CN104527971B - The reverse jet flow spray orifice of a kind of hypersonic aircraft drag reduction solar heat protection method for designing - Google Patents
The reverse jet flow spray orifice of a kind of hypersonic aircraft drag reduction solar heat protection method for designing Download PDFInfo
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Abstract
The invention discloses the reverse jet flow spray orifice of a kind of hypersonic aircraft drag reduction solar heat protection method for designing, be specifically related to the Practical Method of Designing of the reverse jet flow drag reduction of hypersonic aircraft solar heat protection, the method for designing of polygonal spray orifice such as proposed. First,, according to passivation radius R 0, select area of injection orifice S; Secondly, polygonal angle number n such as determine; When waiting corner point place radius of a circle in the circumradius R of polygon spray orifice and polygon to determine with the ratio cc of R, definite polygonal quantity n, can determine polygonal spray orifice shapes such as spray orifice simultaneously. The present invention is waiting on the basis of nozzle hole area, adjust etc. the shape of polygonal spray orifice by the position of polygonal angle of flare numbers such as control and inside lock, control the influence area of jet flow stream field with the method, improve the performance of hypersonic aircraft by expanding the influence area of spray orifice stream field, realize optimum drag reduction and anti-thermal characteristics, for Flight Vehicle Design provides technical support.
Description
Technical field
The present invention relates to the drag reduction solar heat protection conceptual design of hypersonic aircraft, be specifically related to hypersonic aircraft reverseThe Practical Method of Designing of jet flow drag reduction solar heat protection, for the object blunt nosed precursor that is hypersonic aircraft.
Background technology
Along with the development of aeronautical and space technology, faster flying speed, farther flying distance, higher flying height,Larger flight domain has become the target that Aero-Space scientific worker constantly pursues. Hypersonic aircraft was flyingCheng Zhong, can be subject to great resistance, and main resistance is from wave resistance, and how effectively to reduce resistance is numerous research all the timeThe problem that scholar pays close attention to.
In the time that hypersonic aircraft enters atmosphere with flank speed, drag reduction and thermal protection are particularly important for it.This type of aircraft comprises hypersonic missile, reentry vehicle and Hypersonic Aircraft. When aircraft is during with hypersonic flight,Wave resistance will account for the more than 50% of drag overall, and along with the increase of flight Mach number, wave resistance will sharply increase simultaneously, therefore, and drag reduction masterConcentrate on the reduction of wave resistance. Meanwhile, maximum heat flow valuve appears at the stationary point place of aircraft front end conventionally, therefore should be by researchFocus on the Configuration Design at front end stationary point place. For this class hypersonic aircraft, drag reduction and solar heat protection are effectivelyA key technology.
In recent years, researcher has proposed scalable such as the concentrated energy deposition along stationary point line, blunt body headThimble and carry out drag reduction and reduce the heat flux distribution of aircraft surface in technology such as the reverse jet flows in region, stationary point, and, according toWhether controlled active and the passive scheme divided into of scheme. The scheme that scalable thimble is wherein installed on blunt body top belongs toIn passive drag reduction scheme, this kind of scheme is used for reducing shock strength. And belong to along reverse jet flow and the energy deposition scheme of stationary point lineIn ACTIVE CONTROL scheme. Because the technical difficulty of engineering application aspect promotes, the just side of resting on of the research of energy deposition schemeCase and theoretical research aspect. And oppositely jet flow deters one of scheme as reduction of heat, attract increasing researcher to openExhibition research, groundwork just concentrates on the reverse jet flow design studies of circular spray orifice. But the anti-thermal effect of the drag reduction of its designFruit is general, can not significantly improve the drag reduction thermal protective performance of hypersonic aircraft.
Summary of the invention
Can not significantly improve the defect of the anti-thermal characteristics of its drag reduction in order to improve circular spray orifice, the present invention proposes a kind of superbThe reverse jet flow spray orifice of velocity of sound aircraft drag reduction solar heat protection method for designing, can solve its deficiency well, realizes its efficiently drag reductionThe object of solar heat protection.
