CN114936430B - Wide-speed-range hypersonic aircraft aerodynamic layout design method and system - Google Patents
Wide-speed-range hypersonic aircraft aerodynamic layout design method and system Download PDFInfo
- Publication number
- CN114936430B CN114936430B CN202210879045.5A CN202210879045A CN114936430B CN 114936430 B CN114936430 B CN 114936430B CN 202210879045 A CN202210879045 A CN 202210879045A CN 114936430 B CN114936430 B CN 114936430B
- Authority
- CN
- China
- Prior art keywords
- cone
- speed
- wide
- range
- guided wave
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Computer Hardware Design (AREA)
- Computational Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Computer Graphics (AREA)
- Software Systems (AREA)
- Algebra (AREA)
- Computing Systems (AREA)
- Fluid Mechanics (AREA)
- Mathematical Physics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a wide-speed-range hypersonic aircraft pneumatic layout design method and a system, wherein a volume increasing method is adopted to passivate the front edge of a constructed cone guided wave body, then a pneumatic optimization method is utilized to optimize the wing profile of the wide-speed-range hypersonic aircraft, the hypersonic flight of the aircraft is considered, the multi-objective optimization is carried out on the original wing profile in a set hypersonic and subsonic cruise state, the lower surface of the obtained optimal wing profile has double S characteristics, loading and balancing moments can be formed on the front edge and the rear edge of the wing profile under subsonic speed, and front and rear shock waves are formed under ultrasound to increase the pressure of the lower surface; and finally, coupling the passivated cone guided wave body and the wing based on the optimal airfoil modeling to obtain the wide-speed-range hypersonic aircraft.
Description
Technical Field
The invention belongs to the field of aerodynamic layout of aircrafts, and particularly relates to a wide-speed-range hypersonic aircraft aerodynamic layout design method and system.
Background
The wide-speed-range aircraft is a novel aircraft with the capabilities of horizontal runway take-off and landing and hypersonic cruise. Compared with the traditional aircraft, the wide-speed-range aircraft has higher cruising speed and flying height and has the characteristic of reutilization, so that the wide-speed-range aircraft quickly becomes a research leading-edge hotspot in the aerospace field.
While the wide-speed-range aircraft has many advantages, the wide-speed-range aircraft is required to have wide-speed-range and full-envelope aerodynamic performance. However, in the design of the aircraft layout, the optimization of the pneumatic performance in the subsonic state and the pneumatic performance in the supersonic state often contradicts each other, which makes it difficult for the aircraft to consider the optimal pneumatic performance in different states. The wide-speed domain configuration research of the existing aircraft only expands the configuration of the waverider and does not simultaneously consider the aerodynamic characteristics in the states of sub-velocity, cross-velocity and supersonic velocity, so that the corresponding wide-speed domain layout is designed to be a leading-edge research hotspot in the aerospace field of the 21 st century and is one of key technologies which need to be broken through in the engineering research of the wide-speed domain aircraft.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a wide-speed-range hypersonic aircraft aerodynamic layout design method and a system, the method comprehensively utilizes low-speed vortex lift force and supersonic shock wave lift force, improves aerodynamic performance by utilizing vortex rolled up by a sharp front edge of a sweepback wing under a large attack angle under subsonic speed, improves aerodynamic characteristics by utilizing a cone guided wave body front edge and a wide-speed-range wing under supersonic speed, and realizes that the wide-speed-range hypersonic aircraft has optimal aerodynamic performance under each sound velocity state by geometrically coupling the sweepback sharp front edge excitation vortex of the subsonic high attack angle with the supersonic tip front edge excitation shock wave.
The invention is realized by the following technical scheme:
a wide-speed-range hypersonic aircraft aerodynamic layout design method comprises the following steps:
step 1, constructing a cone guided wave body of a wide-speed-range hypersonic aircraft;
step 3, parameterizing the set original airfoil profile, determining sample point pneumatic parameters of the parameterized airfoil profile, establishing a proxy model by taking the parameterized airfoil profile as input and the sample point pneumatic parameters as output, and optimizing the proxy model by taking the lift-drag ratio of the original airfoil profile in supersonic and subsonic cruising states as an optimization target to obtain an optimal airfoil profile;
and 4, establishing a three-dimensional wing according to the optimal wing profile, and coupling the three-dimensional wing with the cone guided wave body with the passivated leading edge obtained in the step 2 to obtain the wide-speed-range hypersonic aircraft.
Preferably, the construction method of the cone-guide waverider in step 1 is as follows:
s11, setting basic parameters of the cone guided wave-rider, including an upper edge line of the cone guided wave-rider and a cone shock wave flow field;
s12, projecting the upper edge line to the conical surface of the conical shock wave flow field along the axial direction of the conical shock wave flow field to obtain a front edge line of a conical guide wave multiplier;
s13, solving according to the leading edge line of the cone-guided wave body and by combining a streamline tracing method to obtain the lower surface of the cone-guided wave body;
s14, obtaining the upper surface of the cone-guided wave body according to the front edge line of the cone-guided wave body and by combining a free flow surface method;
and S15, coupling the lower surface obtained in the step S13 and the upper surface obtained in the step S14 to obtain the cone-guided wave.
