CN105667811B - The design method of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct - Google Patents
The design method of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
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Abstract
The invention discloses the design method of a kind of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct, multi-stage compression waverider forebody derived is coupled and has blocked two kinds of layout designs technologies of Busemann air intake ducts, the integrated Waverider of forebody and inlet that flowing capture curve and air intake duct capture curve are given under any flying height and Mach number can be generated.The problem of leading to not couple with multi-stage compression Waverider for the singular point angle in Busemann benchmark flow field, transition compression section is added between both benchmark flow fields, leading edge curve discrete point streams benchmark flow field and transition compression section circular cone with angle and streamed in zero-incidence circular cone respectively carries out streamlined impeller in benchmark flow field, until first of inner conical flow field Mach wave angle is less than singular point angle, so as to solve coupled problem.Combine the good off design point startability of multi-stage compression waverider forebody derived and block the advantage of Busemann air intake duct isentropic Compressions, new technological approaches is provided for the design of hypersonic aircraft forebody and inlet integrated configuration.
Description
Technical field：
The present invention relates to the design method 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, precursor to flow to slow down as compressing surface to being pressurized, and the performance to air intake duct is played certainly
Qualitatively act on.Waverider is due to its excellent performance and to being Air-breathing hypersonic vehicle ratio the compression that flows
Comparatively ideal precursor scheme.Waverider is pushed to Practical, it is necessary to develop the one of rider body-air intake duct-jet pipe
Change designing technique, hinder the technology barrier of the further Practical of Waverider to be the integrated technique bottle of Waverider and air intake duct
Neck.
Multi-stage compression Waverider and Busemann air intake ducts can be to carrying out deceleration supercharging to flow, but the principle of both compressions
Difference, therefore respectively there are advantage and disadvantage.Multi-stage compression Waverider (lead by Lv Zhenjun, Wang Xudong, Ji Weidong, Wang Jiang peaks three stage compressions cone
Waverider designing technique and experimental analysis [J] experimental fluid mechanics, 2015,05:It is 38-44.) to flowing by multiple tracks shock wave
It is compressed, compression process is directly efficient, and still there is excellent performance in off-design state, to flying condition
Change less sensitive.But by then passing through shock wave compression, certain pitot loss can be all often caused by one of shock wave, is compressed
Series is more, and pitot loss is bigger.And Busemann air intake ducts (Ramasubramanian V, Starkey R, Lewis M.An
Euler Numerical Study of Busemann and Quasi-Busemann Hypersonic Inlets at On-
And Off-Design Speeds [J] .AIAA 2008,2008,66.) it is by a series of compression mach waves and end shock wave pair
Carry out stream to be compressed, except shock wave whole compression process in end is all constant entropy, stagnation pressure keeps constant in compression process.But wait
Entropic spueezing, which has one disadvantage in that, is exactly, and compression process is slow, causes the length of Busemann air intake ducts longer, and being not suitable for engineering should
With.In addition, the wave system textural anomaly of Busemann air intake ducts is complicated, the small change of flying condition can all make Busemann air intake ducts
Off-design state, startability is poor under the conditions of low mach.
Therefore a kind of new technology of both combination multi-stage compression Waverider and Busemann air intake ducts advantages is proposed, is fitted
The forebody and inlet integrated configuration of hypersonic aircraft propulsion system is closed, with very high academic significance and Practical
Value.
The content of the invention：
The purpose of the present invention is to combine the good off design point startability of existing multi-stage compression waverider forebody derived with blocking
The characteristics of Busemann air intake duct isentropic Compressions, propose that a kind of brand-new hypersonic aircraft precursor is coupled with air intake duct multistage
The design method of integrated configuration, can generate and be given under any flying height and Mach number before leading edge curve and shock wave curve
Body inlet integration Waverider, designs for hypersonic aircraft forebody and inlet integrated configuration and provides new technology way
Footpath.
