CN108304598B - A kind of high-speed aircraft is forced to turn to twist device and design method - Google Patents
A kind of high-speed aircraft is forced to turn to twist device and design method Download PDFInfo
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Abstract
The present invention proposes that a kind of high-speed aircraft is forced to turn to twist device and design method, by determine turn to twist cell type, determine force to turn to twist device initial placement position, determine force to turn to twist device turn to twist unit size and etc. realize that high-speed aircraft forces the design for turning to twist device.The present invention fully considers influence of the exhibition to flow gradient to turning to twist, and the high-speed aircraft for realizing curved surface precursor forces the design for turning to twist device.
Description
Technical field
It forces to turn to twist device and design method the present invention relates to a kind of high-speed aircraft, belongs to high-speed aircraft aerodynamic analysis
Technical field.
Background technique
Currently, air suction type high-speed aircraft (Mach number is more than 5 aircraft) is surpassed using aloof punching engine as power
Can burning ramjet steady operation decision flight test success or failure.In order to guarantee scramjet engine steady operation, commonly use
Means be aircraft precursor lower surface install additional force turn twist device.It forces to turn to twist device to be a row by a series of base units
The device of composition.The shape of base unit includes triangular form, cylindrical type and brilliant as shown in Figure 1, sweepback ramp type etc..
Device design method is twisted in existing pressure turn two classes, and one kind is the low-speed operations device for taper, flat-type；Separately
One kind is the high-speed aircraft for precursor for plane.Pressure for low-speed operations device turns to twist device design method, generally adopts
It is designed, is lacked to the effective understanding for turning to twist device mechanism is forced, relative to low-speed operations device, high-speed flight with engineering empirical method
Device turns to twist mechanism there are great differences, including the factors such as Mach number, the angle of attack, incoming flow turbulivity, directlys adopt existing low speed
Design method can bring very big error, even result in flight test failure.It is the high-speed aircraft of plane for precursor, by examining
Consider under high-speed condition turn twist mechanism, establish it is related force to turn to twist device design method, this method only only accounts for plate stream
Change to boundary layer, but be only that planar profile is effective to precursor, is the high-speed aircraft of curved surface for precursor, directlys adopt
Precursor, which twists device design method for the pressure turn of planar profile, can bring very big error.
In short, being the high-speed aircraft of curved profile for precursor, force to turn to twist device design method meeting using existing
Relatively large deviation is brought, the research for carrying out related fields is needed.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, it is strong to provide a kind of high-speed aircraft suitable for curved surface precursor
System turns to twist device and design method.
Technical solution of the invention: a kind of high-speed aircraft is forced to turn to twist device, turns to twist unit by a row and forms, institute
The height for turning to twist unit stated determines that wherein k is to turn to twist cell height, and δ is total enthalpy by following height design criteria n=k/ δ
Boundary layer thickness, n are height design criteria coefficient；The side length w for turning to twist unit passes through formula w=Δwδ is determining, wherein
ΔwFor side length proportionality coefficient.
The height design criteria coefficient n determination basis is, when Mach 2 ship 5~7, n ∈ [0.5,0.8], and Mach number
When being 7~10, n ∈ [0.8,1].
The side length ratio coefficient deltawValue is 0.5~1.5.
The exhibition that device is twisted in the pressure turn uses following criterion to width: pressure turns to twist device and open up to width to be greater than pressure
Turn to twist the streamline width that device installed position enters air intake duct, maximum, which is no more than aircraft, is forcing to turn to twist device installation site
The structure width at place.
The spacing for turning to twist unit is the smaller the better according to actual processing level.
A design method for device is twisted in a kind of high-speed aircraft pressure turn, is realized by following steps:
The first step, determine force turn twist device turn twist cell type；
This step is techniques well known, and those skilled in the art comprehensively consider heat according to flight test actual demand
Protection turns to twist the factors such as effect, structure design, twists in cell type and chooses from existing turn.
If commonly used brilliant unit and sweepback ramp type unit respectively have superiority and inferiority, brilliant unit has shape letter
It is single, easily occur to turn the advantages of twisting；But brilliant flows to vortex strength due to caused by, will lead to and introduces additional thermal protection.Then
It plunders ramp type unit and has and be also easy to produce and flow to whirlpool, the small advantage of additional increased thermal protection, but unit complex contour.
