CN107146475A - Ground service system, airborne guiding system and aircraft enter nearly Landing Guidance System - Google Patents
Ground service system, airborne guiding system and aircraft enter nearly Landing Guidance System Download PDFInfo
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- CN107146475A CN107146475A CN201710419763.3A CN201710419763A CN107146475A CN 107146475 A CN107146475 A CN 107146475A CN 201710419763 A CN201710419763 A CN 201710419763A CN 107146475 A CN107146475 A CN 107146475A
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- 230000011664 signaling Effects 0.000 claims description 4
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- 230000005540 biological transmission Effects 0.000 claims description 2
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- 238000012546 transfer Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 9
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- 230000008569 process Effects 0.000 abstract description 5
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- 230000008859 change Effects 0.000 description 10
- 230000006870 function Effects 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 6
- 230000000007 visual effect Effects 0.000 description 5
- 238000005728 strengthening Methods 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 3
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- 230000009286 beneficial effect Effects 0.000 description 2
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- 230000009471 action Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
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Classifications
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/02—Automatic approach or landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data
- G08G5/025—Navigation or guidance aids
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
- B64D45/08—Landing aids; Safety measures to prevent collision with earth's surface optical
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
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- General Physics & Mathematics (AREA)
- Traffic Control Systems (AREA)
Abstract
The present invention provides a kind of ground service system and airborne guiding system for entering nearly landing guidance for aircraft, and a kind of aircraft enters nearly Landing Guidance System.Wherein, the ground service system that the present invention is provided, including：Photoelectric sensing apparatus, ground-based server and ground communication facilities.Compared to prior art, the invention by photoelectric sensing apparatus located at airport side and in non-aircraft, so as to shoot the real-time imaging of aircraft landing process from sideline, and the airborne guiding system to aircraft is sent after real-time imaging is merged with reference landing course line, so that pilot is by merging guiding image and guiding image to control the aircraft landing according to the fusion described in the airborne guiding system real time inspection.Pilot can check whether undercarriage puts down safely according to this, meanwhile, system has the advantages that observation picture is more vivid, is easily installed, implements, simple in construction, cost is relatively low.
Description
Technical field
The present invention relates to field of aerospace technology, and in particular to a kind of ground service for entering nearly landing guidance for aircraft
System and airborne guiding system, and a kind of aircraft enter nearly Landing Guidance System.
Background technology
Enter that nearly landing period is normal to flight and flight safety have a very important meaning, such as airplane crash on Yichun airport with
And the airplane crash in the Capital Airport sixties etc., all occur in nearly landing period is entered.Currently the majority airline uses ILS
The guiding that instrument-landing-system is closely landed as entering, the system is the product of the forties, and the world has been reached by constantly improvement
II class standard as defined in civil aviation organization.Due to the limitation of its technical performance, the standard that reach III class is highly difficult.
The synthetic vision system (SVS) that the current U.S. is developed, what comes into a driver's strengthening system (EVS) and enhancing flight scene system
(EFVS) gratifying progress is achieved, our times is also represented and is entering the research direction and level in nearly Landing Guidance System field.
The SVS that Ke Lesi Man of the U.S. develops, is combined by GPS and airport three-dimensional land map, can be in complicated gas
Vector aircraft lands as under the conditions of.Oneself obtains U.S. FAA permissions for it, available on business airplane, it is allowed to which pilot is away from ground 30
Meter Gao Du declines in the case of not seeing runway, but the system uses the three-dimensional land map of simulation, it is impossible to reflect on true runway
Whether have an impact the things of safe landing, hidden danger to security presence so unusable to airline operation person.
The what comes into a driver's strengthening system EVS that the Ke Lesi Man in the U.S. and Ke Lin companies develop, is with fog penetrating function
Forward-looking infrared sensor is installed on aircraft, allows pilot to see runway when entering closely to arrive liftoff certain altitude.The own distich in the U.S.
MD-10/11, A310, A300 of express company of nation and the BBJ business airplanes of Boeing are reequiped.The system needs and flown
Machine producer coordinates installs infrared sensor aboard, and practice is got up relative difficulty in reality, and the system cost is very
It is high.
EFVS is a kind of image sensing technology, in the form of strengthening image, and external environment condition is presented to aircraft in real time and flown
Office staff, it is really the combination of what comes into a driver's strengthening system (EVS) and HUD system (HUD), so EFVS is needed also exist for infrared biography
Sensor is installed aboard so that practice is got up relative difficulty, and cost is very high；In addition, EFVS systems are only entering near
Worked on a bit of glissade landed.
Due to it is above-mentioned enter nearly Landing Guidance System using later, service aircraft if desired configure it is above-mentioned enter nearly landing guidance system
System need to be reequiped, and high cost.Accordingly, it is capable to reference to the advantage and disadvantage of above-mentioned each system, there is provided a kind of simple in construction, installation fee
Very big meaning will be had by entering nearly Landing Guidance System with cheap aircraft.
The content of the invention
For advantage and disadvantage of the prior art, the present invention provides a kind of ground service system for entering nearly landing guidance for aircraft
System and airborne guiding system, and a kind of aircraft enter nearly Landing Guidance System, to lift the efficiency and safety of aircraft glide landing
Ability.
