CN105667811A - Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft - Google Patents

Abstract

The invention discloses a design method for a multi-stage coupling integrated structure of a front body and an air inflow channel of a hypersonic aircraft. Two layout design techniques of the multi-stage compression wave-riding front body and the cut Busemann air inflow channel are coupled, and the front body and the air inflow channel integrated wave-riding structure at any flight height and with a given flow capture curve and a given air inflow channel capture curve under a Mach number can be generated. In order to solve the problem that the front body and the air inflow channel cannot be coupled with a multi-stage compression wave-riding body due to the singular point angles of Busemann standard flow fields, a transition compression section is additionally arranged between the standard flow fields of the front body and the air inflow channel, front edge curve discrete points conduct streamline tracking in a zero-incidence cone flow bypass standard flow field and a cone flow bypass standard flow field with an inclination angle in the transition compression section till the first Mach wave angle of an inner conic flow field is smaller than the singular point angles, and therefore the coupling purpose is achieved. The good non-design state starting performance of the multi-stage compression wave-riding front body and the beneficial effects of isentropic compression of the cut Busemann air inflow channel are combined, so that a new technical way is provided for integrated layout design of the front body and the air inflow channel of the hypersonic aircraft.

Description

The method for designing of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct

Technical field:

The present invention relates to the method for designing of a kind of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct, belong to air line design field.

Background technology:

For hypersonic aircraft, incoming flow is slowed down supercharging by precursor as compressing surface, and the performance of air intake duct is played conclusive effect. The Waverider performance due to its excellence and the compression to incoming flow, be the more satisfactory precursor scheme of Air-breathing hypersonic vehicle. Waverider is pushed to Practical, it is necessary to the integrated design technology of development rider body-air intake duct-jet pipe, hinder the technology barrier of the further Practical of Waverider to be in that the integrated technique bottleneck of Waverider and air intake duct.

Incoming flow can be carried out deceleration supercharging by multi-stage compression Waverider and Busemann air intake duct, but the principle of both compressions is different, therefore respectively has pluses and minuses. Multi-stage compression Waverider (Lv Zhenjun, Wang Xudong, Ji Weidong, Wang Jiangfeng. three stage compression cone leads Waverider designing technique and experimental analysis [J]. experimental fluid mechanics, 2015,05:38-44.) by multiple tracks shock wave, incoming flow being compressed, compression process is directly efficient, and still there is the performance of excellence in off-design state, the change of flying condition is less sensitive. But by then passing through shock wave compression, often all causing certain pitot loss through one shock wave, number of compression stages is more many, and pitot loss is more big. And Busemann air intake duct (RamasubramanianV, StarkeyR, LewisM.AnEulerNumericalStudyofBusemannandQuasi-BusemannH ypersonicInletsatOn-andOff-DesignSpeeds [J] .AIAA2008,2008,66.) it is by a series of compression mach waves and end shock wave, incoming flow is compressed, except the whole compression process of end shock wave is all constant entropy, in compression process, stagnation pressure remains unchanged. But isentropic Compression has one disadvantage in that and is exactly, compression process is slow, causes that the length of Busemann air intake duct is longer, is not suitable for engineer applied.It addition, the wave system textural anomaly of Busemann air intake duct is complicated, the change that flying condition is little all can make Busemann air intake duct off-design state, and when low mach, startability is poor.

It is proposed that a kind of new technique in conjunction with multi-stage compression Waverider and Busemann air intake duct advantage, it is thus achieved that it is suitable for the forebody and inlet integrated configuration of hypersonic aircraft propulsion system, there is very high academic significance and engineering practical value.

Summary of the invention:

It is an object of the invention in conjunction with the good off design point startability of existing multi-stage compression waverider forebody derived and the feature blocking Busemann air intake duct isentropic Compression, the method for designing of a kind of brand-new hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct is proposed, the forebody and inlet integration Waverider of given leading edge curve and shock wave curve under any flying height and Mach number can be generated, provide new technological approaches for the design of hypersonic aircraft forebody and inlet integrated configuration.

The present invention adopts the following technical scheme that the method for designing of a kind of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct, and it comprises the steps:

Step 1, given air intake duct catches curve and curve is caught in flowing, bores method according to osculating and is converted in second order accuracy by three-dimensional problem two-dimensional problems, namely in each osculating face, leading edge point is carried out streamlined impeller;

Step 2, multi-stage compression waverider forebody derived part being carried out streamlined impeller, gained streamline is multi-stage compression waverider forebody derived compressing surface;