Second step determines and forces to turn to twist device in the initial placement position that aircraft surface flows to,
A2.1, it forces to turn to twist device placement location while meeting following two condition:
(1) pressure turn is twisted device and is placed on before air intake duct flowing disengaged position；
According to the engine operation envelope curve of aircraft, the operating condition (limiting condition) for being least easy to turn to twist is chosen, using numerical value
Analogy method (such as CFD can be used commercial engineering calculation software and be calculated, similarly hereinafter) obtains air intake duct and flows disengaged position
(flow separation refers to that air-flow streamline in flow process bends, and forms eddy structure, this is techniques well known art
Language).
(2) force to turn to twist device be placed on flow to whirlpool development distance (flow over pressure turn to twist it is complete rapid to being formed after device
The distance at position is flowed, this is techniques well known term) before；
If forcing to turn to twist device and have determined that installation site, according to method for numerical simulation be can determine flow to the development in whirlpool away from
From, in this step, the initial value for the development distance that one flows to whirlpool is first selected in a certain range, generally in high-speed condition,
Initial value takes 300~600mm, i.e., from inlet lip along the length of inverse airflow direction.
A2.2, the condition for meeting step A2.1 determine that pressure turn is twisted device and put in conjunction with the integral structure layout of aircraft
Seated position；
Third step determines and forces to turn to twist turning to twist cell parameters original dimension and forcing to turn to twist the Zhan Xiangkuan of device for device
Degree turns to twist cell parameters to include side length, spacing and height,
Unit side length is twisted for cylindrical type turn and directs at diameter of a circle.Turn to twist cell parameters (side length, spacing and height) definition
For techniques well known.
A3.1, determination turn to twist unit elemental height size and side length,
According to following height design criteria n=k/ δ, elemental height size is determined,
When Mach 2 ship 5~7, n ∈ [0.5,0.8], when Mach 2 ship 7~10, n ∈ [0.8,1], wherein k is to turn to twist list
First height, δ are total enthalpy boundary layer thickness, and n is height design criteria coefficient；
Turn to twist a length of Δ of element sideswδ, ΔwFor side length proportionality coefficient, effect highly is twisted to turn turning to twist in cell parameters
Maximum is influenced, other parameters are less to the influence for turning to twist effect, ΔwValue preferably 0.5~1.5 changes in aforementioned proportion range
When, to turning to twist the influence very little of effect, can be neglected in engineering.
Turn to twist cell parameters (side length, spacing, height) and local (forcing to turn to twist device installed position) total enthalpy boundary layer
Thickness δ is (referring to document Boundary Layer Control Hypersonic Airbreathing Vehicles, Scott
A.Berry, Robert J.Nowak) it is related.When Preliminary design, one is chosen from height design criteria k/ δ given herein above
Initial value.
A3.2, determination turn to twist cell spacing；
Force to turn to twist device and turn to twist that cell spacing is the smaller the better, but the actual size of cell spacing need to consider it is practical plus
Work is horizontal.
A3.3, it determines and forces to turn to twist device exhibition Xiang Kuandu,
Force turn twist device open up to width refer to force turn twist device extend to width, that is, turn to twist unit side length and spacing
Summation.
Pressure turn is twisted device and opened up to width using following criterion: pressure turns to twist device and open up to turn to twist device greater than pressure to width
Installed position enters the streamline width of air intake duct, and maximum, which is no more than aircraft, is forcing the structure for turning to twist device installed position
Width；
Method for numerical simulation acquisition can be used in streamline width into air intake duct, and method for numerical simulation is skill known in this field
Art.
A3.4, turn to twist cell parameters original dimension according to what step A3.1~3.3 was determined, foundation is forced to turn to twist device mould
Type；
That forces to turn to twist mounted cast is established as techniques well known, can pass through business software such as UG modeling software etc.
It realizes.
A3.5, determined by method for numerical simulation step A3.4 establish pressure turn twist mounted cast turn twist effect, protect
It is turbulent flow that card, which meets and enters the incoming flow fluidised form of air intake duct, if satisfied, then completing to force to turn to twist device design, to strong if being unsatisfactory for
System turn is twisted device and is modified, until the incoming flow fluidised form that satisfaction enters air intake duct is turbulent flow.