The present invention is adopted the following technical scheme that：A kind of hypersonic aircraft precursor and the multistage coupling integrated structure of air intake duct
The design method of type, it comprises the following steps：
Three-dimensional problem, is converted into by step 1, given air intake duct capture curve and flowing capture curve according to osculating cone method
Two-dimensional problems in second order accuracy, i.e., carry out streamlined impeller in each osculating face to leading edge point；
Step 2, to multi-stage compression waverider forebody derived part carry out streamlined impeller, gained streamline is multi-stage compression waverider forebody derived
Compressing surface；
Step 3, construction block Busemann inner conical benchmark flow fields and carry out streamlined impeller, and streamline is last in waverider forebody derived
Be tracked in one-level benchmark flow field until block at first of Mach wave of Busemann air intake ducts, the Mach wave compression angle with
Busemann inner conical benchmark flow field iteration ends angle is supplementary angle relation, and iteration ends angle is necessarily less than flow field Taylor-
Maccoll equation singular points angle, otherwise changes integrated configuration afterbody compression angle and repeat step 2-3 is until meet integration
Coupling condition, step 3 needs to iterate until meeting flow field parameter at the iteration ends angle of Busemann inner conical benchmark flow field
It is identical with the angle of attack with blocking the preceding flow field Mach number of first of Mach wave of Busemann air intake ducts, and entrance enters at iteration initial angle
Flow field direction level after air flue lip reflected shock wave, in the Busemann inner conical benchmark flow field, the continuous streamlined impeller that carries out of relaying is obtained
Busemann air intake duct compressing surfaces must be blocked；
Step 4, obtained streamline is followed the trail of in each osculating face three-dimensional fitting is carried out, ultimately generated before multi-stage compression rider
Body coupling arrangement integrated with blocking Busemann air intake ducts.
Further, step 2 is specifically included：
Step 2-1, construction first order benchmark flow field simultaneously carry out streamlined impeller, and one stage of compression benchmark flow field can use zero-incidence
Circular cone streams benchmark flow field to construct, and flow field is by Taylor-Maccoll equation solutions, to flow by one stage of compression Mach wave
Stream and be tracked in benchmark flow field until reaching two-stage compression Mach wave position in zero-incidence circular cone after compression；
Step 2-2, construction second level benchmark flow field simultaneously carry out streamlined impeller, and streamline streams benchmark flow field in zero-incidence circular cone
In when tracking two-stage compression Mach wave position, two grades of shock wave front flow field parameters have certain angle of attack, now need with angle by two grades
Circular cone benchmark flow field axis rotates respective angles around cone point to be made parallel with direction of flow before two-stage compression Mach wave, and air-flow passes through two
Continue to stream in two grades of circular cones with angle after level compression mach wave compression and streamlined impeller is carried out in benchmark flow field；
Step 2-3, the benchmark flow field building method more than more than two grades are identical with two stage approach, and the afterbody of precursor
Compressing surface is that air-flow continues after shock wave compression in its base with blocking the changeover portion that is of coupled connections that Busemann air intake ducts are combined
Streamlined impeller is carried out in quasi- flow field, until position at first of Mach wave compression angle of Busemann air intake ducts is blocked, if multistage pressure
Contracting waverider forebody derived only has two-stage, then the step is identical with step 2-2.
Further, the integrated configuration geometry design parameter of forebody and inlet includes：Air intake duct captures curve and flowing is caught
Curve is obtained, to flow capture curve in plane of symmetry intersection point as the origin of coordinates, wherein flowing capture curve includes straightway and curve
Section, straightway equation form is：0≤x≤Lu, y=0, curved section equation form is：x≥Lu, y=B (x-Lu)m；Air intake duct is caught
Obtaining curve includes straightway and curved section, and straightway equation form is：0≤x≤Ls, y=-H, curved section equation form is：x≥
Ls, y=-H+A (x-Ls)n, flowing capture curve is (X with air intake duct capture intersections of complex curve coordinatecoj,Ycoj), flowing capture curve
It is s to capture intersections of complex curve in y directions relative position ratio with air intake duct, and whole air intake duct is highly H, is met | Ycoj|=sH.
Further, multi-stage compression waverider forebody derived benchmark flow field design parameter is as follows in each osculating face：Every grade of reference flow
The cone shock stream that comes is parallel relative to benchmark flow field symmetry axis, therefore every grade of benchmark flow field of rotation makes axis drift angle αaxisWith
To flow drift angle αstrIt is equal, i.e. αaxis=αstr, parameter after every grade of compression shock is tried to achieve by oblique shock wave relational expression and is used as every grade of base
Quasi- flow field primary condition, every grade of benchmark flow field calculation equation is dimensionless Taylor-Maccoll equations, and equation form is
WhereinFlow field iteration angle (size on the basis of θ
For the angle with flow field axis), VθFor circumferential speed component, VrFor radial velocity component, asterisk is characteristic, and a is the velocity of sound, M
For Mach number, footmark ∞ is expressed as flowing parameter, and according to stream function formula, flowing capture curve discrete point is in every grade of benchmark flow field
Middle carry out streamlined impeller, gained streamline is multi-stage compression waverider forebody derived Partial shrinkage face.