Preferably, the expression of the leading edge line in step S12 is as follows:
wherein, the first and the second end of the pipe are connected with each other,Ris the bottom circle radius of the conical shock wave flow field,Lis the length of the flow field of the conical shock wave flow field,θis a half cone angle of a conical shock wave flow field,xbeing a leading edge linexThe coordinates of the position of the object to be measured,y,zrespectively leading edge lineyCoordinates andzand (4) coordinates.
Preferably, the leading edge of the cone-guided waverider is passivated by a volume-increasing passivation method in step 2.
Preferably, in step 3, the set original airfoil profile is parameterized by using a CST method, and an expression of the obtained parameterized airfoil profile is as follows:
wherein the content of the first and second substances,ψfor parameterising airfoilsxThe coordinates of the position of the object to be imaged,
for parameterising airfoilsyThe coordinates of the position of the object to be imaged,
in the form of a function of the class,N1，N2in order to be a function class parameter,S(ψ)is a shape function.
Preferably, the method for determining the aerodynamic parameters of the sample points of the parameterized airfoil profile in step 3 is as follows:
sampling the parameterized airfoil profile to obtain proxy model sample points, carrying out grid reconstruction on the proxy model sample points based on the original airfoil profile pneumatic computation grid by using a grid deformation method, and carrying out numerical simulation on the reconstructed grid to obtain sample point pneumatic parameters of the parameterized airfoil profile.
Preferably, in step 3, the parameterized airfoil is sampled by adopting an LHS method.
Preferably, the mesh deformation method in step 3 is TFI interpolation or RBF interpolation.
Preferably, in the step 3, a multi-objective optimization algorithm is adopted to optimize the proxy model, and the wing profile with the maximum subsonic lift-drag ratio is obtained to serve as the optimal wing profile.
A system of a wide-speed-range hypersonic aircraft aerodynamic layout design method comprises,
the wave rider module is used for constructing a cone guided wave rider of the wide-speed-range hypersonic aircraft;
the front edge passivation module is used for passivating the front edge of the cone guided wave multiplier output by the wave multiplier module to obtain a cone guided wave multiplier with a passivated front edge;
the airfoil optimization module is used for parameterizing the set original airfoil, determining sample point pneumatic parameters of the parameterized airfoil, establishing a proxy model by taking the parameterized airfoil as input and the sample point pneumatic parameters as output, and optimizing the proxy model by taking the lift-drag ratio of the original airfoil in supersonic and subsonic cruising states as an optimization target to obtain an optimal airfoil;
and the coupling module is used for establishing a three-dimensional wing according to the optimal airfoil profile and coupling the three-dimensional wing with the cone guided wave body with the passivated leading edge to obtain the wide-speed-range hypersonic aircraft.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a wide-speed-range hypersonic aircraft aerodynamic layout design method, which comprises the steps of firstly passivating the front edge of a constructed cone guided wave multiplier by adopting a volume increasing method; then, optimizing the original wing profile of the wide-speed-range aircraft by using a pneumatic optimization method, and considering that the aircraft needs supersonic flight, firstly, performing multi-target optimization on the original wing profile in a set supersonic and subsonic cruising state in the optimization process to enable the lower surface of the wing profile to have double-S characteristics, enabling the front edge and the rear edge of the wing profile to form loading and balance moments under the subsonic speed, and forming front and rear shock waves under the supersonic to increase the pressure of the lower surface; and finally, coupling the passivated cone guided wave body and the wing based on the optimal airfoil profile modeling to obtain the wide-speed-range hypersonic aircraft.
Further, the wide-speed-range hypersonic aircraft can comprehensively utilize the lift force of the high-attack-angle vortex at the subsonic speed and the wave-lifting force at the supersonic speed, and the lift coefficient of the wide-speed-range hypersonic aircraft greatly rises at the subsonic speed and the high-attack-angle state, because the large sweepback arrow-shaped wing front edge of the wide-speed-range hypersonic aircraft generates upward turning vortices at the subsonic speed and a low-pressure area is generated at the wing front edge. Under the supersonic speed state, the incoming flow is increased through the shock wave, a high-pressure area is generated on the lower surface of the hypersonic speed aircraft in the wide speed area, and the lift-drag ratio is improved.
