CN107341323A - A kind of design method for the continuously adjustabe air intake duct that rigid/flexible combines - Google Patents

A kind of design method for the continuously adjustabe air intake duct that rigid/flexible combines Download PDF

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CN107341323A
CN107341323A CN201710664785.6A CN201710664785A CN107341323A CN 107341323 A CN107341323 A CN 107341323A CN 201710664785 A CN201710664785 A CN 201710664785A CN 107341323 A CN107341323 A CN 107341323A
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venturi
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CN107341323B (en
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孙姝
王晨曦
谭慧俊
凌棫
黄河峡
张悦
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Abstract

A kind of design method of the continuously adjustabe air intake duct combined the invention discloses rigid/flexible, determine to correspond to fixation compressing surface and adjustable compression face angular distribution that shock wave pastes mouth under design point, determine the requirement to venturi height under air intake duct different working condition, design adjustable compression face type face, design venturi section and diffuser, according to Its Track Design linkage expected from inlet throat section, the Design of Main Structure of air intake duct is completed.Meanwhile also configured in design process by careful wide fast domain wave system, wave absorption processing is carried out using the expansion fan of compressing surface shoulder arcuate surface, suppresses influence of the Shock/Boundary-Layer interference to inlet characteristic.In addition, the design method also determines venturi height and the relation of actuation mechanism horizontal displacement by motion simulation, and then work Mach number and the corresponding relation of governor motion regulated quantity are determined, that is, the Rule adjusting of air intake duct is determined.

Description

A kind of design method for the continuously adjustabe air intake duct that rigid/flexible combines
Technical field
The present invention relates to field of flight vehicle design, especially a kind of Supersonic Inlet.
Background technology
Air suction type supersonic aircraft is one of prior development direction of aerospace field, there is higher military affairs, society It can be worth, therefore be paid attention to by various countries.And inlet duct of the air intake duct as engine, it is that the three of airbreathing propulsion system are big One of key aerodynamic part, directly facing the combustion chamber that High Mach number incoming and operating mode are complicated, its design form and working characteristics Significantly affect the overall performance of whole propulsion system or even aircraft.In actual applications, engine needs are operated in wider Flight envelope in, this requires air intake duct to have more broad Mach number working range.
The contract ratio of air intake duct is a key parameter in design process.For being operated in wide range of Mach numbers For air intake duct, it needs less contract than to ensure the starting performance of air intake duct under low mach, and in high Mach It is several lower, it is necessary to which larger contract is than improving the decrement of air intake duct, therefore, when air intake duct works under high and low Mach number For air intake duct contract than demand run counter to completely.For determining geometry air intake duct scheme, due to its geometry profile not It is adjustable, the big shrinkage ratio requirement under small shrinkage ratio and the High Mach number under low mach can not be met simultaneously, therefore often adopt With tradeoff design, it is difficult to meet the work requirements in wide range of Mach numbers.In order to solve this contradiction, adjustable air intake can be used Design to realize the contract under different Mach number than regulation in road.
At present, the Main Developed Countries such as U.S., France, Japan etc. all to adjustable air intake duct accordingly grind in the world Study carefully, as can be seen that there are some relatively feasible regulation schemes from existing open source literature.For example, enter for axial symmetry The center cone translation and fluting scheme that air flue uses, change throat area by center cone, meet the flow under different Mach number Demand, widen the working range of air intake duct.There is lip cover scheme of rotation using more in two dimensional inlet, it can pass through lip Opener controls the opening and closing of inlet mouth, and the regulation of shrinkage ratio is realized during lip cover rotates.
However, existing scheme is there is governor motion is complicated, corresponding time length, the problems such as reliability is low, exist during regulation Problems, and existing scheme for contract than adjustable range than relatively limited.In addition, in existing variable geometry inlet In design process, influence of the Shock/Boundary-Layer interference to air intake duct inside control air intake duct is often ignored.Therefore, it is necessary to set Count out a kind of simple in construction, reliability is high, can in wide in range range of Mach numbers high-performance steady operation variable geometry inlet.
The content of the invention
Wide range of Mach numbers is operated in order to solve air intake duct, the problem of contract ratio need to be with work Mach number regulation, this Invented the design method for providing the variable geometry inlet that a kind of rigid/flexible combines, using the teaching of the invention it is possible to provide variable geometry inlet it is reliable Property and enable air intake duct high-performance steady operation in wide in range range of Mach numbers.