Further, Busemann inner conical benchmark flow field design parameter is as follows in each osculating face：Block Busemann
The integrated configuration afterbody compression section of air intake duct, therefore its benchmark flow field iteration ends angle θendMust be with integrated configuration
Afterbody compression angle βbMeet supplementary angle relation, i.e. θend=180 ° of-βb, benchmark flow field free stream Mach number is Mb1When, Taylor-
Maccoll equations are in singular point angle θsp=180 ° of-arcsin (1/Mb1) place's flow field parameter has flex point, to solve to block Busemann
Air intake duct coupling singular point problem integrated with multi-stage compression waverider forebody derived, Busemann inner conical benchmark flow field iteration ends angle
θendIt is necessarily less than singular point angle θsp, Busemann inner conical benchmark flow field Lai Liu drift angles are αstrWhen, it is necessary to make θend180 ° of ＜-
arcsin(1/Mb1)-αstr, Busemann inner conical benchmark flow field calculations equation is dimension Taylor-Maccoll equations, equation
Form is
Wherein Flow field iteration angle, v on the basis of θθFor circumferential speed component, vrFor radial velocity component, double asterisk is immeasurable
Guiding principle amount, a is the velocity of sound, T0To flow stagnation temperature, γ is specific heats of gases ratio, R is gas constant.
The present invention has the advantages that：Solved on technological layer before Busemann air intake ducts and multi-stage compression rider
The interference of Taylor-Maccoll parametric singular points problem in body coupling process；With existing multi-stage compression waverider forebody derived designing technique phase
Than multistage coupling technique method of the invention has been obviously improved the lift-drag ratio and inlet mouth of conventional multi-level compression waverider forebody derived
Total pressure recovery coefficient；Improve air intake duct low rate start performance；Improve the superb anti-clogging performance of air intake duct.
Brief description of the drawings：
Fig. 1 is multi-stage compression waverider forebody derived in single osculating face and blocks Busemann air intake duct coupling arrangement schematic diagrames.
Fig. 2 captures curve synoptic diagram for flowing capture curve and air intake duct.
Fig. 3 is multi-stage compression waverider forebody derived benchmark flow field schematic diagrames at different levels.
Fig. 4 is to block Busemann air intake duct benchmark flow field schematic diagram.
Fig. 5 is multi-stage compression waverider forebody derived and blocks Busemann air intake duct coupling arrangement graphics.
Fig. 6 is that the method for the invention generates integrated configuration and conventional multi-level compression waverider forebody derived contrast side view.
Fig. 7 is that the method for the invention generates integrated configuration and conventional multi-level compression waverider forebody derived contrast front view.
Fig. 8 is that the method for the invention generates integrated configuration and conventional multi-level compression waverider forebody derived contrast upward view.
Fig. 9 is that the method for the invention generates integrated configuration and conventional multi-level compression waverider forebody derived contrast perspective view.
Figure 10 is that the method for the invention generates integrated 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.
Label title in figure：1- multi-stage compression waverider forebody deriveds, 2- blocks Busemann air intake ducts, and 3- is of coupled connections transition
Section, 4- flowing capture curves (FCC), 5- air intake ducts capture curve (ICC), 6- zero-incidence circular cones stream benchmark flow field, 7-
Busemann inner conical benchmark flow field, 8- circular cones with angle stream benchmark flow field, and 9- inlet lip reflected shock waves, 10- is blocked
First of Mach wave of Busemann air intake ducts, 11- two-stage compression Mach waves, 12- one stage of compression Mach waves, 13- osculatings face, 14-
Traditional three stage compression waverider forebody derived, 15- two-stage compressions waverider forebody derived coupling arrangement integrated with blocking Busemann, 16- air inlets
Road distance piece, 17- flows capture cross section, 18- inlet mouth capture cross sections, 19- distance piece capture cross sections.
Embodiment：
The present invention is further described with reference to the accompanying drawings and examples.
A kind of hypersonic aircraft precursor and the multistage coupling integrated design method of air intake duct, with reference to multi-stage compression rider
Precursor and the integrated three-dimensional layout for blocking Busemann air intake ducts, emphatically to multi-stage compression waverider forebody derived with blocking Busemann
Air intake duct integration coupling technique is illustrated.