Drawings
FIG. 1 is a block diagram of a wide speed range hypersonic aircraft of the present invention;
the view a is a front view of the wide-speed-range hypersonic aerocraft, the view b is a side view of the wide-speed-range hypersonic aerocraft, and the view c is a top view of the wide-speed-range hypersonic aerocraft;
FIG. 2 is a flow chart of the design of the aerodynamic layout of the wide-speed-range hypersonic aircraft of the present invention;
FIG. 3 is a schematic diagram of the design of the cone-guided waverider of the present invention;
FIG. 4 is a schematic illustration of cone-guided waverider leading edge passivation in accordance with the present invention;
wherein, a is a side view of the passivation of the leading edge of the cone-guided wave body, and b is a front view of the passivation of the leading edge of the cone-guided wave body;
FIG. 5 is a partial optimization Pareto solution set and a partial optimization airfoil of the invention;
FIG. 6 is a comparison of an original airfoil profile of the present invention and a selected optimized airfoil profile;
in the figure: the solid line is an optimal airfoil profile, and the dotted line is an original airfoil profile;
FIG. 7 is a supersonic pressure cloud chart of the optimum airfoil profile of the present invention at Ma4/4 deg. state;
FIG. 8 is a subsonic pressure cloud for the optimum airfoil profile of the present invention at Ma0.8/1.5;
FIG. 9 is a graph of the variable Mach number lift coefficient of the wide-speed-range hypersonic aircraft at different angles of attack;
FIG. 10 is a resistance coefficient line graph of the wide-speed-range hypersonic aircraft of the invention with variable Mach number at different angles of attack;
FIG. 11 is a lift-drag ratio line graph of the wide-speed-range hypersonic aircraft of the invention with variable Mach number at different angles of attack;
FIG. 12 is a pressure cloud of the wide-speed-range hypersonic aircraft Ma0.8/4-degree angle of attack according to the invention;
FIG. 13 is a pressure cloud diagram of the wide-speed-range hypersonic aircraft Ma 4/4-degree angle of attack according to the invention.
Detailed Description
The present invention will now be described in further detail with reference to the attached drawings, which are illustrative, but not limiting, of the present invention.
Referring to fig. 2, a wide-speed-range hypersonic aircraft aerodynamic layout design method includes the following steps:
step 1, establishing a cone guided wave-rider of the aircraft according to a cone guided wave-rider design theory, which specifically comprises the following steps:
s11, setting basic parameters of the cone guided wave body, wherein the basic parameters comprise an upper edge line of the cone guided wave body, a cone shock wave flow field and the design Mach number of the cone guided wave body.
The upper edge line is described by a quadratic function, the half cone angle theta of the conical shock wave flow field and the flow field length of the conical shock wave flow field areLAnd determining the design Mach number of the cone-guide-multiplier according to the ideal cruising speed of the wide-speed-range hypersonic aircraft in the supersonic speed state.
Referring to fig. 3, the upper edge line is a curve fg, the flow field length of the conical shock wave flow field is AB, and the mach number in this embodiment isMaAnd =4, the cone guided wave bodies account for 1/3 of the length of the wide-speed-range hypersonic aircraft, and the performance of the cone guided wave bodies is optimal when the half cone angle is 12 degrees under the condition that the volume of the wide-speed-range hypersonic aircraft is not considered.
And S12, projecting the upper edge line to the conical surface of the conical shock wave flow field along the axial direction of the conical shock wave flow field to obtain a leading edge line of the conical guide wave multiplier, wherein the leading edge line is a curve from a point e to a point g, and the leading edge line is represented by eg in the following description, as shown in FIG. 3.
The expression of the upper edge line of the cone-lead waverider is as follows:
wherein, the first and the second end of the pipe are connected with each other,A,bare quadratic curve parameters.
Projecting the upper edge line to the conical flow field to obtain a front edge line, wherein the expression is as follows:
wherein the content of the first and second substances,Ris the bottom circle radius of the conical shock wave flow field,Lis the length of the flow field of the conical shock wave flow field,θis a half cone angle of a conical shock wave flow field,xbeing the leading edge line egxCoordinates, and leading edge line egy,zCoordinates and upper edge line fgy,zThe coordinates are the same.
S13, solving according to the leading edge line of the cone-guided wave body and by combining a streamline tracing method to obtain the lower surface of the cone-guided wave body;
and S14, obtaining the upper surface of the cone-guided wave body according to the front edge line of the cone-guided wave body and by combining a free flow surface method.
And S15, coupling the lower surface and the upper surface of the cone-guided wave-rider to obtain the cone-guided wave-rider.
The wide-speed-range hypersonic aircraft generates oblique shock waves by the cone guided wave bodies in the supersonic speed stage, so that the pneumatic performance of the wide-speed-range hypersonic aircraft in the supersonic speed state can be improved; secondly, for the arrangement of the scramjet in the supersonic speed state, the cone guided wave bodies initially compress and pressurize the airflow, and the internal and external flow integrated design of the scramjet is facilitated.