In order to achieve the above object, the design of variable geometry inlet adopts the following technical scheme that in the present invention：
The design method for the continuously adjustabe air intake duct that a kind of rigid/flexible combines, it is characterised in that the design method is set Meter object is a kind of variable geometry inlet, including before air intake duct lip cover, the precursor compressing surface positioned at air intake duct lip cover front lower place, connection Body compress surface rear end and extend back adjustable compression face, connection adjustable compression surface rear end and extend back venturi section, connection Venturi section rear end and extend back diffuser, positioned at venturi section back to lip cover side two rocking bars, carrying rocking bar and from before The drive device that horizontal operating bar, the horizontal operating bar of driving to extend back moves forward and backward；Precursor compressing surface is included positioned at front portion One stage of compression face and the two-stage compression face that is extended back from one stage of compression face；The front end in the adjustable compression face and two-stage compression The rear end in face is hinged；The rear end of the front end and adjustable compression face of the venturi section is hinged；Shape between venturi section and air intake duct lip cover Into venturi；The diffuser is flexible material；The front end of rocking bar is articulated with venturi section and cut with scissors back to the side of lip cover, the rear end of rocking bar It is connected on horizontal operating bar；When horizontal operating bar moves forward, the front end of rocking bar withstands venturi section makes venturi to lip cover movement Section diminishes with the distance between lip cover；When horizontal operating bar is moved rearwards, the front end of rocking bar retract venturi section make venturi section with The distance between lip cover becomes big；
The design method design procedure is as follows：
(1) wave system configures：
(1.1) the highest work Mach number of air intake duct is set to design point, mouth principle is pasted according to shock wave under this Mach number Carry out wave system configuration；According to the traffic demand and working depth of air intake duct cruising condition, the stream of design point is determined by flow formula Amount capture area
In formula, m be design point demand gas flow, ρ0、u0The density and speed of respectively free incoming；And then according to Air intake duct length-width ratio determines lip cover oral area height h0；
(1.2) according to air intake duct forebody length and the requirement of total compression amount, one-level Angle of Shock Waves β is determined1；In face of one stage of compression For edge as origin, it is β to make with horizontal line angle1Ray, the ray and height h0Horizontal intersection point is lip cover oral area position Put；There is following relational expression by oblique shock wave wave angle β and flow-deviation angle δ：
In formula, M is oblique shock wave wavefront Mach number；So as to according to one-level oblique shock wave wave angle β1Determine the air-flow in one stage of compression face Deflection angle δ1；
(1.3) in order to obtain the total pressure recovery coefficient of maximum, according to the equal principle of the normal direction Mach number before each oblique shock wave, I.e.
M0 sinβ1=M1 sinβ2
Determine two level oblique shock wave wave angle β2；It is (β to cross lip to make one with horizontal line angle2+δ1) ray, with one stage of compression The intersection point in face is two-stage compression face starting point；Two-stage compression face is determined according to the relational expression of oblique shock wave wave angle and flow-deviation angle Flow-deviation angle δ2, then two-stage compression face and horizontal line angle theta2=δ1+δ2；
(1.4) adjustable compression face is considered as into fixed compressing surface in design point to be designed, determines pressure-adjustable under cruising condition Contracting face adjust to during correspondence position with horizontal line angle theta3Size；It is specific as follows：First still according to the method before each oblique shock wave To Mach number equal principle, the wave angle β of three-level oblique shock wave is determined3；It is (β to cross lip to make one with horizontal line angle3+θ2) ray, Intersection point with two-stage compression face is the starting point in adjustable compression face；Similarly, according to oblique shock wave wave angle and the relation of flow-deviation angle Formula determines the flow-deviation angle δ in adjustable compression face3, then adjustable compression face and horizontal line angle theta under design point3=θ2+δ3；
(1.5) lip cover quasi spline；Due to lip cover oral area height h0It has been determined that lip cover (1) inner mold face was designed as lip One horizontal line of mouth；Lip cover outer surface and horizontal line angle are according to the restriction of Inlet drag and lip shock not lift-off, really It is scheduled on 8 ° -10 °；
(2) determination in venturi height and compressing surface type face：
(2.1) minimum venturi height h is determinedmin；Air intake duct cruising condition corresponds to minimum venturi height, and design causes this When venturi gasflow mach number be 1.3, therefore minimum venturi is highly：
In formula, h3For the vertical distance of lip cover oral area under design point to adjustable compression face, due to step
(1) lip cover position and third level adjustable compression face angle degree, therefore h are had determined that in3It is known；
q(λ3) it is flow function of the design point downstream after three-level oblique shock wave；
q(λt) it is flow function corresponding to venturi (12) Mach number 1.3；
σaFor air-flow 0.95 is taken after three-level oblique shock wave ripple to the total pressure recovery coefficient of venturi, approximation；
(2.2) adjustable compression face type face is designed；In design point according to adjustable compression face and horizontal line angle and most small larynx Road height hminIt is determined that；Rounding design is carried out to compressing surface shoulder molded line, lip cover shock wave is fallen in shoulder rounding area, to utilize shoulder Portion's expansion fan weakens the intensity of reflected shock wave；Rounding design makes compressing surface gradually transit to height distance lip cover inner mold face hmin's Position, meets the needs of design point is to minimum venturi height；