Hypersonic aircraft precursor of the present invention is with the multistage coupling integrated configuration of air intake duct by multi-stage compression waverider forebody derived 1
Constituted with blocking Busemann air intake ducts 2, wherein the afterbody compression section of multi-stage compression waverider forebody derived 1 is the changeover portion that is of coupled connections
3.Under any flying height and Mach number, the variable flowing capture curve (FCC, leading edge curve) 4 of given parameters and air intake duct are caught
Curve (ICC) 5 is obtained, is converted into three-dimensional multistage coupling integrated configuration generation using osculating cone theazy every in second order accuracy
Two-dimentional streamline generation problem in individual osculating face 13, streamline is carried out to given flowing capture curve 4 in benchmark flow fields at different levels
Tracking obtains multi-stage compression curved surface configuration integrated with blocking Busemann compressing surfaces；It is used for multi-stage compression in each osculating face 13
The zero-incidence circular cone of Waverider design streams benchmark flow field 6 and belongs to axial symmetry for Busemann inner conical benchmark flow field 7
Taper flow field, is described using no quantization Taylor-Maccoll flow equations；For the strange of existing Busemann benchmark flow field 7
Point angle causes the problem of it can not be coupled with existing multi-stage compression waverider forebody derived 1, existing design method is improved, in both reference flows
Between add one section of changeover portion 3 that is of coupled connections, flowing capture curve (leading edge curve) 4 discrete points respectively zero-incidence circular cone around
Stream benchmark flow field 6 and transition compression section circular cone with angle stream and streamlined impeller are carried out in benchmark flow field 8, until Busemann inner cones
The iteration ends angle θ of shape benchmark flow field 7endLess than singular point angle θsp, conversion benchmark flow field is to block Busemann inner conical benchmark flow field
7 and proceed streamlined impeller to inlet lip reflected shock wave 9；It is fitted streamline in all osculating faces bent into multistage coupling compression
Face obtains integrated configuration.
Above-mentioned hypersonic aircraft precursor is specifically retouched with the multistage coupling integrated configuration of air intake duct and its benchmark flow field
State parameter as follows, due to symmetry, take half module configuration to be described for convenience of description is following：
The integrated configuration geometry design parameter of 2-1, forebody and inlet includes：Air intake duct capture curve (ICC) 5 and flowing are caught
Obtain curve (FCC) 4.To flow capture curve (FCC) 4 in plane of symmetry intersection point as the origin of coordinates, wherein flowing capture curve (FCC)
4 include straightway and curved section, and straightway equation form is：0≤x≤Lu, y=0, curved section equation form is：x≥Lu, y=B
(x-Lu)m；Air intake duct capture curve (ICC) 5 includes straightway and curved section, and straightway equation form is：0≤x≤Ls, y=-
H, curved section equation form is：x≥Ls, y=-H+A (x-Ls)n.Flowing capture curve (FCC) 4 captures curve with air intake duct
(ICC) 5 intersecting point coordinates are (Xcoj,Ycoj), flowing capture curve (FCC) 4 and air intake duct capture curve (ICC) 5 intersection point in y directions
Relative position ratio is s, and whole air intake duct is highly H, is met | Ycoj|=sH.
Multi-stage compression waverider forebody derived benchmark flow field design parameter is as follows in 2-2, each osculating face 13.Every grade of benchmark flow field cone
Lambda shock wave come stream it is parallel relative to benchmark flow field symmetry axis, therefore rotation every grade of benchmark flow field make axis drift angle αaxisWith flowing
Drift angle αstrIt is equal, i.e. αaxis=αstr.Parameter after every grade of compression shock is tried to achieve by oblique shock wave relational expression and is used as every grade of reference flow
Field primary condition.Every grade of benchmark flow field calculation equation is dimensionless Taylor-Maccoll equations, and equation form is
WhereinFlow field iteration angle (size on the basis of θ
For the angle with flow field axis), VθFor circumferential speed component, VrFor radial velocity component, asterisk is characteristic, and a is the velocity of sound, M
For Mach number, footmark ∞ is expressed as flowing parameter.According to stream function formula, flowing capture curve (FCC) 4 discrete point is in every grade of base
Streamlined impeller is carried out in quasi- flow field, gained streamline is multi-stage compression waverider forebody derived Partial shrinkage face.
7 design parameters of Busemann inner conical benchmark flow field are as follows in 2-3, each osculating face.Block Busemann air inlets
The integrated configuration afterbody compression section in road 2, therefore its benchmark flow field iteration ends angle θendMust be last with integrated configuration
One stage of compression angle betabMeet supplementary angle relation, i.e. θend=180 ° of-βb.Benchmark flow field free stream Mach number is Mb1When, Taylor-
Maccoll equations are in singular point angle θsp=180 ° of-arcsin (1/Mb1) place's flow field parameter has flex point.Therefore blocked for solution
The coupling singular point problem integrated with multi-stage compression waverider forebody derived 1 of Busemann air intake ducts 2, Busemann inner conical benchmark flow field 7
Iteration ends angle θendIt is necessarily less than singular point angle θsp, drift angle is flowed for α in Busemann inner conical benchmark flow field 7strWhen, it is necessary to make
θend180 ° of-arcsin (1/M of ＜b1)-αstr.It is dimension Taylor- that Busemann inner conical benchmark flow field 7, which solves equation,
Maccoll equations, equation form is
Wherein Flow field iteration angle (size is the angle with flow field axis), v on the basis of θθFor circumferential speed component, vrFor
Radial velocity component, double asterisk is characteristic, and a is the velocity of sound, T0To flow stagnation temperature, γ is specific heats of gases ratio, R is that gas is normal
Number.According to stream function formula, continuation carries out streamlined impeller in Busemann benchmark flow field 7, and gained streamline enters for Busemann
Airway portion compressing surface.