The present invention relates to the drag reduction solar heat protection conceptual design of hypersonic aircraft, be specifically related to hypersonic aircraft reverseThe Practical Method of Designing of jet flow drag reduction solar heat protection, the method for designing of polygonal spray orifice such as has proposed, specific as follows:
The reverse jet flow spray orifice of a kind of hypersonic aircraft drag reduction solar heat protection method for designing, its step is as follows:
First, determine nozzle hole area S;
According to passivation radius R0, selecting area of injection orifice S, area of injection orifice S meets: 0.01 × π × R0 2<S<0.25×π×R0 2；
Secondly, determine polygonal angle number n;
When aircraft is during with hypersonic flight, wave resistance will account for the more than 50% of drag overall, simultaneously along with flight Mach numberIncrease, wave resistance will sharply increase, therefore, drag reduction mainly concentrates on the reduction of wave resistance. Oppositely jet flow can change original arcThe flow field of shock wave, makes bowshock be transformed into separation shock wave, thereby realizes drag reduction object, and reducing of resistance, not only can improveThe lift-drag ratio of aircraft, and relatively in situation, can improve propulsive efficiency, fuel saving. As n → ∞, nozzle configuration will becomeCircle, reduces the domain of influence of three-dimensional flow field. Therefore, waiting under the prerequisite of area of injection orifice, along with the increase of n, the impact of jet flowTerritory reduces after first increasing gradually, has optimum spray angle number, make the domain of influence maximum of jet flow, and then drag-reduction effect is best, optimumSpray angle number can be by the method for exhaustion (calculating one by one until find out the optimum angle number of spraying) or optimization method (according to orthogonal arrayArrange test number (TN), the result then obtaining according to test is carried out fitting of a polynomial, finally adopts genetic algorithm to multinomialLimiting the interval optimum spray angle number of finding) determine. At this, considering structural design difficulty or ease, heat protection design Demand BaseUpper, adopt multidisciplinary design optimization (to consider the optimization among a small circle of the limiting factors such as structure, thermal protection, refer to article WangZG,HuangW,YanL.MultidisciplinarydesignoptimizationapproachanditsApplicationtoaerospaceengineering.Chin.Sci.Bull., 2014,59:5338-5353), select to closeN is counted at suitable angle, can improve the resistance reducing performance of jet flow. Wherein n must meet: n > 2 and for integer, n is not more than 20.
The 3rd step, determines the value of R and r;
By etc. polygonal nozzle hole area formulaKnown, count n when area of injection orifice S and angle and determineAfter, etc. the circumradius R of polygonal spray orifice scheme with etc. place, the polygonal spray orifice inside lock summit radius of a circle r pass that is inversely proportional toSystem, R has determined the value farthest that polygonal can be touched, r such as has determined at the patient minimum in polygonal spray orifice inside lock summitValue, but R must be less than R0, and 0 < r < R, known according to α=r/R relation, determine that α can determine R and r, the interval of α is[0.2,0.8]。
Wherein: R such as is at the circumradius of polygonal spray orifice scheme, r such as is at place, the polygonal spray orifice inside lock summit circleRadius, θ be adjacent two spray angles angle, θ=2 π/n, wherein, the angle number that n is spray orifice, α=r/R.
The 4th step, after determining R and r value, generation waits the spray orifice shape of n dihedral.
Obtain after S, n and α, according to dependency relation formula be α=r/R and etc. polygonal nozzle hole area formulaTry to achieve R and r,, in 3D sculpting software (Solidworks, Catia or ProE etc.), determine sprayThe concrete shape of mouth, then generates reverse jet flow scheme in blunt body leading edge. Finally, polygonal reverse jet flow scheme such as obtainProfile.
In the present invention: r value can not be too little, R can not exceed the radius of blunt body in theory, but actual conditions R value was difficult forGreatly, and r < R < 0.5R0. The quantity at the polygonal angles such as the present invention can control and etc. polygonal size control hypersonicThe impact of aircraft precursor flow field characteristic, and then realize the control to drag reduction solar heat protection.
As everyone knows, in homalographic profile, the outermost border minimum that circle can reach, therefore convection current in three-dimensional flow fieldThe domain of influence of field is also less, and the highest distance position that separation shock wave can be released is also nearer, and that will certainly produce near blunt bodyStronger shock wave, and then produce larger resistance. Near the recirculating zone producing spray orifice also less simultaneously, to the shadow in whole flow fieldRing territory less. The polygonal spray orifice schemes such as employing, for three-dimensional flow field, can make full use of the mutual shadow between three-dimensional flow fieldRing, change the little shortcoming of the circular spray orifice domain of influence, further improve drag reduction and thermal protective performance, promote its overall performance.
Waiting on the basis of nozzle hole area, adjusting by the position of polygonal angle of flare numbers such as control and inside lock etc.The shape of polygonal spray orifice, controls the influence area of jet flow stream field with the method, by expanding the impact of spray orifice stream fieldThe performance of hypersonic aircraft is improved in region, realizes optimum drag reduction and anti-thermal characteristics, props up for Flight Vehicle Design provides technologyHold.
Brief description of the drawings
Fig. 1 is reverse jet flow schematic diagram. In figure, 1 is second-compressed shock wave, and 2 is recirculating zone, and 3 is jet layer, and 4 is MachDish, 5 for separating shock wave, and 6 is contact-making surface, and 7 is spray orifice. M∞For incoming flow Mach number, P0∞For incoming flow stagnation pressure, MjFor jet flow Mach number,P0jFor jet flow stagnation pressure.