(2.3) maximum venturi height h is determinedmax；Maximum stream flow according to needed for engine when taking off, venturi highly want energy The air-flow of enough air intake ducts that ensures then can be calculated normal through without being jammed at venturi by flow formula：
In formula, maximum stream flow coefficient when ψ is takeoff condition；
h∞For the height of free incoming flow tube；
q(λ0) it is free inlet flow rate function；
σbFor air-flow from inlet mouth to venturi at total pressure recovery coefficient；
q(λt) it is flow function corresponding to venturi gasflow mach number；
(2.4) the venturi adjusting position in accelerator is determined：Free stream Mach number M0During less than 1, venturi position is not adjusted Section；As free stream Mach number M0During more than 1, because a two-stage compression face, two-stage compression face geometry profile are fixed, therefore according to one-dimensional Stream oblique shock wave relational expression can extrapolate one-level oblique shock wave wave angle β1And gasflow mach number M after ripple1, two level oblique shock wave wave angle β2 And gasflow mach number M after ripple2.It can be obtained by flow formula：
In formula, h2For the vertical distance of the lip cover oral area that is determined by geometrical relationship to second level compressing surface；
q(λ2) be two level oblique shock wave ripple after air-flow flow function；
σcRule of thumb estimated to the total pressure recovery coefficient of venturi, value after two level oblique shock wave ripple for air-flow；
q(λt) it is flow function corresponding to venturi gasflow mach number；
(3) venturi section and diffuser are designed：
(3.1) design of venturi section；Venturi segment length is chosen for minimum venturi height hmin3-4 times；Venturi section rear portion is entered Row rounding designs, gentle transition to diffuser；
(3.2) design of diffuser；Using etc. angle of flare rule determine the expection type face of diffuser under design point, the angle of flare No more than 10 °；
(3.3) diffuser material is determined；Spring steel is chosen as diffuser material
(4) rigid deformation mechanism is designed：
(4.1) two rocking bars are divided into preceding rocking bar, rear rocking bar, the pin joint of preceding rocking bar and venturi section venturi section most before Edge, rear rocking bar and the pin joint of venturi section are set in：Venturi section and diffuser tie point and preceding rocking bar and venturi section it is be hinged Between point, and close to venturi section and diffuser tie point；
(4.2) design procedure (1.1), lip cover oral area height h is determined in (2.1) respectively0And the minimum constructive height of venturi hmin, can be drawn by geometrical relationship, preceding rocking bar, the minimum length of rear rocking bar are (h0-hmin)；By the length l of preceding rocking bar1Choosing It is taken as 1.5 times of minimum length；
(4.3) the length l of rocking bar afterwards2It is chosen for 1.6 times of minimum length；
(4.4) pin joint of rocking bar and venturi section is the center of circle in the past, l1Work is justified, the circle and the water for crossing one stage of compression face starting point The articulated position of rocking bar and horizontal operating bar before horizontal line intersection point is set to；Later rocking bar and the pin joint of venturi section are the center of circle, l2Make Circle, the circle are set to the articulated position of rear rocking bar and horizontal operating bar with crossing the horizontal line intersection point of one stage of compression face starting point；
(5) boundary layer deflation section is arranged：According to oblique shock wave formula and corresponding geometrical relationship, different operating horse is determined It is conspicuous it is several under wave system structure, and then excursion of the lip cover shock incidence point in adjustable compression face is determined, according to this scope can Adjust and deflation seam is opened up on compressing surface so that lip cover shock wave is always beaten in the vent region of boundary layer, likewise, according to reflected shock wave Incoming position under different working condition, deflation seam is opened up in lip cover.
Beneficial effect：The air intake duct designed according to the design method, by assigning drive end simple lateral displacement, just The synchronous adjustment of compressing surface angle and venturi height can be realized by linkage, so as to which the working condition according to air intake duct is real When continuously adjust the contract ratio of air intake duct, ensure that air intake duct can steady operation in the range of whole flight Mach number.Meanwhile Also configured by careful wide fast domain wave system in design process, carried out using the expansion fan of compressing surface shoulder arcuate surface at wave absorption Reason.Seam of uniformly deflating is arranged on compressing surface in the incoming position of compressing surface according to lip cover shock wave under different operating modes, absorbs border Layer.Above-mentioned design ensure that air intake duct is not in serious Shock/Boundary-Layer interference in the range of All Speed Range, improve into The resistance to back-pressure ability of air flue.
Further, the present invention gives the method for determining intake valve deposit rule：To design in design procedure (4) The method that linkage uses motion simulation, the corresponding relation of horizontal operating bar lateral displacement distance and venturi section height is determined, In conjunction with the work Mach number and the functional relation of required venturi height obtained in design procedure (2.4), so that it is determined that for each Work Mach number, the lateral displacement size that horizontal operating bar should be realized, that is, draws the Rule adjusting of air intake duct.
Brief description of the drawings
Fig. 1 is the design pair of the design method for the continuously adjustabe air intake duct that a kind of rigid/flexible provided by the invention combines As schematic diagram；
Fig. 2 is the design object schematic diagram in Fig. 1, different from the label in Fig. 1；
Fig. 3 is the Rule adjusting for the continuously adjustabe air intake duct that a kind of rigid/flexible designed using the present invention combines Schematic diagram；
Fig. 4 is the design flow diagram of the design method for the continuously adjustabe air intake duct that a kind of rigid/flexible of the present invention combines.
