CN102862676B - 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 leading edge surface flow-disturbing, for reducing interior violent noise and self-holding pressure oscillation in weapon-bay while burying the supersonic flight of weapon-bay aircraft.
Background technology
In weapon, burying is the inevitable development trend of supersonic aircraft weapon carrying mode, buries weapon-bay and weapon carry schematic diagram in Fig. 1 is fighter plane, and the structure of having described weapon-bay under hatch door unlatching situation in figure forms.During aircraft supersonic flight, open after weapon-bay, as schematic diagram 2 (a), high velocity air flows through air in weapon-bay surface and cabin and is mixed to form shear layer, 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 cabin, and induce shear layer scrollwork to rise, after shear layer scrollwork frequency is consistent with reflected pressure frequency, cause acoustic feed back ring to form, and cause the persistent oscillation under characteristic frequency of cabin internal pressure.Pressure oscillation in weapon-bay not only can cause damage to equipment such as weaponry, weapon mount point, electronic machines in 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.Many weapon-bay acoustic feed backs of Ru U.S. exploitation suppress system, and basic thought is in weapon-bay leading edge surface, additional device to be set to force high velocity air to depart from weapon-bay mostly, to avoid gas in incoming flow and cabin to be mixed to form shear layer and acoustic feed back ring.For another example the weapon-bay plasma actuator system occurring in China, this system is utilized plasma actuator to induct to flow and is made to depart from hatch through the shear layer of weapon-bay, reaches the object that reduces the pressure oscillation in cabin.These technology are principle mainly with forcing shear layer to depart from weapon-bay greatly, the apparatus system more complicated adopting, reliability when the not only design proposition extra demand to aerocraft system, and the operation of these complex appts also can be executed the task to aircraft 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 leading edge surface flow-disturbing is provided, solve supersonic aircraft when carrying out supersonic flight, inside buried 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 supersonic aircraft weapon-bay noise-reduction method based on leading edge surface flow-disturbing, step is as follows:
(1) according to the flight operating mode of supersonic aircraft, obtain 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, pass through formula
the incoming flow reynolds number Re of calculating based on 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 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 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 while adopting 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 length of supersonic aircraft and the ratio of the degree of depth, when this ratio is greater than 4, the thickness H of fundamental frequency disturbance sheet is reduced to 10～20%; When this is when being not more than 4, the thickness H of fundamental frequency disturbance sheet is increased to 10～20%;
(4) fundamental frequency disturbance sheet is fixed on supersonic aircraft to complete supersonic aircraft weapon-bay leading edge surface flow-disturbing noise reduction.
Described fundamental frequency disturbance sheet is fixed on supersonic aircraft and is specially: fundamental frequency disturbance sheet is fixedly mounted on the place ahead of weapon-bay, sawtooth is towards carrying out flow path direction, and fundamental frequency disturbance sheet trailing edge is parallel with weapon-bay leading edge with the trailing edge that distance B between weapon-bay leading edge meets B=0～1W and fundamental frequency disturbance sheet.
Between fundamental frequency disturbance sheet and weapon-bay, can also fixedly mount a sub-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 sub-harmonics disturbance sheet is also towards carrying out flow path direction, the leading edge of sub-harmonics disturbance sheet and the distance between the trailing edge of fundamental frequency disturbance sheet are 1～2W, and sub-harmonics disturbance sheet trailing edge and distance between weapon-bay leading edge are that the trailing edge of 0～1W and sub-harmonics disturbance sheet is parallel with weapon-bay leading edge.
The present invention's advantage is compared with prior art: this method can effectively reduce supersonic aircraft when carrying out supersonic flight, buries after weapon-bay internal pressure serious self sustained oscillation problem in cabin in opening.This method is simple, easy to operate, reliable in function, and can with various in bury weapon-bay fighter plane reasonable combination.This method, by zigzag fashion size design, can guarantee, when weapon-bay hatch door is not opened, to avoid aircraft surface boundary layer perturbation, to guarantee that aircraft surface incoming flow keeps former flow performance.
Accompanying drawing explanation
Fig. 1 buries weapon-bay hatch door to open schematic diagram in high-performance fighter aircraft;
The interior shear flow of weapon-bay and reflected pressure interaction schematic diagram when Fig. 2 (a) is Supersonic Stream;
Fig. 2 (b) is for pasting shear flow and reflected pressure interaction schematic diagram in disturbance sheet weapon-bay afterwards
Fig. 3 is arrangement relation and each size schematic diagram of sawtooth disturbance sheet and weapon-bay leading edge surface
Fig. 4 is that fundamental frequency sawtooth disturbance sheet and sub-harmonics sawtooth disturbance chip size are related to schematic diagram
Fig. 5 is the inventive method diagram of circuit.
The specific embodiment
For avoiding shear layer to clash into weapon-bay trailing edge, the invention provides a kind of supersonic aircraft weapon-bay noise-reduction method based on leading edge surface flow-disturbing, the method not only can effectively reduce violent pressure oscillation in weapon-bay, and can with current various complexity in bury 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) according to the flight operating mode of supersonic aircraft, obtain 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, pass through formula
the incoming flow reynolds number Re of calculating based on 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 and even surpass local boundary layer thickness δ, to prevent that weapon-bay from closing under situation, the flow-disturbing effect that disturbance sheet is unnecessary.The width of disturbance sheet determines the forcing frequency of the other side chamber stream.Disturbance sheet tooth width D determines that exhibition, to disturbance wave number, embodies three-dimensional turbulence effect.
Tooth width D on 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 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 while adopting 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 length of supersonic aircraft and the ratio of the degree of depth, when this ratio is greater than 4, the thickness H of fundamental frequency disturbance sheet is reduced to 10～20%; When this is when being not more than 4, the thickness H of fundamental frequency disturbance sheet is increased to 10～20%;
(4) fundamental frequency disturbance sheet is fixed on supersonic aircraft to complete supersonic aircraft weapon-bay leading edge surface flow-disturbing noise reduction.
Described fundamental frequency disturbance sheet is fixed on supersonic aircraft and is specially: fundamental frequency disturbance sheet is fixedly mounted on the place ahead of weapon-bay, sawtooth is towards carrying out flow path direction, and fundamental frequency disturbance sheet trailing edge is parallel with weapon-bay leading edge with the trailing edge that distance B between weapon-bay leading edge meets B=0～1W and fundamental frequency disturbance sheet.
If the vacant size of weapon-bay leading edge surface is limited, one row's fundamental frequency sawtooth disturbance sheet is only set, if space is enough, can between fundamental frequency disturbance sheet and weapon-bay, fixedly mount again a sub-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 sub-harmonics disturbance sheet is also towards carrying out flow path direction, the leading edge of sub-harmonics disturbance sheet and the distance between the trailing edge of fundamental frequency disturbance sheet are 1～2W, sub-harmonics disturbance sheet trailing edge and distance between weapon-bay leading edge are that the trailing edge of 0～1W and sub-harmonics disturbance sheet is parallel with weapon-bay leading edge.
Theoretical investigation discovery, sub-humorous resonance wave has the booster action that accelerates to inspire boundary 1ayer unstability, can make shear layer turn fast and twist formation turbulent flow, before therefore this method is arranged on fundamental frequency disturbance sheet, its leading perturbation action, after sub-harmonics disturbance is arranged on, plays auxiliary perturbation action.
Disturbance sheet quality can be selected iron, aluminium or other complex fire resistant metallic material.
As Fig. 2 (b), when high velocity air flows through weapon-bay, sawtooth disturbance sheet forms three-dimensional turbulence ripple, in induction shear layer, flowing to vortex structure occurs, and impel to flow and turn and twist to microturbulence structure by large scale eddy, thereby suppress acoustic feed back ring, form, reduce the periodic oscillation of weapon-bay internal pressure.
So far, weapon-bay leading edge flow-disturbing noise-reduction method has been implemented.
Embodiment:
The general flying height 0km～15km of aircraft, 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, long is 450mm, and length depth ratio is 3; If flight Mach number is 1.5, for referencial use with sea level value, the incoming flow velocity of sound is 340m/s, and carrying out current density is 1.225kg/m
3, temperature of incoming flow is 288.16K, coefficient of dynamic viscosity is 1.7894 * 10
-5kg/ (ms), square leading edge cavity surface-boundary layer thickness is 5mm, the Re based on square leading edge cavity surface-boundary layer thickness
δnumber is 1.73 * 10
5.
1), as Fig. 3, disturbance sheet thickness H chooses 25% local boundary layer thickness 5mm, i.e. H=1.25mm.
2), as Fig. 3, W represents disturbance sheet width.Linearized stability analysis method obtains without adding least Stable Perturbation frequency limit ω=0～29200Hz of disturbance time side chamber shear layer, gets ω=20000Hz in this example; 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 sub-harmonics disturbance sheet width is 2 times of fundamental frequency disturbance sheet width, i.e. 2W=18.72mm.
3) as Fig. 4, D is disturbance sheet tooth width, and the tooth width of getting disturbance sheet in this example equates with sheet is wide, i.e. D=W=9.36mm, and sub-harmonics disturbance sheet tooth width is 2D=2W=18.72mm.Disturbance sheet number of teeth n is determined by weapon-bay developed width L, as fundamental frequency disturbance sheet number of teeth n=L/D.
4) in this example, get subharmonic disturbance sheet and be close to weapon-bay costa, i.e. B=0mm.As Fig. 4, fundamental frequency disturbance sheet is before 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, removes 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.Disturbance sheet all with weapon-bay costa keeping parallelism.
The fundamental frequency disturbance sheet designing and sub-harmonics disturbance sheet are fixed on to supersonic aircraft weapon-bay leading edge surface by modes such as pasting, inlay, checking by experiment, this embodiment can effectively realize the noise reduction in weapon-bay.
The present invention not detailed description is known to the skilled person technology.
Claims (5)
1. the supersonic aircraft weapon-bay noise-reduction method based on leading edge surface flow-disturbing, is characterized in that step is as follows:
(1) according to the flight operating mode of supersonic aircraft, obtain 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, pass through formula
the incoming flow reynolds number Re of calculating based on 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 length of supersonic aircraft and the ratio of the degree of depth, when this ratio is greater than 4, the thickness H of fundamental frequency disturbance sheet is reduced to 10～20%; When this is when being not more than 4, the thickness H of fundamental frequency disturbance sheet is increased to 10～20%;
(4) fundamental frequency disturbance sheet is fixed on supersonic aircraft to complete supersonic aircraft weapon-bay leading edge surface flow-disturbing noise reduction.
2. a kind of supersonic aircraft weapon-bay noise-reduction method based on 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 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 while adopting 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 leading edge surface flow-disturbing according to claim 1, is characterized in that: the tooth width D on described fundamental frequency disturbance sheet is D=0.5W～3W.
4. a kind of supersonic aircraft weapon-bay noise-reduction method based on leading edge surface flow-disturbing according to claim 1, it is characterized in that: described fundamental frequency disturbance sheet is fixed on supersonic aircraft and is specially: fundamental frequency disturbance sheet is fixedly mounted on the place ahead of weapon-bay, sawtooth is towards carrying out flow path direction, and fundamental frequency disturbance sheet trailing edge is parallel with weapon-bay leading edge with the trailing edge that distance B between weapon-bay leading edge meets B=0～1W and fundamental frequency disturbance sheet.
5. a kind of supersonic aircraft weapon-bay noise-reduction method based on leading edge surface flow-disturbing according to claim 1, it is characterized in that: between fundamental frequency disturbance sheet and weapon-bay, also fixedly mount a sub-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 sub-harmonics disturbance sheet is also towards carrying out flow path direction, the leading edge of sub-harmonics disturbance sheet and the distance between the trailing edge of fundamental frequency disturbance sheet are 1～2W, sub-harmonics disturbance sheet trailing edge and distance between weapon-bay leading edge are that the trailing edge of 0～1W and sub-harmonics disturbance sheet is parallel with weapon-bay leading edge.
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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 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1319063A (en) * | 1998-09-25 | 2001-10-24 | 吉科有限公司 | Load-bearing structure with reduced tip vortex |
| US7413408B1 (en) * | 2007-02-22 | 2008-08-19 | Samuel B Tafoya | Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades |
| CN101332870A (en) * | 2007-05-25 | 2008-12-31 | 波音公司 | Plasma actuator system and method for use with a weapons bay on a high speed mobile platform |
| CN102530242A (en) * | 2011-12-01 | 2012-07-04 | 中国航天空气动力技术研究院 | Wingtip noise control and device |
-
2012
- 2012-09-29 CN CN201210380283.8A patent/CN102862676B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1319063A (en) * | 1998-09-25 | 2001-10-24 | 吉科有限公司 | Load-bearing structure with reduced tip vortex |
| US7413408B1 (en) * | 2007-02-22 | 2008-08-19 | Samuel B Tafoya | Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades |
| CN101332870A (en) * | 2007-05-25 | 2008-12-31 | 波音公司 | Plasma actuator system and method for use with a weapons bay on a high speed mobile platform |
| CN102530242A (en) * | 2011-12-01 | 2012-07-04 | 中国航天空气动力技术研究院 | Wingtip noise control and device |
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