Hypersonic aircraft precursor of the present invention and the multistage coupling integrated configuration of air intake duct and its design method, including such as
Lower step：
Step 1, given air intake duct capture curve (ICC) 5 and flowing capture curve (FCC) 4, method is bored by three according to osculating
Dimension problem is converted into two-dimensional problems in second order accuracy, i.e., carry out streamlined impeller to leading edge point in each osculating face 13；
Step 2, to multi-stage compression waverider forebody derived part carry out streamlined impeller, gained streamline is multi-stage compression waverider forebody derived
1 compressing surface.
Step 2-1, construction first order benchmark flow field simultaneously carry out streamlined impeller.One stage of compression benchmark flow field can use zero-incidence
Circular cone streams benchmark flow field 6 to construct, and flow field is by Taylor-Maccoll equation solutions, to flow by one stage of compression Mach wave
Stream and be tracked in benchmark flow field 6 until reaching the position of two-stage compression Mach wave 11 in zero-incidence circular cone after 12 compressions.
Step 2-2, construction second level benchmark flow field simultaneously carry out streamlined impeller.Streamline streams benchmark flow field in zero-incidence circular cone
When two-stage compression 11 position of Mach wave is tracked in 6, two grades of shock wave front flow field parameters have certain angle of attack, now need to incline on two grades of bands
The axis of angle circular cone benchmark flow field 8 around cone point rotate respective angles make it is parallel with direction of flow before two-stage compression Mach wave 11.Air-flow
Continue to stream in two grades of circular cones with angle after the compression of two-stage compression Mach wave 11 and streamlined impeller is carried out in benchmark flow field 8.
Step 2-3, the benchmark flow field building method more than more than two grades are identical with two stage approach, and the afterbody of precursor
Compressing surface is that air-flow continues at it after shock wave compression with blocking the changeover portion 3 that is of coupled connections that Busemann air intake ducts 2 are combined
Streamlined impeller is carried out in benchmark flow field, until position at the compression angle of first of Mach wave of Busemann air intake ducts 10 is blocked, if many
Level compression waverider forebody derived 1 only has two-stage, then the step is identical with step 2-2.
Step 3, construction block Busemann inner conical benchmark flow field 7 and carry out streamlined impeller.Streamline in waverider forebody derived most
It is tracked in rear stage benchmark flow field until blocking at first of Mach wave of Busemann air intake ducts 10, the Mach wave compression angle
It is supplementary angle relation with the iteration ends angle of Busemann inner conical benchmark flow field 7, and iteration ends angle is necessarily less than flow field Taylor-
Maccoll equation singular points angle, otherwise changes integrated configuration afterbody compression angle and repeat step 2-3 is until meet integration
Coupling condition.Step 3 needs to iterate until meeting flow field parameter at the iteration ends angle of Busemann inner conical benchmark flow field 7
It is identical with the angle of attack with blocking the preceding flow field Mach number of first of Mach wave of Busemann air intake ducts 10, and entrance at iteration initial angle
Flow field direction level after inlet lip reflected shock wave 9.Proceed streamline in the Busemann inner conical benchmark flow field 7 to chase after
Track obtains and blocks the compressing surface of Busemann air intake ducts 2.
Step 4, the streamline that the interior tracking in each osculating face 13 is obtained carry out three-dimensional fitting, ultimately generate multi-stage compression rider
Precursor 1 is with blocking the integrated coupling arrangement of Busemann air intake ducts 2.
Application example
To verify design method validity, with two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann
Exemplified by illustrate.
1. technical parameter
Selecting technology parameter is as shown in the table
The two-stage compression waverider forebody derived of table 1. design parameter of coupling arrangement 15 integrated with blocking Busemann
Two-stage compression waverider forebody derived has been ultimately generated using design method of the present invention and blocks Busemann air intake ducts one
Change and generate traditional three stage compression waverider forebody derived 14 under configuration 15, same design parameter.