In a first aspect, a kind of ground service system for entering nearly landing guidance for aircraft that the present invention is provided, including：Photoelectricity
Sensing device, ground-based server and ground communication facilities；Wherein,
The photoelectric sensing apparatus is located at airfield runway side, and is communicated to connect with the ground-based server, for gathering
Real-time imaging during aircraft landing, and the real-time imaging is sent to the ground-based server；
The ground-based server is communicated to connect with the ground communication facilities, and the ground-based server receives the real-time shadow
As after, the real-time imaging is merged with the reference landing course line of the runway, and the fusion obtained after fusion is guided
Image is sent to the ground communication facilities；
The ground communication facilities is communicated to connect with the airborne guiding system on aircraft, for the fusion to be guided into image
Send to the airborne guiding system, so that pilot is by merging guiding image described in the airborne guiding system real time inspection
And guide image to control the aircraft landing according to the fusion.
Optionally, the installation of the photoelectric sensing apparatus meets following constraints：The photoelectric sensing apparatus is away from described
The distance of runway and the shooting angle of the photoelectric sensing apparatus make the optical signalling acquisition range bag of the photoelectric sensing apparatus
Scope containing specified location point on therefrom index point to runway.
Optionally, the photoelectric sensing apparatus includes visible light sensor, and/or infrared sensor.
Optionally, the infrared sensor includes passive type thermal infrared imager.
Optionally, the ground service system that nearly landing guidance is entered for aircraft, in addition to：Safe pedestal；
The photoelectric sensing apparatus is installed on the safe pedestal and protrudes from ground, and the safe pedestal is by super
When going out the gravity compressing of predetermined threshold value, the photoelectric sensing apparatus dropped into below ground so that the photoelectric sensing apparatus
Top surface is parallel to the ground.
Optionally, the ground service system that nearly landing guidance is entered for aircraft, in addition to：Memory；
The memory is communicated to connect with the ground-based server, and the fusion is also guided image by the ground-based server
Send to the memory and stored.
Optionally, the photoelectric sensing apparatus is communicated to connect using optical fiber with the ground-based server.
Second aspect, a kind of airborne guiding system for entering nearly landing guidance for aircraft that the present invention is provided, including：It is airborne
Communication equipment and display device；
The ground service system described in any one that the airborne communication control is provided with the present invention is communicated to connect, for connecing
The fusion guiding image that the ground service system is sent is received, and guides image to be forwarded to the display device fusion；
The display device is used to show the fusion guiding image, so that pilot guides image control according to the fusion
Make the aircraft landing.
Optionally, the display device includes：Head-up display.
A kind of third aspect, aircraft that the present invention is provided enters nearly Landing Guidance System, including：Any one that the present invention is provided
The airborne guiding system that described ground service system and the present invention is provided；
The ground service system and the airborne guiding system communication connection；
The ground service system is used to gathering real-time imaging during aircraft landing, and by the real-time imaging and institute
The reference landing course line for stating runway is merged, and the fusion obtained after fusion guiding image is sent to the airborne guiding
System；
The airborne guiding system is used to show the fusion guiding image received in real time, so that pilot is according to institute
State fusion guiding image and control the aircraft landing.
As shown from the above technical solution, a kind of ground service system for entering nearly landing guidance for aircraft that the present invention is provided
System, including：Photoelectric sensing apparatus, ground-based server and ground communication facilities.Compared to prior art, the general of the invention
Photoelectric sensing apparatus located at airport side and in non-aircraft so that from sideline shoot aircraft landing process real-time imaging, and
The airborne guiding system to aircraft is sent after real-time imaging is merged with reference landing course line so that pilot pass through it is described
Fusion guiding image described in airborne guiding system real time inspection simultaneously guides image to control the aircraft landing according to the fusion.Tool
Have the advantage that：
1) compared with ILS：Pilot understands the truth of aircraft accordingly by can see real-time video picture,
Observe picture more vivid.
2) compared with SVS：The runway and aircraft that SVS is used are the virtual data set up by three-dimensional artificial, pilot's profit
The actual conditions on current runway can not be viewed with SVS systems, and the system is real-time True Data, what pilot saw is
True runway, actual airplane.
3) compared with EVS and SVS：Because the system is arranged on runway side, pilot, which is sitting in driving cabin, to be seen
To the flight attitude of not having gear down for oneself aircraft, and oneself aircraft, and EVS and SVS is installed aboard, so
This point can not be accomplished.
4) reference landing that pilot can provide during declining, landing and sliding with reference to fusion guiding image
Course line drives an airplane；And ILS, EFVS are required for by visual observation operating in last landing period, therefore, the system can be kept away
Exempt to land after landing or float in advance caused by visual deviation, security is higher, and can lift the efficiency of aircraft glide landing.
5) the system is the system of independent completion, varies without existing equipment on aircraft, does not interfere with and leads to international
Boat, is easily installed, implements, and simple in construction, and cost is relatively low.
6) pilot utilizes the system, can real time inspection undercarriage situation, it is to avoid undercarriage is not put in descent
Under cause security incident.
What the present invention was provided a kind of enter the airborne guiding system of nearly landing guidance for aircraft and is and above-mentioned ground service system
What system was used cooperatively, with above-mentioned ground service system for identical inventive concept, with identical beneficial effect.