Specific embodiment
The invention discloses a kind of rigid/flexible combine continuously adjustabe air intake duct design method, its towards design Object is the continuously adjustabe air intake duct that a kind of rigid/flexible combines, referring specifically to shown in Fig. 1 and Fig. 2.The air intake duct main body bag Include：Air intake duct lip cover 1, the precursor compressing surface positioned at the front lower place of air intake duct lip cover 4, connection precursor compression surface rear end simultaneously extend back Adjustable compression face 4, the rear end of connection adjustable compression face 4 and the venturi section 5 to extend back, the rear end of connection venturi section 5 and prolong backward The diffuser 6 stretched, positioned at venturi section 5 back to the side of lip cover 1 two rocking bars 7,8, carrying rocking bar and the water extended from front to back The movable drive device (such as motor) of flat operating bar 9, the horizontal operating bar 9 of driving；Precursor compressing surface is included positioned at front portion One stage of compression face 2 and the two-stage compression face 3 to be extended back from one stage of compression face；The front end in the adjustable compression face 4 and two level pressure The rear end in contracting face 3 is hinged；The rear end of the front end and adjustable compression face 4 of the venturi section 5 is hinged；Venturi section 5 and air intake duct lip cover Between formed venturi 12；The diffuser 6 is flexible material；The front end of rocking bar is articulated with venturi section 5 back to the side of lip cover, shakes The rear end of bar is articulated with horizontal operating bar 9；When horizontal operating bar moves forward, venturi section is withstood to lip cover in the front end of rocking bar It is mobile the distance between venturi section and lip cover is diminished；When horizontal operating bar is moved rearwards, the front end of rocking bar retracts venturi section The distance between venturi section and lip cover is set to become big.The horizontal horizontal diffuser of operating bar 9 of operating bar 9.
Refer to shown in Fig. 4, and combine Fig. 1 and Fig. 2, design procedure of the invention is as follows：
(1) wave system configures：
(1.1) the highest work Mach number of air intake duct is set to design point, mouth principle is pasted according to shock wave under this Mach number Carry out wave system configuration；According to the traffic demand and working depth of air intake duct cruising condition, the stream of design point is determined by flow formula Amount capture area
In formula, m be design point demand gas flow, ρ0、u0The density and speed of respectively free incoming；And then according to Air intake duct length-width ratio determines the oral area height h of lip cover 10；
(1.2) according to air intake duct forebody length and the requirement of total compression amount, one-level Angle of Shock Waves β is determined1；With one stage of compression face 2 For leading edge as origin, it is β to make with horizontal line angle1Ray, the ray and height h0Horizontal intersection point is the oral area of lip cover 1 Position；There is following relational expression by oblique shock wave wave angle β and flow-deviation angle δ：
In formula, M is oblique shock wave wavefront Mach number；So as to according to the wave angle β of one-level oblique shock wave 101Determine one stage of compression face 2 Flow-deviation angle δ1；
(1.3) in order to obtain the total pressure recovery coefficient of maximum, according to the equal principle of the normal direction Mach number before each oblique shock wave, I.e.
M0 sinβ1=M1 sinβ2
Determine the wave angle β of two level oblique shock wave 112；It is (β to cross lip to make one with horizontal line angle2+δ1) ray, with one-level pressure The intersection point in contracting face 2 is the starting point of two-stage compression face 3；Two-stage compression is determined according to the relational expression of oblique shock wave wave angle and flow-deviation angle The flow-deviation angle δ in face 32, then two-stage compression face 3 and horizontal line angle theta2=δ1+δ2；
(1.4) adjustable compression face 4 is considered as into fixed compressing surface in design point to be designed, determines pressure-adjustable under cruising condition Contracting face 4 adjust to during correspondence position with horizontal line angle theta3Size；It is specific as follows：First still according to the method before each oblique shock wave To Mach number equal principle, the wave angle β of three-level oblique shock wave 13 is determined3；It is (β to cross lip to make one with horizontal line angle3+θ2) penetrate Line, the intersection point with two-stage compression face 3 are the starting point in adjustable compression face 4；Similarly, according to oblique shock wave wave angle and flow-deviation angle Relational expression determines the flow-deviation angle δ in adjustable compression face 43, then adjustable compression face 4 and horizontal line angle theta under design point3=θ2+ δ3；
(1.5) quasi spline of lip cover 1；Due to the oral area height h of lip cover 10It has been determined that the inner mold face of lip cover 1 was designed as lip One horizontal line of mouth；The outer surface of lip cover 1 and horizontal line angle are according to the restriction of Inlet drag and lip shock not lift-off, really It is scheduled on 8 ° -10 °；
(2) determination in the height of venturi 12 and the type face of compressing surface 4：
(2.1) minimum venturi height h is determinedmin；Air intake duct cruising condition corresponds to minimum venturi height, and design causes this When venturi 12 gasflow mach number be 1.3, therefore minimum venturi is highly：
In formula, h3Vertical distance for the oral area of lip cover under design point 1 to adjustable compression face 4, due to being had determined in step 1 The position of lip cover 1 and the angle of third level adjustable compression face 4, therefore h3It is known；
q(λ3) it is flow function of the design point downstream after three-level oblique shock wave 13；
q(λt) it is flow function corresponding to the Mach number 1.3 of venturi 12；
σaFor air-flow 0.95 is taken after the ripple of three-level oblique shock wave 13 to the total pressure recovery coefficient of venturi 12, approximation；
