CN102862676A - Noise reduction method for weapon cabin of supersonic aircraft on basis of turbulent flow on front-edge surface - Google Patents
Noise reduction method for weapon cabin of supersonic aircraft on basis of turbulent flow on front-edge surface Download PDFInfo
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Abstract
A noise reduction method for a weapon cabin of a supersonic aircraft on the basis of turbulent flow on a front-edge surface includes steps of (1), acquiring the flight speed, the incoming flow density, the incoming flow temperature, an incoming flow viscosity coefficient and the thickness of a boundary layer of the front-edge surface of the weapon cabin according to the flight condition of the supersonic aircraft, and computing an incoming Reynolds number on the basis of the thickness of the boundary layer of the front-edge surface of the weapon cabin; (2), selecting a fundamental-frequency disturbance sheet; (3), computing the ratio of the length to the depth of the supersonic aircraft according to the length, the depth and the width of the weapon cabin of the supersonic aircraft, reducing the thickness H of the fundamental-frequency disturbance sheet by 10-20% if the ratio is larger than 4, or increasing the thickness H of the fundamental-frequency disturbance sheet by 10-20% if the ratio is not larger than 4; and (4), fixing the fundamental-frequency disturbance sheet on the supersonic aircraft to complete noise reduction for the weapon cabin of the supersonic aircraft on the basis of the turbulent flow on the front-edge surface. The noise reduction method has the advantage that the problem of severe self-sustained oscillation of pressure of the inside of the cabin after the buried weapon cabin is opened during supersonic flight of the supersonic aircraft can be effectively solved.
Description
Technical field
The present invention relates to a kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing, for reducing interior violent noise in the weapon-bay and the pressure oscillation of controlling oneself when burying the supersonic flight of weapon-bay aircraft.
Background technology
Burying in the weapon is the inevitable development trend of supersonic aircraft weapon carrying mode, Fig. 1 be fighter plane in bury weapon-bay and weapon carry scheme drawing, described hatch door among the figure and opened the structure of weapon-bay under the situation and form.During the aircraft supersonic flight, after opening weapon-bay, such as scheme drawing 2 (a), high velocity air flows through the weapon-bay surface and mixes the formation shear layer with air in the cabin, shear layer vortex row and the effect of weapon-bay trailing edge form the reflected pressure of propagating forward, this reflected pressure is transmitted to weapon-bay leading edge initial shear layer position in the cabin, and induce the shear layer scrollwork to rise, when shear layer scrollwork frequency with after the reflected pressure frequency is consistent, namely cause the acoustic feed back ring to form, and cause the persistent oscillation under characteristic frequency of cabin internal pressure.Pressure oscillation in the weapon-bay not only can cause damage to the equipment such as weaponry, weapon mount point, electronic machine in the cabin, even may threaten the safety that weapon is thrown in.For addressing this problem, dropped into more research both at home and abroad, and formed some achievements.Suppress system such as the many weapon-bay acoustic feed backs in U.S.'s exploitation, basic thought is in the weapon-bay leading edge surface additional device to be set to force high velocity air to depart from weapon-bay mostly, forms shear layer and acoustic feed back ring to avoid incoming flow to mix with gas in the cabin.The weapon-bay plasma actuator system that occurs in China for another example, this system utilizes plasma actuator to induct mobile so that the shear layer of process weapon-bay departs from hatch, reaches the purpose that reduces the pressure oscillation in the cabin.These technology are principle mainly with forcing shear layer to depart from weapon-bay greatly, the apparatus system more complicated that adopts, not only the design of aerocraft system is proposed extra demand, and the reliability of the operation of these complex appts also can execute the task to aircraft the time brings impact.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, a kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing is provided, solved supersonic aircraft when carrying out supersonic flight, in bury the problem that weapon-bay is opened the serious self sustained oscillation of rear deck internal pressure.