Step 3, structure blocks Busemann inner conical benchmark flow field and carries out streamlined impeller, streamline is tracked until blocking Busemann air intake duct first Mach wave place in waverider forebody derived afterbody benchmark flow field, this Mach wave compression angle and iteration ends angle, Busemann inner conical benchmark flow field are supplementary angle relation, and iteration ends angle is necessarily less than Taylor-Maccoll equation singular point angle, flow field, otherwise revise integration configuration afterbody compression angle and repeat step 2-3 until meeting integration coupling condition, step 3 need iterate until meet iteration ends angle place, Busemann inner conical benchmark flow field flow field parameter with block Busemann air intake duct first Mach wave front flow field Mach number with the angle of attack identical, and flow field direction level after iteration initial angle place inlet induction road lip reflected shock wave, obtain block Busemann air intake duct compressing surface at the continuous streamlined impeller that carries out of this Busemann inner conical benchmark flow field relaying,

Step 4, carry out three-dimensional matching following the trail of the streamline obtained in each osculating face, the coupling arrangement integrated with blocking Busemann air intake duct that ultimately generate multi-stage compression waverider forebody derived.

Further, step 2 specifically includes:

Step 2-1, structure first order benchmark flow field also carry out streamlined impeller, one stage of compression benchmark flow field can be streamed benchmark flow field with zero-incidence circular cone and construct, Taylor-Maccoll equation solution is passed through in flow field, and incoming flow streams at zero-incidence circular cone after one stage of compression Mach wave compresses and is tracked until arriving two-stage compression Mach wave position in benchmark flow field;

Step 2-2, structure benchmark flow field, the second level also carry out streamlined impeller, streamline is when zero-incidence circular cone streams and tracks two-stage compression Mach wave position in benchmark flow field, two grades of shock wave front flow field parameter have certain angle of attack, now needing that around cone point, two grades of circular cone benchmark flow field with angle axis are rotated the respective angles flow path direction that makes to come with two-stage compression Mach wave parallel, air-flow continues to stream at two grades of circular cones with angle to carry out streamlined impeller in benchmark flow field after two-stage compression Mach wave compresses;

Step 2-3, benchmark flow field building method more than more than two grades are identical with two stage approach, and the afterbody compressing surface of precursor is and blocks the changeover portion that is of coupled connections that Busemann air intake duct is combined, air-flow continues to carry out streamlined impeller in its benchmark flow field after shock wave compression, until blocking position, Busemann air intake duct first Mach wave compression angle place, if multi-stage compression waverider forebody derived only has two-stage, then this step is identical with step 2-2.

Further, forebody and inlet integration configuration geometry design parameter includes: air intake duct catches curve and curve is caught in flowing, catching curve at plane of symmetry intersection point for zero with flowing, wherein flowing is caught curve and is included straightway and curved section, and straightway equation form is: 0≤x≤L_u, y=0, curved section equation form is: x >=L_u, y=B (x-L_u)^m; Air intake duct is caught curve and is included straightway and curved section, and straightway equation form is: 0≤x≤L_s, y=-H, curved section equation form is: x >=L_s, y=-H+A (x-L_s)ⁿ, curve and air intake duct are caught in flowing, and to catch intersections of complex curve coordinate be (X_coj,Y_coj), flowing catch curve and air intake duct to catch intersections of complex curve at y direction relative position ratio be s, whole air intake duct height is H, meets | Y_coj|=sH.

Further, in each osculating face, multi-stage compression waverider forebody derived benchmark flow field design parameter is as follows: before every grade of benchmark flow field cone shock, incoming flow is parallel relative to benchmark flow field axis of symmetry, therefore rotates every grade of benchmark flow field and makes axis drift angle α_axisWith incoming flow drift angle α_strEqual, i.e. α_axis=α_str, after trying to achieve every grade of compression shock by oblique shock wave relational expression, parameter is as every grade of benchmark flow field initial condition, and every grade of benchmark flow field solving equation is dimensionless Taylor-Maccoll equation, and equation form is

$\left\{\begin{array}{c}\frac{{\mathrm{dV}}_{\mathrm{\θ}}^{*}}{d\mathrm{\θ}}=-V_r^{*}+{(a/a_{\mathrm{\∞}})}^2\frac{V_r^{*}+V_{\mathrm{\θ}}^{*}\cot \mathrm{\θ}}{V_{\mathrm{\θ}}^{*2}-{(a/a_{\mathrm{\∞}})}^2}\\ \frac{{\mathrm{dV}}_r^{*}}{d\mathrm{\θ}}=V_{\mathrm{\θ}}^{*}\end{array}\right.$

Wherein $V_{\mathrm{\θ}}^{*}=\frac{V_{\mathrm{\θ}}}{a_{\mathrm{\∞}}},V_r^{*}=\frac{V_r}{a_{\mathrm{\∞}}},{\left(\frac{a}{a_{\mathrm{\∞}}}\right)}^2=1+\frac{\mathrm{\γ}-1}{2}(M_{\mathrm{\∞}}^2-V_r^{*2}-V_{\mathrm{\θ}}^{*2}),$ θ is iteration angle, benchmark flow field (being sized to and the angle of flow field axis), V_θFor circumferential speed component, V_rFor radial velocity component, asterisk is characteristic, and a is the velocity of sound, M is Mach number, and footmark ∞ is expressed as incoming flow parameter, according to stream function formula, flowing is caught curve discrete point and is carried out streamlined impeller in every grade of benchmark flow field, and gained streamline is multi-stage compression waverider forebody derived Partial shrinkage face.