3. numerical simulation result
Two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann is compared to traditional three stage compression rider
The lift-drag ratio of precursor 14 has greatly improved.During without viscous state, lift-drag ratio maximal increment at Mach number 5,6,7 is respectively
74.29%th, 75.96%, 77.47% and be both present in 0 ゜ design the angle of attack.When having viscous state, lift-drag ratio is at Mach number 5,6,7
Maximal increment be respectively 48.79%, 52.71%, 55.34% and be both present in 0 ゜ design the angle of attack.High ultrasound proposed by the present invention
Fast aircraft precursor has greatly improved with the multistage coupling integrated design method of air intake duct to superb waverider forebody derived lifting resistance characteristic.
Without two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann under viscous design point and tradition three
The level compression discharge coefficient of waverider forebody derived 14 is of substantially equal, and both are close to 100%；When having viscous state two-stage compression waverider forebody derived with
Block the integrated discharge coefficients of coupling arrangement 15 of Busemann bigger, illustrate compared to traditional three stage compression waverider forebody derived 14 have compared with
Few overflow.No matter have viscous without gluing simultaneously, two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann is being set
The total pressure recovery coefficient of inlet mouth capture cross section 18 has more than 11% lifting under the conditions of meter.Although two kinds of configurations have approximate phase
Deng the sectional area of air intake duct distance piece 16, but two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann exists
Inlet mouth has more uniform flow field and less low-pressure area, therefore has less total crushing in air intake duct distance piece 16
Consumption.Two-stage compression waverider forebody derived coupling arrangement 15 integrated with blocking Busemann is captured in the distance piece away from inlet mouth 3m
There is without total pressure recovery coefficient under viscous state nearly 34.7% lifting at section 19, there is the lifting for having nearly 20.2% under viscous state.Say
Bright hypersonic aircraft precursor proposed by the present invention is with the multistage coupling integrated design method of air intake duct to superb waverider forebody derived
Compression performance have more significant lifting.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, some improvement can also be made under the premise without departing from the principles of the invention, and these improvement also should be regarded as the present invention's
Protection domain.
Claims (5)
1. the design method of a kind of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct, it is characterised in that：
Comprise the following steps
Step 1, given air intake duct capture curve (5) and flowing capture curve (4), convert three-dimensional problem according to osculating cone method
For two-dimensional problems in second order accuracy, i.e., streamlined impeller is carried out to leading edge point in each osculating face (13)；
Step 2, to multi-stage compression waverider forebody derived part carry out streamlined impeller, gained streamline is multi-stage compression waverider forebody derived (1)
Compressing surface；
Step 3, construction block Busemann inner conical benchmark flow field (7) and carry out streamlined impeller, and streamline is last in waverider forebody derived
It is tracked in one-level benchmark flow field until blocking first of Mach wave of Busemann air intake ducts (10) place, the Mach wave compression angle
With blocking Busemann inner conical benchmark flow field (7) iteration ends angle for supplementary angle relation, and iteration ends angle is necessarily less than flow field
Taylor-Maccoll equation singular points angle, otherwise changes integrated configuration afterbody compression angle and repeat step 2-3 is until full
Sufficient integration coupling condition, step 3 needs to iterate blocks Busemann inner conical benchmark flow field (7) iteration end until meeting
Flow field parameter is identical with the angle of attack with blocking the preceding flow field Mach number of first of Mach wave of Busemann air intake ducts (10) at angle till, and
Inlet induction road lip reflected shock wave (9) flow field direction level afterwards, Busemann inner conical bases are blocked at this at iteration initial angle
Proceed streamlined impeller acquisition in quasi- flow field (7) and block Busemann air intake ducts (2) compressing surface；
Step 4, the streamline that the interior tracking of each osculating face (13) is obtained carry out three-dimensional fitting, ultimately generate before multi-stage compression rider
Body coupling arrangement integrated with blocking Busemann air intake ducts.