The amendment, is realized by following steps:
A4.1, judge force turn twist device turn twist unit height whether have reached height design criteria k/ δ determine most
Big value, if not reaching, carries out step A4.2, if reaching, is transferred to step A4.3；
A4.2, increase and force to turn to twist the height that device turn twists unit, height increases true no more than height design criteria k/ δ
Fixed maximum value is established and forces to turn to twist mounted cast, verifying force to turn to twist mounted cast turn twist effect, enter air inlet if meeting
The incoming flow fluidised form in road is turbulent flow, then completes to force to turn to twist device design, step A4.1 is carried out if being unsatisfactory for；
The development distance that A4.3, increase flow to whirlpool, which changes, to be forced to turn to twist device placement location, repeats third step, the 4th step,
Until the incoming flow fluidised form that satisfaction enters air intake duct is turbulent flow.
The present invention compared with prior art the utility model has the advantages that
(1) apparatus of the present invention fully consider influence of the exhibition to flow gradient to turning to twist, and the high speed for realizing curved surface precursor flies
Row device forces the design for turning to twist device；
(2) present invention is by specifically turning to twist the design criteria of unit, and it is more accurate to make to force to turn to twist device design, significantly
Improve the safety of flight test；
(3) present invention is subsequent inspiration formula high-speed aircraft by the way that the entire design cycle for forcing to turn to twist device has been determined
Design lay a good foundation.
Detailed description of the invention
Fig. 1 is existing turn and twists cell type, and a is brilliant, and b is sweepback ramp type；
Fig. 2 is flow chart of the present invention；
Fig. 3 for the embodiment of the present invention design turn twist cellular construction.
Specific embodiment
Below with reference to specific example and attached drawing, the present invention is described in detail.
High-speed aircraft is forced to turn to twist device, twists the device that unit forms by a row turn.Specific design method as indicated with 2,
It is realized by following steps:
1, determine force turn twist device turn twist cell type
It chooses and forces to turn when twisting device unit type, need to combine flight test actual demand, including thermal protection, turn to twist effect
The factors such as fruit, structure design.Meanwhile comprehensively considering common type and turning to twist the advantage and disadvantage of unit, this example chooses sweepback ramp type
It forces to turn to twist unit, as shown in Figure 3.
2, determine that pressure turn twists device and flows to placement location in aircraft surface
(1) it is placed on before air intake duct flow separation
According to the engine operation envelope curve of aircraft, the calculating state for being least easy to turn to twist is chosen in envelope, is adopted
It is calculated with numerical simulation software Fluent and obtains aircraft air intake duct flowing disengaged position under this state, calculating position is to flow to x
At=0.4m.
(2) consideration flows to the development distance in whirlpool
It flows over pressure to turn after twisting device, will form and flow to whirlpool.Flowing to whirlpool and needing to develop a certain distance could form entirely
Turbulent flow.It is 400mm that the development for flowing to whirlpool, which is chosen, apart from initial value.
(3) consider the realizability of structure installation
The air intake duct flowing disengaged position and step (2) obtained according to step (1) flows to the development distance in whirlpool, aircraft into
Air flue entry position is at 1.4m, and device is twisted in determining pressure turn, and installation site is at 0.4m on board the aircraft.Meanwhile according to flight
The structure feature of device is investigated and forces to turn to twist the device realizability that structure is installed at this location, knot of the aircraft at 0.4m
Structure is installed with sufficient space, is met the requirements.
3, it forces to turn to twist the acquisition of device unit parameter
(1) total enthalpy boundary layer thickness
Determine the major parameter for forcing to turn to twist device unit are as follows: unit side length, cell spacing, cell height, remaining ginseng
Number such as angle, is 10 degree according to sweepback ramp type unit conventional design value, flows to length and obtained according to height and angle calculation,
It is as shown in Figure 3 that ramp type turn twists cell schematics.These three parameters all (force to turn to twist device installed position) total enthalpy with locality
Boundary layer thickness δ is related.
The flow field parameter for forcing to turn to twist device installed position is calculated using numerical simulation software Fluent, according to total enthalpy side
The definition of thickness of boundary layer obtains total enthalpy boundary layer thickness δ=6mm.
