transducer; There are two displacement transducers each monitoring point, is installed in the horizontal X axle and the Y axle both direction of monitoring point respectively, and the monitoring point on the said aircraft is separately positioned on fuselage and the wing.
2. aircraft crackle real-time monitoring system as claimed in claim 1; It is characterized in that said land station comprises that ground control centre, power subsystem, communication monitoring subsystem, emission receive subsystem, antenna; Said ground control centre connects power subsystem, communication monitoring subsystem, emission reception subsystem respectively, and said emission receives subsystem and is connected with Navsat through antenna.
3. aircraft crackle real-time monitoring system as claimed in claim 2 is characterized in that said monitoring equipment comprises wave filter, amplifier, ARM plate, and said displacement transducer connects wave filter, amplifier, ARM plate in regular turn.
4. aircraft crackle real-time monitoring system as claimed in claim 3 is characterized in that on the said ARM plate warning device being set.
5. aircraft crackle real-time monitoring system as claimed in claim 4 is characterized in that said aircraft crack monitoring system comprises Big Dipper Navsat time dissemination system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120252677 CN202158845U (en) | 2011-07-18 | 2011-07-18 | Airplane crack real-time monitoring system based on Beidou navigation satellites |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120252677 CN202158845U (en) | 2011-07-18 | 2011-07-18 | Airplane crack real-time monitoring system based on Beidou navigation satellites |
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| Publication Number | Publication Date |
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| CN202158845U true CN202158845U (en) | 2012-03-07 |
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| CN 201120252677 Expired - Fee Related CN202158845U (en) | 2011-07-18 | 2011-07-18 | Airplane crack real-time monitoring system based on Beidou navigation satellites |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102831790A (en) * | 2012-09-24 | 2012-12-19 | 中国航空无线电电子研究所 | Beidou-based air traffic collision early warning method |
| CN107238408A (en) * | 2017-05-04 | 2017-10-10 | 安徽广安电子科技有限公司 | A kind of safety monitoring system based on Beidou navigation satellite |
| CN109931933A (en) * | 2017-12-15 | 2019-06-25 | 中国航空工业集团公司成都飞机设计研究所 | Mission planning and navigation method for drafting based on GIS platform |
| CN114236585A (en) * | 2021-12-09 | 2022-03-25 | 国网思极神往位置服务（北京）有限公司 | Target motion monitoring method based on Beidou navigation satellite system and storage medium |
-
2011
- 2011-07-18 CN CN 201120252677 patent/CN202158845U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102831790A (en) * | 2012-09-24 | 2012-12-19 | 中国航空无线电电子研究所 | Beidou-based air traffic collision early warning method |
| CN107238408A (en) * | 2017-05-04 | 2017-10-10 | 安徽广安电子科技有限公司 | A kind of safety monitoring system based on Beidou navigation satellite |
| CN109931933A (en) * | 2017-12-15 | 2019-06-25 | 中国航空工业集团公司成都飞机设计研究所 | Mission planning and navigation method for drafting based on GIS platform |
| CN114236585A (en) * | 2021-12-09 | 2022-03-25 | 国网思极神往位置服务（北京）有限公司 | Target motion monitoring method based on Beidou navigation satellite system and storage medium |
| CN114236585B (en) * | 2021-12-09 | 2023-04-14 | 国网思极位置服务有限公司 | Target motion monitoring method based on Beidou navigation satellite system and storage medium |
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