(2.2) the type face of adjustable compression face 4 is designed；In design point according to adjustable compression face 4 and horizontal line angle and minimum Venturi height hminIt is determined that；Rounding design is carried out to compressing surface shoulder molded line 14, lip cover shock wave is fallen in shoulder rounding area 15, with Weaken the intensity of reflected shock wave 17 using shoulder expansion fan 16；Rounding design makes compressing surface 4 gradually transit to height distance lip cover 1 Inner mold face hminPosition, meet the needs of design point is to minimum venturi height；
(2.3) maximum venturi height h is determinedmax；Maximum stream flow according to needed for engine when taking off, venturi 12 highly will The air-flow of air intake duct can be ensured into normal through without being jammed at venturi 12, then being calculated by flow formula can ：
In formula, maximum stream flow coefficient when ψ is takeoff condition；
h∞For the height of free incoming flow tube；
q(λ0) it is free inlet flow rate function；
σbFor air-flow from inlet mouth 18 to venturi 12 at total pressure recovery coefficient；
q(λt) it is flow function corresponding to the gasflow mach number of venturi 12；
(2.4) adjusting position of venturi 12 in accelerator is determined：Free stream Mach number M0During less than 1, the position of venturi 12 is not Adjust；As free stream Mach number M0During more than 1, because a two-stage compression face 2, the geometry profile of two-stage compression face 3 are fixed, therefore root The wave angle β of one-level oblique shock wave 10 can be extrapolated according to one dimensional flow oblique shock wave relational expression1And gasflow mach number M after ripple1, two level tiltedly swashs The wave angle β of ripple 112And gasflow mach number M after ripple2.It can be obtained by flow formula：
In formula, h2For the vertical distance of the oral area of lip cover 1 that is determined by geometrical relationship to second level compressing surface 3；
q(λ2) be two level oblique shock wave ripple after air-flow flow function；
σcRule of thumb estimated to the total pressure recovery coefficient of venturi 12, value after two level oblique shock wave ripple for air-flow；
q(λt) it is flow function corresponding to the gasflow mach number of venturi 12；
(3) venturi section 5 and diffuser 6 are designed：
(3.1) design of venturi section 5；The length of venturi section 5 is chosen for minimum venturi height hmin3-4 times；After venturi section 5 Portion carries out rounding design, gentle transition to diffuser 6；
(3.2) design of diffuser 6；Using etc. angle of flare rule determine the expection type face of diffuser 6 under design point, expansion Angle is no more than 10 °；Herein, the outlet of diffuser 6 needs to dock engine chamber, therefore diffuser outlet size is Combustion chamber inlet size, and combustion chamber intake condition is given by other departments, and the parameter use directly can be used as into air intake duct Design requirement, particular design need not be carried out herein；
(3.3) material of diffuser 6 is determined；Spring steel is chosen as the material of diffuser 6；
(4) rigid deformation mechanism is designed：
(4.1) two rocking bars are divided into preceding rocking bar 7, rear rocking bar 8, the pin joint of preceding rocking bar 7 and venturi section 5 is in venturi section 5 Most leading edge, rear rocking bar 8 and the pin joint of venturi section 5 be set in：Venturi section 5 and the tie point of diffuser 6 and preceding rocking bar 7 and larynx Between the pin joint of road section 5, and close to venturi section 5 and the tie point of diffuser 6；Preferably, in present embodiment, by preceding rocking bar 7 are designed as Length discrepancy with rear rocking bar 8, and so as to realize cruising condition venturi section level, what takeoff condition venturi section was slightly expanded sets Count purpose.
(4.2) design procedure (1.1), the oral area height h of lip cover 1 is determined in (2.1) respectively0And the minimum constructive height of venturi hmin, can be drawn by geometrical relationship, preceding rocking bar 7, the minimum length of rear rocking bar 8 are (h0-hmin)；By the length l of preceding rocking bar 71 It is chosen for 1.5 times of minimum length；
(4.3) the length l of rocking bar 8 afterwards2It is chosen for 1.6 times of minimum length；
(4.4) pin joint of rocking bar and venturi section is the center of circle in the past, l1Work is justified, and the circle is with crossing the starting point of one stage of compression face 2 The articulated position of rocking bar 7 and horizontal operating bar 9 before horizontal line intersection point is set to；Later rocking bar and the pin joint of venturi section are the center of circle, l2Work is justified, and the circle is set to the articulated position of rear rocking bar 8 and horizontal operating bar 9 with crossing the horizontal line intersection point of the starting point of one stage of compression face 2；
(5) boundary layer deflation section is arranged：According to oblique shock wave formula and corresponding geometrical relationship, different operating horse is determined It is conspicuous it is several under wave system structure, and then determine that the incidence point of lip cover shock wave 19 in the excursion in adjustable compression face 4, exists according to this scope Deflation seam 20 is opened up on adjustable compression face 4 so that lip cover shock wave 19 is always beaten in the vent region of boundary layer, the control of deflation flow Within the 3% of total flow, lip cover shock wave 19 and interfering for boundary layer are controlled by so that lip cover shock wave 19 is always beaten In the vent region of boundary layer, multi-region independence deflation control measure are used.Likewise, according to reflected shock wave 17 in different operating shape Incoming position under state, deflation seam 21 is opened up in lip cover 1.Multi-region independence deflation control measure in present embodiment refer to Record in Chinese patent " a kind of aircraft Supersonic Inlets with variable blow-off system of ZL.2014101589066 ".
Referring to Fig. 3, further, the present invention gives the method for determining intake valve deposit rule：To design procedure (4) method that the linkage of design uses motion simulation in, horizontal operating bar lateral displacement distance and venturi section height are determined Corresponding relation, in conjunction with the functional relation of work Mach number and the required venturi height obtained in design procedure (2.4), so as to It is determined that be directed to each work Mach number, the lateral displacement size that horizontal operating bar should be realized, that is, the Rule adjusting of air intake duct is drawn.