It is to be based on above-mentioned ground service system and airborne guiding that a kind of aircraft that the present invention is provided, which enters nearly Landing Guidance System,
What system was realized, with above-mentioned ground service system for identical inventive concept, with identical beneficial effect.
Brief description of the drawings
, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical scheme of the prior art
The accompanying drawing used required in embodiment or description of the prior art is briefly described.In all of the figs, similar element
Or part is general by similar reference mark.In accompanying drawing, each element or part might not be drawn according to actual ratio.
Fig. 1 shows a kind of ground service system for entering nearly landing guidance for aircraft that first embodiment of the invention is provided
The schematic diagram of system；
Fig. 2 shows a kind of angularly disposed schematic top plan view of photoelectric sensing apparatus that the embodiment of the present invention is provided；
Fig. 3 shows showing for the angularly disposed corresponding fusion guiding image of photoelectric sensing apparatus provided in an embodiment of the present invention
It is intended to；
Fig. 4 shows that the vertically disposed aircraft of a kind of photoelectric sensing apparatus that the embodiment of the present invention is provided enters near land and drawn
The schematic diagram of guiding systems；
Fig. 5 shows that a kind of angularly disposed aircraft of photoelectric sensing apparatus that the embodiment of the present invention is provided enters near land and drawn
The schematic diagram of guiding systems.
Embodiment
The embodiment of technical solution of the present invention is described in detail below in conjunction with accompanying drawing.Following examples are only used for
Clearly illustrate technical scheme, therefore be intended only as example, and the protection of the present invention can not be limited with this
Scope.
It should be noted that unless otherwise indicated, technical term or scientific terminology used in this application should be this hair
The ordinary meaning that bright one of ordinary skill in the art are understood.
The present invention provides a kind of ground service system and airborne guiding system for entering nearly landing guidance for aircraft, Yi Jiyi
Plant aircraft and enter nearly Landing Guidance System, wherein, the ground service system is to coordinate to implement with the airborne guiding system, and
Collectively constitute the aircraft and enter nearly Landing Guidance System.The ground service system is laid in airdrome scene, for gathering aircraft
Real-time imaging in landing mission, and accordingly generate fusion guiding image and send to airborne guiding system, in airborne guiding system
Provided with display device to show the fusion guiding image in real time, so, pilot can fusion guiding shadow described in real time inspection
Picture, and determine that entering for current aircraft closely lands whether on reference landing course line, so that it is guaranteed that aircraft landing circuit is correct,
If not on reference landing course line, aircraft can be adjusted in time into the reference landing course line, and then drawn according to the fusion
Lead image and control the aircraft landing.
The technical concept of the present invention is based on following principle：
The runway on airport is changeless after fixing, so the center line of runway and its be also not along long line (course line)
Become.If after gliding angle regulation, the glissade formed be also it is constant, course line and glissade combine form it is winged
Machine enters the course line closely landed, and is also constant.It is runway, neighbouring if photoelectric sensing apparatus is fixedly mounted on runway side
The point position that reference landing course line of scenery and aircraft landing etc. is shown on video pictures is also changeless, so standard
Land course line can be drawn by the method for mapping, to be presented in the form of fixing straight line on picture, in the straight line representation theory most
Accurate reference landing course line, the reference landing course line is unrelated with weather quality.Above-mentioned principle can refer to Fig. 1 and be understood.
Embodiments of the invention are illustrated below in conjunction with the accompanying drawings.
It refer to Fig. 1, what Fig. 1 showed that first embodiment of the invention is provided a kind of enters nearly landing guidance for aircraft
The schematic diagram of ground service system.As shown in figure 1, the one kind provided according to a first embodiment of the present invention enters nearly landing for aircraft
The ground service system of guiding includes：Photoelectric sensing apparatus 101, ground-based server 102 and ground communication facilities 103；Wherein,
The photoelectric sensing apparatus 101 is located at airfield runway side, and is communicated to connect with the ground-based server 102, uses
Real-time imaging during collection aircraft landing, and the real-time imaging is sent to the ground-based server 102；
The ground-based server 102 is communicated to connect with the ground communication facilities 103, and the ground-based server 102 is received
After the real-time imaging, the real-time imaging is merged with the reference landing course line of the runway, and will be obtained after fusion
Fusion guiding image send to the ground communication facilities 103；
The ground communication facilities 103 is communicated to connect with the airborne guiding system on aircraft, for the fusion to be guided
Image is sent to the airborne guiding system, so that pilot is guided by being merged described in the airborne guiding system real time inspection
Image simultaneously guides image to control the aircraft landing according to the fusion.
Wherein, in a change embodiment of first embodiment of the invention, ground-based server 102 is the center of system
Process part, the desktop computer of mainstream configuration is all processing that the system can be achieved, for the particularity of airport security, can be with
Using commercial common desktop computer；
The process that the ground-based server 102 is merged the real-time imaging with the reference landing course line of the runway
It is as follows：
1) real-time video (i.e. real-time imaging) of infrared sensor (one kind of photoelectric sensing apparatus) acquisition is received, decoding should
Video；
2) reference landing course line is drawn in the video pictures of real-time imaging, the reference landing course line is available in video pictures
Single straight line, multi straight, cube pipeline are represented, are recommended using single straight line, concise；
3) decision height line, straight line table of the decision height perpendicular to course line are drawn in the video pictures of real-time imaging
Show, decision height, such as 60 meters, 30 meters can be superimposed with beside decision height line；
By above-mentioned steps 1) -3), fusion process is completed, fusion guiding image is obtained.Next, ground-based server 102
The fusion guiding image that drafting can be had to reference landing course line and decision height line is transported to memory, while the fusion is drawn
Image is led to be transferred on aircraft using ground communication facilities 103.