And 2, passivating the front edge of the cone-guided wave body to obtain the cone-guided wave body with the passivated front edge.
In consideration of aerodynamic thermal protection problems at hypersonic speeds in engineering applications and geometric fairing, it is desirable to passivate the sharp leading edge of the cone-guided wavelets. The front edge is passivated by adopting a passivation method for increasing the volume, and the passivation method has small influence on the volume, the lifting surface and the flow field structure of the cone-shaped guided wave body.
Referring to FIG. 4, a schematic diagram of a cone-guided-wave-rider leading edge passivation scheme; the upper surface of the cone guided wave multiplier is moved upwards, and a gap generated in the process of passivating the cone guided wave multiplier is sealed by utilizing an arc passivation curve or a Bezier curve and the like, so that the purpose of passivating the front edge is achieved.
Step 3, parameterizing the set original airfoil profile, determining sample point pneumatic parameters of the parameterized airfoil profile, establishing a proxy model by taking the parameterized airfoil profile as input and the sample point pneumatic parameters as output, and optimizing the proxy model by taking the lift-drag ratio of the original airfoil profile in supersonic and subsonic cruising states as an optimization target to obtain an optimal airfoil profile; referring to fig. 2, the specific steps are as follows:
s3.1, parameterizing the set original airfoil profile by adopting a CST (class function/shape function transformation) method to obtain a parameterized airfoil profile, wherein the expression of the parameterized airfoil profile is as follows:
wherein the content of the first and second substances,ψfor parameterised airfoilsxThe coordinates of the position of the object to be imaged,
for parameterised airfoilsyThe coordinates of the position of the object to be measured,
in the form of a function of the class,N1，N2in order to be a function class parameter,S(ψ)is a shape function. The class function is an analytic function similar to the parameterized target geometric shape, and different geometric topological structures can be described by selecting different class functions; the shape function is a linearly weighted Bernstein polynomial and is used for further adjusting the geometric shape of the class function, so that the CST parameterization method has geometric deformation capacity, and the wing profile is described as a mathematical parameter by the CST method.
And S3.2, sampling the parameterized airfoil profile by adopting LHS to obtain proxy model sample points, carrying out grid reconstruction on the proxy model sample points based on the original airfoil profile pneumatic computation grid by using a grid deformation method, and carrying out numerical simulation on the reconstructed grid to obtain the sample point pneumatic parameters of the parameterized airfoil profile.
The grid deformation method is a TFI interpolation method or a RBF interpolation method, and the grid reconstruction can also be carried out by utilizing a macro script obtained by a grid generation tool.
And S3.3, establishing a proxy model by taking the parameterized airfoil profile as input and the sample point aerodynamic parameter as output, optimizing the proxy model by adopting a multi-objective optimization algorithm, solving a Pareto solution set of a multi-objective optimization problem, and selecting the airfoil profile with the maximum subsonic lift-drag ratio in the Pareto solution set as an optimal airfoil profile.
The agent model is a Kriging model, and the multi-target optimization algorithm is an NSGA2 or MOEAD algorithm.
In this embodiment, the optimization process of the original airfoil profile is as follows, the lift-drag ratio of the original airfoil profile in the states of Ma0.8/1.5 ° and Ma4/4 ° is jointly optimized, and in consideration of the fact that the wide-speed-range hypersonic aircraft needs to perform supersonic flight, NASA _ SC (2) _0404 with a thickness of 4% is selected as the original airfoil profile, and a Pareto solution and a airfoil profile with a part of the Pareto solution concentrated are drawn, as shown in fig. 5. The airfoil profile with the maximum subsonic lift-drag ratio in the pareto solution is selected as the optimal airfoil profile of the wide-speed-range hypersonic aircraft, and the comparison between the optimal airfoil profile and the original airfoil profile is shown in fig. 6.
And 4, establishing a three-dimensional wing based on the optimal airfoil profile, and coupling the three-dimensional wing with the cone guided wave multiplier with the passivated leading edge obtained in the step 2 to obtain the wide-speed-range hypersonic aircraft.
Based on the idea that the subsonic and large attack angle of a large-sweepback strake wing can induce the vortex of the upper surface of the aircraft, a 12 wide-speed-range hypersonic aircraft Ma0.8/4-degree attack angle pressure intensity cloud chart is referred to, the large sweepback of the upper surface of a cone guided wave body plays a role in inducing the vortex, a streamline starts to roll over through the cone guided wave body, and the pressure intensity of the upper surface of the wide-speed-range hypersonic aircraft is reduced; and secondly, turning and rolling the airflow along the front edge of the sweepback wing to the upper surface to form negative pressure gradient and generate a secondary vortex, further reducing the front edge pressure of the upper surface of the cone-guided wave carrier, and improving the lift force of the wide-speed-range hypersonic aircraft. The characteristics that the lower cone of an attack angle of Ma0.8/4 degrees is subjected to wave-rider induced swirl and the large backswept wing induces airflow rollover are described as swirl characteristics of the flow field.