Technical solution of the present invention is:
A kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing, step is as follows:
(1) the flight operating mode according to supersonic aircraft obtains flying speed ν, incoming flow density p, temperature of incoming flow T, incoming flow coefficient of viscosity μ and weapon-bay leading edge surface boundary layer thickness δ, passes through formula
Calculating is based on the incoming flow reynolds number Re of weapon-bay leading edge surface boundary layer thickness δ
δ
(2) determine fundamental frequency disturbance sheet: described fundamental frequency disturbance sheet indentation, each profile of tooth is equicrural triangle, and each between cog gapless is evenly distributed, and the thickness H of fundamental frequency disturbance sheet is 15%～50% of weapon-bay leading edge surface boundary layer thickness δ; The width W of fundamental frequency disturbance sheet is passed through formula
Calculate, wherein, u is that weapon-bay leading edge surface boundary 1ayer inner height is the speed of incoming flow of H position, and ω is forcing frequency;
Tooth width D on the described fundamental frequency disturbance sheet is D=0.5W～3W.
The concrete of described forcing frequency ω determines that method is: by the flying speed ν under the supersonic aircraft state of flight, incoming flow reynolds number Re
δ, incoming flow density p, temperature of incoming flow T and incoming flow coefficient of viscosity μ, the unstable forcing frequency scope of weapon-bay shear layer when adopting the linearized stability analysis method to obtain without additional disturbance, wherein the most unsettled frequency values is forcing frequency ω.
(3) according to the length of supersonic aircraft weapon-bay, dark, wide size, calculate the ratio of length and the degree of depth of supersonic aircraft, when this ratio greater than 4 the time, the thickness H of fundamental frequency disturbance sheet is reduced 10～20%; When this when being not more than 4, the thickness H of fundamental frequency disturbance sheet is increased by 10～20%;
(4) fundamental frequency disturbance sheet is fixed on the supersonic aircraft to finish supersonic aircraft weapon-bay leading edge surface flow-disturbing noise reduction.
Described fundamental frequency disturbance sheet is fixed on the supersonic aircraft is specially: fundamental frequency disturbance sheet is fixedly mounted on the place ahead of weapon-bay, sawtooth is towards coming flow path direction, between fundamental frequency disturbance sheet trailing edge and the weapon-bay leading edge to satisfy the trailing edge of B=0～1W and fundamental frequency disturbance sheet apart from B parallel with the weapon-bay leading edge.
Between fundamental frequency disturbance sheet and weapon-bay, can also fixedly mount an inferior harmonics disturbance sheet, the thickness of this Asia harmonics disturbance sheet is identical with fundamental frequency disturbance sheet, width is 2 times of fundamental frequency disturbance sheet width, tooth width is 2 times of fundamental frequency disturbance sheet tooth width, the sawtooth of inferior harmonics disturbance sheet is also towards coming flow path direction, distance between the leading edge of inferior harmonics disturbance sheet and the trailing edge of fundamental frequency disturbance sheet is 1～2W, and inferior harmonics disturbance sheet trailing edge and distance between the weapon-bay leading edge are that the trailing edge of 0～1W and inferior harmonics disturbance sheet is parallel with the weapon-bay leading edge.
The present invention's advantage compared with prior art is: this method can effectively reduce supersonic aircraft when carrying out supersonic flight, bury weapon-bay in opening after, the serious self sustained oscillation problem of cabin internal pressure.This method is simple, easy to operate, reliable in function, and can with various in bury weapon-bay the fighter plane reasonable combination.This method can guarantee to avoid the aircraft surface boundary layer perturbation when the weapon-bay hatch door is not opened by to the zigzag fashion size design, keeps former flow performance to guarantee the aircraft surface incoming flow.
Description of drawings
Fig. 1 buries the weapon-bay hatch door to open scheme drawing in the high-performance fighter aircraft;
The interior shear flow of weapon-bay and reflected pressure interaction scheme drawing when Fig. 2 (a) is Supersonic Stream;
Fig. 2 (b) is for pasting shear flow and reflected pressure interaction scheme drawing in the disturbance sheet weapon-bay afterwards
Fig. 3 is arrangement relation and each size scheme drawing of sawtooth disturbance sheet and weapon-bay leading edge surface
Fig. 4 is that fundamental frequency sawtooth disturbance sheet and inferior harmonics sawtooth disturbance chip size concern scheme drawing
Fig. 5 is the inventive method diagram of circuit.