Further, in each osculating face, Busemann inner conical benchmark flow field design parameter is as follows: block Busemann air intake duct integrated configuration afterbody compression section, therefore its iteration ends angle, benchmark flow field θ_endMust with integrated configuration afterbody compression angle β_bMeet supplementary angle relation, i.e. θ_end=180 ° of-β_b, benchmark flow field free stream Mach number is M_b1Time, Taylor-Maccoll equation is at singular point angle θ_sp=180 ° of-arcsin (1/M_b1) place's flow field parameter has flex point, in order to solve to block, Busemann air intake duct is integrated with multi-stage compression waverider forebody derived couples singular point problem, Busemann inner conical benchmark flow field iteration ends angle θ_endIt is necessarily less than singular point angle θ_sp, incoming flow drift angle, Busemann inner conical benchmark flow field is α_strTime, it is necessary to make θ_end180 ° of-arcsin (1/M of <_b1)-α_str, Busemann inner conical benchmark flow field solving equation is dimension Taylor-Maccoll equation, and equation form is

$\left\{\begin{array}{c}\frac{{\mathrm{dv}}_{\mathrm{\&theta;}}^{**}}{d\mathrm{\&theta;}}=-v_r^{**}+a^{**2}\frac{v_r^{**}+v_{\mathrm{\&theta;}}^{**}\cot \mathrm{\&theta;}}{v_{\mathrm{\&theta;}}^{**2}-a^{**2}}\\ \frac{{\mathrm{dv}}_r^{**}}{d\mathrm{\&theta;}}=v_{\mathrm{\&theta;}}^{**}\end{array}\right.$

Wherein $v_{\mathrm{\&theta;}}^{**}=v_{\mathrm{\&theta;}}/V_{max},v_r^{**}=v_r/V_{max},a^{**2}={(a/V_{max})}^2,{\left(\frac{a}{V_{max}}\right)}^2=\frac{\mathrm{\&gamma;}-1}{2}(1-v_r^{**2}-v_{\mathrm{\&theta;}}^{**2}),$ θ is iteration angle, benchmark flow field, v_θFor circumferential speed component, v_rFor radial velocity component, double asterisk is characteristic, and a is the velocity of sound, T₀For incoming flow stagnation temperature, γ is specific heats of gases ratios, and R is gas constant.

There is advantages that and technological layer solves Busemann air intake duct and the interference of Taylor-Maccoll parametric singular point problem in multi-stage compression waverider forebody derived coupling process;Compared with existing multi-stage compression waverider forebody derived designing technique, the multistage coupling technique method of the present invention has been obviously improved the lift-drag ratio of conventional multi-level compression waverider forebody derived and the total pressure recovery coefficient of inlet mouth; Improve air intake duct low rate start performance; Improve the superb blockage resisting performance of air intake duct.

Accompanying drawing illustrates:

Fig. 1 be in single osculating face multi-stage compression waverider forebody derived with block Busemann air intake duct coupling arrangement schematic diagram.

Fig. 2 is that curve is caught in flowing and air intake duct catches curve synoptic diagram.

Fig. 3 is multi-stage compression waverider forebody derived benchmark flow field at different levels schematic diagram.

Fig. 4 is for blocking Busemann air intake duct benchmark flow field schematic diagram.

Fig. 5 is multi-stage compression waverider forebody derived and block Busemann air intake duct coupling arrangement graphics.

Fig. 6 is that the method for the invention generates integration configuration and conventional multi-level compression waverider forebody derived contrast side view.

Fig. 7 is that the method for the invention generates integration configuration and conventional multi-level compression waverider forebody derived contrast front view.

Fig. 8 is that the method for the invention generates integration configuration and conventional multi-level compression waverider forebody derived contrast upward view.

Fig. 9 is that the method for the invention generates integration configuration and conventional multi-level compression waverider forebody derived contrast perspective view.

Figure 10 is that the method for the invention generates integration configuration flow field non-dimensional density cloud atlas.

Figure 11 is conventional multi-level compression waverider forebody derived flow field non-dimensional density cloud atlas.

