CN104654926B - A kind of mixed supersonic coating control method - Google Patents
A kind of mixed supersonic coating control method Download PDFInfo
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- CN104654926B CN104654926B CN201510076363.8A CN201510076363A CN104654926B CN 104654926 B CN104654926 B CN 104654926B CN 201510076363 A CN201510076363 A CN 201510076363A CN 104654926 B CN104654926 B CN 104654926B
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- 230000003287 optical effect Effects 0.000 abstract description 26
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- 238000005516 engineering process Methods 0.000 abstract description 11
- 238000012937 correction Methods 0.000 description 6
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- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 4
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Abstract
The present invention relates to mixed supersonic coating control method, develop mixed supersonic layer Pneumatic optical control technology, realize the effective control to aero-optical effect, reach the object that improves optical imagery guided weapon guidance precision, on demarcation strip, paste disturbance sheet and produce disturbance, distance between disturbance sheet outer face and demarcation strip end is L, changes the phase place of disturbance through adjusting L; The thickness of disturbance sheet is H, changes the amplitude of disturbance through pasting the disturbance sheet of different-thickness; Carry out the waveform of control disturbance through pasting difform disturbance sheet; The length of disturbance sheet is λ, the length lambda of disturbance sheet equals the mean wavelength that flows to of mixed layer large scale eddy structure, in the process of adjustment L, the length of laminar flow section can change, and determines the numerical value of L with reference to the length of laminar flow section, adjust the thickness H of disturbance sheet, determine the numerical value of H with reference to the length of laminar flow section, adjust the shape of disturbance sheet, determine the shape of disturbance sheet with reference to the length of laminar flow section, structure is ingenious, has reached extraordinary technique effect.
Description
Technical field
The present invention relates to a kind of mixed supersonic coating control method.
Background technology
The world today, military struggle is day by day fierce, and various countries are more and more higher to the dependency degree of precision strike weapon,Adopt the optical imagery guided weapon of high guidance precision day by day to come into one's own. But, aircraft cooling blast withInteraction between incoming flow, cause its around the refractive index of flow field of mixed layers on time and space, all presentGo out obvious inhomogeneities, from the light of target during through such refractive index field, can produce deflection of light,Phase distortion or imaging defocus, the target image being disturbed being that optical system receives, and this will be largeThe large ability that affects its detection, identification and tracking target, reduces the degree of accuracy hitting the mark, and even misses the target[1]。Therefore, study the flow mechanism of mixed supersonic lamellar field, seek its aero-optical effect and flow field structure itBetween internal relation, and take suitable control method to reduce Pneumatic optical impact, improve its optical property,It is one of key issue in the research work of optical imagery guided weapon.
The people such as StanekMJ[2]Point out, the motion of macroturbulence structure has caused deviation and the shake of light beam;The diffusion of mesoscale turbulence structure to energy, spreads light beam, and then has caused image blur;Microturbulence structure, to scattering of light, makes light beam pass through energy attenuation behind flow field, has caused Si Teer ratioThe reduction of SR. Above-mentioned aero-optical effect is relevant with the scale of turbulence, and is simultaneous. FitzgeraldEJ[3]And CatrakisHJ[4]Deng people's research discovery, the large-scale structure during turbulent shear laminar flow is moving is leadingNear field aero-optical effect. 2006, the people such as ZubairFR[5]Study optics ripple in compressible turbulent flowThe variation of forward position direction of beam propagation, analyzes near field wavefront variation corresponding to different resolution flow field, finds rippleBefore overall distribution there is no significant change, what overall distribution before near field wave was played an important role is large in turbulent flowYardstick structure. From the above-mentioned result of study about relation between aero-optical effect and flow field structure, noTurbulence structure with yardstick has impact in various degree to aero-optical effect, and these impacts are to deposit simultaneously; What affect light beam deviation and shake is mainly the large scale eddy structure in mixed layer.