2. the design side of hypersonic aircraft precursor as claimed in claim 1 and the multistage coupling integrated configuration of air intake duct
Method, it is characterised in that：Step 2 is specifically included
Step 2-1, construction first order benchmark flow field simultaneously carry out streamlined impeller, and zero-incidence is used in first order benchmark flow field in the method
Circular cone streams benchmark flow field (6) to construct, and flow field is by Taylor-Maccoll equation solutions, to flow by one stage of compression Mach
Stream and be tracked in benchmark flow field (6) until reaching two-stage compression Mach wave (11) position in zero-incidence circular cone after ripple (12) compression
Put；
Step 2-2, construction second level benchmark flow field simultaneously carry out streamlined impeller, and second level benchmark flow field is in the method with angle
Circular cone streams benchmark flow field (8) to construct, and streamline streams in zero-incidence circular cone tracks two-stage compression Mach in benchmark flow field (6)
During ripple (11) position, two grades of shock wave front flow field parameters have certain angle of attack, now need circular cone with angle streaming benchmark flow field (8) axle
Line around cone point rotate respective angles make it is parallel with direction of flow before two-stage compression Mach wave (11), air-flow by two-stage compression Mach
Continue to carry out streamlined impeller in circular cone with angle streams benchmark flow field (8) after ripple (11) compression；
Step 2-3, the benchmark flow field building method more than more than two grades are identical with two stage approach, and the afterbody compression of precursor
Face is the changeover portion that is of coupled connections (3) with blocking Busemann air intake ducts (2) combination, and air-flow continues at it after shock wave compression
Streamlined impeller is carried out in benchmark flow field, until position at first of Mach wave of Busemann air intake ducts (10) compression angle is blocked, if
Multi-stage compression waverider forebody derived (1) only has two-stage, then the step is identical with step 2-2.
3. the design side of hypersonic aircraft precursor as claimed in claim 2 and the multistage coupling integrated configuration of air intake duct
Method, it is characterised in that：
Precursor includes with the multistage coupling integrated configuration geometry design parameter of air intake duct：Air intake duct capture curve (5) and flowing are caught
Curve (4) is obtained, to flow capture curve (4) in plane of symmetry intersection point as the origin of coordinates, including straightway and curved section, straight line
Section equation form be：0≤x≤Lu, y=0, wherein LuFor flowing capture curve (4) length of straigh line, curved section equation form is：
x≥Lu, y=B (x-Lu)m, wherein B and m are flowing capture curve (4) curved section equation linear coefficient and power exponent；Air intake duct is caught
Obtaining curve (5) includes straightway and curved section, and straightway equation form is：0≤x≤Ls, y=-H, wherein LsIt is air intake duct with H
Curve (5) length of straigh line and air intake duct height are captured, curved section equation form is：x≥Ls, y=-H+A (x-Ls)n, wherein A
It is that air intake duct captures curve (5) curved section equation linear coefficient and power exponent with n；Flowing capture curve (4) is captured with air intake duct
Curve (5) intersecting point coordinate is (Xcoj,Ycoj), flowing capture curve (4) and air intake duct capture curve (5) intersection point are relative in y directions
Position ratio is s, is met | Ycoj|=sH.
4. the design side of hypersonic aircraft precursor as claimed in claim 3 and the multistage coupling integrated configuration of air intake duct
Method, it is characterised in that：
The interior multi-stage compression waverider forebody derived benchmark flow field design parameter in each osculating face (13) is as follows：Every grade of benchmark flow field cone shock
Coming, it is parallel relative to benchmark flow field symmetry axis to flow, therefore every grade of benchmark flow field of rotation makes axis drift angle αaxisWith flowing drift angle
αstrIt is equal, i.e. αaxis=αstr, tried to achieve by oblique shock wave relational expression at the beginning of parameter after every grade of compression shock is used as every grade of benchmark flow field
Beginning condition, every grade of benchmark flow field calculation equation is dimensionless Taylor-Maccoll equations, and equation form is
<mfenced open = "{" close = "">
<mtable>
<mtr>
<mtd>
<mrow>
<mfrac>
<mrow>
<msubsup>
<mi>dV</mi>
<mi>&theta;</mi>
<mo>*</mo>
</msubsup>
</mrow>
<mrow>
<mi>d</mi>
<mi>&theta;</mi>
</mrow>
</mfrac>
<mo>=</mo>
<mo>-</mo>
<msubsup>
<mi>V</mi>
<mi>r</mi>
<mo>*</mo>
</msubsup>
<mo>+</mo>
<msup>
<mrow>
<mo>(</mo>
<mi>a</mi>
<mo>/</mo>
<msub>
<mi>a</mi>
<mi>&infin;</mi>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
<mfrac>
<mrow>
<msubsup>
<mi>V</mi>
<mi>r</mi>
<mo>*</mo>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>V</mi>
<mi>&theta;</mi>
<mo>*</mo>
</msubsup>
<mi>cot</mi>
<mi>&theta;</mi>
</mrow>
<mrow>
<msubsup>
<mi>V</mi>
<mi>&theta;</mi>
<mrow>
<mo>*</mo>
<mn>2</mn>
</mrow>
</msubsup>
<mo>-</mo>
<msup>
<mrow>
<mo>(</mo>
<mi>a</mi>
<mo>/</mo>
<msub>
<mi>a</mi>
<mi>&infin;</mi>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
</mrow>
</mfrac>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<mfrac>
<mrow>
<msubsup>
<mi>dV</mi>
<mi>r</mi>
<mo>*</mo>
</msubsup>
</mrow>
<mrow>
<mi>d</mi>
<mi>&theta;</mi>
</mrow>
</mfrac>
<mo>=</mo>
<msubsup>
<mi>V</mi>
<mi>&theta;</mi>
<mo>*</mo>
</msubsup>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
WhereinIteration angle in flow field on the basis of θ, size be with
The angle of flow field axis, VθFor circumferential speed component, VrFor radial velocity component, asterisk is characteristic, and a is the velocity of sound, and γ is gas
Body specific heat ratio, M is Mach number, and footmark ∞ is expressed as flowing parameter, according to stream function formula, flowing capture curve (4) discrete point
Streamlined impeller is carried out in every grade of benchmark flow field, gained streamline is multi-stage compression waverider forebody derived Partial shrinkage face.