Number in the figure title: 1-multi-stage compression waverider forebody derived, 2-blocks Busemann air intake duct, 3-is of coupled connections changeover portion, curve (FCC) is caught in 4-flowing, 5-air intake duct catches curve (ICC), 6-zero-incidence circular cone streams benchmark flow field, 7-Busemann inner conical benchmark flow field, 8-circular cone with angle streams benchmark flow field, 9-inlet lip reflected shock wave, 10-blocks Busemann air intake duct first Mach wave, 11-two-stage compression Mach wave, 12-one stage of compression Mach wave, 13-osculating face, 14-tradition three stage compression waverider forebody derived, 15-two-stage compression waverider forebody derived coupling arrangement integrated with blocking Busemann, 16-air intake duct distance piece, 17-incoming flow capture cross section, 18-inlet mouth capture cross section, 19-distance piece capture cross section.

Detailed description of the invention:

Below in conjunction with drawings and Examples, the present invention is further described.

A kind of hypersonic aircraft precursor and the multistage coupling integrated design method of air intake duct, in conjunction with multi-stage compression waverider forebody derived and the integrated three-dimensional layout blocking Busemann air intake duct, emphatically multi-stage compression waverider forebody derived coupling technique integrated with blocking Busemann air intake duct is illustrated.

Hypersonic aircraft precursor of the present invention and the multistage coupling integrated configuration of air intake duct are made up of with blocking Busemann air intake duct 2 multi-stage compression waverider forebody derived 1, and wherein multi-stage compression waverider forebody derived 1 afterbody compression section is the changeover portion 3 that is of coupled connections. Under any flying height and Mach number, curve (FCC, leading edge curve) 4 is caught in the variable flowing of given parameters and air intake duct catches curve (ICC) 5, adopt osculating cone theazy that three-dimensional multistage coupling integrated configuration is generated the two-dimentional streamline in each osculating face 13 being converted in second order accuracy and generate problem, given flowing is caught curve 4 in benchmark flow fields at different levels, carries out the streamlined impeller configuration integrated with blocking Busemann compressing surface that obtain multi-stage compression curved surface; Stream benchmark flow field 6 for the zero-incidence circular cone of multi-stage compression Waverider design and broadly fall into axial symmetry taper flow field for Busemann inner conical benchmark flow field 7 in each osculating face 13, adopting no quantization Taylor-Maccoll flow equation to describe;Singular point angle for existing Busemann benchmark flow field 7 causes its problem that cannot couple with existing multi-stage compression waverider forebody derived 1, improve existing method for designing, one section of changeover portion 3 that is of coupled connections is added between both benchmark flow fields, flowing is caught curve (leading edge curve) 4 discrete points and is streamed benchmark flow field 6 and supercompression section circular cone with angle streams and carries out streamlined impeller in benchmark flow field 8 at zero-incidence circular cone respectively, until Busemann inner conical benchmark flow field 7 iteration ends angle θ_endLess than singular point angle θ_sp, conversion benchmark flow field is for blocking Busemann inner conical benchmark flow field 7 and proceeding streamlined impeller to inlet lip reflected shock wave 9; In matching all osculatings face, streamline becomes how grade coupled compression curved surface to obtain integration configuration.

The concrete characterising parameter of above-mentioned hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct and benchmark flow field thereof is as follows, due to symmetry, takes half module configuration be below described for convenience of describing:

2-1, forebody and inlet integration configuration geometry design parameter include: air intake duct catches curve (ICC) 5 and curve (FCC) 4 is caught in flowing. Catching curve (FCC) 4 at plane of symmetry intersection point for zero with flowing, wherein flowing is caught curve (FCC) 4 and is included straightway and curved section, and straightway equation form is: 0≤x≤L_u, y=0, curved section equation form is: x >=L_u, y=B (x-L_u)^m; Air intake duct is caught curve (ICC) 5 and is included straightway and curved section, and straightway equation form is: 0≤x≤L_s, y=-H, curved section equation form is: x >=L_s, y=-H+A (x-L_s)ⁿ. Curve (FCC) 4 is caught in flowing, and to catch curve (ICC) 5 intersecting point coordinate with air intake duct be (X_coj,Y_coj), flowing catch curve (FCC) 4 and air intake duct to catch curve (ICC) 5 intersection point at y direction relative position ratio be s, whole air intake duct height is H, meets | Y_coj|=sH.