The distortion of Pneumatic optical that mixed supersonic lamellar field causes has very high frequency, to such an extent as to current fromAdaptive optics system can not be revised in real time to it[6]. Want to reduce the Pneumatic optical disturbance bringing in flow field, canThe way of row is that the geometric shape by optical window changes flow field structure, or toward jet-stream wind in flow fieldThe index distribution inhomogeneities in compensation flow field. The SmittsAJ of Princeton university and MilesRBIn turbulent region by the territory, transition range toward middle plateform boundary layer, Ma=8 flow field and development completely, spray helium,Improve its Pneumatic optical performance[7], and adopt the observation of FRS technology to have or not the flow field structure that sprays helium. 2005Year, the people such as WyckhamC are to spraying the Pneumatic optical transonic speed causing with hypersonic turbulent boundary layer of heliumDistortion is measured[8]. The people such as WyckhamC adopt Hartmann Wavefront sensor, to transonic speed and highReal-time measurement has been carried out in the Pneumatic optical distortion that supersonic boundary layer brings, and the time precision of this sensor can reach 2μ s. Obtain the Pneumatic optical that has or not the mixed layer turbulent flow of spraying helium to cause in Ma=0.6 and Ma=8 flow fieldA series of data of disturbance, these data have very great help to control wave front-distortion[8]. 2006, WyckhamThe people such as C to transonic speed with Hypersonic Flow Field in spray helium turbulent mixing layer produce optical distortion carry outRelatively, find that the large-scale structure in mixed layer is the principal element that affects Pneumatic optical distortion[9], verified largeThe approximate hypothesis in aperture. In this respect, domestic Pneumatic optical researcher has also done a lot of fruitful worksDo. The new problem that Fei Jindong adopts infrared image terminal guidance technology to face from high-speed missile, has studiedAero-optical effect rule, the design of the correction of pointing out to carry out aero-optical effect to high-speed missile optical dome,Improve the signal to noise ratio of target seeker to target acquisition, and improve terminal guidance precision and antijamming capability has importantEffect[10]. 2004, Zhang Liqin and Fei Jindong ran into for the precise guidance aircraft of hypersonic flightPneumatic optical problem, introduced the Photoelectric correction methods of aero-optical effect, comprise based on wavefront detect withBased on adaptive optics correction, picture frame frequency and frames such as the correction of picture sharpening and the corrections of high frequency miniature photoelectronThe time of integration, adaptive change correction and optics and image were processed the methods such as integrated calibration, and to the whole bag of tricksCompare analysis. Point out picture frame frequency and frame integral time adaptive change alignment technique energy raising effectDistance and image definition, and can effectively improve the fuzzy and high dither of image. Phase difference synthetic methodPrinciple is simple, be easy to realize, and is relatively suitable for missile-borne environment, has good in aero-optical effect is proofreaied and correctApplication prospect[11]. 2005, the people such as Li Yanfang introduced three kinds of sides for Flat Plate Turbulent Boundary Layer controlMethod: the optimization of wall cooling, air-breathing and wall shape, result of study shows that these three kinds of methods are flat for controllingPlate turbulent boundary layer, the disturbance of reduction Pneumatic optical can be brought into play useful effect[12]。
Above-mentioned scholar is making very important work aspect Pneumatic optical control technology, but for ultrasonicThe Pneumatic optical control of speed mixed layer does not also have effective method.
Summary of the invention
For above-mentioned situation, for overcoming the defect of prior art, the present invention proposes a kind of mixed supersonic layer controlMethod processed, develops mixed supersonic layer Pneumatic optical control technology, realize to aero-optical effect effectivelyControl, finally reach the object that improves optical imagery guided weapon guidance precision.
The technical scheme of its solution is that the method for pasting disturbance sheet on mixed supersonic layer demarcation strip, producesRaw disturbance, the horizontal range between disturbance sheet outer face and demarcation strip end is L, is changed and is disturbed by adjustment LMoving phase place; The thickness of disturbance sheet is H, changes the amplitude of disturbance by pasting the disturbance sheet of different-thickness;Carry out the waveform of control disturbance by pasting difform disturbance sheet; The length of disturbance sheet is λ, disturbance sheetLength lambda equals the mean wavelength that flows to of mixed layer large scale eddy structure, and the numerical value of λ is known, adjusts L,Adjust in the process of L, the length of laminar flow section can change, and gets and adjusts in L process laminar flow extentLarge value, determine the numerical value of L; The thickness H that adjusts disturbance sheet, the length of laminar flow section also can be along with the variation of HAnd change, get the maximum of adjusting laminar flow extent in H process, determine the numerical value of H; Adjust disturbance sheetShape, the length of laminar flow section changes along with the variation of disturbance plate shape, gets the disturbance plate shape process of adjustingThe maximum of middle laminar flow extent, determines the shape of disturbance sheet.
Structure of the present invention is ingenious, has reached extraordinary technique effect.
Brief description of the drawings
Fig. 1 is mixed supersonic layer density field structure.
Fig. 2 is demarcation strip and disturbance chip architecture schematic diagram.
Fig. 3 is difform disturbance sheet schematic diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Provided by Fig. 1 to Fig. 3, mixed supersonic lamellar field structure exists significantly periodically, as Fig. 1 instituteShow, the large scale eddy structure in Fig. 1 is the principal element that causes light beam deviation and shake, therefore only has inhibitionThe generation of this large scale eddy structure, namely postpones to turn to twist, so that the flow field that light beam passes through is laminar flow shapeState, just can reach the object of Pneumatic optical control.
Postpone turning of mixed layer and twist, perturbation scheme must have corresponding amplitude, phase place and waveform; ThisThe method that bright employing is pasted disturbance sheet on mixed supersonic layer demarcation strip, produces disturbance, disturbance sheet outer endHorizontal range between face and demarcation strip end is L, changes the phase place of disturbance, as Fig. 2 institute by adjusting LShow; The thickness of disturbance sheet is H, changes the amplitude of disturbance, as Fig. 2 by pasting the disturbance sheet of different-thicknessShown in; Carry out the waveform of control disturbance by pasting difform disturbance sheet, as shown in Figure 3; Disturbance sheetLength is λ, and the length lambda of disturbance sheet equals the mean wavelength that flows to of mixed layer large scale eddy structure, the number of λValue, for known, is adjusted L, and in the process of adjustment L, the length of laminar flow section can change, and gets and adjusts L mistakeThe maximum of laminar flow extent in journey, determines the numerical value of L; Adjust the thickness H of disturbance sheet, the length of laminar flow sectionDegree also can change along with the variation of H, gets the maximum of adjusting laminar flow extent in H process, determines HNumerical value; The shape of adjusting disturbance sheet, the length of laminar flow section changes along with the variation of disturbance plate shape, getsAdjust the maximum of laminar flow extent in disturbance plate shape process, determine the shape of disturbance sheet.
In the process of adjustment disturbance plate shape, the shape of disturbance sheet chooses at random, until the length of laminar flow sectionReach the length needing;
Adjusting in the process of L, H and disturbance plate shape, do not have sequential requirement, also can first adjust disturbance sheetThickness H or the shape of disturbance sheet.
The present invention is according to three factors that affect large scale eddy structure, the side of pasting disturbance sheet on demarcation strip 1Method reaches the object that suppresses large scale eddy structure, by adjusting the distance between disturbance pitch of fins demarcation strip 1 endFrom the shape of thickness H and the disturbance sheet of H, disturbance sheet, and relation between reasonable coordination three, suppress largeThe generation in yardstick whirlpool.
The present invention is at the planar laser scattering (Nanoparticle-based of a new technology-based on nano particlePlanarLaserScattering,NPLS)(ZhaoYX,YiSH,TianLF,etal.Supersonicflowimagingviananoparticles.SciChinaSerE-tech,2009,52 (12): 3640-3648) under, the present invention is verified, NPLS technology is a kind of new supersonic flow field essenceFine texture measuring technology, can carry out time correlation high to a certain cross section in supersonic speed complex three-dimensional flow field timeEmpty resolution ratio Transient Flow demonstration, its spatial resolution can be up to micron dimension, and temporal resolution is 6ns, timeBetween dependent resolution reach as high as 0.2 μ s, and there is higher signal to noise ratio, just can take with general cameraFlow field structure picture clearly, under the condition of above-mentioned technology, does two groups of checkings;
(1), in the mixed supersonic layer wind-tunnel of convective Mach Mc=0.5, L is 10mm, H is 1mm,λ is 37.2mm, disturbance sheet be shaped as rectangle, with this understanding, the length of laminar flow section is measured as 30mm,Then adjust L, L is adjusted into 21mm, the length that records laminar flow section is 40mm, by adjusting L, greatlyIncrease the length of laminar flow section;
(2), in the mixed supersonic layer wind-tunnel of convective Mach Mc=0.3, L is 10mm, H is 1.2mm,λ is 42mm, disturbance sheet be shaped as rectangle, with this understanding, the length that records laminar flow section is 42mm, soRear adjustment L, is adjusted into 7mm by L, and the length that records laminar flow section is 50mm, by adjusting L, greatly increasesThe length of laminar flow section.
The principle that the present invention is based on waveform stack, the form of pasting disturbance sheet on mixed layer demarcation strip, passes throughThickness, shape and the position of adjusting disturbance sheet, suppress the generation of large scale eddy, reached ultrasonicThe object that speed flow field of mixed layers and aero-optical effect thereof are effectively controlled, method is ingenious, effective.
Bibliography
[1] Li Guichun. Pneumatic optical [M]. Beijing: National Defense Industry Press, 2006.
[2]StanekMJ,SinhaN,SeinerJM,etal.Highfrequencyflowcontrol-suppressionofaero-opticsintacticaldirectedenergybeampropagation&thebirthofanewmodel(partI)[C].AIAAPaper,2002,2002-2272。
[3]FitzgeraldEJ,JumperEJ.Theopticaldistortionmechanisminanearlyincompressiblefreeshearlayer[J].J.FluidMech.,2004,512:153-189。
[4]CatrakisHJ,AguirreRC.Newinterfacialfluidthicknessapproachinaero-opticswithapplicationstocompressibleturbulence[J].AIAAJournal,2004,42(10):1973-1981。
[5] Fei Jindong. aero-optical effect alignment technique initial analysis [J]. infrared and laser engineering,1999,28(5):10-12。
[6]TrumanCR.Theinfluenceofturbulentstructureonopticalphasedistortionthroughturbulentshearflows[C].AIAAPaper,1992,92-2817。
[7]SmittsAJ,MilesRB.Shockwaveandboundarylayercontrolforaero-opticapplication[R].AFOSRGRANTF-49620-00-1-0139,2002。
[8]WyckhamC,ZaidiSH,MilesRB,etal.Measurementofaero-optic distortionintransonicandhypersonic,turbulentboundarylayerswithgasinjection[C].AIAAPaper,2005,2005-4775。
[9]WyckhamCM,SmitsAJ.Comparisonofaero-opticdistortioninhypersonicandtransonic,turbulentboundarylayerswithgasinjection[C].AIAAPaper,2006,2006-3067。
[10] Fei Jindong. the demand of high-speed missile infrared image terminal guidance to aero-optical effect technical research[J]. infrared and laser engineering, 1998,27 (1): 42-43.
[11] Zhang Liqin, Fei Jindong. aero-optical effect Photoelectric correction methods research [J]. infrared and laserEngineering, 2004,33 (6): 580-583.
[12] Li Yanfang, Han Zhiping, Yin Xingliang. Turbulent Flow Field controlling party in aero-optical effect correctionMethod [J]. modern defense technology, 2005,33 (1): 32-35.
Claims (1)
1. a mixed supersonic coating control method, it is characterized in that, adopt the method for pasting disturbance sheet on mixed supersonic layer demarcation strip, produce disturbance, horizontal range between disturbance sheet outer face and demarcation strip end is L, changes the phase place of disturbance by adjusting L, the thickness of disturbance sheet is H, changes the amplitude of disturbance by pasting the disturbance sheet of different-thickness, carry out the waveform of control disturbance by pasting difform disturbance sheet, the length of disturbance sheet is λ, the length lambda of disturbance sheet equals the mean wavelength that flows to of mixed layer large scale eddy structure, the numerical value of λ is known, adjust L, in the process of adjustment L, the length of laminar flow section can change, get the maximum of adjusting laminar flow extent in L process, determine the numerical value of L, adjust afterwards the thickness H of disturbance sheet, the length of laminar flow section also can change along with the variation of H, get the maximum of adjusting laminar flow extent in H process, determine the numerical value of H, then adjust the shape of disturbance sheet, the length of laminar flow section changes along with the variation of disturbance plate shape, get the maximum of adjusting laminar flow extent in disturbance plate shape process, determine the shape of disturbance sheet.
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| US8016246B2 (en) * | 2007-05-25 | 2011-09-13 | The Boeing Company | Plasma actuator system and method for use with a weapons bay on a high speed mobile platform |
| CN102862676B (en) * | 2012-09-29 | 2014-10-08 | 中国航天空气动力技术研究院 | Noise reduction method for weapon cabin of supersonic aircraft on basis of turbulent flow on front-edge surface |
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