CN107239635A - A kind of virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method - Google Patents
A kind of virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method Download PDFInfo
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Abstract
A kind of virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method.It includes setting up virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system；The static three-dimensional spatial value of aeroplane engine tail gas particle is obtained using system；The Cross shaft model of tail gas particle is obtained using coordinate value；The corresponding relation set up between the Cross shaft model of tail gas particle and aero-engine running status, so that the step such as relevant information including obtaining the burning degree including aircraft engine fuel, engine aging, component failure.The present invention can realize the three-dimensional flow field measurement to tail gas particle, the form of soot particle, spatial distribution, particle speed in tail gas are monitored in real time, set up its corresponding relation with aero-engine fault type, the potential safety hazard of aero-engine is predicted in advance, the early warning information of failure is provided, flight safety is ensured, engine maintenance cost is reduced.
Description
Technical field
The invention belongs to aero-engine condition monitoring and fault diagnosis technology field, more particularly to a kind of virtual three-dimensional
Vision aeroplane engine tail gas particle flux monitoring method.
Background technology
With developing rapidly for China's aviation transport, aircraft navigation safety problem is received more and more attention.According to having
Statistics are closed, as the core component of aircraft, aero-engine failure occupies sizable ratio in aircraft flight failure,
In the aircraft accident of China's last decade, more than the 60% of machinery and engineering failure is accounted for by failure caused by aero-engine.Cause
This, strengthens the monitoring to aero-engine running status, the especially on-line monitoring in flight and the airline of aircraft is pacified
There is vital effect entirely, and early warning of the potential safety hazard there is provided failure of aero-engine can be predicted in advance
Information, reduces the maintenance cost of aero-engine.
The general carbon particle by burning completely of aeroplane engine tail gas particle and internal spare and accessory parts are because of collision, friction, burning
The particle composition that the failures such as erosion, material loss are produced.Traditional aeroplane engine tail gas is monitored frequently with offline sampling method, this
Method needs aero-engine being fixed under a stable service condition, its tail gas is sampled offline, it has the disadvantage
System architecture complexity, technical difficulty height, time of measuring length, analytical instrument function are single, testing expense is expensive, therefore general only suitable
For experimental stage.With continuing to develop for detection technique, a series of advanced noncontacts, visualization, high-precision lossless inspection
Survey technology occurs in succession.Such as passive type Fourier transform infrared spectroscopy (FTIR) remote sensing technology, can be to the absolute light of radiation source
Spectral power distribution and gas concentration carry out remote sensing survey, but real-time monitoring can not be realized to tail gas；Engine air passage electrostatic is monitored
The charged particle that technology can be used in monitoring exotic and tail gas, in gas circuit charged particle Producing reason generally include abrasion,
Ablation, material are peeled off and fuel nozzle is blocked, therefore, it is possible to provide failure early stage information, for judging gas circuit property abnormality
Or failure, but this method needs electrostatic induction probe being placed in engine air passage, and the diameter of gas path pipe is very big, probe is adopted
The simply information of discrete point one by one in pipeline collected, and the cross section information of pipeline can not be monitored, therefore measurement ginseng
Number is not comprehensive；Capacitance chromatography imaging (ECT) technology of rising in recent years, measurement section is rebuild by measuring object field border capacitance information
Material distribution situation on face, because the relative dielectric constant of particle and air in gas circuit is variant, can pass through ECT skills in theory
Art is imaged to inner material distribution, and extracts characteristic parameter, but still can not intuitively obtain particle in motor exhaust
The distribution situation and granular size of thing；Vision measuring method is also often applied in the detection of motor exhaust particle flow field, at present
Common stereo visual system is made up of the camera of two and above quantity more, and the contra according to two cameras is needed during measurement
Position and the requirement of primary optical axis angle carry out reasonable placement to camera, not only need to calibrate the internal reference of two cameras respectively, at a high speed
Moving target carry out IMAQ when, in addition it is also necessary to specific device come ensure two camera stringent synchronizations trigger so that system is occupied
Larger space, is that the on-line measurement in aero-engine tail gas flow field brings difficulty.
The content of the invention
In order to solve the above problems, it is an object of the invention to provide a kind of virtual three-dimensional vision aeroplane engine tail gas grain
Subflow monitoring method.
In order to achieve the above object, the virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring side that the present invention is provided
Method includes the following steps carried out in order：
1) virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system is set up；
2) aeroplane engine tail is obtained using above-mentioned virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system
The static three-dimensional spatial value of gas particle；
3) the Cross shaft model of tail gas particle is obtained using the static three-dimensional spatial value of above-mentioned tail gas particle；
4) corresponding relation set up between the Cross shaft model of tail gas particle and aero-engine running status, so that
Obtain the relevant information including the burning degree of aircraft engine fuel, engine aging, component failure.
In step 1) in, described virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system includes：High energy
Pulse laser emission device, Transmission Fibers, focusing system, eliminating device, virtual three-dimensional vision system, image processing apparatus, triggering
Control device；Wherein eliminating device is arranged on outside the one end in aeroplane engine tail gas area, and focusing system is arranged on aeroplane engine
Outside the other end in tail gas area, it is connected by Transmission Fibers with high energy pulse generating laser, and high energy pulse laser is sent out
Emitter, focusing system and eliminating device are set along same straight line；Virtual three-dimensional vision system is arranged on aeroplane engine tail gas
On the outside of area, and in the position for making three-dimensional Chi Hua speckles area be located in virtual three-dimensional vision system areas imaging；Triggering control dress
Put while being connected with high energy pulse generating laser and virtual three-dimensional vision system, for controlling high energy pulse generating laser
Triggered in succession with the high speed camera on virtual three-dimensional vision system；Image processing apparatus is connected with virtual three-dimensional vision system,
For storing and handling virtual three-dimensional vision system acquired image.
Described focusing system uses lens focusing telescope.
Described virtual three-dimensional vision system is made up of a high speed camera and two groups of light path reflection units.
In step 2) in, the above-mentioned virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system of described utilization is obtained
The specific method for obtaining the static three-dimensional spatial value of aeroplane engine tail gas particle is as follows：
Under the control of trigger control device, the high speed phase in high energy pulse generating laser and virtual three-dimensional vision system
Machine is triggered in succession, and high energy pulse generating laser sends pulse laser beam, is then transferred to focusing system by Transmission Fibers, it
Enhancing is focused to above-mentioned pulse laser beam by focusing system afterwards, enhanced pulse laser beam passes through aeroplane engine tail gas
Absorbed behind area by eliminating device；In the process, the tail gas particle in laser beam focus area is excited rear temperature and can drastically risen
Up to more than 2500K, after high energy laser beam irradiation terminates, environment temperature can be rapidly decreased to by being excited the temperature of tail gas particle,
Its in temperature-fall period will send incandescence, be consequently formed three-dimensional Chi Hua speckles area；At the same time, virtual three-dimensional vision system will be even
Several vehementization speckle stereo-pictures in continuous collection three-dimensional Chi Hua speckles area, and send above-mentioned stereo-picture to image procossing dress
Put；The stereo-picture of collection is divided into two images in left and right by image processing apparatus first, then utilizes pole outside epipolar line restriction
The static three-dimensional that angle three-dimensional speckle grid cell matching process calculates tail gas particle in each vehementization speckle stereo-picture is empty
Between coordinate value.
The outer polar angle three-dimensional speckle grid cell matching process of described utilization epipolar line restriction calculates each vehementization and dissipated
The specific method of the static three-dimensional spatial value of tail gas particle is as follows in spot stereo-picture：
Each vehementization speckle stereo-picture for first being gathered virtual three-dimensional vision system by image processing apparatus is split
For the image of left and right two, and according to virtual three-dimensional vision system 7 after calibrating parameters and optical path analysis are split image institute it is right
The relative bearing of two virtual base stations is answered, then speckle in left image is determined in two imaging virtual base stations using epipolar line restriction method
Characteristic point is the corresponding constraint EP point of picture point and right image of tail gas particle；Then left images are carried out with appropriately sized net
Lattice are divided, near based on gray-scale Matching algorithm to EP point in grid where speckle characteristics point in left image and right image
Grid scans for matching primitives, and similitude highest grid is matched in right image, so that it is determined that going out speckle characteristics block i.e.
The three-dimensional space position of tail gas particle；Above-mentioned matching process is repeated, that is, is capable of determining that current time each vehementization speckle characteristics point
That is the static three-dimensional space coordinate of tail gas particle.
In step 3) in, the static three-dimensional spatial value of the above-mentioned tail gas particle of described utilization obtains the three of tail gas particle
The specific method for tieing up Flow Field Distribution model is as follows：
Utilize step 2) obtain two any times t1, t2 tail gas particle static three-dimensional spatial value, pass through
Spatial correlation algorithm sets up identical tail gas particle in two vehementization speckle stereo-pictures corresponding to the two any times t1, t2
Matching relationship, so as to obtain the velocity of tail gas particle, and then calculate the Cross shaft model of tail gas particle.
In step 4) in, described sets up between the Cross shaft model of tail gas particle and aero-engine running status
Corresponding relation, so as to obtain the phase including the burning degree including aircraft engine fuel, engine aging, component failure
The specific method for closing information is as follows：
According to step 2)-step 3) method the aeroplane engine tail gas particle of different running statuses is monitored, wrap
Include the aero-engine normally run and because long-time is used and the aero-engine of aging or is led due to internal fault
The aero-engine scrapped is caused, is thus set up between the Cross shaft model of tail gas particle and aero-engine running status
Corresponding relation, so as to obtain the phase including the burning degree including aircraft engine fuel, engine aging, component failure
Close information.
The virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method that the present invention is provided can be realized to tail gas
The three-dimensional flow field measurement of particle, is monitored, is set up in real time to the form of soot particle, spatial distribution, particle speed in tail gas
Its corresponding relation with aero-engine fault type, the potential safety hazard of aero-engine is predicted in advance, and there is provided the early stage of failure
Warning information, ensures flight safety, reduces engine maintenance cost.
Brief description of the drawings
Fig. 1 is for what the virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method that the present invention is provided was used
System structural representation.
The virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method flow chart that Fig. 2 provides for the present invention.
Fig. 3 is virtual three-dimensional Vision imaging system structure principle chart.
Fig. 4 is the epipolar line restriction schematic diagram of speckle characteristics point.
Fig. 5 (a), (b) are respectively the mesh fitting schematic diagram of left images in Fig. 3.
Embodiment
The virtual three-dimensional vision aeroplane engine tail gas particle provided below in conjunction with the accompanying drawings with specific embodiment the present invention
Flow field monitoring method is described in detail.
As shown in Figure 1, 2, the virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method bag that the present invention is provided
Include the following steps carried out in order：
1) virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system is set up；
Described system includes：It is high energy pulse generating laser 1, Transmission Fibers 2, focusing system 3, eliminating device 6, virtual
Stereo visual system 7, image processing apparatus 8, trigger control device 9；Wherein eliminating device 6 is arranged on aeroplane engine tail gas area
Outside 5 one end, focusing system 3 is arranged on outside the other end in aeroplane engine tail gas area 5, passes through Transmission Fibers 2 and high energy
Pulse laser emission device 1 is connected, and high energy pulse generating laser 1, focusing system 3 and eliminating device 6 are along same straight line
Set；Virtual three-dimensional vision system 7 is arranged on the outside of aeroplane engine tail gas area 5, and being in is located at three-dimensional Chi Hua speckles area 4
Position in the areas imaging of virtual three-dimensional vision system 7；Trigger control device 9 simultaneously with high energy pulse generating laser 1 and void
Intend stereo visual system 7 to be connected, for controlling the high speed on high energy pulse generating laser 1 and virtual three-dimensional vision system 7
Camera is triggered in succession；Image processing apparatus 8 is connected with virtual three-dimensional vision system 7, is regarded for storing and handling virtual three-dimensional
The acquired image of feel system 7.
Described focusing system 3 uses lens focusing telescope.Virtual three-dimensional vision system 7 is by a high speed camera and two
Group light path reflection unit composition.
2) aeroplane engine tail is obtained using above-mentioned virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system
The static three-dimensional spatial value of gas particle；
Under the control of trigger control device 9, the height in high energy pulse generating laser 1 and virtual three-dimensional vision system 7
Fast camera is triggered in succession, and it is that 1062nm, frequency are 100KHz, pulse energy that wherein high energy pulse generating laser 1, which sends wavelength,
Pulse laser beam of the amount more than 1.0mJ, is then transferred to focusing system 3, afterwards by focusing system 3 to above-mentioned by Transmission Fibers 2
Pulse laser beam is focused enhancing, and enhanced pulse laser beam is inhaled after passing through aeroplane engine tail gas area 5 by eliminating device 6
Receive；In the process, the tail gas particle in laser beam focus area, which is excited rear temperature, can drastically be increased to more than 2500K,
After high energy laser beam irradiation terminates, environment temperature can be rapidly decreased to by being excited the temperature of tail gas particle, and it will hair in temperature-fall period
Go out incandescence, be consequently formed three-dimensional Chi Hua speckles area 4.At the same time, virtual three-dimensional vision system 7 is by three-dimensional vehementization of continuous acquisition
Several vehementization speckle stereo-pictures in speckle area 4, and send above-mentioned stereo-picture to image processing apparatus 8；Image procossing is filled
Put 8 and the stereo-picture of collection is divided into two images in left and right first, then utilize polar angle three-dimensional speckle net outside epipolar line restriction
Lattice units match method calculates the static three-dimensional spatial value of tail gas particle in each vehementization speckle stereo-picture.
Described virtual three-dimensional vision system 7 gathers the tool of several vehementization speckle stereo-pictures in three-dimensional Chi Hua speckles area 4
Body method is as follows：As shown in figure 3, wherein L is tail gas particle；M1, P1 and M2, P2 are two groups of light path reflection units, this two groups of light
Road reflection unit plays " binocular ", two in traditional Binocular Stereo Vision System camera can be reduced into a camera.
By the optical path analysis to light path reflection unit, monocular can be imaged base station CCBe reduced to relative bearing determination two are virtual
Base station CLWith CR, monocular imaging base station CCEquivalent to two virtual base station C of the image of collectionL, CRThe splicing synthesis of gathered image.
In addition, virtual three-dimensional vision system 7 need to be demarcated, first with the high speed camera in the system and two groups of light paths
The original image of several different positions and poses of the known target of reflection unit collection, is then divided into left and right two by the original image of collection
Image, according to binocular stereo vision scaling method, sets up the camera calibration model of virtual three-dimensional vision system, calibrates system
Camera internal reference and virtual outer ginseng.
It is three-dimensional that each vehementization speckle is calculated using polar angle three-dimensional speckle grid cell matching process outside epipolar line restriction
The specific method of the static three-dimensional spatial value of tail gas particle is as follows in image：
The each vehementization speckle stereo-picture point gathered first by image processing apparatus 8 to virtual three-dimensional vision system 7
It is segmented into two images in left and right, and the two virtual base station C according to corresponding to optical path analysis determines image after segmentationL, CRContra
Position；Then epipolar line restriction is carried out to speckle characteristics point in two images after segmentation using epipolar line restriction method, as shown in figure 4,
Wherein OL、ORFor the virtual base station C of left and right twoL, CRPhotocentre point, I, II is respectively left images, and M is speckle characteristics point (i.e. tail gas
Particle), P is the matching of m points in the EP point that the straight line m ' m " in interference point, right image II are point m in left image I, left image I
Point is constrained on the straight line m ' m " of right image II.Then mesh generation and grid are carried out to left images I, II according to appropriate size
Matching search, as shown in figure 5, grid m matching area necessarily constrains in the straight line m ' m " of right image II grid in left image I
On, according to gray areas related algorithm (such as NCC algorithms) by straight line m ' m " in the speckle grid m of left image I and right image II
Neighbouring grid scans for matching primitives, rejects interference grid p ', similitude highest m ' grids is found out, so that it is determined that going out scattered
Spot characteristic block M (i.e. tail gas particle) three-dimensional space position.Above-mentioned matching process is repeated, that is, is capable of determining that current time space
The static three-dimensional space coordinate of each speckle characteristics point (i.e. tail gas particle).
In order to accurate acquisition vehementization speckle stereo-picture, the high speed phase of reasonable set virtual three-dimensional vision system 7 is needed
The time for exposure of machine：The incandescence signals duration that black body radiation phenomenon is produced is relevant with diameter of particle size, usual aeroplane engine
Burnt under machine normal operating conditions generation carbon particle particle diameter between two intervals of 5-7nm and 20-30nm, because collision, friction,
Ablation, material such as lose at the failure cause and the grain diameter that produces is not less than 40 μm, therefore the incandescence signals duration is ten to receive
Second between a microsecond, thus the time for exposure of high-speed camera may be set to 10ns.
In addition, to make pulse laser beam transmitting and the collection of vehementization speckle stereo-picture appropriately can complete in an orderly manner, this is
System ensures high energy pulse generating laser 1 and the high speed camera interval of virtual three-dimensional vision system 7 using trigger control device 9
Right times are successively triggered.
3) the Cross shaft model of tail gas particle is obtained using the static three-dimensional spatial value of above-mentioned tail gas particle；
Utilize step 2) obtain two any times t1, t2 tail gas particle static three-dimensional spatial value, pass through
Spatial correlation algorithm sets up identical tail gas particle in two vehementization speckle stereo-pictures corresponding to the two any times t1, t2
Matching relationship, so as to obtain the velocity of tail gas particle, and then calculate the Cross shaft model of tail gas particle.
4) corresponding relation set up between the Cross shaft model of tail gas particle and aero-engine running status, so that
Obtain the relevant information including the burning degree of aircraft engine fuel, engine aging, component failure；
According to step 2)-step 3) method the aeroplane engine tail gas particle of different running statuses is monitored, wrap
Include the aero-engine normally run and because long-time is used and the aero-engine of aging or is led due to internal fault
The aero-engine scrapped is caused, is thus set up between the Cross shaft model of tail gas particle and aero-engine running status
Corresponding relation, so as to obtain the phase including the burning degree including aircraft engine fuel, engine aging, component failure
Information is closed, the mesh of aero-engine running status is monitored in real time therefore, it is possible to reach by monitoring aeroplane engine tail gas area 5
's.
The embodiment of the present invention is described above in association with accompanying drawing, but these explanations can not be understood to limitation
The scope of the present invention, protection scope of the present invention is limited by appended claims, any in the claims in the present invention base
Change on plinth is all protection scope of the present invention.
Claims (8)
1. a kind of virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method, it is characterised in that：Described is virtual vertical
Body vision aeroplane engine tail gas particle flux monitoring method includes the following steps carried out in order：
1) virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system is set up；
2) aeroplane engine tail gas grain is obtained using above-mentioned virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system
The static three-dimensional spatial value of son；
3) the Cross shaft model of tail gas particle is obtained using the static three-dimensional spatial value of above-mentioned tail gas particle；
4) corresponding relation set up between the Cross shaft model of tail gas particle and aero-engine running status, so as to obtain
The relevant information including burning degree, engine aging, component failure including aircraft engine fuel.
2. virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method according to claim 1, its feature exists
In：In step 1) in, described virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system includes：High energy pulse swashs
Optical transmitting set (1), Transmission Fibers (2), focusing system (3), eliminating device (6), virtual three-dimensional vision system (7), image procossing
Device (8), trigger control device (9)；Wherein eliminating device (6) is arranged on outside the one end in aeroplane engine tail gas area (5), is adjusted
Burnt system (3) is arranged on outside the other end in aeroplane engine tail gas area (5), passes through Transmission Fibers (2) and high energy pulse laser
Transmitter (1) is connected, and high energy pulse generating laser (1), focusing system (3) and eliminating device (6) are along same straight line
Set；Virtual three-dimensional vision system (7) is arranged on the outside of aeroplane engine tail gas area (5), and in making three-dimensional Chi Hua speckles area
(4) it is located at the position in virtual three-dimensional vision system (7) areas imaging；Trigger control device (9) at the same with high energy pulse laser
Transmitter (1) is connected with virtual three-dimensional vision system (7), for controlling high energy pulse generating laser (1) and virtual three-dimensional
High speed camera on vision system (7) is triggered in succession；Image processing apparatus (8) is connected with virtual three-dimensional vision system (7), uses
In storage and processing virtual three-dimensional vision system (7) acquired image.
3. virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method according to claim 2, its feature exists
In：Described focusing system (3) uses lens focusing telescope.
4. virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method according to claim 2, its feature exists
In：Described virtual three-dimensional vision system (7) is made up of a high speed camera and two groups of light path reflection units.
5. virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method according to claim 1, its feature exists
In：In step 2) in, the above-mentioned virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring system of described utilization is navigated
The specific method of the static three-dimensional spatial value of empty motor exhaust particle is as follows：
Under the control of trigger control device (9), in high energy pulse generating laser (1) and virtual three-dimensional vision system (7)
High speed camera is triggered in succession, and high energy pulse generating laser (1) sends pulse laser beam, is then transmitted by Transmission Fibers (2)
Focusing system (3) is given, enhancing, enhanced pulse laser are focused to above-mentioned pulse laser beam by focusing system (3) afterwards
Beam is passed through behind aeroplane engine tail gas area (5) by eliminating device (6) absorption；In the process, in laser beam focus area
Tail gas particle, which is excited rear temperature, can drastically be increased to more than 2500K, after high energy laser beam irradiation terminates, be excited tail gas particle
Temperature can be rapidly decreased to environment temperature, and it will send incandescence in temperature-fall period, be consequently formed three-dimensional Chi Hua speckles area (4)；
At the same time, virtual three-dimensional vision system (7) is by several vehementization speckle stereograms in continuous acquisition three-dimensional Chi Hua speckles area (4)
Picture, and send above-mentioned stereo-picture to image processing apparatus (8)；Image processing apparatus (8) is first by the stereo-picture of collection
Two images in left and right are divided into, are then calculated using polar angle three-dimensional speckle grid cell matching process outside epipolar line restriction each
The static three-dimensional spatial value of tail gas particle in vehementization speckle stereo-picture.
6. virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method according to claim 5, its feature exists
In：It is three-dimensional that the outer polar angle three-dimensional speckle grid cell matching process of described utilization epipolar line restriction calculates each vehementization speckle
The specific method of the static three-dimensional spatial value of tail gas particle is as follows in image：
Each vehementization speckle stereo-picture point for first being gathered virtual three-dimensional vision system (7) by image processing apparatus (8)
It is segmented into two images in left and right, and according to virtual three-dimensional vision system (7) image after calibrating parameters and optical path analysis are split
The relative bearing of corresponding two virtual base station, is then determined in two imaging virtual base stations in left image using epipolar line restriction method
Speckle characteristics point is the corresponding constraint EP point of picture point and right image of tail gas particle；Then left images are carried out appropriately sized
Mesh generation, using attached to grid where speckle characteristics point and EP point in right image in left image based on gray-scale Matching algorithm
Near grid scans for matching primitives, similitude highest grid is matched in right image, so that it is determined that going out speckle characteristics
Block is the three-dimensional space position of tail gas particle；Above-mentioned matching process is repeated, that is, is capable of determining that current time each vehementization speckle is special
Levy the static three-dimensional space coordinate of a little i.e. tail gas particle.
7. virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method according to claim 1, its feature exists
In：In step 3) in, the static three-dimensional spatial value of the above-mentioned tail gas particle of described utilization obtains the three-dimensional flow of tail gas particle
The specific method of field distribution model is as follows：
Utilize step 2) obtain two any times t1, t2 tail gas particle static three-dimensional spatial value, pass through space
Related algorithm sets up of identical tail gas particle in two vehementization speckle stereo-pictures corresponding to the two any times t1, t2
With relation, so as to obtain the velocity of tail gas particle, and then the Cross shaft model of tail gas particle is calculated.
8. virtual three-dimensional vision aeroplane engine tail gas particle flux monitoring method according to claim 1, its feature exists
In：In step 4) in, described pair set up between the Cross shaft model of tail gas particle and aero-engine running status
It should be related to, so that the related letter including obtaining the burning degree including aircraft engine fuel, engine aging, component failure
The specific method of breath is as follows：
According to step 2)-step 3) method the aeroplane engine tail gas particle of different running statuses is monitored, including just
The aero-engine often run and because long-time is used and the aero-engine of aging or causes due to internal fault report
Useless aero-engine, thus sets up pair between the Cross shaft model of tail gas particle and aero-engine running status
It should be related to, so that the related letter including obtaining the burning degree including aircraft engine fuel, engine aging, component failure
Breath.
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