In order to ensure the vortex characteristics of the flow field, the coupling position of the cone-shaped guided wave body and the wing needs to be smoothly coupled in a geometrical configuration, referring to a top view of a three-view diagram of a wide-speed-range hypersonic aircraft in fig. 1, a leading edge curve of the wing is tangent to a leading edge line of the cone-shaped guided wave body on a top view plane, that is, the end point angle of the leading edge line of the cone-shaped guided wave body is the same as the sweepback of the leading edge, so that the three-dimensional wing model constructed based on the optimal airfoil profile has the following steps:
and taking the end point of the leading edge line of the cone guided wave carrier as the original point of the wing, taking the length of the box section of the fuselage as the chord length (5.79 m), and taking the amplified optimal airfoil as the initial curve of the wing sweep. The sweep is performed along the direction of trailing edge sweep at 32 degrees (typical range of arrow-shaped wings is 15-35 degrees), and the direction of leading edge sweep at 76.5 degrees, and the sweep is tangent to the upper edge line of the cone guided wave body on the top plan, until the tip-root ratio is 0.23 (typical range is less than 0.3), so that the three-dimensional configuration of the wing is obtained, and the fuselage box section is closed by a first-order continuous curved surface as required.
Simulation verification
The optimal wing profile and the constructed wide-speed-range hypersonic aircraft are subjected to numerical simulation, and the numerical simulation conclusion is as follows:
1. numerical simulation of optimum airfoil profile
And carrying out CFL3D numerical simulation on the optimal airfoil profile under the simulation condition that the transonic speed Ma0.8 attack angle is 1.5 degrees and the supersonic speed Ma4 attack angle is 4 degrees.
Under the condition of transonic speed, a pressure cloud picture of optimal airfoil numerical simulation is shown in fig. 8, the first S on the front edge of the lower surface enables the lower surface of the optimal airfoil to be concave inwards near a front edge point, and front loading is formed to increase lift force; while the second "S" creates an afterload near the optimum airfoil trailing edge to likewise increase lift.
Under the supersonic speed condition, the pressure cloud chart of numerical simulation of the optimal airfoil profile is shown in fig. 7, the reduction of the radius of the front edge of the optimal airfoil profile is beneficial to reducing shock wave resistance, meanwhile, a shock wave high-pressure area is generated at the double S-shaped bends of the lower surface, and expansion airflow lifting force is generated on the upper surface of the rear edge of the optimal airfoil profile, so that the resistance ratio is further improved.
2. Numerical simulation of wide-speed-range hypersonic aircraft
And (4) carrying out a numerical simulation experiment by using numerical simulation software CFD + +. The numerical simulation condition is a typical wide-speed-range aircraft flight envelope, the numerical simulation atmospheric environment is 0 to 25km, and the Mach number range is 0.5 to 7Ma.
The aerodynamic performance curve obtained by numerical simulation of the wide-speed-range hypersonic aerocraft is as follows: fig. 9 is a graph of a lift coefficient of the wide-speed-range hypersonic aircraft with variable mach numbers at different angles of attack, fig. 10 is a graph of a resistance coefficient of the wide-speed-range hypersonic aircraft with variable mach numbers at different angles of attack, and fig. 11 is a graph of a lift-drag ratio of the wide-speed-range hypersonic aircraft with variable mach numbers at different angles of attack.
According to the design principle of the wide-speed-range hypersonic aircraft, the lift coefficient of the wide-speed-range hypersonic aircraft is greatly increased in a subsonic state (referring to a subsonic angle of attack of 8 degrees in a graph 9), because upward turning vortexes are generated at the front edge of the large backward swept arrow-shaped wing at the subsonic speed, and a low-pressure region is generated at the front edge of the wing. There is still a tendency for ma0.8 to have a pressure cloud at 4 deg. angle of attack, which is plotted as shown in fig. 12, with the air flow turning up on the upper surface, creating a low pressure zone on the upper surface of the wide velocity range hypersonic aircraft.
Under the supersonic speed state, the incoming flow is increased through shock waves, a high-pressure area is generated on the lower surface of the wide-speed-range hypersonic aircraft, the lift-drag ratio is improved, and the aerodynamic performance of supersonic speed flight is improved. Similarly, a typical flow field cloud chart under an attack angle of Ma4,4 ° is drawn, as shown in fig. 13, it is found that a high-pressure area on the lower surface of the wide-speed-region hypersonic aircraft is mainly concentrated on the head of the cone guided wave carrier and the front and rear edges of the wing, which is the same as the optimal airfoil pressure distribution trend obtained under two-dimensional optimization, and the obtained wide-speed-region hypersonic aircraft has the advantages of being capable of comprehensively utilizing the high-attack-angle vortex lift force under subsonic speed and the wave-lifting force under supersonic speed state, so that the wide-speed-region hypersonic aircraft has excellent aerodynamic performance under the wide speed region.
