CN203318684U - Aircraft fixed-point landing image system - Google Patents
Aircraft fixed-point landing image system Download PDFInfo
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- CN203318684U CN203318684U CN2013201949170U CN201320194917U CN203318684U CN 203318684 U CN203318684 U CN 203318684U CN 2013201949170 U CN2013201949170 U CN 2013201949170U CN 201320194917 U CN201320194917 U CN 201320194917U CN 203318684 U CN203318684 U CN 203318684U
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Abstract
The utility model relates to an aircraft fixed-point landing image system which comprises a ground image launching system and an airborne image receiving system, wherein S band radio waves are transited and received between the ground image launching system and the airborne image receiving system; the ground image launching system comprises a central camera; the central camera is connected with a signal conversion device, an image transmitter, a radio frequency power amplifier and a transmitting antenna sequentially respectively; the airborne image receiving system comprises an airborne antenna; and the airborne antenna is connected with an integrated image receiver and an airborne image display sequentially. According to the aircraft fixed-point landing image system, ground specific image information is uploaded to an aircraft cockpit through wireless transmission by the aid of a specific structure, so that an aviator can see the image, observed from a landing point, of the driven aircraft timely, the flying attitude is adjusted timely according to the position of the aircraft in the image, and successful fixed-point landing of each time is guaranteed.
Description
One, technical field:
The utility model relates to a kind of aircraft accuracy vision system.
Two, background technology:
In the aircraft flight process of the test, the reference landing system is microwave landing system (MLS), simultaneously cross-reference instrument compressed air (ILS) and Radar Controlled Approach system.
Landing system provides accurate landing orientation to aircraft, the guidance informations such as glide path and distance, and aircraft is according to these information line up with runways and march into the arena and land according to gliding angle, with the deviation that guarantees earth point within the limits prescribed.
During aircraft short range pinpoint landing, the aviator on the one hand helps and falls optical signalling according to landing system information and observation, also to listen ground control person's password on the other hand so that more accurate operating aircraft flight attitude, make aircraft after wheel drop on straight on the earth point of 5 meters.
During landing, ground control person's password plays a decisive role to aircraft accuracy success or not, ground control person's password forms and depends on the specific image display information in ground, and the commanding officer has hysteresis phenomenon by the specific image display information notification aviator in ground on the time, making the aviator adjust flight attitude also has hysteresis phenomenon, can not guarantee so each accuracy success.
Three, utility model content:
The utility model is in order to solve the weak point in the above-mentioned background technology, provide the utility model to relate to a kind of aircraft accuracy vision system, it is uploaded to flight passenger cabin by the specific image information in ground by transmission over radio by certain structure, make the aviator see in time the image that drive an airplane is observed from level point, and the position in image is adjusted flight attitude in time according to aircraft, guarantee each pinpoint landing success.
For achieving the above object, the technical solution adopted in the utility model is:
A kind of aircraft accuracy vision system, comprise ground image emission coefficient and airborne image receiving system, between described ground image emission coefficient and airborne image receiving system, by the S-band radiowave, receives and dispatches;
Described ground image emission coefficient comprises the center camera, and described center camera is connected successively with signal-conversion equipment, picture transmitter, radio-frequency power amplifier and emitting antenna respectively;
Described airborne image receiving system comprises airborne antenna, is connected with integrated image receiver and airborne display plotter on described airborne antenna in turn.
Described integrated image receiver is by power module, signal receiving module, signal demodulation module and signal conversion module form, the mouth of described power module is connected with the input end of signal demodulation module and the input end of signal conversion module, the mouth of signal receiving module is connected with the input end of signal demodulation module, and the mouth of described signal demodulation module is connected with the input end of signal conversion module.
Described airborne antenna is 3255 pocket knife antennas.
The model of described airborne display plotter is: XXS-1.
Described integrated image receiver model is: XTX-1.