Change embodiment as one of first embodiment of the invention, in order that pilot can intuitively view it is winged
Machine actual flight path complete in nearly landing mission is entered and the match condition in reference landing course line, the photoelectric sensing apparatus 101
Installation meet following constraints：Distance and the photoelectric sensing apparatus of the photoelectric sensing apparatus 101 away from the runway
101 shooting angle makes the optical signalling acquisition range of the photoelectric sensing apparatus 101 include finger on therefrom index point to runway
Determine the scope of location point.
Wherein, the middle index point refers to the corresponding index point of 60m decision heights, and the specified location point can be runway
On any point, for example, it is contemplated that can determine that safe landing when typically being slided to aircraft in the middle part of runway, runway can be selected
The certain point in centre position is used as specified location point.It is easily understood that those skilled in the art can set according to the actual requirements
The position of the photoelectric sensing apparatus 101 is put, for example, including the optical signalling acquisition range of the photoelectric sensing apparatus 101
From outer index point to the scope of course platform, with gather aircraft from enter nearly anchor point to landing complete overall process.
The photoelectric sensing apparatus 101 can install (as shown in Figure 1) perpendicular to runway, to shoot aircraft from side pros
Landing mission, can also be diagonally-installed in sideline, using almost just to aircraft by the way of shoot, such as Fig. 2, Fig. 3 institute
Show, it is respectively that a kind of angularly disposed schematic top plan view of photoelectric sensing apparatus provided in an embodiment of the present invention and the present invention are real
The schematic diagram of the angularly disposed corresponding fusion guiding image of photoelectric sensing apparatus of example offer is provided, as seen from the figure, set using oblique
The mode put, can shoot from the angle almost just to aircraft, compared to the mode installed perpendicular to runway, apart from runway
Can be closer to, by periphery apart from the aircraft landed also more recently, therefore the real-time imaging shot becomes apparent from, effect is more preferable
The influence of other runways is smaller and the visual field is farther.
In the specific embodiment that first embodiment of the invention is provided, the photoelectric sensing apparatus 101 is arranged on
Apart from the first 1000 meters of right positions of runway, so achievable monitoring aircraft declines the overall process with landing flare.
In another change embodiment of first embodiment of the invention, the photoelectric sensing apparatus 101 includes visible
Optical sensor, and/or infrared sensor.For example, it is possible to use only visible light sensor such as video camera etc. gathers visible light signal,
But target is difficult at night or haze weather in this case, in this regard, infrared letter can also be gathered using infrared sensor
Number, because airplane tail spray temperature is up to 500 degree, can accurately it be caught far above peripheral temperature, therefore using infrared sensor
The flight path of aircraft, it is of course also possible to set visible light sensor and/or infrared sensor simultaneously, so gather simultaneously visible ray with
Infrared signal, function is more powerful, adapts to sporting flying different demands and various weather conditions.
Specifically, in another change embodiment of first embodiment of the invention, the infrared sensor can be adopted
Passive type thermal infrared imager is used, passive type thermal infrared imager does not launch light source actively, the vision of pilot will not be produced any
Influence.
In another change embodiment of first embodiment of the invention, the ground that nearly landing guidance is entered for aircraft
Face service system, in addition to：Safe pedestal；
The photoelectric sensing apparatus 101 is installed on the safe pedestal and protrudes from ground, the safe pedestal by
When being oppressed to the gravity beyond predetermined threshold value, the photoelectric sensing apparatus 101 is dropped into below ground so that the photoelectric transfer
The top surface of induction device 101 is parallel to the ground.
In a specific embodiment, the safe pedestal uses stress damage-type structure, is receiving weight more than 15-
During 20kg external impacts, safe pedestal automatic crushing, and then the photoelectric sensing apparatus sink to automatically it is flat with Airport Surface
OK, it is to avoid produce security incident.
In another change embodiment of first embodiment of the invention, the ground that nearly landing guidance is entered for aircraft
Face service system, in addition to：Memory；
The memory is communicated to connect with the ground-based server 102, and the ground-based server 102 also draws the fusion
Lead image and send to the memory and stored.The memory is mainly used in storing the result that ground-based server 102 is exported
Picture, the important references as ex-post analysis；Requirement can be met using the memory of common configuration.
In another change embodiment of first embodiment of the invention, the photoelectric sensing apparatus 101 uses optical fiber
Communicated to connect with the ground-based server 102.The optical fiber is used for the real-time pictures for transmitting the acquisition of photoelectric sensing apparatus 101, can
Using single mode single or single-mode dual-core optical fiber, preferably can use single mode single, you can meet requirements of real time, and can drop
Low cost.The ground communication facilities 103 is connected with airborne communication control 201 using communication, specifically, can profit
Realize that the embodiment of the present invention is not limited, and those skilled in the art can with airport existing communication equipment or the mobile 5G communication technologys
To realize the present invention using other wireless communication technologys after flexible change, it is also within protection scope of the present invention.