In 2-2, each osculating face 13, multi-stage compression waverider forebody derived benchmark flow field design parameter is as follows. Before every grade of benchmark flow field cone shock, incoming flow is parallel relative to benchmark flow field axis of symmetry, therefore rotates every grade of benchmark flow field and makes axis drift angle α_axisWith incoming flow drift angle α_strEqual, i.e. α_axis=α_str. After trying to achieve every grade of compression shock by oblique shock wave relational expression, parameter is as every grade of benchmark flow field initial condition. Every grade of benchmark flow field solving equation is dimensionless Taylor-Maccoll equation, and equation form is

$\left\{\begin{array}{c}\frac{{\mathrm{dV}}_{\mathrm{\&theta;}}^{*}}{d\mathrm{\&theta;}}=-V_r^{*}+{(a/a_{\mathrm{\&infin;}})}^2\frac{V_r^{*}+V_{\mathrm{\&theta;}}^{*}\cot \mathrm{\&theta;}}{V_{\mathrm{\&theta;}}^{*2}-{(a/a_{\mathrm{\&infin;}})}^2}\\ \frac{{\mathrm{dV}}_r^{*}}{d\mathrm{\&theta;}}=V_{\mathrm{\&theta;}}^{*}\end{array}\right.$

Wherein $V_{\mathrm{\&theta;}}^{*}=\frac{V_{\mathrm{\&theta;}}}{a_{\mathrm{\&infin;}}},V_r^{*}=\frac{V_r}{a_{\mathrm{\&infin;}}},{\left(\frac{a}{a_{\mathrm{\&infin;}}}\right)}^2=1+\frac{\mathrm{\&gamma;}-1}{2}(M_{\mathrm{\&infin;}}^2-V_r^{*2}-V_{\mathrm{\&theta;}}^{*2}),$ θ is iteration angle, benchmark flow field (being sized to and the angle of flow field axis), V_θFor circumferential speed component, V_rFor radial velocity component, asterisk is characteristic, and a is the velocity of sound, and M is Mach number, and footmark ∞ is expressed as incoming flow parameter. According to stream function formula, flowing is caught curve (FCC) 4 discrete point and is carried out streamlined impeller in every grade of benchmark flow field, and gained streamline is multi-stage compression waverider forebody derived Partial shrinkage face.

In 2-3, each osculating face, Busemann inner conical benchmark flow field 7 design parameter is as follows. Block Busemann air intake duct 2 integrated configuration afterbody compression section, therefore its iteration ends angle, benchmark flow field θ_endMust with integrated configuration afterbody compression angle β_bMeet supplementary angle relation, i.e. θ_end=180 ° of-β_b. Benchmark flow field free stream Mach number is M_b1Time, Taylor-Maccoll equation is at singular point angle θ_sp=180 ° of-arcsin (1/M_b1) place's flow field parameter has flex point. Therefore Busemann air intake duct 2 coupling integrated with multi-stage compression waverider forebody derived 1 singular point problem, Busemann inner conical benchmark flow field 7 iteration ends angle θ are blocked for solution_endIt is necessarily less than singular point angle θ_sp, incoming flow drift angle, Busemann inner conical benchmark flow field 7 is α_strTime, it is necessary to make θ_end180 ° of-arcsin (1/M of <_b1)-α_str.Busemann inner conical benchmark flow field 7 solving equation is dimension Taylor-Maccoll equation, and equation form is

$\left\{\begin{array}{c}\frac{{\mathrm{dv}}_{\mathrm{\&theta;}}^{**}}{d\mathrm{\&theta;}}=-v_r^{**}+a^{**2}\frac{v_r^{**}+v_{\mathrm{\&theta;}}^{**}\cot \mathrm{\&theta;}}{v_{\mathrm{\&theta;}}^{**2}-a^{**2}}\\ \frac{{\mathrm{dv}}_r^{**}}{d\mathrm{\&theta;}}=v_{\mathrm{\&theta;}}^{**}\end{array}\right.$

Wherein $v_{\mathrm{\&theta;}}^{**}=v_{\mathrm{\&theta;}}/V_{max},v_r^{**}=v_r/V_{max},a^{**2}={(a/V_{max})}^2,{\left(\frac{a}{V_{max}}\right)}^2=\frac{\mathrm{\&gamma;}-1}{2}(1-v_r^{**2}-v_{\mathrm{\&theta;}}^{**2}),$ θ is iteration angle, benchmark flow field (being sized to and the angle of flow field axis), v_θFor circumferential speed component, v_rFor radial velocity component, double asterisk is characteristic, and a is the velocity of sound, T₀For incoming flow stagnation temperature, γ is specific heats of gases ratios, and R is gas constant. According to stream function formula, continuing to carry out streamlined impeller in Busemann benchmark flow field 7, gained streamline is Busemann air intake duct Partial shrinkage face.

Hypersonic aircraft precursor of the present invention and the multistage coupling integrated configuration of air intake duct and method for designing thereof, comprise the steps:

Step 1, given air intake duct catches curve (ICC) 5 and curve (FCC) 4 is caught in flowing, bores method according to osculating and is converted in second order accuracy by three-dimensional problem two-dimensional problems, namely in each osculating face 13, leading edge point is carried out streamlined impeller;

Step 2, multi-stage compression waverider forebody derived part being carried out streamlined impeller, gained streamline is multi-stage compression waverider forebody derived 1 compressing surface.