It should be pointed out that the method and approach of the present invention specific implementation technical scheme are a lot, described above is only the present invention Preferred embodiment.For those skilled in the art, under the premise without departing from the principles of the invention, also Some improvements and modifications can be made, these improvements and modifications also should be regarded as protection scope of the present invention.It is unknown in the present embodiment The available prior art of true each part is realized.

Claims (5)

  1. A kind of 1. design method for the continuously adjustabe air intake duct that rigid/flexible combines, it is characterised in that the design of the design method Object is a kind of variable geometry inlet, including air intake duct lip cover (1), the precursor compressing surface positioned at air intake duct lip cover (4) front lower place, even Adjustable compression face (4), connection adjustable compression face (4) rear end and the larynx to extend back for connecing precursor compression surface rear end and extending back Road section (5), connection venturi section (5) rear end and the diffuser (6) to extend back, positioned at venturi section (5) back to lip cover (1) side Two rocking bars (7,8), carrying rocking bar and the horizontal operating bar (9) extended from front to back, the horizontal operating bar (9) of driving are movable Drive device；Precursor compressing surface is included positioned at anterior one stage of compression face (2) and the two level to be extended back from one stage of compression face Compressing surface (3)；The rear end of the front end and two-stage compression face (3) of the adjustable compression face (4) is hinged；Before the venturi section (5) The rear end with adjustable compression face (4) is held to be hinged；Venturi (12) is formed between venturi section (5) and air intake duct lip cover；The diffuser (6) it is flexible material；The front end of rocking bar is articulated with venturi section (5) and is articulated with horizontal work back to the side of lip cover, the rear end of rocking bar In lever (9)；When horizontal operating bar moves forward, the front end of rocking bar withstands venturi section makes venturi section and lip cover to lip cover movement The distance between diminish；When horizontal operating bar is moved rearwards, the front end of rocking bar, which retracts venturi section, to be made between venturi section and lip cover Distance become big；
    The design method design procedure is as follows：
    (1) wave system configures：
    (1.1) the highest work Mach number of air intake duct is set to design point, pasting mouth principle according to shock wave under this Mach number is carried out Wave system configures；According to the traffic demand and working depth of air intake duct cruising condition, the flow for determining design point by flow formula is caught Obtain area
    <mrow> <msub> <mi>A</mi> <mn>0</mn> </msub> <mo>=</mo> <mfrac> <mi>m</mi> <mrow> <msub> <mi>&amp;rho;</mi> <mn>0</mn> </msub> <msub> <mi>u</mi> <mn>0</mn> </msub> </mrow> </mfrac> </mrow>
    In formula, m be design point demand gas flow, ρ0、u0The density and speed of respectively free incoming；And then according to air inlet Road length-width ratio determines lip cover (1) oral area height h0；
    (1.2) according to air intake duct forebody length and the requirement of total compression amount, one-level Angle of Shock Waves β is determined1；With one stage of compression face (2) leading edge As origin, it is β to make with horizontal line angle1Ray, the ray and height h0Horizontal intersection point is lip cover (1) oral area position Put；There is following relational expression by oblique shock wave wave angle β and flow-deviation angle δ：
    <mrow> <mfrac> <mn>1</mn> <mrow> <mi>t</mi> <mi>g</mi> <mi>&amp;delta;</mi> </mrow> </mfrac> <mo>=</mo> <mrow> <mo>(</mo> <mfrac> <mrow> <mi>k</mi> <mo>+</mo> <mn>1</mn> </mrow> <mn>2</mn> </mfrac> <mfrac> <msup> <mi>M</mi> <mn>2</mn> </msup> <mrow> <msup> <mi>M</mi> <mn>2</mn> </msup> <msubsup> <mi>sin</mi> <mi>&amp;beta;</mi> <mn>2</mn> </msubsup> <mo>-</mo> <mn>1</mn> </mrow> </mfrac> <mo>-</mo> <mn>1</mn> <mo>)</mo> </mrow> <mi>t</mi> <mi>g</mi> <mi>&amp;beta;</mi> </mrow>
    In formula, M is oblique shock wave wavefront Mach number；So as to according to one-level oblique shock wave (10) wave angle β1Determine the gas of one stage of compression face (2) Flow deflection angle δ1；
    (1.3) in order to obtain the total pressure recovery coefficient of maximum, according to the equal principle of the normal direction Mach number before each oblique shock wave, i.e.,
    M0sinβ1=M1sinβ2
    Determine two level oblique shock wave (11) wave angle β2；It is (β to cross lip to make one with horizontal line angle2+δ1) ray, with one stage of compression The intersection point in face (2) is two-stage compression face (3) starting point；Two level pressure is determined according to the relational expression of oblique shock wave wave angle and flow-deviation angle The flow-deviation angle δ in contracting face (3)2, then two-stage compression face (3) and horizontal line angle theta2=δ1+δ2；
    (1.4) adjustable compression face (4) are considered as into fixed compressing surface in design point to be designed, determine adjustable compression under cruising condition Face (4) regulation to during correspondence position with horizontal line angle theta3Size；It is specific as follows：First still according to the method before each oblique shock wave To Mach number equal principle, the wave angle β of three-level oblique shock wave (13) is determined3；It is (β to cross lip to make one with horizontal line angle3+θ2) Ray, the intersection point with two-stage compression face (3) are the starting point of adjustable compression face (4)；Similarly, it is inclined according to oblique shock wave wave angle and air-flow The relational expression of corner determines the flow-deviation angle δ in adjustable compression face (4)3, then adjustable compression face (4) and horizontal wire clamp under design point Angle θ3=θ2+δ3；
    (1.5) lip cover (1) quasi spline；Due to lip cover (1) oral area height h0It has been determined that lip cover (1) inner mold face was designed as lip One horizontal line of mouth；Lip cover (1) outer surface and horizontal line angle according to the restriction of Inlet drag and lip shock not lift-off, It is determined that at 8 ° -10 °；
    (2) determination in venturi (12) height and compressing surface (4) type face：
    (2.1) minimum venturi height h is determinedmin；Air intake duct cruising condition corresponds to minimum venturi height, and design causes now larynx The gasflow mach number in road (12) is 1.3, therefore minimum venturi is highly：
    <mrow> <msub> <mi>h</mi> <mrow> <mi>m</mi> <mi>i</mi> <mi>n</mi> </mrow> </msub> <mo>=</mo> <mfrac> <mrow> <msub> <mi>h</mi> <mn>3</mn> </msub> <mo>&amp;CenterDot;</mo> <mi>q</mi> <mrow> <mo>(</mo> <msub> <mi>&amp;lambda;</mi> <mn>3</mn> </msub> <mo>)</mo> </mrow> </mrow> <mrow> <msub> <mi>&amp;sigma;</mi> <mi>a</mi> </msub> <mo>&amp;CenterDot;</mo> <mi>q</mi> <mrow> <mo>(</mo> <msub> <mi>&amp;lambda;</mi> <mi>t</mi> </msub> <mo>)</mo> </mrow> </mrow> </mfrac> </mrow>
    In formula, h3For the vertical distance of (1) oral area of lip cover under design point to adjustable compression face (4), due to true in step (1) Lip cover (1) position and third level adjustable compression face (4) angle, therefore h are determined3It is known；
    q(λ3) it is flow function of the design point downstream after three-level oblique shock wave (13)；
    q(λt) it is flow function corresponding to venturi (12) Mach number 1.3；
    σaFor air-flow 0.95 is taken after three-level oblique shock wave (13) ripple to the total pressure recovery coefficient of venturi (12), approximation；
    (2.2) adjustable compression face (4) type face is designed；In design point according to adjustable compression face (4) and horizontal line angle and minimum Venturi height hminIt is determined that；Rounding design is carried out to compressing surface shoulder molded line (14), lip cover shock wave is fallen in shoulder rounding area (15) intensity of (16) weakening reflected shock wave (17), is fanned to utilize shoulder to expand；Rounding design makes compressing surface (4) gradually transit to Height distance lip cover (1) inner mold face hminPosition, meet the needs of design point is to minimum venturi height；
    (2.3) maximum venturi height h is determinedmax；Maximum stream flow according to needed for engine when taking off, venturi (12) highly want energy The air-flow of enough air intake ducts that ensures, then can by flow formula calculating normal through without being jammed at venturi (12) place ：
    <mrow> <msub> <mi>h</mi> <mrow> <mi>m</mi> <mi>a</mi> <mi>x</mi> </mrow> </msub> <mo>=</mo> <mfrac> <mrow> <msub> <mi>&amp;psi;h</mi> <mi>&amp;infin;</mi> </msub> <mi>q</mi> <mrow> <mo>(</mo> <msub> <mi>&amp;lambda;</mi> <mn>0</mn> </msub> <mo>)</mo> </mrow> </mrow> <mrow> <msub> <mi>&amp;sigma;</mi> <mi>b</mi> </msub> <mi>q</mi> <mrow> <mo>(</mo> <msub> <mi>&amp;lambda;</mi> <mi>t</mi> </msub> <mo>)</mo> </mrow> </mrow> </mfrac> </mrow>
    In formula, maximum stream flow coefficient when ψ is takeoff condition；
    h∞For the height of free incoming flow tube；
    q(λ0) it is free inlet flow rate function；
    σbFor air-flow from inlet mouth (18) to venturi (12) from total pressure recovery coefficient；
    q(λt) it is flow function corresponding to venturi (12) gasflow mach number；
    (2.4) venturi (12) adjusting position in accelerator is determined：Free stream Mach number M0During less than 1, venturi (12) position is not done Regulation；As free stream Mach number M0During more than 1, because a two-stage compression face (2), two-stage compression face (3) geometry profile are fixed, therefore One-level oblique shock wave (10) wave angle β can be extrapolated according to one dimensional flow oblique shock wave relational expression1And gasflow mach number M after ripple1, two level Oblique shock wave (11) wave angle β2And gasflow mach number M after ripple2；It can be obtained by flow formula：
    <mrow> <msub> <mi>h</mi> <mi>t</mi> </msub> <mo>=</mo> <mfrac> <mrow> <msub> <mi>h</mi> <mn>2</mn> </msub> <mo>.</mo> <mi>q</mi> <mrow> <mo>(</mo> <msub> <mi>&amp;lambda;</mi> <mn>2</mn> </msub> <mo>)</mo> </mrow> </mrow> <mrow> <msub> <mi>&amp;sigma;</mi> <mi>c</mi> </msub> <mo>.</mo> <mi>q</mi> <mrow> <mo>(</mo> <msub> <mi>&amp;lambda;</mi> <mi>t</mi> </msub> <mo>)</mo> </mrow> </mrow> </mfrac> </mrow>
    In formula, h2For the vertical distance of lip cover (1) oral area that is determined by geometrical relationship to second level compressing surface (3)；
    q(λ2The flow function of)-be air-flow after two level oblique shock wave ripple；
    σc- rule of thumb estimated to the total pressure recovery coefficient of venturi (12), value after two level oblique shock wave ripple for air-flow；