Fig. 4, Fig. 5 are refer to, is vertically set which respectively show a kind of photoelectric sensing apparatus that the embodiment of the present invention is provided
The schematic diagram and a kind of angularly disposed aircraft of photoelectric sensing apparatus that the aircraft put enters nearly Landing Guidance System enter near land and drawn
The schematic diagram (set-up mode of both photoelectric sensing apparatus is different, and corresponding fusion guiding image is also different) of guiding systems, according to
Fig. 4, Fig. 5, the aircraft enter nearly Landing Guidance System and are made up of ground service system and airborne guiding system, below based on
Fig. 4, Fig. 5 are illustrated to second embodiment of the invention and 3rd embodiment.
Second embodiment of the invention provides a kind of airborne guiding system for entering nearly landing guidance for aircraft, due to the machine
It is to coordinate to implement with the ground service system to carry guiding system, therefore partial content repeats no more, relevant portion incorporated by reference to
The explanation of above-mentioned first embodiment is understood.As shown in Figure 4, Figure 5, one kind that second embodiment of the invention is provided is used for aircraft
Entering the airborne guiding system of nearly landing guidance includes：Airborne communication control 201 and display device 202；
The airborne communication control 201 is communicated to connect with the ground service system that the present invention is provided, for receiving
The fusion guiding image of ground service system transmission is stated, and guides image to be forwarded to the display device 202 fusion；
The display device 202 is used to show the fusion guiding image, so that pilot guides shadow according to the fusion
As controlling the aircraft landing.
Fig. 4, Fig. 5 are refer to, by the display device 202 of the airborne guiding system, pilot can intuitively check
To the real-time flight posture of aircraft and reference landing course line and decision height line, so that it is guaranteed that the correct nothing of aircraft landing circuit
By mistake, if not on reference landing course line, aircraft can be adjusted in time into the reference landing course line, and then according to the fusion
Image is guided to control the aircraft landing.
In a change embodiment of first embodiment of the invention, the display device 202 can use and look squarely aobvious
Show device.Head-up display (Head Up Display), abbreviation HUD is with flight supplementary instrument on aircraft at present on aircraft.Look squarely
Be meant that pilot need not bow just it can be seen that he need important information., can be more using head-up display
Facilitate pilot's real time inspection fusion guiding image, it is to avoid notice is interrupted and lost to situationawareness (Situation
Awareness grasp), it is ensured that safely, smoothly land.
Third embodiment of the invention provides a kind of aircraft and enters nearly Landing Guidance System, because the aircraft enters nearly landing guidance
System is made up of ground service system and airborne guiding system, therefore partial content is repeated no more, relevant portion incorporated by reference to
The explanation of above-mentioned first embodiment and second embodiment is understood.As shown in Figure 4, Figure 5, third embodiment of the invention is provided
A kind of aircraft enters nearly Landing Guidance System, including：It is airborne that the ground service system and the present invention that the present invention is provided are provided
Guiding system；
The ground service system and the airborne guiding system communication connection；
The ground service system is used to gathering real-time imaging during aircraft landing, and by the real-time imaging and institute
The reference landing course line for stating runway is merged, and the fusion obtained after fusion guiding image is sent to the airborne guiding
System；
The airborne guiding system is used to show the fusion guiding image received in real time, so that pilot is according to institute
State fusion guiding image and control the aircraft landing.
The aircraft that the present invention is provided enters nearly Landing Guidance System, and ingenious utilization aircraft enters glide path during nearly landing
Immobilize, on this basis with reference to photoelectric sensing apparatus 101 and display device 202, construct a kind of simple, image but very
Accurately enter nearly landing guidance method, with advantages below：
(1) compared with ILS：Pilot by the system see for real-time video picture, and can see oneself and fly
The truth of machine, it is therefore, more vivid, directly perceived；
(2) compared with EFVS：EFVS is to install infrared sensor aboard, the temperature difference of detection runway and environment, and
Infrared sensor can be arranged on runway side by the system, detect aerial aircraft, and in aircraft operation, tail spray temperature is up to 500
Degree, therefore, the system detection range is farther；The video pictures that EFVS is provided are the enhancing video image outside machine, without standard
Glide path, so, can only be worked on a bit of glissade closely landed is entered, and the system during whole glide all
Work.
(3) compared with SVS：The runway and aircraft that SVS is used are the virtual data set up by three-dimensional artificial, pilot's profit
The actual conditions on current runway can not be viewed with SVS systems, and the system is real-time True Data, what pilot saw is
True runway, actual airplane.
(4) compared with EVS and SVS：Because the system is arranged on runway side, pilot, which is sitting in driving cabin, to be seen
To the flight attitude of not having gear down for oneself aircraft, and oneself aircraft, and EVS and SVS is installed aboard, so
This point can not be accomplished；
(5) pilot can drive during declining, landing and sliding with reference to the reference landing course line provided
Aircraft；And ILS, EFVS are required for by visual observation operating in last landing period, therefore, the system can avoid visual deviation
It is caused land or float in advance after land.
(6) the system is the system of independent completion, varies without existing equipment on aircraft, does not interfere with and leads to international
Boat, is easily installed, implements, and simple in construction, and cost is relatively low.