(2) cell height and side length design
Pressure turn is twisted device unit height and is determined according to cell height design criteria k/ δ=n, wherein k is to turn to twist unit height
Degree, δ are the total enthalpy boundary layer thickness for turning to twist device installed position, and n value needs to be determined according to flight Mach number, the horse of this example
Conspicuous number is the design initial value of 6, n value to 0.7；ΔwValue is 1, forces to turn to twist a length of 6mm of element sides, is highly 4.2mm.
(3) pressure turn twists device and turns to twist cell spacing
It forces to turn to twist there are spacing between device unit, cell spacing influences to turn to twist effect.Under normal conditions, it forces to turn to twist
Cell spacing is the smaller the better, but the determination of cell spacing actual size needs to comprehensively consider level of processing.The unit of this example
Minimum spacing is 0.3mm.
(4) it forces to turn to twist device exhibition Xiang Kuandu
It forces to turn to twist device unit parameter and flow to after installation site determines, finally determine and turn to twist the exhibition Xiang Kuandu of device.
To ensure that the flowing into engine is all turbulent flow, the width for turning to twist device is forced to should be greater than forcing to turn to twist device installed position
Into the streamline width of air intake duct.Streamline width into air intake duct uses Fluent that width is calculated as 480mm, and flies
Device is 600mm forcing the structure width for turning to twist at device installed position (x=0.4m), is met the requirements.
(5) UG modeling software is used, the parameter determined according to early period, which is established, to be forced to turn to twist mounted cast.
(6) using the pressure that Fluent numerical simulation software calculates design turn to twist device turn twist effect, discovery enter into
The incoming flow fluidised form of air flue is not turbulent flow, is unsatisfactory for requiring.
4, it corrects
Increase first and force to turn to twist δ=0.8 device height k/, side length proportionality coefficient is constant, and pressure turn twists cell height and is
4.8mm, side length is constant, and modeling finds that meeting the fluidised form for entering air intake duct is turbulent flow by calculating, and pressure turn is twisted device and designed
At.
Unspecified part of the present invention is known to the skilled person technology.
Claims (10)
1. a kind of high-speed aircraft is forced to turn to twist device, the device that unit forms is twisted by a row turn, it is characterised in that: described turns
The height for twisting unit determines that wherein k is to turn to twist cell height, and δ is total enthalpy boundary layer by following height design criteria n=k/ δ
Thickness, n are height design criteria coefficient；The side length w for turning to twist unit passes through formula w=Δwδ is determining, wherein ΔwFor side
Long proportionality coefficient；
The height design criteria coefficient n determination basis is, when Mach 2 ship 5~7, n ∈ [0.5,0.8], Mach 2 ship 7~
When 10, n ∈ [0.8,1]；
The side length ratio coefficient deltawValue is 0.5~1.5.
2. a kind of high-speed aircraft according to claim 1 is forced to turn to twist device, it is characterised in that: the pressure turns to twist
The exhibition of device uses following criterion to width: pressure turns to twist device and open up to turn to twist the entrance of device installed position greater than pressure to width
The streamline width of air intake duct, maximum, which is no more than aircraft, is forcing the structure width for turning to twist device installed position.
3. a kind of high-speed aircraft according to claim 1 is forced to turn to twist device, it is characterised in that: described to turn to twist unit
The minimum 0.3mm of spacing.
4. a kind of high-speed aircraft forces the design method for turning to twist device, which is characterized in that realized by following steps:
The first step, determine force turn twist device turn twist cell type；
Second step determines and forces to turn to twist device in the initial placement position that aircraft surface flows to,
A2.1, it forces to turn to twist device placement location while meeting following two condition:
(1) pressure turn is twisted device and is placed on before air intake duct flowing disengaged position；
(2) pressure turn is twisted device and is placed on before the development distance for flowing to whirlpool；
A2.2, the condition for meeting step A2.1 are determined in conjunction with the integral structure layout of aircraft and are forced to turn to twist device placement position
It sets；
Third step determines and forces to turn to twist turning to twist cell parameters original dimension and forcing to turn to twist the exhibition Xiang Kuandu of device for device, turns
Twisting cell parameters includes side length, spacing and height,
A3.1, determination turn to twist unit elemental height and side length,
According to following height design criteria k/ δ=n, elemental height size is determined, wherein n is height design criteria coefficient, and k is to turn
Cell height is twisted, δ is total enthalpy boundary layer thickness,
Turn to twist a length of Δ of element sideswδ, ΔwFor side length proportionality coefficient；
A3.2, determination turn to twist cell spacing；
A3.3, it determines and forces to turn to twist device exhibition Xiang Kuandu；
A3.4, turn to twist cell parameters original dimension according to what step A3.1~3.3 was determined, foundation is forced to turn to twist mounted cast；
A3.5, determined by method for numerical simulation pressure that step A3.4 is established turn to twist mounted cast turn twist effect, guarantee full
The incoming flow fluidised form of foot into air intake duct is turbulent flow, if satisfied, then completing to force to turn to twist device design, is turned if being unsatisfactory for pressure
It twists device to be modified, until the incoming flow fluidised form that satisfaction enters air intake duct is turbulent flow.
5. a kind of high-speed aircraft according to claim 4 forces the design method for turning to twist device, it is characterised in that: described
Step A3.5 amendment, is realized by following steps:
A4.1, judge force turn twist device turn twist unit height whether have reached height design criteria k/ δ determine maximum value,
If not reaching, step A4.2 is carried out, if reaching, is transferred to step A4.3；
A4.2, increase are forced to turn to twist the height that device turn twists unit, and height increase is determined no more than height design criteria k/ δ
Maximum value is established and forces to turn to twist mounted cast, verifying force to turn to twist mounted cast turn twist effect, enter air intake duct if meeting
Incoming flow fluidised form is turbulent flow, then completes to force to turn to twist device design, step A4.1 is carried out if being unsatisfactory for；
The development distance that A4.3, increase flow to whirlpool, which changes, to be forced to turn to twist device placement location, repeats third step, the 4th step, until
Meeting and entering the incoming flow fluidised form of air intake duct is turbulent flow.
6. a kind of high-speed aircraft according to claim 4 forces the design method for turning to twist device, it is characterised in that: described
In step A3.1, height design criteria coefficient n value range is determined by following rule, when Mach 2 ship 5~7, n ∈ [0.5,
0.8], when Mach 2 ship 7~10, n ∈ [0.8,1].
7. a kind of high-speed aircraft according to claim 4 forces the design method for turning to twist device, it is characterised in that: described
In step A3.1, side length ratio coefficient deltawValue range is 0.5~1.5.
8. a kind of high-speed aircraft according to claim 4 forces the design method for turning to twist device, it is characterised in that: described
Step A2.1 condition (1) chooses the operating condition for being least easy to turn to twist, using Numerical-Mode according to the engine operation envelope curve of aircraft
Quasi- method obtains air intake duct and flows disengaged position；The condition (2), the initial value for flowing to the development distance in whirlpool takes 300~
600mm。
9. a kind of high-speed aircraft according to claim 4 forces the design method for turning to twist device, it is characterised in that: described
Step A3.3 pressure turn is twisted device and opened up to width using following criterion: pressure turns to twist device and open up to turn to twist device greater than pressure to width
Installed position enters the streamline width of air intake duct, and maximum, which is no more than aircraft, is forcing the structure for turning to twist device installed position
Width.
10. a kind of high-speed aircraft according to claim 4 forces the design method for turning to twist device, it is characterised in that: institute
It states in step A3.2 and twists the minimum 0.3mm of cell spacing for determining turn.
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| CN101318553A (en) * | 2008-05-28 | 2008-12-10 | 中国航天空气动力技术研究院 | Wing flow control device |
| CN106124626A (en) * | 2016-06-30 | 2016-11-16 | 中国航天空气动力技术研究院 | Postpone hypersonic boundary layer material and turn the Study system and experiment research twisted |
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| US20040065375A1 (en) * | 2002-10-07 | 2004-04-08 | Snider John Michael | Constant acceleration and constant hydraulic diameter eliminate pressure loss in internal and external flow |
| US10071798B2 (en) * | 2012-11-19 | 2018-09-11 | The Regents Of The University Of California | Hypersonic laminar flow control |
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| CN101318553A (en) * | 2008-05-28 | 2008-12-10 | 中国航天空气动力技术研究院 | Wing flow control device |
| CN106124626A (en) * | 2016-06-30 | 2016-11-16 | 中国航天空气动力技术研究院 | Postpone hypersonic boundary layer material and turn the Study system and experiment research twisted |
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