    q(λt) it is flow function corresponding to venturi (12) gasflow mach number；
    (3) venturi section (5) and diffuser (6) are designed：
    (3.1) design of venturi section (5)；Venturi section (5) length is chosen for minimum venturi height hmin3-4 times；Venturi section (5) Rear portion carries out rounding design, gentle transition to diffuser (6)；
    (3.2) design of diffuser (6)；Using etc. angle of flare rule determine the expection type face of diffuser under design point (6), expansion Angle is no more than 10 °；
    (3.3) diffuser (6) material is determined；
    (4) rigid deformation mechanism is designed：
    (4.1) two rocking bars are divided into preceding rocking bar (7), rear rocking bar (8), the pin joint of preceding rocking bar (7) and venturi section (5) is in venturi Most leading edge, rear rocking bar (8) and the pin joint of venturi section (5) of section (5) are set in：Venturi section (5) and diffuser (6) tie point with Preceding rocking bar (7) and venturi section (5) pin joint between, and close to venturi section (5) and diffuser (6) tie point；
    (4.2) design procedure (1.1), lip cover (1) oral area height h is determined in (2.1) respectively0And the minimum constructive height of venturi hmin, can be drawn by geometrical relationship, preceding rocking bar (7), the minimum length of rear rocking bar (8) are (h0-hmin)；By preceding rocking bar (7) Length l1It is chosen for 1.5 times of minimum length；
    (4.3) the length l of rocking bar (8) afterwards2It is chosen for 1.6 times of minimum length；
    (4.4) pin joint of rocking bar and venturi section is the center of circle in the past, l1Work is justified, the circle and the level for crossing one stage of compression face (2) starting point Line intersection point is set to the articulated position of preceding rocking bar (7) and horizontal operating bar (9)；Later rocking bar and the pin joint of venturi section are the center of circle, l2Work is justified, and the circle is set to the hinge of rear rocking bar (8) and horizontal operating bar (9) with crossing the horizontal line intersection point of one stage of compression face (2) starting point Connect position；
    (5) boundary layer deflation section is arranged：According to oblique shock wave formula and corresponding geometrical relationship, different operating Mach number is determined Under wave system structure, and then determine that lip cover shock wave (19) incidence point in the excursion of adjustable compression face (4), exists according to this scope Deflation seam (20) is opened up on adjustable compression face (4) so that lip cover shock wave (19) is always beaten in the vent region of boundary layer, equally , according to incoming position of the reflected shock wave (17) under different working condition, deflation seam (21) is opened up in lip cover (1).
  2. 2. the design method for the continuously adjustabe air intake duct that rigid/flexible according to claim 2 combines, it is characterised in that： Preceding rocking bar (7) and rear rocking bar (8) are designed as Length discrepancy, so as to realize cruising condition venturi section level, takeoff condition venturi section The purpose of design slightly expanded.
  3. 3. the design method for the continuously adjustabe air intake duct that rigid/flexible according to claim 2 combines, it is characterised in that： The method for using motion simulation to the linkage of design in design procedure (4), determines horizontal operating bar (9) lateral displacement distance With the corresponding relation of venturi section (5) height, in conjunction with the work Mach number that is obtained in design procedure (2.4) and required venturi (5) The functional relation of height, so that it is determined that each work Mach number is directed to, the lateral displacement size that horizontal operating bar (9) should be realized, i.e., Draw the Rule adjusting of air intake duct.
  4. 4. the design method for the continuously adjustabe air intake duct that rigid/flexible according to claim 2 combines, it is characterised in that： In step (3.3), spring steel is chosen as diffuser (6) material.
  5. 5. the design method for the continuously adjustabe air intake duct that rigid/flexible according to claim 2 combines, it is characterised in that： The drive device for driving horizontal operating bar (9) movable elects motor as.
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Publication number Priority date Publication date Assignee Title
CN108412619A (en) * 2018-05-09 2018-08-17 南京航空航天大学 A kind of multiple degrees of freedom single argument control combination power variable geometry inlet
CN108412619B (en) * 2018-05-09 2024-03-29 南京航空航天大学 Multi-degree-of-freedom univariate control combined power adjustable air inlet passage
CN112651187A (en) * 2020-11-20 2021-04-13 南京航空航天大学 Binary supersonic speed adjustable air inlet restart boundary prediction method
CN112651187B (en) * 2020-11-20 2023-04-28 南京航空航天大学 Binary supersonic adjustable air inlet channel restarting boundary prediction method
CN113700561A (en) * 2021-09-24 2021-11-26 西安航天动力研究所 Supporting plate lifting adjustable type lower jaw type supersonic air inlet channel
CN115030817A (en) * 2022-04-14 2022-09-09 中国航天空气动力技术研究院 Wide-speed-range adjustable air inlet channel with controllable wave system structure and engine
CN115030817B (en) * 2022-04-14 2024-06-11 中国航天空气动力技术研究院 Wide-speed-range adjustable air inlet channel with controllable wave system structure and engine

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