(7) pilot utilizes the system, can real time inspection undercarriage situation, it is to avoid undercarriage is not put in descent
Under cause security incident.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " change an embodiment party
The description of formula ", " example ", " specific example " or " some examples " etc. means to combine the specific spy that the embodiment or example are described
Levy, structure, material or feature are contained at least one embodiment of the present invention or example.In this manual, to above-mentioned
The schematic representation of term is necessarily directed to identical embodiment or example.Moreover, the specific features of description, structure, material
Material or feature can in an appropriate manner be combined in any one or more embodiments or example.In addition, not conflicting
In the case of, those skilled in the art can be by the not be the same as Example or example and non-be the same as Example described in this specification
Or the feature of example is combined and combined.
It should be noted that the flow chart and block diagram in accompanying drawing show according to the present invention multiple embodiments system,
Architectural framework in the cards, function and the operation of method and computer program product.At this point, in flow chart or block diagram
Each square frame can represent a part for a module, program segment or code, the part bag of the module, program segment or code
Containing one or more executable instructions for being used to realize defined logic function.It should also be noted that in some realities as replacement
In existing, the function of being marked in square frame can also be with different from the order marked in accompanying drawing generation.For example, two continuous sides
Frame can essentially be performed substantially in parallel, and they can also be performed in the opposite order sometimes, and this is according to involved function
It is fixed.It is also noted that the group of each square frame in block diagram and/or flow chart and the square frame in block diagram and/or flow chart
Close, can be realized with the special hardware based system of defined function or action is performed, or specialized hardware can be used
Combination with computer instruction is realized.
, can be with several embodiments provided herein, it should be understood that disclosed systems, devices and methods
Realize by another way.Device embodiment described above is only schematical, for example, multiple units or component can
To combine or be desirably integrated into another system, or some features can be ignored, or not perform.It is another, it is shown or beg for
The coupling each other of opinion or direct-coupling or communication connection can be by some communication interfaces, device or unit it is indirect
Coupling is communicated to connect, and can be electrical, machinery or other forms.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, or which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme, it all should cover among the claim of the present invention and the scope of specification.
Claims (10)
1. a kind of ground service system for entering nearly landing guidance for aircraft, it is characterised in that including：Photoelectric sensing apparatus,
Face server and ground communication facilities；Wherein,
The photoelectric sensing apparatus is located at airfield runway side, and is communicated to connect with the ground-based server, for gathering aircraft
Real-time imaging in landing mission, and the real-time imaging is sent to the ground-based server；
The ground-based server is communicated to connect with the ground communication facilities, and the ground-based server receives the real-time imaging
Afterwards, the real-time imaging is merged with the reference landing course line of the runway, and the fusion obtained after fusion is guided into shadow
As sending to the ground communication facilities；
The ground communication facilities is communicated to connect with the airborne guiding system on aircraft, for guiding image to send the fusion
To the airborne guiding system, so that pilot is by merging guiding image and root described in the airborne guiding system real time inspection
Image is guided to control the aircraft landing according to the fusion.
2. the ground service system according to claim 1 for entering nearly landing guidance for aircraft, it is characterised in that the light
The installation of electrical sensor apparatus meets following constraints：Distance and the photoelectric transfer of the photoelectric sensing apparatus away from the runway
The shooting angle of induction device makes the optical signalling acquisition range of the photoelectric sensing apparatus include finger on therefrom index point to runway
Determine the scope of location point.
3. the ground service system according to claim 1 for entering nearly landing guidance for aircraft, it is characterised in that the light
Electrical sensor apparatus includes visible light sensor, and/or infrared sensor.
4. the ground service system according to claim 3 for entering nearly landing guidance for aircraft, it is characterised in that described red
Outer sensor includes passive type thermal infrared imager.
5. the ground service system according to claim 1 for entering nearly landing guidance for aircraft, it is characterised in that also wrap
Include：Safe pedestal；
The photoelectric sensing apparatus is installed on the safe pedestal and protrudes from ground, and the safe pedestal is by beyond pre-
If during the gravity compressing of threshold value, the photoelectric sensing apparatus is dropped into below ground so that the top surface of the photoelectric sensing apparatus
It is parallel to the ground.
6. the ground service system according to claim 1 for entering nearly landing guidance for aircraft, it is characterised in that also wrap
Include：Memory；
The memory is communicated to connect with the ground-based server, and the fusion is also guided image to send by the ground-based server
Stored to the memory.
7. the ground service system according to claim 1 for entering nearly landing guidance for aircraft, it is characterised in that the light
Electrical sensor apparatus is communicated to connect using optical fiber with the ground-based server.
8. a kind of airborne guiding system for entering nearly landing guidance for aircraft, it is characterised in that including：Airborne communication control and aobvious
Show equipment；
The airborne communication control is communicated to connect with the ground service system described in claim any one of 1-7, for receiving
The fusion guiding image of ground service system transmission is stated, and guides image to be forwarded to the display device fusion；
The display device is used to show the fusion guiding image, so that pilot guides image control institute according to the fusion
State aircraft landing.
9. the airborne guiding system according to claim 8 for entering nearly landing guidance for aircraft, it is characterised in that described aobvious
Show that equipment includes：Head-up display.
