CN105173116B - The close curved surface Waverider method for designing of hypersonic aircraft - Google Patents
The close curved surface Waverider method for designing of hypersonic aircraft Download PDFInfo
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Abstract
The invention discloses a kind of close curved surface Waverider method for designing of hypersonic aircraft, belongs to technical field of aircraft design.The present invention is improved to cone Waverider method for designing closely first, and carries out continuation to close inner cone Waverider method for designing.Based on simplification of the Sobieczky to Three-dimensional Flow, closely cone is transitioned into close wedge, then is transitioned into the process of close inner cone and compares smooth-going, it is believed that horizontal mobility is weaker, flows and occurs mainly in osculating plane.Therefore, to the complex section shock wave curve with any curvature, concave curved line segment, evagination line segment and changeover portion can be divided into, it is approximate with the equal locality cone/wedge flow closely of series of shock intensity respectively, after gained ripple, flow field has second order accuracy, is used for Waverider design.The present invention can utilize the shock wave of any curvature cross sectional shape to be designed, and generate the more complicated Waverider of flat shape, improve its rider characteristic in big range of Mach numbers.
Description
Technical field
Hypersonic aircraft design field of the present invention, and in particular to a kind of close curved surface of hypersonic aircraft is taken advantage of
Ripple body method for designing.
Background technology
The conventional in layout form such as multi-wall interference, lifting body is compared, Waverider layout has higher lift-drag ratio, and is easy to
Using body/Propulsion Integrated design, therefore adopting Waverider or class rider recent Air-breathing hypersonic vehicle more
Body aerodynamic arrangement.
Waverider method for designing so far mainly includes Λ type Waverider methods for designing, taper flow Waverider design side
Method, closely cone Waverider method for designing, wedge cone mixed flow Waverider method for designing, fixed/change key groove configuration method, inner cone/close
Cut 6 class of inner cone Waverider method for designing.The basic flow field of these Waverider methods for designing has been limited to which and can be used for Waverider and set
The shock wave cross sectional shape of meter.Profile of shock wave is only used for into straight line based on the Λ type Waveriders in wedge shape flow field, fixed/change angle of wedge method
Or the Waverider design of sag vertical curve；Profile of shock wave is only used for based on the taper flow method in Conical Shock Wave flow field, close cone method
Waverider for sag vertical curve is designed, and the close flow field method for being developed based on close cone method in the recent period is also only capable of using shock wave section shape
Shape carries out Waverider design for segmentation sag vertical curve；The wedge cone mixed flow method that mixing flow field is bored based on wedge is only used for profile of shock wave
Waverider for sag vertical curve is designed；Inner cone based on inner cone shock wave flow field/inner cone method closely is only used for designing profile of shock wave
For the Waverider of convex curve.
Based on the line small pertubation theory of supersonic flow field, under potential function is to cylindrical coordinate, the second dervative of polar angle is little
Amount, that is, almost do not open up under conditions of flowing, the microvariations line equation under cylindrical coordinate is deteriorated under axial symmetry
Small perturbation equation.After Sobieczky thinks to simplify, equation can be replaced by local close axial symmetry flow, the speed of local flowing
Direction and gradient depend on local taper flow field closely.Due to the change width of pressure, Mach number with polar angle in Conical Shock Wave flow field
Degree is little, therefore application cone method closely, for section is the random shock flow field of concave curve, can by shock wave curve discrete into
Some sections, and replaced with Conical Shock Wave flow field, can preferably approximate shock wave flow field.But cone method closely is approximation method, by
In Conical Shock Wave flow field, flow field parameter is changed with polar angle, and the flowing after cone Waverider shock wave is not fully in locality closely
In osculating plane.In addition, to based on the close cone Waverider that streamline is generated is followed the trail of in circular cone flow field, as the streamline angle of current changes
It is larger, it is ensured that the angle of current of streamline be in can obtain promotion resistance angle-of-attack range be the highly difficult thing of part.Thus can break
Fixed, cone Waverider generates high lift-drag ratio along some regions of grain direction closely, and low lift-drag ratio is in some regions
State.
Meanwhile, in existing close inner cone Waverider method for designing, streamline integration terminating point is singular line polar angle.For anti-fluid stopping
Specified cross-section is not reached also when line integral is to singular line polar angle, it is desirable to which given shock wave curve curvature radius are as big as possible, to ensure
From leading edge point to trailing edge, the streamline of point is respectively positioned on the limit of integration of inner cone shocked flow place permission.Which limits close inner cone to take advantage of
The application of ripple body method for designing, because it is strange to decide that when profile of shock wave cannot be given at the beginning of design whether streamline integration can exceed
Line polar angle.
It is sag vertical curve, segmentation sag vertical curve or evagination that current Waverider method for designing is only used for designing shock wave cross sectional shape
The Waverider of line, therefore the flat shape of Waverider can only be the simple profile that leading edge sweep constantly increases.Curved surface closely is taken advantage of
Ripple body method for designing is designed using the shock wave with any curvature cross sectional shape, generates that flat shape is more complicated takes advantage of
Ripple body, improves its rider characteristic in big range of Mach numbers.
The content of the invention
The present invention proposes a kind of close curved surface Waverider method for designing of hypersonic aircraft, and methods described is first to close
Cone Waverider method for designing is improved, and carries out continuation to close inner cone Waverider method for designing, based on Sobieczky to three
The simplification of dimension flowing, closely cone are transitioned into close wedge, then are transitioned into the process of close inner cone and compare smooth-going, it is believed that horizontal mobility
Weaker, flowing is occurred mainly in osculating plane.Therefore, to the complex section shock wave curve with any curvature, can be by its stroke
Be divided into concave curved line segment, evagination line segment and changeover portion, respectively with the equal locality of series of shock intensity closely cone, close inner cone and
Wedge flow is approximate closely, and after gained ripple, flow field has second order accuracy, is used for Waverider design.
The close curved surface Waverider method for designing of hypersonic aircraft that the present invention is provided, comprises the following steps：
Step 1：The shock wave cross section curve of certain cross sectional shape is given, and it is micro- that shock wave cross section curve is divided into some shock waves
Section.Determined in the osculating plane of micro- section of the shock wave by shape and the local the curvature center relation of micro- section of shock wave, will be adopted
It is approximate with which kind of flow field.According to each flow field approximate way, then local micro- section of shock surface is determined by Shock Wave Parameters.
Step 2：Given Waverider upper surface cross section curve, edge is from origin stream streamline by Waverider upper surface curve discrete point
Upstream follow the trail of, obtain leading edge point；Upstream followed the trail of by Waverider upper surface cross section curve, obtain capture flow tube curved surface；To work as
The intersection of micro- section of ground shock wave face and capture flow tube curved surface connects micro- section of each costa and obtains as micro- section of the costa of Waverider
Waverider leading edge curve；Along upstream following the trail of from origin stream streamline, capture flow tube curved surface is obtained；With local shock surface and capture stream
Costa micro- section of the intersection of pipe curved surface as Waverider.
Step 3：Flow field after ripple is determined by free stream Mach number, Angle of Shock Waves, streamline after ripple is downstream followed the trail of for micro- section by costa
Form Waverider lower surface.
Step 4：From on Waverider leading edge curve, micro- section of a certain costa is downstream followed the trail of from origin stream streamline, that is, taken advantage of
Micro- section of ripple body upper surface；Connecting micro- section of all costas, downstream to follow the trail of the Waverider upper surface obtained from origin stream streamline micro-
Section, that is, form Waverider upper surface.
If there is other demands, Waverider upper surface can be designed according to demand.
It is an advantage of the current invention that：At present Waverider method for designing be simply possible to use in design shock wave cross sectional shape be sag vertical curve,
The Waverider of segmentation sag vertical curve or convex curve, therefore the flat shape of Waverider can only be the simple of the continuous increase of leading edge sweep
Profile.The present invention can utilize the shock wave of any curvature cross sectional shape to be designed, and generate the more complicated Waverider of flat shape,
Improve its rider characteristic in big range of Mach numbers.
Description of the drawings
Fig. 1 determines method schematic diagram for costa in close curved surface Waverider method for designing；
Fig. 2 is lower surface generation method schematic diagram in close curved surface Waverider method for designing；
Fig. 3 is Waverider top view designed in embodiment；
Fig. 4 is the lift-drag ratio and Mach number relation curve of designed Waverider in embodiment；
Fig. 5 is pressure cloud atlas obtained by designed Waverider N-S Equation for Calculating in embodiment.
In figure：
1. leading edge point；2. micro- section of costa；3. Waverider upper surface curve discrete point；4. from origin stream streamline；5. rider
Body upper surface cross section curve；6. shock wave cross section curve；7. micro- section of shock surface；8. micro- section of shock wave；9. local radius of curvature；10. ripple
Streamline afterwards；11. trailing edge points.
Specific embodiment
The present invention is described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of hypersonic aircraft close curved surface Waverider method for designing, for any curvature section shape
The shock wave of shape, it is identical in shock strength, and it is uniform to flow after ripple, open up to flow it is insignificant under the conditions of, sag vertical curve part adopts
Coning tower tray field is approximate closely, and convex curve part is approximate using close inner cone flow field, and sag vertical curve is to convex curve transition portion using close
Wedge flow field is approximate, and requires that the Angle of Shock Waves in each locality cone/wedge shape flow field is equal.This method can utilize any curvature cross sectional shape
Shock wave is designed, and generates the more complicated Waverider of flat shape, improves its rider characteristic in big range of Mach numbers.
The close curved surface Waverider method for designing of described hypersonic aircraft, with reference to Fig. 1 and Fig. 2, comprises the following steps：
Step 1：The shock wave cross section curve 6 of certain cross sectional shape is given, shock wave cross section curve 6 is divided into into micro- section of some shock waves
8, micro- section 8 of each shock wave should be made when dividing micro- section 8 of shock wave to be only sag vertical curve, convex curve or changeover portion.By micro- section 8 of shock wave shape with
The local the curvature center relation determination of micro- section of shock wave, will be approximate using which kind of flow field in its osculating plane：To sag vertical curve, adopt
It is approximate with close coning tower tray field；It is to convex curve, approximate using close inner cone flow field；From sag vertical curve to convex curve transition portion using close
Cut wedge flow field approximate.According to each approximate way, then determined by Shock Wave Parameters (including local radius of curvature 9 and Angle of Shock Waves) local sharp
Micro- section 7 of corrugated.To cone and close inner cone flow field closely, local cone shock is determined jointly by local radius of curvature 9 and Angle of Shock Waves
Micro- section of face；To close wedge flow field, micro- section of local wedge shape shock surface is determined by local shock wave angle beta only.
Adopt close coning tower tray field and close inner cone flow field approximate described in step 1, be that the present invention is basic in existing method
On closely cone Waverider method for designing is improved, and the stream obtained after carrying out continuation to close inner cone Waverider method for designing
Field approximation method.
First, cone Waverider method for designing closely is improved.Can based on simplification of the Sobieczky to Three-dimensional Flow
Know, after ripple, flow field can be replaced to a series of little taper flow fields of flowing with exhibition.Analyze accordingly, in shock strength identical situation
Under, flow field not only can use close taper flow field to replace, and also directly can be opened up to less flow field of flowing from other and be replaced.Accordingly, if
A series of flow fields as wanting to exist, in flowing is still occurred in by the osculating plane determined when ground shock wave curve, flow in flow field
Line direction is fixed as the flow direction of flow field starting point after ripple.The flow field is not taper flow, can regard the wedge in osculating plane as
Shape stream.As this flow field is, to the approximate of close taper flow, therefore to replace the given section of close taper flow field description with this flow field
The shock wave flow field of shape.Wedge flow (close wedge) in local osculating plane, therefore can be very square due to given grain direction
Just the object plane angle of attack of Waverider lower surface is controlled in high lift-drag ratio angle of attack area, more high lift-drag ratio can be obtained.Also, after ripple
Flow field is supersonic flow field, and microvariations upstream will not be propagated.Although therefore wedge shape flow field parameter and Conical Shock Wave flow field parameter
There is certain difference, as starting point parameter is consistent after ripple, the change of flow field parameter on the streamline of downstream swashs can't starting point
Wave parameter changes, and the Waverider generated based on AC line can still keep the rider characteristic for boring closely Waverider.
Then, continuation is carried out to close inner cone Waverider method for designing.Although during inner cone shocked flow field grain direction tends to
Heart line direction change, as stream tube area gradually increases, therefore flowing is in constantly expansion.When reaching near singular line, because of horse
Conspicuous line passes through origin, overlaps with polar diameter direction now, and according to Euler equation properties, integration cannot cross over characteristic curve.After singular line
Flow field does not interfere with existing inner cone shock wave flow field to a certain extent, as long as not adding strong disturbance in flow field, you can random structure
Make flow field after singular line.The close inner cone Waverider generation method of continuation, of the invention tangential according to singular line edge streamline for convenience
Flow field after directional structure vectorical structure singular line, carries out continuation to the integral domain of close inner cone Waverider method for designing.
Based on simplification of the Sobieczky to Three-dimensional Flow, cone is transitioned into close wedge, then the mistake for being transitioned into close inner cone closely
Journey compares smooth-going, it is believed that horizontal mobility is weaker, and flowing is occurred mainly in osculating plane.The complex section shock wave of any curvature
The locality that curve can use series of shock intensity equal cone/wedge flow closely is approximate, and has second order accuracy.Therefore, in step 1
In the close inner cone method of improved close cone method, continuation is respectively adopted to sag vertical curve, convex curve and changeover portion shock wave for micro- section 8
And wedge method closely is carried out approximately, it is possible to obtain flow field after the basically identical ripple of flow field parameter, to carry out Waverider design.
Step 2：Given Waverider upper surface cross section curve 5, edge is from origin stream streamline 4 by Waverider upper surface curve discrete
Point 3 is upstream followed the trail of, and obtains leading edge point 1；Upstream followed the trail of by Waverider upper surface cross section curve 5, obtain capture flow tube curved surface.
Using the intersection of micro- section 7 of local shock surface and capture flow tube curved surface as micro- section 2 of the costa of Waverider, connect micro- section of each costa
2 obtain Waverider leading edge curve.
Step 3：Flow field after ripple is determined according to free stream Mach number, Angle of Shock Waves, and then obtains streamline 10 after ripple.Before Waverider
On edge curve, a certain leading edge point 1 starts, according to micro- section of 2 position cone shocks of costa or wedge shape shock wave flow field, downstream
Follow the trail of ripple after streamline 10 to required Waverider basal surface position, such as Fig. 2, that is, after obtaining the 1 corresponding Waverider lower surface of leading edge point
Edge point 11, connects each trailing edge point 11 and Waverider lower surface trailing edge curve is obtained.By the leading edge between two neighboring leading edge point 1
Line downstream follows the trail of streamline 10 after ripple for micro- section 2, that is, obtain micro- section of corresponding Waverider lower surface.Connect all costas micro- section 2
Micro- section of the lower surface for obtaining downstream is followed the trail of, that is, obtains Waverider lower surface.
Step 4：From on Waverider leading edge curve, a certain costa is downstream followed the trail of for micro- section 2 from origin stream streamline 4, that is, obtain
Micro- section of Waverider upper surface；Connect all costas and downstream follow the trail of from origin stream streamline 4 the Waverider upper surface for obtaining for micro- section 2
Micro- section, that is, form Waverider upper surface.If there is other demands, upper surface can be designed according to demand.
The method that the present invention is provided, is improved to cone Waverider method for designing closely first, and to close inner cone rider
Body method for designing carries out continuation so that Conical Shock Wave flow field not only can be approximate using cone closely or close inner cone flow field, can also adopt
It is approximate with close wedge flow field, so as to the shock wave to any curvature cross sectional shape, can be divided into concave curved line segment, evagination line segment and
Changeover portion, is respectively adopted cone wedge flow field closely and approximately, to carry out Waverider design, improves its taking advantage of in big range of Mach numbers
Wave property.
Embodiment：Design Mach number Ma=5.0, shock wave angle beta=14.3 °.Devised with S using close curved surface Waverider
The Waverider of type leading edge, this is that traditional method cannot be realized.The Waverider top view that design is obtained is as shown in Figure 3.Fig. 4 gives
Change curve of the designed Waverider lift-drag ratio with Mach number is gone out.It is visible in figure, based on the close curved surface side that the present invention is provided
The Waverider of method design has good lifting resistance characteristic, reaches 8.85 without viscosity flow maximum lift-drag ratio, maximum lift-drag ratio in viscous flow
Reach 6.86.The aircraft is respectively provided with higher lift-drag ratio in the range of Mach number 4-6.
By the flow field isobar cloud atlas of N-S equation numerical simulations when Fig. 5 gives design point.It is visible in figure, shock wave
The similar S types of cross sectional shape curve, existing sag vertical curve part also have a convex curve part, and gases at high pressure seldom leak aircraft upper table
Face.
Claims (3)
1. the close curved surface Waverider method for designing of hypersonic aircraft, it is characterised in that：Any curvature cross sectional shape is swashed
Ripple, is divided into concave curved line segment, evagination line segment and changeover portion, be respectively adopted improved close cone method, continuation it is close in
Cone method and close wedge method are carried out approximately, obtain flow field after the consistent ripple of flow field parameter, to carry out Waverider design；
Described improved close cone method is referred to, it is contemplated that there are a series of such flow fields, and flowing is still occurred in by locality
In the osculating plane that shock wave curve determines, in flow field, grain direction is fixed as the flow direction of flow field starting point after ripple, the flow field
Regard the wedge flow in osculating plane as；
The close inner cone method of described continuation is referred to according to flow field after the streamline tangential direction construction singular line of singular line edge, to close
The integral domain for cutting inner cone Waverider method for designing carries out continuation.
2. the close curved surface Waverider method for designing of hypersonic aircraft according to claim 1, it is characterised in that：Including
Following steps,
Step 1：The shock wave cross section curve of certain cross sectional shape is given, and shock wave cross section curve is divided into into micro- section of some shock waves；By
The shape that micro- section of shock wave and local the curvature center relation determined in the osculating plane of micro- section of the shock wave, will be using which kind of
Flow field is approximate；According to each flow field approximate way, then local micro- section of shock surface is determined by Shock Wave Parameters；
Step 2：Given Waverider upper surface cross section curve, along from origin stream streamline by Waverider upper surface curve discrete point upwards
Trip is followed the trail of, and obtains leading edge point；Upstream followed the trail of by Waverider upper surface cross section curve, obtain capture flow tube curved surface；Swashed with local
The intersection of micro- section of corrugated and capture flow tube curved surface connects micro- section of each costa and obtains rider as micro- section of the costa of Waverider
Body leading edge curve；
Step 3：Flow field after ripple is determined by free stream Mach number, Angle of Shock Waves, streamline after ripple is downstream followed the trail of by micro- section of costa and is formed
Waverider lower surface；
Step 4：From on Waverider leading edge curve, micro- section of a certain costa is downstream followed the trail of from origin stream streamline, that is, obtain Waverider
Micro- section of upper surface；Connect micro- section of all costas and downstream follow the trail of from origin stream streamline micro- section of the Waverider upper surface for obtaining, i.e.,
Form Waverider upper surface.
3. the close curved surface Waverider method for designing of hypersonic aircraft according to claim 2, it is characterised in that：Step
3 are specially：Flow field after ripple is determined according to free stream Mach number, Angle of Shock Waves, and then obtains streamline after ripple；By on Waverider leading edge curve
A certain leading edge point starts, and according to micro- section of position cone shock of costa or wedge shape shock wave flow field, flows after downstream following the trail of ripple
Line obtains the corresponding Waverider lower surface trailing edge point of the leading edge point to required Waverider basal surface position, connects each trailing edge point and is
Obtain Waverider lower surface trailing edge curve；Streamline after ripple is downstream followed the trail of for micro- section by the costa between two neighboring leading edge point,
Micro- section of corresponding Waverider lower surface is obtained；Connect micro- section of all costas and downstream follow the trail of micro- section of the lower surface for obtaining, i.e.,
Obtain Waverider lower surface.
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| CN105667811B (en) * | 2016-01-27 | 2017-11-07 | 南京航空航天大学 | The design method of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct |
| CN105674811B (en) * | 2016-03-07 | 2017-06-13 | 晋西工业集团有限责任公司 | A kind of guided rocket bullet with Waverider structure |
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| CN109969374B (en) * | 2019-04-09 | 2021-05-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Standard mode pneumatic layout and design method for hypersonic velocity boundary layer transition research |
| CN110795794B (en) * | 2019-10-31 | 2022-02-18 | 厦门大学 | Bump design method for inhibiting high-speed pulse noise of helicopter rotor |
| CN111553119B (en) * | 2020-03-24 | 2024-02-13 | 南京航空航天大学 | Three-dimensional curved surface shock wave reverse design method for hypersonic aircraft under non-uniform flowing down |
| CN113148222B (en) * | 2021-05-24 | 2023-01-31 | 北京航空航天大学 | Close curved surface wave-rider positive design method suitable for complex leading edge shape |
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