The specific embodiment
For avoiding shear layer bump weapon-bay trailing edge, the invention provides a kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing, the method not only can effectively reduce violent pressure oscillation in the weapon-bay, and can with current various complexity in bury the weapon-bay fighter plane unit design merge well.
As shown in Figure 5, the present invention carries out in accordance with the following steps:
(1) the flight operating mode according to supersonic aircraft obtains flying speed ν, incoming flow density p, temperature of incoming flow T, incoming flow coefficient of viscosity μ and weapon-bay leading edge surface boundary layer thickness δ, passes through formula
Calculating is based on the incoming flow reynolds number Re of weapon-bay leading edge surface boundary layer thickness δ
δ
(2) determine fundamental frequency disturbance sheet: described fundamental frequency disturbance sheet indentation, each profile of tooth is equicrural triangle, and each between cog gapless is evenly distributed, and the thickness H of fundamental frequency disturbance sheet is 15%～50% of weapon-bay leading edge surface boundary layer thickness δ; The width W of fundamental frequency disturbance sheet is passed through formula
Calculate, wherein, u is that weapon-bay leading edge surface boundary 1ayer inner height is the speed of incoming flow of H position, and ω is forcing frequency;
The thickness H of disturbance sheet has determined strength of turbulence, and general thicker disturbance sheet strength of turbulence is larger, but this thickness should not approach even surpass local boundary layer thickness δ, closes under the situation flow-disturbing effect that the disturbance sheet is unnecessary to prevent weapon-bay.The width of disturbance sheet determines the forcing frequency of the other side chamber stream.Disturbance sheet tooth width D determines that exhibition to the disturbance wave number, embodies the three-dimensional turbulence effect.
Tooth width D on the described fundamental frequency disturbance sheet is D=0.5W～3W.
The concrete of described forcing frequency ω determines that method is: by the flying speed ν under the supersonic aircraft state of flight, incoming flow reynolds number Re
δ, incoming flow density p, temperature of incoming flow T and incoming flow coefficient of viscosity μ, the unstable forcing frequency scope of weapon-bay shear layer when adopting the linearized stability analysis method to obtain without additional disturbance, wherein the most unsettled frequency values is forcing frequency ω.
(3) according to the length of supersonic aircraft weapon-bay, dark, wide size, calculate the ratio of length and the degree of depth of supersonic aircraft, when this ratio greater than 4 the time, the thickness H of fundamental frequency disturbance sheet is reduced 10～20%; When this when being not more than 4, the thickness H of fundamental frequency disturbance sheet is increased by 10～20%;
(4) fundamental frequency disturbance sheet is fixed on the supersonic aircraft to finish supersonic aircraft weapon-bay leading edge surface flow-disturbing noise reduction.
Described fundamental frequency disturbance sheet is fixed on the supersonic aircraft is specially: fundamental frequency disturbance sheet is fixedly mounted on the place ahead of weapon-bay, sawtooth is towards coming flow path direction, between fundamental frequency disturbance sheet trailing edge and the weapon-bay leading edge to satisfy the trailing edge of B=0～1W and fundamental frequency disturbance sheet apart from B parallel with the weapon-bay leading edge.
If the vacant size of weapon-bay leading edge surface is limited, one row's fundamental frequency sawtooth disturbance sheet then only is set, if the space is enough, then can between fundamental frequency disturbance sheet and weapon-bay, fixedly mount again an inferior harmonics disturbance sheet, the thickness of this Asia harmonics disturbance sheet is identical with fundamental frequency disturbance sheet, width is 2 times of fundamental frequency disturbance sheet width, tooth width is 2 times of fundamental frequency disturbance sheet tooth width, the sawtooth of inferior harmonics disturbance sheet is also towards coming flow path direction, distance between the leading edge of inferior harmonics disturbance sheet and the trailing edge of fundamental frequency disturbance sheet is 1～2W, and inferior harmonics disturbance sheet trailing edge and distance between the weapon-bay leading edge are that the trailing edge of 0～1W and inferior harmonics disturbance sheet is parallel with the weapon-bay leading edge.