Step 2-1, structure first order benchmark flow field also carry out streamlined impeller. One stage of compression benchmark flow field can be streamed benchmark flow field 6 with zero-incidence circular cone and construct, Taylor-Maccoll equation solution is passed through in flow field, and incoming flow streams at zero-incidence circular cone after one stage of compression Mach wave 12 compresses and is tracked in benchmark flow field 6 until arriving two-stage compression Mach wave 11 position.

Step 2-2, structure benchmark flow field, the second level also carry out streamlined impeller. Streamline is when zero-incidence circular cone streams and tracks two-stage compression Mach wave 11 position in benchmark flow field 6, two grades of shock wave front flow field parameter have certain angle of attack, now need that around cone point, two grades of circular cone benchmark flow field 8 with angle axis are rotated the respective angles flow path direction that makes to come with two-stage compression Mach wave 11 parallel. Air-flow continues to stream at two grades of circular cones with angle to carry out streamlined impeller in benchmark flow field 8 after two-stage compression Mach wave 11 compresses.

Step 2-3, benchmark flow field building method more than more than two grades are identical with two stage approach, and the afterbody compressing surface of precursor is and blocks the changeover portion 3 that is of coupled connections that Busemann air intake duct 2 is combined, air-flow continues to carry out streamlined impeller in its benchmark flow field after shock wave compression, until blocking position, Busemann air intake duct first Mach wave 10 compression angle place, if multi-stage compression waverider forebody derived 1 only two-stage, then this step is identical with step 2-2.

Step 3, structure block Busemann inner conical benchmark flow field 7 and carry out streamlined impeller. Streamline is tracked until blocking Busemann air intake duct first Mach wave 10 place in waverider forebody derived afterbody benchmark flow field, this Mach wave compression angle and iteration ends angle, Busemann inner conical benchmark flow field 7 are supplementary angle relation, and iteration ends angle is necessarily less than Taylor-Maccoll equation singular point angle, flow field, otherwise revises integration configuration afterbody compression angle and repeat step 2-3 until meeting integration coupling condition. Step 3 needs to iterate until meeting iteration ends angle place, Busemann inner conical benchmark flow field 7 flow field parameter with to block Busemann air intake duct first Mach wave 10 front flow field Mach number identical with the angle of attack, and flow field direction level after iteration initial angle place inlet induction road lip reflected shock wave 9. This Busemann inner conical benchmark flow field 7 proceeds streamlined impeller acquisition and blocks Busemann air intake duct 2 compressing surface.

Step 4, carry out three-dimensional matching following the trail of the streamline obtained in each osculating face 13, the coupling arrangement integrated with blocking Busemann air intake duct 2 that ultimately generate multi-stage compression waverider forebody derived 1.

Application example

For verifying method for designing effectiveness, illustrate for two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann.

1. technical parameter

Selecting technology parameter is as shown in the table

Table 1. two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann design parameter

Utilize the method for designing of the present invention configuration 15 integrated with blocking Busemann air intake duct that ultimately generated two-stage compression waverider forebody derived, under same design parameter, generate tradition three stage compression waverider forebody derived 14.

3. numerical simulation result

Two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann has greatly improved compared to tradition three stage compression waverider forebody derived 14 lift-drag ratio. During without viscous state, lift-drag ratio is maximal increment respectively 74.29%, 75.96%, 77.47% and be both present in the 0 design angle of attack when Mach number 5,6,7. When having viscous state, lift-drag ratio is maximal increment respectively 48.79%, 52.71%, 55.34% and be both present in the 0 design angle of attack when Mach number 5,6,7. Superb waverider forebody derived lifting resistance characteristic is had greatly improved by the hypersonic aircraft precursor that the present invention proposes and the multistage coupling integrated design method of air intake duct.

Of substantially equal with tradition three stage compression waverider forebody derived 14 discharge coefficient without two-stage compression waverider forebody derived coupling arrangement integrated with blocking Busemann 15 under viscous design point, and both are close to 100%; When having a viscous state, two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann discharge coefficient is bigger, illustrates there is less overflow compared to tradition three stage compression waverider forebody derived 14. No matter having viscous without viscous, two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann inlet mouth capture cross section 18 total pressure recovery coefficient under design condition has more than 11% to promote simultaneously. Although two kinds of configurations have approximately equalised air intake duct distance piece 16 sectional area, but two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann has comparatively uniform flow field and less low-pressure area at inlet mouth, therefore has less stagnation pressure loss at air intake duct distance piece 16. Two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann total pressure recovery coefficient under distance piece capture cross section 19 place from inlet mouth 3m is without viscous state has the lifting of nearly 34.7%, has under viscous state to have the lifting of nearly 20.2%. Illustrate that the compression performance of superb waverider forebody derived is had more significant lifting with the multistage coupling integrated design method of air intake duct by the hypersonic aircraft precursor that the present invention proposes.