The invention also provides a wide-speed-range hypersonic aircraft aerodynamic layout design system which comprises a wave multiplier module, a leading edge passivation module, an airfoil optimization module and a coupling module.
The wave rider module is used for constructing a cone guided wave rider of the wide-speed-range hypersonic aircraft;
the front edge passivation module is used for passivating the front edge of the cone guided wave multiplier output by the wave multiplier module to obtain a cone guided wave multiplier with a passivated front edge;
the airfoil optimization module is used for parameterizing the set original airfoil, determining sample point pneumatic parameters of the parameterized airfoil, establishing a proxy model by taking the parameterized airfoil as input and the sample point pneumatic parameters as output, and optimizing the proxy model by taking the lift-drag ratio of the original airfoil in supersonic and subsonic cruising states as an optimization target to obtain an optimal airfoil;
and the coupling module is used for establishing a three-dimensional wing according to the optimal airfoil profile and coupling the three-dimensional wing with the cone guided wave body with the passivated leading edge to obtain the wide-speed-range hypersonic aircraft.
The above contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention should not be limited thereby, and any modification made on the basis of the technical idea proposed by the present invention falls within the protection scope of the claims of the present invention.
Claims (7)
1. A wide-speed-range hypersonic aircraft aerodynamic layout design method is characterized by comprising the following steps:
step 1, constructing a cone guided wave multiplier of a wide-speed-range hypersonic aircraft, wherein the construction method of the cone guided wave multiplier comprises the following steps:
s11, setting basic parameters of the cone guided wave body, including an upper edge line of the cone guided wave body and a cone shock wave flow field;
s12, projecting the upper edge line to the conical surface of the conical shock wave flow field along the axial direction of the conical shock wave flow field to obtain a leading edge line of the conical guide wave multiplier, wherein the expression of the leading edge line is as follows:
wherein the content of the first and second substances,Ris the bottom circle radius of the conical shock wave flow field,Lis the length of the flow field of the conical shock wave flow field,θis a half cone angle of a conical shock wave flow field,xbeing a leading edge linexThe coordinates of the position of the object to be imaged,y,zrespectively leading edge lineyCoordinates andzcoordinates;
s13, solving according to the leading edge line of the cone-guided wave body and by combining a streamline tracing method to obtain the lower surface of the cone-guided wave body;
s14, obtaining the upper surface of the cone-guided wave body according to the front edge line of the cone-guided wave body and by combining a free flow surface method;
s15, coupling the lower surface obtained in the step S13 with the upper surface obtained in the step S14 to obtain a cone-guided wave;
step 2, passivating the front edge of the cone-guided waverider to obtain a cone-guided waverider with a passivated front edge;
step 3, parameterizing the set original airfoil profile, determining sample point pneumatic parameters of the parameterized airfoil profile, establishing a proxy model by taking the parameterized airfoil profile as input and the sample point pneumatic parameters as output, and optimizing the proxy model by taking the lift-to-drag ratio of the original airfoil profile in supersonic and subsonic cruising states as an optimization target to obtain an optimal airfoil profile;
parameterizing the set original wing profile by adopting a CST method to obtain an expression of the parameterized wing profile as follows:
wherein the content of the first and second substances,ψfor parameterised airfoilsxThe coordinates of the position of the object to be imaged,
for parameterised airfoilsIsyThe coordinates of the position of the object to be imaged,
in the form of a function of the class,N1，N2in order to be a function class parameter,S(ψ)is a shape function;
and 4, establishing a three-dimensional wing according to the optimal wing profile, and coupling the three-dimensional wing with the cone guided wave body with the passivated leading edge obtained in the step 2 to obtain the wide-speed-range hypersonic aircraft.
2. The aerodynamic layout design method of a wide-velocity-range hypersonic aircraft according to claim 1, characterized in that the leading edge of the cone-guided waverider is passivated by a passivation method of increasing volume in step 2.
3. The method for designing the aerodynamic layout of the wide-speed-range hypersonic aircraft according to claim 1, wherein the method for determining the aerodynamic parameters of the sample points of the parameterized airfoil profile in step 3 is as follows:
sampling the parameterized airfoil profile to obtain proxy model sample points, performing grid reconstruction on the proxy model sample points based on the original airfoil profile pneumatic computation grid by using a grid deformation method, and performing numerical simulation on the reconstructed grid to obtain sample point pneumatic parameters of the parameterized airfoil profile.
4. The method for designing the aerodynamic layout of the wide-speed-range hypersonic flight vehicle according to claim 3, wherein in step 3, the parametric airfoil profile is sampled by adopting an LHS method.