Fig. 2 is polygonal spray scheme. Wherein O is the center of polygonal spray orifice, and R such as is at the external of polygonal spray orifice schemeRadius of circle, r such as is at place, the polygonal spray orifice inside lock summit radius of a circle, θ is the angle at adjacent two spray angles, θ=2 π/n, itsIn, the angle number that n is spray orifice, α=r/R.
Fig. 3 is positive pentagon spray orifice schematic diagram in the present invention.
Detailed description of the invention
In Supersonic Stream, the type of flow that adopts reverse jet flow is very complicated, and as shown in Figure 1, it comprises secondaryCompression shock 1, recirculating zone 2, jet layer 3, mach disk 4, separation shock wave 5 and contact-making surface 6, wherein 7 is spray orifice. M∞For incoming flow MachNumber, P0∞For incoming flow stagnation pressure, MjFor jet flow Mach number, P0jFor jet flow stagnation pressure. Mach disk 4 balances in flow field the pressure of jet flowWith the incoming-flow pressure after bowshock, form contact-making surface 6 in the outer end of mach disk 4, counter-flow jets forms back under incoming flow effectStream region, then invest object plane. Free incoming flow forms bowshock under the acting in opposition of jet flow, and border, recirculating zone outer rim shapeBecome second-compressed shock wave. Due to the existence of recirculating zone, reduce Aerodynamic Heating, in the recirculating zone of stationary point in jet flow, fall simultaneouslyNear gas temperature low stagnation region, and a little less than recompression shock wave wants more than the bowshock without in jet flow situation, and dot againThe dot temperature again at wall place also by the stagnation temperature far below without in jet flow situation, therefore for Aerodynamic Heating, playGood anti-thermal effect.
Known according to reverse jet flow principle, spray orifice shape is most important to the flow of whole aircraft. The present invention carriesGo out a kind of contrainjection scheme that is different from conventional spray orifice, wait polygon spray scheme. When etc. polygonal spray orifice scheme outsideConnect radius of circle R and etc. the ratio cc of polygonal spray orifice inside lock summit place radius of a circle and R determine, determine polygonal simultaneouslyQuantity n, can determine polygonal spray orifice shapes such as spray orifice. In the present embodiment, its spray orifice scheme as shown in Figure 2, is selected etc. five jiaosShape spray orifice, as its spray orifice scheme, generates jet model.
Design process of the present invention comprises the following steps:
Step 1: determine area of injection orifice S.
After the passivation of hypersonic aircraft precursor, resistance increment, for effective drag reduction, can adopt at blunt body front end anti-Realize drag reduction solar heat protection to jet flow. In the time that actual area of injection orifice is selected, if area of injection orifice is too small, the domain of influence to three-dimensional flow fieldLess, drag-reduction effect is not obvious; If area of injection orifice is excessive, by increase jet flow flow control difficulty, and be not suitable for engineering shouldWith. Therefore, according to passivation radius R0, selecting rational area of injection orifice S, S meets: 0.01 × π × R0 2<S<0.25×π×R0 2, comeControl jet flow flow, and then affect flow field, make bowshock be transformed into precursor and separate shock wave, and then realize anti-drag function.
Step 2: determine that polygonal angle counts n.
When aircraft is during with hypersonic flight, wave resistance will account for the more than 50% of drag overall, simultaneously along with flight Mach numberIncrease, wave resistance will sharply increase, therefore, drag reduction mainly concentrates on the reduction of wave resistance. Oppositely jet flow can change original arcThe flow field of shock wave, makes bowshock be transformed into separation shock wave, thereby realizes drag reduction object, and reducing of resistance, not only can improveThe lift-drag ratio of aircraft, and relatively in situation, can improve propulsive efficiency, fuel saving. As n → ∞, nozzle configuration will becomeCircle, reduces the domain of influence of three-dimensional flow field. Therefore, waiting under the prerequisite of area of injection orifice, along with the increase of n, the impact of jet flowTerritory reduces after first increasing gradually, has optimum spray angle number, make the domain of influence maximum of jet flow, and then drag-reduction effect is best, optimumSpray angle number can be determined by the method for exhaustion or optimization method. Therefore, considering structural design difficulty or ease, heat protection design demand baseOn plinth, adopt multidisciplinary design optimization, select suitable angle to count n, can improve the resistance reducing performance of jet flow. Wherein n is necessaryMeet: n 2 and be integer, advise that n is not more than 20. N=5 in the present embodiment.
Step 3: determine R and r.
On the basis of step 1 and step 2, according to area of injection orifice formulaKnown, R and rThe relation that is inversely proportional to, R has determined the value farthest that polygonal can be touched, r has determined etc. that polygonal spray orifice inside lock summit can holdThe minimum of a value of bearing, but R must be less than R0, and 0 < r < R.
Step 4: determine α.
Known according to α=r/R relation, determine that α can determine R and r, choose reasonable α is most important to nozzle configuration, buildsThe interval of view α is [0.2,0.8].
Step 5: determine reverse jet flow profile.
Obtain, after S, n and α, trying to achieve R and r according to dependency relation formula, 3D sculpting software (Solidworks, Catia orProE etc.) in determine the concrete shape of spout, then generate reverse jet flow scheme in blunt body leading edge. Finally, obtain etc. polygonalThe reverse jet flow scheme profile of shape.
The embodiment of the present invention is according to the design principle of Fig. 1 and Fig. 2, the pentagon spray orifice such as finally selects as its spray sideCase, generates jet model referring to Fig. 3.
Claims (4)
1. the reverse jet flow spray orifice of a hypersonic aircraft drag reduction solar heat protection method for designing, is characterized in that its step is as follows:
First, determine nozzle hole area S;
According to passivation radius R0, select area of injection orifice S;
Secondly, polygonal angle number n such as determine;
Waiting under the prerequisite of area of injection orifice, along with the increase of n, the domain of influence of jet flow reduces after first increasing gradually, therefore existsExcellent spray angle number, make the domain of influence maximum of jet flow, and then drag-reduction effect is best, and optimum spray angle number can be passed through the method for exhaustion or excellentChange method is determined; At this, considering, on structural design difficulty or ease, heat protection design Demand Base, to adopt multidisciplinary design optimizationMethod, selects suitable angle to count n, can improve the resistance reducing performance of jet flow, and wherein n must meet: n > 2 and for integer;
The 3rd step, determines the value of R and r;
By etc. polygonal nozzle hole area formulaKnown, after area of injection orifice S and angle are counted n and are determined, etc.The circumradius R of polygonal spray orifice scheme with etc. place, the polygonal spray orifice inside lock summit radius of a circle r relation that is inversely proportional to, RThe value farthest that polygonal can be touched such as determined, r such as has determined at the polygonal spray orifice inside lock summit patient minimum of a value,But R must be less than R0, and 0 < r < R; Known according to α=r/R relation, determine that α can determine R and r, the interval of α is[0.2,0.8]；
Wherein: R such as is at the circumradius of polygonal spray orifice scheme, r such as is at half of place, the polygonal spray orifice inside lock summit circleFootpath, θ is the angle at adjacent two spray angles, θ=2 π/n, wherein, the angle number that n is spray orifice, α=r/R;
The 4th step, after determining R and r value, generation waits the spray orifice shape of n dihedral;
Obtain after S, n and α, according to dependency relation formula be α=r/R and etc. polygonal nozzle hole area formulaTry to achieve R and r, in 3D sculpting software, determine the concrete shape of spout, then generate reverse jet flow scheme in blunt body leading edge,Polygonal reverse jet flow scheme profile such as finally obtain.
2. the reverse jet flow spray orifice of hypersonic aircraft drag reduction according to claim 1 solar heat protection method for designing, its feature existsIn, area of injection orifice S meets: 0.01 × π × R0 2<S<0.25×π×R0 2。
3. the reverse jet flow spray orifice of hypersonic aircraft drag reduction according to claim 2 solar heat protection method for designing, its feature existsIn, wait polygonal angle number n to be not more than 20.
4. according to the reverse jet flow spray orifice of the hypersonic aircraft drag reduction solar heat protection method for designing described in claim 2 or 3, its featureBe, 3D sculpting software has Solidworks, Catia or ProE.
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| CN104898286B (en) * | 2015-06-03 | 2020-03-06 | 中国人民解放军战略支援部队航天工程大学 | Method for reducing IV-type shock wave interference heat carrier and wave resistance by laser |
| US9725159B2 (en) * | 2015-11-10 | 2017-08-08 | The Boeing Company | Mitigating shock using plasma |
| CN109250073A (en) * | 2018-09-30 | 2019-01-22 | 中国人民解放军国防科技大学 | Hypersonic aircraft head drag reduction method based on three-electrode spark discharge thermal jet |
| CN109250074A (en) * | 2018-09-30 | 2019-01-22 | 中国人民解放军国防科技大学 | Hypersonic aircraft drag reduction method based on shock wave weakening of leading edge of synthetic jet wing |
| CN113588199B (en) * | 2021-09-30 | 2021-12-24 | 中国空气动力研究与发展中心超高速空气动力研究所 | Reverse jet flow blockage degree test device and test method for hypersonic wind tunnel |
| CN113955069B (en) * | 2021-10-26 | 2023-07-14 | 中国运载火箭技术研究院 | High-speed aircraft drag reduction closed-loop control method based on active flow control |
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