The above is only the preferred embodiment of the present invention, it is noted that for those skilled in the art, can also make some improvement under the premise without departing from the principles of the invention, and these improvement also should be regarded as protection scope of the present invention.

Claims (5)

1. the method for designing of a hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct, it is characterised in that: comprise the steps

Step 1, given air intake duct catches curve (5) and curve (4) is caught in flowing, bore method according to osculating and be converted in second order accuracy by three-dimensional problem two-dimensional problems, namely in each osculating face (13), leading edge point is carried out streamlined impeller;

Step 2, multi-stage compression waverider forebody derived part being carried out streamlined impeller, gained streamline is multi-stage compression waverider forebody derived (1) compressing surface;

Step 3, structure blocks Busemann inner conical benchmark flow field (7) and carries out streamlined impeller, streamline is tracked until blocking Busemann air intake duct first Mach wave (10) place in waverider forebody derived afterbody benchmark flow field, this Mach wave compression angle and Busemann inner conical benchmark flow field (7) iteration ends angle are supplementary angle relation, and iteration ends angle is necessarily less than Taylor-Maccoll equation singular point angle, flow field, otherwise revise integration configuration afterbody compression angle and repeat step 2-3 until meeting integration coupling condition, step 3 need iterate until meet Busemann inner conical benchmark flow field (7) iteration ends angle place flow field parameter with block Busemann air intake duct first Mach wave (10) front flow field Mach number with the angle of attack identical, and inlet induction road, iteration initial angle place lip reflected shock wave (9) flow field direction level afterwards, this Busemann inner conical benchmark flow field (7) proceeds streamlined impeller acquisition and blocks Busemann air intake duct (2) compressing surface,

Step 4, carry out three-dimensional matching following the trail of the streamline obtained in each osculating face (13), the coupling arrangement integrated with blocking Busemann air intake duct that ultimately generate multi-stage compression waverider forebody derived.

2. the method for designing of hypersonic aircraft precursor as claimed in claim 1 and the multistage coupling integrated configuration of air intake duct, it is characterised in that: step 2 specifically includes

Step 2-1, structure first order benchmark flow field also carry out streamlined impeller, one stage of compression benchmark flow field can be streamed benchmark flow field (6) with zero-incidence circular cone and construct, Taylor-Maccoll equation solution is passed through in flow field, and incoming flow streams at zero-incidence circular cone after one stage of compression Mach wave (12) compresses and is tracked until arriving two-stage compression Mach wave (11) position in benchmark flow field (6);

Step 2-2, structure benchmark flow field, the second level also carry out streamlined impeller, streamline is when zero-incidence circular cone streams and tracks two-stage compression Mach wave (11) position in benchmark flow field (6), two grades of shock wave front flow field parameter have certain angle of attack, now needing that around cone point, two grades of circular cone benchmark flow field (8) axis with angle are rotated the respective angles flow path direction that makes to come with two-stage compression Mach wave (11) parallel, air-flow continues to stream at two grades of circular cones with angle to carry out streamlined impeller in benchmark flow field (8) after two-stage compression Mach wave (11) compresses;

Step 2-3, benchmark flow field building method more than more than two grades are identical with two stage approach, and the afterbody compressing surface of precursor is and blocks the changeover portion that is of coupled connections (3) that Busemann air intake duct (2) combines, air-flow continues to carry out streamlined impeller in its benchmark flow field after shock wave compression, until blocking position, Busemann air intake duct first Mach wave (10) compression angle place, if multi-stage compression waverider forebody derived (1) only has two-stage, then this step is identical with step 2-2.

3. the method for designing of hypersonic aircraft precursor as claimed in claim 2 and the multistage coupling integrated configuration of air intake duct, it is characterised in that:

Forebody and inlet integration configuration geometry design parameter includes: air intake duct catches curve (5) and curve (4) is caught in flowing, curve (4) is caught at plane of symmetry intersection point for zero with flowing, wherein flowing is caught curve (4) and is included straightway and curved section, and straightway equation form is: 0≤x≤L_u, y=0, curved section equation form is: x >=L_u, y=B (x-L_u)^m; Air intake duct is caught curve (5) and is included straightway and curved section, and straightway equation form is: 0≤x≤L_s, y=-H, curved section equation form is: x >=L_s, y=-H+A (x-L_s)ⁿ, curve (4) and air intake duct are caught in flowing, and to catch curve (5) intersecting point coordinate be (X_coj,Y_coj), flowing catch curve (4) and air intake duct to catch curve (5) intersection point at y direction relative position ratio be s, whole air intake duct height is H, satisfied | Y_coj|=sH.

4. the method for designing of hypersonic aircraft precursor as claimed in claim 3 and the multistage coupling integrated configuration of air intake duct, it is characterised in that:

Each osculating face (13) interior multi-stage compression waverider forebody derived benchmark flow field design parameter is as follows: before every grade of benchmark flow field cone shock, incoming flow is parallel relative to benchmark flow field axis of symmetry, therefore rotates every grade of benchmark flow field and makes axis drift angle α_axisWith incoming flow drift angle α_strEqual, i.e. α_axis=α_str, after trying to achieve every grade of compression shock by oblique shock wave relational expression, parameter is as every grade of benchmark flow field initial condition, and every grade of benchmark flow field solving equation is dimensionless Taylor-Maccoll equation, and equation form is

$\left\{\begin{array}{c}\frac{{\mathrm{dV}}_{\mathrm{\&theta;}}^{*}}{d\mathrm{\&theta;}}=-V_r^{*}+{(a/a_{\mathrm{\&infin;}})}^2\frac{V_r^{*}+V_{\mathrm{\&theta;}}^{*}\cot \mathrm{\&theta;}}{V_{\mathrm{\&theta;}}^{*2}-{(a/a_{\mathrm{\&infin;}})}^2}\\ \frac{{\mathrm{dV}}_r^{*}}{d\mathrm{\&theta;}}=V_{\mathrm{\&theta;}}^{*}\end{array}\right.$

Wherein $V_{\mathrm{\&theta;}}^{*}=\frac{V_{\mathrm{\&theta;}}}{a_{\mathrm{\&infin;}}},V_r^{*}=\frac{V_r}{a_{\mathrm{\&infin;}}},{\left(\frac{a}{a_{\mathrm{\&infin;}}}\right)}^2=1+\frac{\mathrm{\&gamma;}-1}{2}(M_{\mathrm{\&infin;}}^2-V_r^{*2}-V_{\mathrm{\&theta;}}^{*2}),$ θ is iteration angle, benchmark flow field (being sized to and the angle of flow field axis), V_θFor circumferential speed component, V_rFor radial velocity component, asterisk is characteristic, a is the velocity of sound, M is Mach number, footmark ∞ is expressed as incoming flow parameter, according to stream function formula, flowing is caught curve (4) discrete point and is carried out streamlined impeller in every grade of benchmark flow field, and gained streamline is multi-stage compression waverider forebody derived Partial shrinkage face.

5. the method for designing of hypersonic aircraft precursor as claimed in claim 4 and the multistage coupling integrated configuration of air intake duct, it is characterised in that:

In each osculating face, Busemann inner conical benchmark flow field (7) design parameter is as follows: block Busemann air intake duct (2) integrated configuration afterbody compression section, therefore its iteration ends angle, benchmark flow field θ_endMust with integrated configuration afterbody compression angle β_bMeet supplementary angle relation, i.e. θ_end=180 ° of-β_b, benchmark flow field free stream Mach number is M_b1Time, Taylor-Maccoll equation is at singular point angle θ_sp=180 ° of-arcsin (1/M_b1) place's flow field parameter has flex point, in order to solve to block, Busemann air intake duct (2) is integrated with multi-stage compression waverider forebody derived (1) couples singular point problem, Busemann inner conical benchmark flow field (7) iteration ends angle θ_endIt is necessarily less than singular point angle θ_sp, Busemann inner conical benchmark flow field (7) incoming flow drift angle is α_strTime, it is necessary to make θ_end180 ° of-arcsin (1/M of <_b1)-α_str, Busemann inner conical benchmark flow field (7) solving equation is dimension Taylor-Maccoll equation, and equation form is

$\left\{\begin{array}{c}\frac{{\mathrm{dv}}_{\mathrm{\&theta;}}^{**}}{d\mathrm{\&theta;}}=-v_r^{**}+a^{**2}\frac{v_r^{**}+v_{\mathrm{\&theta;}}^{**}\cot \mathrm{\&theta;}}{v_{\mathrm{\&theta;}}^{**2}-a^{**2}}\\ \frac{{\mathrm{dv}}_r^{**}}{d\mathrm{\&theta;}}=v_{\mathrm{\&theta;}}^{**}\end{array}\right.$

Wherein $v_{\mathrm{\&theta;}}^{**}=v_{\mathrm{\&theta;}}/V_{max},v_r^{**}=v_r/V_{max},a^{**2}={(a/V_{max})}^2,{\left(\frac{a}{V_{max}}\right)}^2=\frac{\mathrm{\&gamma;}-1}{2}(1-v_r^{**2}-v_{\mathrm{\&theta;}}^{**2}),$ θ is iteration angle, benchmark flow field, v_θFor circumferential speed component, v_rFor radial velocity component, double asterisk is characteristic, and a is the velocity of sound, T₀For incoming flow stagnation temperature, γ is specific heats of gases ratios, and R is gas constant.