5. The method as claimed in claim 3, wherein the mesh deformation method in step 3 is TFI interpolation or RBF interpolation.
6. The method for designing the aerodynamic layout of the wide-speed-range hypersonic aircraft according to claim 1, wherein in step 3, a multi-objective optimization algorithm is adopted to optimize the proxy model, and the airfoil profile with the maximum subsonic lift-drag ratio is obtained as the optimal airfoil profile.
7. A system for performing the wide speed range hypersonic aircraft aerodynamic layout design method of claim 1, comprising,
the wave rider module is used for constructing a cone guided wave rider of the wide-speed-range hypersonic aircraft;
the front edge passivation module is used for passivating the front edge of the cone guided wave multiplier output by the wave multiplier module to obtain a cone guided wave multiplier with a passivated front edge;
the airfoil optimization module is used for parameterizing the set original airfoil, determining sample point pneumatic parameters of the parameterized airfoil, establishing a proxy model by taking the parameterized airfoil as input and the sample point pneumatic parameters as output, and optimizing the proxy model by taking the lift-drag ratio of the original airfoil in supersonic and subsonic cruising states as an optimization target to obtain an optimal airfoil;
and the coupling module is used for establishing a three-dimensional wing according to the optimal wing profile and coupling the three-dimensional wing with the cone guided wave body with the passivated leading edge to obtain the wide-speed-range hypersonic aircraft.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210879045.5A CN114936430B (en) | 2022-07-25 | 2022-07-25 | Wide-speed-range hypersonic aircraft aerodynamic layout design method and system |
| KR1020230017644A KR102616901B1 (en) | 2022-07-25 | 2023-02-09 | Aerodynamic layout design method and system for wide-speed-range hypersonic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210879045.5A CN114936430B (en) | 2022-07-25 | 2022-07-25 | Wide-speed-range hypersonic aircraft aerodynamic layout design method and system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114936430A CN114936430A (en) | 2022-08-23 |
| CN114936430B true CN114936430B (en) | 2022-10-25 |
Family
ID=82868807
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210879045.5A Active CN114936430B (en) | 2022-07-25 | 2022-07-25 | Wide-speed-range hypersonic aircraft aerodynamic layout design method and system |
Country Status (2)
| Country | Link |
|---|---|
| KR (1) | KR102616901B1 (en) |
| CN (1) | CN114936430B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115649417B (en) * | 2022-12-14 | 2023-06-30 | 中国空气动力研究与发展中心空天技术研究所 | High subsonic speed self-balancing high stealth airfoil profile |
| CN116594414B (en) * | 2023-03-28 | 2024-03-15 | 西北工业大学 | Longitudinal control method of hypersonic aircraft |
| CN117669001A (en) * | 2023-12-20 | 2024-03-08 | 中国航空研究院 | Design method of strake wing curved surface for aircraft wide-speed-range lift-increasing drag reduction and curved surface structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043738A (en) * | 2016-06-29 | 2016-10-26 | 中国人民解放军国防科学技术大学 | Design method for wide-speed-range waverider aircraft with equal shock wave flow field and variable mach number |
| CN106364697A (en) * | 2016-11-16 | 2017-02-01 | 中国人民解放军国防科学技术大学 | Wide-speed-domain multistage variant gliding waverider aircraft designing method based on cone-derived theory |
| CN109484623A (en) * | 2018-11-07 | 2019-03-19 | 西北工业大学 | Wide speed domain lift line slope symmetrical airfoil design method and aerofoil profile |
| CN110304267A (en) * | 2019-07-19 | 2019-10-08 | 中国人民解放军国防科技大学 | Hypersonic aircraft design method and system |
| CN114186351A (en) * | 2022-02-14 | 2022-03-15 | 中国科学院力学研究所 | Wave rider configuration design method for wide-speed-range aircraft |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8186616B2 (en) * | 2004-12-21 | 2012-05-29 | Israel Aerospace Industries Ltd. | Hybrid transonic-subsonic aerofoils |
| FR2961601B1 (en) * | 2010-06-22 | 2012-07-27 | Parrot | METHOD FOR EVALUATING THE HORIZONTAL SPEED OF A DRONE, IN PARTICULAR A DRONE SUITABLE FOR AUTOPILOT STATIONARY FLIGHT |
| US11325700B2 (en) * | 2017-07-21 | 2022-05-10 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Hypersonic waverider stream surface actuation for variable design point operation |
| US11535355B2 (en) * | 2020-02-28 | 2022-12-27 | The Boeing Company | Aerodynamic body for supersonic speed |