Compared with prior art, the advantage and the effect that the utlity model has are as follows:
1, for the aircraft accuracy provides a set of new installation, for aviator's accuracy training provides a kind of new approaches, contribute to reduce pilot training's sortie, improve training effectiveness;
2, solved the ground image signal at vertical 10 kilometers, the scope of horizontal 60 ° is interior to aircraft cockpit synchronism stability transmission over radio problem;
3, wayside equipment adopts waterproof, anticorrosion, anti-salt fog, and mould proof design, can realize round-the-clock use;
4, airborne equipment adopts the airborne equipment Specification Design, can realize continuous working under-30～70 ℃ of wide temperature, and earthquake resistant level meets HB5830 standard E curve, can continuous working under the front deck macroseism is transshipped by force environment;
Four, accompanying drawing explanation:
Fig. 1 is aircraft accuracy vision system circuit diagram;
Fig. 2 is ground image emission coefficient block diagram;
The airborne image receiving system block diagram of Fig. 3;
Fig. 4 is integrated image receiver structure block diagram;
Fig. 5 is integrated image receiver circuit figure;
Fig. 6 is airborne image receiving system schematic diagram;
Fig. 7 is ground image emission coefficient circuit diagram;
Fig. 8 is the signal-conversion equipment circuit diagram;
Reference numeral: 1-center camera, 2-signal-conversion equipment, 3-picture transmitter, 4-radio-frequency power amplifier, 5-emitting antenna, 6-airborne antenna, 7-integrated image receiver, 8-airborne display plotter, 9-power module, 10-signal receiving module, 11-signal demodulation module, 12-signal conversion module.
Five, the specific embodiment:
Below in conjunction with the drawings and specific embodiments, the utility model is elaborated.
A kind of aircraft accuracy image bootstrap technique is: in landing point, high-definition camera is installed, camera coverage with glissade heavy and, when aircraft moves along glissade in 5 kilometers overhead, pick up camera absorption aircraft picture, and upload emission by this picture is wireless; Airborne image receiver receives the aircraft picture that pick up camera is taken in, and the aviator keeps suitable horizontal velocity and descending speed according to the picture operating aircraft, and makes all the time aircraft in the picture center, completes the aircraft accuracy.
A kind of aircraft accuracy vision system, comprise ground image emission coefficient and airborne image receiving system, between described ground image emission coefficient and airborne image receiving system, by the S-band radiowave, receives and dispatches (referring to Fig. 1);
Described ground image emission coefficient comprises center camera 1, and described center camera 1 is connected (referring to Fig. 2) successively with signal-conversion equipment 2, picture transmitter 3, radio-frequency power amplifier 4 and emitting antenna 5 respectively;
Described center camera 1 is a commercially available high-definition camera, is arranged on airport aircraft landing point upper, and during installation, the elevation angle remains 3.5 °, and lens direction is over against the landing aircraft.
Described signal-conversion equipment 2: mainly by 5 the electric circuit constitutes, they are circuit D10, circuit D12, circuit D13, circuit D14, circuit D15, wherein circuit D10 completes center camera 1 specific image signal and takes out and draw and export, circuit D12 settling signal automatic gain control function, circuit D13, D14, the scrambling of D15 settling signal is processed, and keeps the stability and the confidentiality that transmit; Circuit D10 includes 3 parts, we are defined as D10D, D10B, D10C. the output of circuit D10D, D15 is connected with the input end of circuit D12, the output of circuit D12 is connected with the input end of circuit D13, and the output of circuit D13 is connected with the input end of circuit D14, and the output of circuit D14 is connected with the input end of circuit D12, output while and the circuit D10B of circuit D12, the input end of D10C connects.(referring to Fig. 8)
Described picture transmitter 3 adopts commercially available WL-2405T picture transmitter, and its is inner integrated radio-frequency power amplifier is modulated into the radio frequency signal of video signal for the specific image signal by center camera 1 and adopts the form of radio magnetic wave to be sent in the air.
Described emitting antenna 5 is 2.4GHz vertical polarization plate aerials, and downrange is perpendicular to antenna panel, and 60 ° of cone angles, form a horn-like emitting electromagnetic wave field.Must keep downrange and ground angle during installation is 3.5 °.
Described airborne image receiving system comprises airborne antenna 6, described airborne antenna 6(3255 pocket knife antenna) on to be connected with integrated image receiver 7(model in turn be XTX-1) and airborne display plotter 8(model be XXS-1) (referring to Fig. 3);
Described airborne image receiving system receives the specific image information of center, ground camera 1 in real time, helps the aviator accurately to land.
The airborne display plotter 8 of described XXS-1 is arranged on aircraft cockpit, completes image and shows.
Described airborne antenna 6 is 3255 pocket knife antennas; Be arranged on the left belly of plane nose, omnidirectional receives the 2.4GHz radio picture signal that picture transmitter is launched.
Described integrated image receiver 7 is by power module 9, signal receiving module 10, and signal demodulation module 11 and signal conversion module 12 form (referring to Fig. 4);
Described power module 9 is output as demodulation module 11 and 12 power supplies of signal conversion module, the mouth of described power module 9 is connected with the input end of signal demodulation module 11 and the input end of signal conversion module 12, the mouth of signal receiving module 10 is connected with the input end of signal demodulation module 11, the mouth of described signal demodulation module 11 is connected (referring to Fig. 4 and Fig. 5) with the input end of signal conversion module 12, receive in real time the graphicinformation of ground central camera 1, demodulation also shows by the airborne image of XXS-1.
Described power module 9 is switch power modules, and it can be+5V by DC28V isolated variable on aircraft ,-5V, and+12V output, offer signal conversion module 12 and signal demodulation module 11.2A is the DC28V input socket, and J1 is vdc+5V ,-5V ,+12V accessory power outlet.(referring to Fig. 4 Fig. 5)
Described signal receiving module 10 is the radiofrequency signal receiver module, by the J3 radio frequency socket, with airborne antenna 6, is connected, and the received RF picture signal, output intermediate frequency picture signal is to signal demodulation module 11; (referring to Fig. 4 Fig. 5)
The signal that described signal demodulation module 11 is sent signal receiving module 10 here is demodulated to the vision signal number of delivering letters conversion module 12, J2 socket settling signal output and+the 12V input, the input of J8 socket settling signal; (referring to Fig. 4, Fig. 5)
Described signal conversion module 12 settling signal deciphering conversion, J4 is the coded signal input, J5 is decrypted signal output.(referring to Fig. 4, Fig. 5)
Fig. 6 is airborne image receiving system circuit diagram, has marked in detail the input/output relation between modules equipment in figure.Airborne antenna 6 is connected with the J3 of signal receiving module 10 on integrated image receiver 7 by the N-type plug, and signal conversion module 12 outputting standard vision signals, and the TNC plug of linking airborne display plotter 8 by J5, carry out the image demonstration.
Fig. 7 is ground image emission coefficient circuit diagram, has marked in detail the annexation between each equipment in figure.The power supply of ground image emission subsystem is AC220V.
Aircraft accuracy vision system using method is described as follows:
At aircraft landing point, a set of ground image emission coefficient (the right 1/2/3/4/5 in figure) has been installed, a set of airborne image receiving system (scheming left 6/7/8) has been installed aboard.Between ground image emission coefficient and airborne image receiving system, signal is received and dispatched the aircraft landing picture signal by S-band.
Center camera (1)---a high-definition camera is arranged on the aircraft landing point, with the ground level angle be 3.5 °, keep the visual field and aircraft glissade heavy with, when aircraft moves along glissade in 5 kilometers overhead, pick up camera is taken in landing aircraft picture, and the plane nose marking point is all the time in picture cross line center, when the plane nose marking point departs from picture cross line center up and down, also show that aircraft has departed from landing point all around, show that on the upper side aircraft will land over landing point, show that on the lower side aircraft will shift to an earlier date landing point and land, the right side of taking back shows that aircraft landing point is not on the line of centers of airport.
When aircraft completes four turnings, appear at apart from overhead, 5～10 kilometers, airport, while aiming at airfield runway preparation landing, the airborne antenna 6 that is contained in the left front below of plane nose just can receive the radiofrequency signal of the aircraft landing picture of 5 beam transmission of emitting antenna, airborne antenna 6 is given the signal received the signal receiving module 10 of the integrated image receiver 7 that is contained in the left front cabin of plane nose, through signal demodulation module 11, radio picture signal is demodulated into to video signal, through signal conversion module 12, video signal being transformed to video standard signal gives the airborne display plotter that is contained in aircraft cockpit 8 demonstrations, for the aviator, watch, the situation operating aircraft that the aviator departs from picture cross line center up and down according to marking point in picture keeps reasonable attitude and horizontal velocity and descending speed, and make aircraft markings point all the time in the picture center, like this, glide paths overlap with the glissade ideal value, complete the aircraft accuracy.
When aircraft, by after landing point, airborne display plotter 8 shows the sky scene, blank screen after 5 seconds, and while again landing, screen is lighted demonstration again.Like this, can avoid disperseing aviator's attention of flying, guarantee flight safety.
At the beginning of 2013, the utility model is installed on certain airport, through 8 group of 48 sortie accuracy training, uses, the aviator feels good, elementary training (the 1st, 2,3 groups) accurate some rate brings up to 55 ﹪ by 22 ﹪, intermediate training (the 4th, 5,6 groups) accurate the some rate bring up to 78 ﹪ by 55 ﹪, advanced training the (the 7th, 8, group) accurate some rate is brought up to 100 ﹪ by 83 ﹪, be below some training statistical report form;
Claims (5)
1. an aircraft accuracy vision system is characterized in that: comprise ground image emission coefficient and airborne image receiving system, receive and dispatch by the S-band radiowave between described ground image emission coefficient and airborne image receiving system;
Described ground image emission coefficient comprises center camera (1), and described center camera (1) is connected successively with signal-conversion equipment (2), picture transmitter (3), radio-frequency power amplifier (4) and emitting antenna (5) respectively;
Described airborne image receiving system comprises airborne antenna (6), is connected with integrated image receiver (7) and airborne display plotter (8) on described airborne antenna (6) in turn.
2. a kind of aircraft accuracy vision system according to claim 1, it is characterized in that: described integrated image receiver is by power module (9), signal receiving module (10), signal demodulation module (11) and signal conversion module (12) form, the mouth of described power module (9) is connected with the input end of signal demodulation module (11) and the input end of signal conversion module (12), the mouth of signal receiving module (10) is connected with the input end of signal demodulation module (11), the mouth of described signal demodulation module (11) is connected with the input end of signal conversion module (12).
3. a kind of aircraft accuracy vision system according to claim 2, it is characterized in that: described airborne antenna (6) is 3255 pocket knife antennas.
4. a kind of aircraft accuracy vision system according to claim 2, it is characterized in that: the model of described airborne display plotter (8) is: XXS-1.
5. a kind of aircraft accuracy vision system according to claim 2, it is characterized in that: integrated image receiver (7) model is: XTX-1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013201949170U CN203318684U (en) | 2013-04-17 | 2013-04-17 | Aircraft fixed-point landing image system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013201949170U CN203318684U (en) | 2013-04-17 | 2013-04-17 | Aircraft fixed-point landing image system |
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| CN203318684U true CN203318684U (en) | 2013-12-04 |
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| CN2013201949170U Expired - Lifetime CN203318684U (en) | 2013-04-17 | 2013-04-17 | Aircraft fixed-point landing image system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104469306A (en) * | 2014-12-08 | 2015-03-25 | 河北汉光重工有限责任公司 | Plane grounding parameter detecting device |
| CN105278541A (en) * | 2015-09-02 | 2016-01-27 | 蔡兆旸 | Aircraft auxiliary landing control method and system |
| CN105730705A (en) * | 2016-02-14 | 2016-07-06 | 中国船舶工业系统工程研究院 | Aircraft camera shooting positioning system |
| CN105758397A (en) * | 2016-02-14 | 2016-07-13 | 中国船舶工业系统工程研究院 | Flying vehicle image pickup positioning method |
| US10824168B2 (en) | 2015-07-06 | 2020-11-03 | Zero Co., Ltd. | Rotorcraft landing device |
-
2013
- 2013-04-17 CN CN2013201949170U patent/CN203318684U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104469306A (en) * | 2014-12-08 | 2015-03-25 | 河北汉光重工有限责任公司 | Plane grounding parameter detecting device |
| US10824168B2 (en) | 2015-07-06 | 2020-11-03 | Zero Co., Ltd. | Rotorcraft landing device |
| US11747829B2 (en) | 2015-07-06 | 2023-09-05 | Aeronext Inc. | Rotorcraft landing device |
| CN105278541A (en) * | 2015-09-02 | 2016-01-27 | 蔡兆旸 | Aircraft auxiliary landing control method and system |
| CN105278541B (en) * | 2015-09-02 | 2018-08-17 | 盐城智博科技有限公司 | A kind of aircraft auxiliary landing control method and system |
| CN105730705A (en) * | 2016-02-14 | 2016-07-06 | 中国船舶工业系统工程研究院 | Aircraft camera shooting positioning system |
| CN105758397A (en) * | 2016-02-14 | 2016-07-13 | 中国船舶工业系统工程研究院 | Flying vehicle image pickup positioning method |
| CN105730705B (en) * | 2016-02-14 | 2017-11-10 | 中国船舶工业系统工程研究院 | A kind of aircraft camera positioning system |
| CN105758397B (en) * | 2016-02-14 | 2018-09-25 | 中国船舶工业系统工程研究院 | A kind of aircraft camera positioning method |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131204 |