Theoretical investigation finds that inferior humorous resonance wave has the booster action that accelerates to inspire the boundary 1ayer unstability, shear layer is turned fast twist the formation turbulent flow, before so this method is installed in fundamental frequency disturbance sheet, its leading perturbation action after inferior harmonics disturbance is installed in, plays auxiliary perturbation action.
Disturbance sheet quality can be selected iron, aluminium or other complex fire resistant metallic material.
Such as Fig. 2 (b), when high velocity air flow through weapon-bay, sawtooth disturbance sheet formed the three-dimensional turbulence ripple, induce and flow to the vortex structure appearance in the shear layer, and impel mobile being turned to the microturbulence structure by large scale eddy to twist, and form thereby suppress the acoustic feed back ring, reduce the periodic oscillation of weapon-bay internal pressure.
So far, weapon-bay leading edge flow-disturbing noise-reduction method is implemented to finish.
Embodiment:
The general flying height 0km of aircraft～15km, flight Mach number is 0～3.Weapon-bay is reduced to chamber, rectangle side, and for example: the square chamber degree of depth is 150mm, and long is 450mm, and length depth ratio is 3; If flight Mach number is 1.5, for referencial use with the sea level value, the incoming flow velocity of sound is 340m/s, and coming current density is 1.225kg/m
3, temperature of incoming flow is 288.16K, then coefficient of dynamic viscosity is 1.7894 * 10
-5Kg/ (ms), square leading edge cavity surface-boundary layer thickness is 5mm, based on the Re of square leading edge cavity surface-boundary layer thickness
δNumber is 1.73 * 10
5
1) such as Fig. 3, disturbance sheet thickness H chooses 25% local boundary layer thickness 5mm, i.e. H=1.25mm.
2) such as Fig. 3, W represents disturbance sheet width.The linearized stability analysis method obtains to get ω=20000Hz in this example without adding least Stable Perturbation frequency limit ω=0～29200Hz of disturbance time side chamber shear layer; Boundary 1ayer is u=187.27m/s in H=1.25mm place speed, determines thus fundamental frequency disturbance sheet width W=u/ ω=9.36mm, and inferior harmonics disturbance sheet width is 2 times of fundamental frequency disturbance sheet width, i.e. 2W=18.72mm.
3) such as Fig. 4, D is disturbance sheet tooth width, and the tooth width of getting the disturbance sheet in this example equates with sheet is wide, i.e. D=W=9.36mm, and inferior harmonics disturbance sheet tooth width is 2D=2W=18.72mm.Disturbance sheet number of teeth n is determined by weapon-bay developed width L, such as fundamental frequency disturbance sheet number of teeth n=L/D.
4) get the subharmonic disturbance sheet in this example and be close to weapon-bay costa, i.e. B=0mm.Such as Fig. 4, fundamental frequency disturbance sheet is before the subharmonic disturbance sheet, and distance is set as W=9.36mm between the two, and fundamental frequency disturbance pitch of fins weapon-bay leading edge distance is W+2W+B=28.08mm.If the vacant area of weapon-bay leading edge surface is not enough, then removes the subharmonic disturbance sheet, and replace subharmonic disturbance sheet position to be close to the arrangement of weapon-bay leading edge, i.e. B=0mm fundamental frequency disturbance sheet.The disturbance sheet all with weapon-bay costa keeping parallelism.
The fundamental frequency disturbance sheet and the inferior harmonics disturbance sheet that design are fixed on supersonic aircraft weapon-bay leading edge surface by modes such as pasting, inlay, by experiment checking, this embodiment can effectively realize the noise reduction in the weapon-bay.
The present invention not detailed description is technology as well known to those skilled in the art.
Claims (5)
1. supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing is characterized in that step is as follows:
(1) the flight operating mode according to supersonic aircraft obtains flying speed v, incoming flow density p, temperature of incoming flow T, incoming flow coefficient of viscosity μ and weapon-bay leading edge surface boundary layer thickness δ, passes through formula
Calculating is based on the incoming flow reynolds number Re of weapon-bay leading edge surface boundary layer thickness δ
δ
(2) determine fundamental frequency disturbance sheet: described fundamental frequency disturbance sheet indentation, each profile of tooth is equicrural triangle, and each between cog gapless is evenly distributed, and the thickness H of fundamental frequency disturbance sheet is 15%～50% of weapon-bay leading edge surface boundary layer thickness δ; The width W of fundamental frequency disturbance sheet is passed through formula
Calculate, wherein, u is that weapon-bay leading edge surface boundary 1ayer inner height is the speed of incoming flow of H position, and ω is forcing frequency;
(3) according to the length of supersonic aircraft weapon-bay, dark, wide size, calculate the ratio of length and the degree of depth of supersonic aircraft, when this ratio greater than 4 the time, the thickness H of fundamental frequency disturbance sheet is reduced 10～20%; When this when being not more than 4, the thickness H of fundamental frequency disturbance sheet is increased by 10～20%;
(4) fundamental frequency disturbance sheet is fixed on the supersonic aircraft to finish supersonic aircraft weapon-bay leading edge surface flow-disturbing noise reduction.
2. a kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing according to claim 1 is characterized in that: the concrete of described forcing frequency ω determines that method is: by the flying speed v under the supersonic aircraft state of flight, incoming flow reynolds number Re
δ, incoming flow density p, temperature of incoming flow T and incoming flow coefficient of viscosity μ, the unstable forcing frequency scope of weapon-bay shear layer when adopting the linearized stability analysis method to obtain without additional disturbance, wherein the most unsettled frequency values is forcing frequency ω.
3. a kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing according to claim 1, it is characterized in that: the tooth width D on the described fundamental frequency disturbance sheet is D=0.5W～3W.
4. a kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing according to claim 1, it is characterized in that: described fundamental frequency disturbance sheet is fixed on the supersonic aircraft is specially: fundamental frequency disturbance sheet is fixedly mounted on the place ahead of weapon-bay, sawtooth is towards coming flow path direction, between fundamental frequency disturbance sheet trailing edge and the weapon-bay leading edge to satisfy the trailing edge of B=0～1W and fundamental frequency disturbance sheet apart from B parallel with the weapon-bay leading edge.
5. a kind of supersonic aircraft weapon-bay noise-reduction method based on the leading edge surface flow-disturbing according to claim 1, it is characterized in that: between fundamental frequency disturbance sheet and weapon-bay, can also fixedly mount an inferior harmonics disturbance sheet, the thickness of this Asia harmonics disturbance sheet is identical with fundamental frequency disturbance sheet, width is 2 times of fundamental frequency disturbance sheet width, tooth width is 2 times of fundamental frequency disturbance sheet tooth width, the sawtooth of inferior harmonics disturbance sheet is also towards coming flow path direction, distance between the leading edge of inferior harmonics disturbance sheet and the trailing edge of fundamental frequency disturbance sheet is 1～2W, and inferior harmonics disturbance sheet trailing edge and distance between the weapon-bay leading edge are that the trailing edge of 0～1W and inferior harmonics disturbance sheet is parallel with the weapon-bay leading edge.
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| CN104654926A (en) * | 2015-02-13 | 2015-05-27 | 中国人民解放军防空兵学院 | Supersonic velocity mixing layer control method |
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| CN108706092A (en) * | 2018-05-31 | 2018-10-26 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of zigzag flight device noise suppression device for weapon bay |
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| CN104654926A (en) * | 2015-02-13 | 2015-05-27 | 中国人民解放军防空兵学院 | Supersonic velocity mixing layer control method |
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| CN108706092B (en) * | 2018-05-31 | 2020-06-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Sawtooth-shaped aircraft weapon cabin noise suppression device |
| CN109941424A (en) * | 2019-03-25 | 2019-06-28 | 西北工业大学 | A kind of thermal protection struc ture integration leading edge for Air-breathing hypersonic vehicle |
| CN114450224A (en) * | 2019-07-01 | 2022-05-06 | 张传瑞 | Aerodynamic techniques and methods for performing quieter supersonic flight |
| CN111470045A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Self-suction type air entraining device for aircraft internal weapon cabin |
| CN112623197A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Shunting device for cavity noise control and noise control method |
| CN112623197B (en) * | 2020-12-29 | 2023-08-04 | 中国航空工业集团公司西安飞机设计研究所 | Shunt device for cavity noise control and noise control method |
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