5. the design side of hypersonic aircraft precursor as claimed in claim 4 and the multistage coupling integrated configuration of air intake duct
Method, it is characterised in that：
It is as follows that Busemann inner conical benchmark flow field (7) design parameter is blocked in each osculating face：Block Busemann air intake ducts
(2) integrated configuration afterbody compression section, therefore its benchmark flow field iteration ends angle θendMust be last with integrated configuration
One stage of compression angle betabMeet supplementary angle relation, i.e. θend=180 ° of-βb, benchmark flow field free stream Mach number is Mb1When, Taylor-
Maccoll equations are in singular point angle θsp=180 ° of-arcsin (1/Mb1) place's flow field parameter has flex point, to solve to block Busemann
Air intake duct (2) coupling singular point problem integrated with multi-stage compression waverider forebody derived (1), blocks Busemann inner conical benchmark flow field
(7) iteration ends angle θendIt is necessarily less than singular point angle θsp, Busemann inner conical benchmark flow field (7) is blocked to flow drift angle for αstr
When, it is necessary to make θend180 ° of-arcsin (1/M of ＜b1)-αstr, it is amount to block Busemann inner conical benchmark flow field (7) and solve equation
Guiding principle Taylor-Maccoll equations, equation form is
<mfenced open = "{" close = "">
<mtable>
<mtr>
<mtd>
<mrow>
<mfrac>
<mrow>
<msubsup>
<mi>dv</mi>
<mi>&theta;</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
</mrow>
</msubsup>
</mrow>
<mrow>
<mi>d</mi>
<mi>&theta;</mi>
</mrow>
</mfrac>
<mo>=</mo>
<mo>-</mo>
<msubsup>
<mi>v</mi>
<mi>r</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
</mrow>
</msubsup>
<mo>+</mo>
<msup>
<mi>a</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
<mn>2</mn>
</mrow>
</msup>
<mfrac>
<mrow>
<msubsup>
<mi>v</mi>
<mi>r</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
</mrow>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>v</mi>
<mi>&theta;</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
</mrow>
</msubsup>
<mi>cot</mi>
<mi>&theta;</mi>
</mrow>
<mrow>
<msubsup>
<mi>v</mi>
<mi>&theta;</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
<mn>2</mn>
</mrow>
</msubsup>
<mo>-</mo>
<msup>
<mi>a</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
<mn>2</mn>
</mrow>
</msup>
</mrow>
</mfrac>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<mfrac>
<mrow>
<msubsup>
<mi>dv</mi>
<mi>r</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
</mrow>
</msubsup>
</mrow>
<mrow>
<mi>d</mi>
<mi>&theta;</mi>
</mrow>
</mfrac>
<mo>=</mo>
<msubsup>
<mi>v</mi>
<mi>&theta;</mi>
<mrow>
<mo>*</mo>
<mo>*</mo>
</mrow>
</msubsup>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
Whereina**2=(a/Vmax)2, θ
On the basis of flow field iteration angle, vθFor circumferential speed component, vrFor radial velocity component, VmaxFor limit velocity, double asterisk is immeasurable
Guiding principle amount, a is the velocity of sound, T0To flow stagnation temperature, γ is specific heats of gases ratio, R is gas constant.
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| CN111619820B (en) * | 2019-12-02 | 2022-02-22 | 中国人民解放军国防科技大学 | Hypersonic speed precursor design method based on two-region flow field |
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| CN115056998A (en) * | 2022-03-26 | 2022-09-16 | 中国空气动力研究与发展中心空天技术研究所 | Longitudinal segmentation and hierarchical compression design method for cone guide multiplier front body |
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