10. a kind of aircraft enters nearly Landing Guidance System, it is characterised in that including：Ground clothes described in claim any one of 1-7
Airborne guiding system described in business system and claim 8 or 9；
The ground service system and the airborne guiding system communication connection；
The ground service system is used to gather the real-time imaging during aircraft landing, and the real-time imaging is run with described
The reference landing course line in road is merged, and the fusion obtained after fusion guiding image is sent to the airborne guiding system
System；
The airborne guiding system is used to show the fusion guiding image received in real time, so that pilot is melted according to described
Close guiding image and control the aircraft landing.
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| CN201710419763.3A CN107146475B (en) | 2017-06-06 | 2017-06-06 | Ground service system, airborne guiding system and aircraft approach landing guiding system |
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|---|---|---|---|
| CN201710419763.3A CN107146475B (en) | 2017-06-06 | 2017-06-06 | Ground service system, airborne guiding system and aircraft approach landing guiding system |
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| CN107146475B CN107146475B (en) | 2023-07-18 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108363034A (en) * | 2018-03-20 | 2018-08-03 | 陈昌志 | Pyromagnetic beacon Penetrating Fog navigation landing system |
| CN108974374A (en) * | 2018-08-08 | 2018-12-11 | 缪纪生 | Round-the-clock what comes into a driver's talk down system |
| CN109613929A (en) * | 2018-12-12 | 2019-04-12 | 北京卫星信息工程研究所 | A kind of flight precision approach and landing concept and system |
| CN111899571A (en) * | 2020-07-29 | 2020-11-06 | 成都民航空管科技发展有限公司 | Method and system for automatically adjusting flight approach procedure based on AMAN system |
| CN112009712A (en) * | 2020-08-21 | 2020-12-01 | 深圳安航科技有限公司 | Helicopter emergency rescue system and method thereof |
| CN113766715A (en) * | 2020-06-02 | 2021-12-07 | 璞洛泰珂(上海)智能科技有限公司 | Airport light monitoring method and system, storage medium and terminal |
| CN114999234A (en) * | 2022-05-19 | 2022-09-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Conflict avoiding device |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86103031A (en) * | 1985-04-04 | 1986-12-24 | 森德斯特兰德数据控制公司 | Improved microwave landing system (MLS) |
| JPH08221123A (en) * | 1995-02-10 | 1996-08-30 | Kawasaki Heavy Ind Ltd | Method and device for travel control over moving body |
| DE19521600A1 (en) * | 1995-06-14 | 1996-12-19 | Bodenseewerk Geraetetech | Landing procedures for unmanned aerial vehicles |
| AU3544600A (en) * | 1999-04-08 | 2000-11-14 | Air Services Australia | Air traffic management system |
| DE19950674A1 (en) * | 1999-10-21 | 2001-04-26 | Eads Airbus Gmbh | Device for landing aircraft establishes moving landing base with which speed difference between landing vehicle and fixed runway at touchdown is minimized or completely eliminated |
| RU2007134278A (en) * | 2007-09-17 | 2009-03-27 | Михаил Ильич СВЕРДЛОВ (RU) | LASER AIRCRAFT LANDING SYSTEM |
| US20090140887A1 (en) * | 2007-11-29 | 2009-06-04 | Breed David S | Mapping Techniques Using Probe Vehicles |
| CN101833104A (en) * | 2010-04-27 | 2010-09-15 | 北京航空航天大学 | Three-dimensional visual navigation method based on multi-sensor information fusion |
| CN101923789A (en) * | 2010-03-24 | 2010-12-22 | 北京航空航天大学 | Safe airplane approach method based on multisensor information fusion |
| CN102332214A (en) * | 2011-08-04 | 2012-01-25 | 南京航空航天大学 | Enhanced airport scene monitoring system |
| CN102591352A (en) * | 2010-12-07 | 2012-07-18 | 空中客车营运有限公司 | Method and device for assisting with the visual assessment of a flight path to be followed by an aircraft in a restricted environment |
| EP2516267A1 (en) * | 2009-12-23 | 2012-10-31 | Deutsches Zentrum für Luft- und Raumfahrt e. V. | Control device for aircraft |
| CN103197682A (en) * | 2013-03-22 | 2013-07-10 | 北京航空航天大学 | Unmanned aerial vehicle airport-entering landing gliding channel design and gliding path adjustment method |
| CN104176267A (en) * | 2014-08-20 | 2014-12-03 | 电子科技大学 | Three-dimensional high-directivity infrared aircraft landing guide system |
| US20150375872A1 (en) * | 2014-06-26 | 2015-12-31 | Airbus Helicopters | Method of facilitating the approach to a platform |
| TW201612863A (en) * | 2014-09-23 | 2016-04-01 | Univ Tunghai | Aircraft landing-guiding system and method |
| CN205943105U (en) * | 2016-07-21 | 2017-02-08 | 江苏南大尚诚高科技实业有限公司 | Parking assistant system uses berth sensor |
| CN106708065A (en) * | 2017-01-17 | 2017-05-24 | 览意科技（上海）有限公司 | Unmanned aerial vehicle landing control method, device and unmanned aerial vehicle |
| CN206789069U (en) * | 2017-06-06 | 2017-12-22 | 中国民用航空总局第二研究所 | Ground service system, airborne guiding system and aircraft enter nearly Landing Guidance System |
-
2017
- 2017-06-06 CN CN201710419763.3A patent/CN107146475B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86103031A (en) * | 1985-04-04 | 1986-12-24 | 森德斯特兰德数据控制公司 | Improved microwave landing system (MLS) |
| JPH08221123A (en) * | 1995-02-10 | 1996-08-30 | Kawasaki Heavy Ind Ltd | Method and device for travel control over moving body |
| DE19521600A1 (en) * | 1995-06-14 | 1996-12-19 | Bodenseewerk Geraetetech | Landing procedures for unmanned aerial vehicles |
| AU3544600A (en) * | 1999-04-08 | 2000-11-14 | Air Services Australia | Air traffic management system |
| DE19950674A1 (en) * | 1999-10-21 | 2001-04-26 | Eads Airbus Gmbh | Device for landing aircraft establishes moving landing base with which speed difference between landing vehicle and fixed runway at touchdown is minimized or completely eliminated |
| RU2007134278A (en) * | 2007-09-17 | 2009-03-27 | Михаил Ильич СВЕРДЛОВ (RU) | LASER AIRCRAFT LANDING SYSTEM |
| US20090140887A1 (en) * | 2007-11-29 | 2009-06-04 | Breed David S | Mapping Techniques Using Probe Vehicles |
| EP2516267A1 (en) * | 2009-12-23 | 2012-10-31 | Deutsches Zentrum für Luft- und Raumfahrt e. V. | Control device for aircraft |
| CN101923789A (en) * | 2010-03-24 | 2010-12-22 | 北京航空航天大学 | Safe airplane approach method based on multisensor information fusion |
| CN101833104A (en) * | 2010-04-27 | 2010-09-15 | 北京航空航天大学 | Three-dimensional visual navigation method based on multi-sensor information fusion |
| CN102591352A (en) * | 2010-12-07 | 2012-07-18 | 空中客车营运有限公司 | Method and device for assisting with the visual assessment of a flight path to be followed by an aircraft in a restricted environment |
| CN102332214A (en) * | 2011-08-04 | 2012-01-25 | 南京航空航天大学 | Enhanced airport scene monitoring system |
| CN103197682A (en) * | 2013-03-22 | 2013-07-10 | 北京航空航天大学 | Unmanned aerial vehicle airport-entering landing gliding channel design and gliding path adjustment method |
| US20150375872A1 (en) * | 2014-06-26 | 2015-12-31 | Airbus Helicopters | Method of facilitating the approach to a platform |
| CN104176267A (en) * | 2014-08-20 | 2014-12-03 | 电子科技大学 | Three-dimensional high-directivity infrared aircraft landing guide system |
| TW201612863A (en) * | 2014-09-23 | 2016-04-01 | Univ Tunghai | Aircraft landing-guiding system and method |
| CN205943105U (en) * | 2016-07-21 | 2017-02-08 | 江苏南大尚诚高科技实业有限公司 | Parking assistant system uses berth sensor |
| CN106708065A (en) * | 2017-01-17 | 2017-05-24 | 览意科技（上海）有限公司 | Unmanned aerial vehicle landing control method, device and unmanned aerial vehicle |
| CN206789069U (en) * | 2017-06-06 | 2017-12-22 | 中国民用航空总局第二研究所 | Ground service system, airborne guiding system and aircraft enter nearly Landing Guidance System |
Non-Patent Citations (2)
| Title |
|---|
| 王永庆: "PAR辅助光电设备的飞机着陆监测与评估系统设计", 《航空学报》 * |
| 王永庆: "PAR辅助光电设备的飞机着陆监测与评估系统设计", 《航空学报》, vol. 37, no. 12, 25 December 2016 (2016-12-25), pages 3803 - 3810 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108363034A (en) * | 2018-03-20 | 2018-08-03 | 陈昌志 | Pyromagnetic beacon Penetrating Fog navigation landing system |
| CN108363034B (en) * | 2018-03-20 | 2023-09-22 | 陈昌志 | Thermo-magnetic beacon fog-penetrating navigation landing system |
| CN108974374A (en) * | 2018-08-08 | 2018-12-11 | 缪纪生 | Round-the-clock what comes into a driver's talk down system |
| CN109613929A (en) * | 2018-12-12 | 2019-04-12 | 北京卫星信息工程研究所 | A kind of flight precision approach and landing concept and system |
| CN109613929B (en) * | 2018-12-12 | 2022-11-25 | 北京卫星信息工程研究所 | Flight precision approach and landing method and system |
| CN113766715A (en) * | 2020-06-02 | 2021-12-07 | 璞洛泰珂(上海)智能科技有限公司 | Airport light monitoring method and system, storage medium and terminal |
| CN111899571A (en) * | 2020-07-29 | 2020-11-06 | 成都民航空管科技发展有限公司 | Method and system for automatically adjusting flight approach procedure based on AMAN system |
| CN111899571B (en) * | 2020-07-29 | 2021-11-02 | 成都民航空管科技发展有限公司 | Method and system for automatically adjusting flight approach procedure based on AMAN system |
| CN112009712A (en) * | 2020-08-21 | 2020-12-01 | 深圳安航科技有限公司 | Helicopter emergency rescue system and method thereof |
| CN114999234A (en) * | 2022-05-19 | 2022-09-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Conflict avoiding device |
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