-
2022
- 2022-07-25 CN CN202210879045.5A patent/CN114936430B/en active Active
-
2023
- 2023-02-09 KR KR1020230017644A patent/KR102616901B1/en active IP Right Grant
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043738A (en) * | 2016-06-29 | 2016-10-26 | 中国人民解放军国防科学技术大学 | Design method for wide-speed-range waverider aircraft with equal shock wave flow field and variable mach number |
| CN106364697A (en) * | 2016-11-16 | 2017-02-01 | 中国人民解放军国防科学技术大学 | Wide-speed-domain multistage variant gliding waverider aircraft designing method based on cone-derived theory |
| CN109484623A (en) * | 2018-11-07 | 2019-03-19 | 西北工业大学 | Wide speed domain lift line slope symmetrical airfoil design method and aerofoil profile |
| CN110304267A (en) * | 2019-07-19 | 2019-10-08 | 中国人民解放军国防科技大学 | Hypersonic aircraft design method and system |
| CN114186351A (en) * | 2022-02-14 | 2022-03-15 | 中国科学院力学研究所 | Wave rider configuration design method for wide-speed-range aircraft |
Non-Patent Citations (9)
| Title |
|---|
| A design approach of wide-speed-range vehicles based on the cone-derived theory;Tian-tian Zhang等;《Aerospace Science and Technology》;20171231;第71卷;全文 * |
| Layout Optimization for Blended Wing Body Aircraft Structure;Zhu Wensheng 等;《International Journal of Aeronautical and Space Sciences》;20191231;全文 * |
| Trim Strategy, Control Model, and Flight Dynamics Characteristics of Canard Rotor/Wing Aircraft in Transition Mode;Honggang Gao等;《IEEE》;20191231;全文 * |
| 乘波布局飞行器宽速域气动特性与研究;王发民等;《中国科学(E辑:技术科学)》;20091120(第11期);全文 * |
| 类乘波体飞行器的气动力工程计算(英文);车竞等;《空气动力学学报》;20070915(第03期);全文 * |
| 高超声速ISR平台乘波外形优化设计及需求验证;《海军航空工程学院学报》;《海军航空工程学院学报》;20190517;全文 * |
| 高超声速锥导乘波体流场的数值模拟研究;赵志等;《弹箭与制导学报》;20091015(第05期);全文 * |
| 高超声速飞行器参数化几何建模研究;高建力等;《计算机仿真》;20080215(第02期);全文 * |
| 高超声速飞行器宽速域翼型/机翼设计与分析;孙祥程等;《航空学报》;20180124(第06期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| KR102616901B1 (en) | 2023-12-27 |
| CN114936430A (en) | 2022-08-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114936430B (en) | Wide-speed-range hypersonic aircraft aerodynamic layout design method and system | |
| Kulfan | Recent extensions and applications of the ‘CST’universal parametric geometry representation method | |
| CN101477710B (en) | Body propelling integrated outer appearance modeling process for supersonic aircraft | |
| US20120166148A1 (en) | Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft | |
| Rodi | The osculating flowfield method of waverider geometry generation | |
| Barabanov et al. | Substantiation of choosing rational appearance of nose of aircraft with the use of mathematical modeling | |
| Zhang et al. | Unsteady aerodynamics of a morphing tandem-wing unmanned aerial vehicle | |
| Feng et al. | A wide-speed-range aerodynamic configuration by adopting wave-riding-strake wing | |
| Roy et al. | Three dimensional rectangular wing morphed to prevent stall and operate at design local two dimensional lift coefficient | |
| CN112926132B (en) | Fixed wing airfoil aerodynamic shape design method considering influence of three-dimensional effect | |
| Abdessemed et al. | Analysis of a 3D unsteady morphing wing with seamless side-edge transition | |
| Buresti et al. | Methods for the drag reduction of bluff bodies and their application to heavy road-vehicles | |
| Julian et al. | Leading edge modification of NACA 0015 and NACA 4415 inspired by beluga whale | |
| Kaygan | Aerodynamic analysis of morphing winglets for improved commercial aircraft performance | |
| CN113626935A (en) | Design method of transonic crescent wing with high cruising efficiency | |
| WO1987007576A1 (en) | Transonic wing design procedure | |
| Hiller et al. | Design Exploration of a Transonic Cruise Slotted Airfoil | |
| Wang et al. | Prediction of Duct Airfoil Aerodynamics using Surface Vorticity | |
| Sutardi et al. | Flow characteristics around a NACA 4412 airfoil in the ground proximity | |
| Maruyama et al. | Aerodynamic design of three-dimensional low wave-drag biplanes using inverse problem method | |
| Liu et al. | Effect of bulging upper surface on waverider performances | |
| Mahmood et al. | Performance comparison of different winglets by CFD | |
| Ali | Aerodynamic characteristics comparison between spiroid and blended winglets | |
| Aljuhashy et al. | Evaluating the effect of unsteady air flow on a slotted aerofoil of wind turbines | |
| Yonezawa et al. | Aerodynamic performance of the three-dimensional lifting supersonic biplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |