CN115437309B - Method and device for generating curved surface transition of aircraft air inlet - Google Patents

Method and device for generating curved surface transition of aircraft air inlet Download PDF

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Publication number
CN115437309B
CN115437309B CN202211061804.3A CN202211061804A CN115437309B CN 115437309 B CN115437309 B CN 115437309B CN 202211061804 A CN202211061804 A CN 202211061804A CN 115437309 B CN115437309 B CN 115437309B
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control point
air inlet
key
spline
inlet channel
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CN115437309A (en
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魏明强
李新
何雪滟
吴梦
许建秋
谭慧俊
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/18—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
    • G05B19/4097—Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using design data to control NC machines, e.g. CAD/CAM
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B2219/00—Program-control systems
    • G05B2219/30—Nc systems
    • G05B2219/32—Operator till task planning
    • G05B2219/32153—Exchange data between user, cad, caq, nc, capp
    • 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

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Abstract

The invention provides a curved surface transition generating method for an aircraft air inletThe method comprises the steps of customizing a B spline type air inlet channel key intercept line and control points and nodes of the air inlet channel key intercept line; the key stubs include an inlet stub, a middle stub, and an outlet stub; c for key section line of air inlet channel 2 Smoothly constraining to obtain the position of a control point of a key section line of the air inlet channel; constructing an air inlet curved surface Laplacian equation according to the position of a control point of an air inlet key section line; calculating the position of a key limit control point according to the Laplacian equation of the curved surface of the air inlet channel; and fitting and transiting the curved surface of the air inlet channel according to the position of the key limit control point. According to the method, the transition curved surface can be obtained only by providing key limit control point information; avoiding conversion into an array point format specified by UG software, directly importing key limit control point information into the UG software, and generating a three-dimensional curved surface according to discrete control points; the direction of the pipeline, the area of each section and the width of the pipeline are precisely controlled.

Description

Method and device for generating curved surface transition of aircraft air inlet
Technical Field
The invention belongs to the technical field of aircraft air inlet design, and particularly relates to a method and a device for generating curved surface transition of an aircraft air inlet.
Background
The air inlet channel is used as a primary component contacted with air flow in the aeroengine, supplies air to the engine according to certain flow, flow speed and distortion, and has the functions of sand prevention, auxiliary stealth and the like. A well-designed aircraft inlet is critical and allows the aircraft to maintain a large angle of attack and sideslip during cruising without interfering with the airflow to the compressor.
The traditional air inlet channel design method is to adjust a basic model based on pilot experience, perform wind tunnel experiments of different parameter combinations to obtain aerodynamic performance data of the air inlet channel under different postures, and finally perform equal proportion air inlet channel test according to test results. However, the design method has the defects that the trend of the pipeline, the area of each section, the width of the pipeline and the like cannot be accurately controlled, and the parameterization is difficult to carry out fine design on the curved surface of the air inlet channel, so that the curved surface of the air inlet channel cannot meet the design and precision requirements.
Disclosure of Invention
The invention provides a method and a device for generating curved surface transition of an aircraft air inlet passage aiming at the defects in the prior art
In a first aspect, the present invention provides a method for generating curved transition of an aircraft air inlet, including:
defining a B spline type air inlet channel key intercept line and control points and nodes of the air inlet channel key intercept line; the key stubs comprise an inlet stub, a middle stub and an outlet stub;
c for the key section line of the air inlet channel 2 Smoothly constraining to obtain the position of a control point of a key section line of the air inlet channel;
constructing an air inlet curved surface Laplacian equation according to the position of a control point of an air inlet key section line;
calculating the position of a key limit control point according to the Laplacian equation of the curved surface of the air inlet channel;
and fitting and transiting the curved surface of the air inlet channel according to the position of the key limit control point.
Further, the critical section line of the air inlet channel is C 2 The smooth constraint, obtain the control point position of the key section line of the air inlet channel, include:
the degree of a key section curve of an air inlet channel is improved, the degree of a p-degree B spline curve with N control points is doubled, and N=2n+2 control points and m=n+p+1 node vectors are obtained;
c, according to the initial control point and the end control point of the key section line of the air inlet channel after the curve degree is increased 2 Smooth constraint:
wherein C' (0) is the first derivative of the starting control point; c' (0) is the second derivative of the starting control point; c' (1) is endingA first derivative of the control point; c' (1) is the second derivative of the ending control point; given n+1 control points are P 0 ，P 1 ，P 2 ，...，P n ；P 0 A value that is the starting control point; p (P) n A value that is an end control point; u (u) p+1 P+1st node; p (P) n-1 A value of the n-1 th control point;is P 0 Is a second derivative of (2); />Is P 2 Is the zero-order derivative of (2); />Is P 0 Is the first derivative of (a); p (P) 1 (1) Is P 1 Is the first derivative of (a); />Is P 0 Is the zero-order derivative of (2); p (P) 1 (0) Is P 1 Is a zero-order derivative of (c).
Further, the constructing the laplace equation of the curved surface of the air inlet according to the position of the control point of the key section line of the air inlet includes:
construction of B-spline parameter DomainTo physical Domain->Parameter mapping:
wherein, if d is 1, the parameter range of the B spline curve is (0, 1), and if d is 2, the parameter range of the B spline curve is the rectangular area (0, 1) formed together 2 ；Is a B spline function expression, which corresponds tou is the range of nodes in the direction of the B-spline surface row, i.e., Ω=C (u), +.>U is; c (u) andall are B spline function expressions; n (N) i,p (u) is a bernstein basis function; p (P) i Is the value of the ith control point; span is the space that is stretched;
constructing a B spline surface S (u, v):
the physical domain and the parameter domain of the B-spline surface S (u, v) are the same, namelyConstructing a Laplacian equation of the B spline surface S (u, v) in a physical domain omega, and taking a key intercept as a Dirichlet boundary condition:
v is the range of nodes in the direction of the B spline surface column; c (C) 1 (u)、C 2 (u)、C 3 (u) and C 4 (u) B-spline forms of key stubs, respectively;and->Respectively four stripsThe boundary line takes a value.
In a second aspect, the present invention provides an aircraft inlet curved transition generating device, including:
the self-defining module is used for self-defining the key cut-off line of the air inlet channel in the form of B spline and the control point and node of the key cut-off line of the air inlet channel; the key stubs comprise an inlet stub, a middle stub and an outlet stub;
a smooth constraint module for performing C on the key intercept line of the air inlet channel 2 Smoothly constraining to obtain the position of a control point of a key section line of the air inlet channel;
the construction module is used for constructing an air inlet curved surface Laplacian equation according to the position of the control point of the key intercept of the air inlet;
the calculation module is used for calculating the position of the key limit control point according to the Laplacian equation of the curved surface of the air inlet channel;
and the fitting transition module is used for performing fitting transition on the curved surface of the air inlet channel according to the position of the key limit control point.
Further, the smoothness constraint module includes:
the curve degree increasing unit is used for increasing the degree of the key section curve of the air inlet channel, and increasing the degree of the p times of B spline curve with N control points by one time to obtain n=2n+2 control points and m=n+p+1 node vectors;
the smooth constraint unit is used for carrying out C according to the initial control point and the final control point of the key intercept of the air inlet channel after the curve degree is increased 2 Smooth constraint:
wherein C' (0) is the first derivative of the starting control point; c' (0) is the second derivative of the starting control point; c' (1) is the first derivative of the ending control point; c' (1) is the second derivative of the ending control point; given n+1 control points are P 0 ，P 1 ，P 2 ，...，P n ；P 0 A value that is the starting control point; p (P) n A value that is an end control point; u (u) p+1 P+1st node; p (P) n-1 A value of the n-1 th control point;is P 0 Is a second derivative of (2); />Is P 2 Is the zero-order derivative of (2); />Is P 0 Is the first derivative of (a); p (P) 1 (1) Is P 1 Is the first derivative of (a); />Is P 0 Is the zero-order derivative of (2); p (P) 1 (0) Is P 1 Is a zero-order derivative of (c).
Further, the building module includes:
a first construction unit for constructing B-spline parameter domainTo physical Domain->Parameter mapping:
wherein, if d is 1, the parameter range of the B spline curve is (0, 1), and if d is 2, the parameter range of the B spline curve is the rectangular area (0, 1) formed together 2 ；Is a B spline function expression, which corresponds tou is the line of B-spline surfacesThe range of nodes in the direction, i.e., Ω=c (u), j->U is; c (u) andall are B spline function expressions; n (N) i,p (u) is a bernstein basis function; p (P) i Is the value of the ith control point; span is the space that is stretched;
a second construction unit for constructing a B-spline surface S (u, v):
a third construction unit for generating a B-spline surface S (u, v) with the same physical domain and parameter domain, i.eUnder the condition of (a), constructing a Laplace equation of the B spline surface S (u, v) in a physical domain omega, and taking a key intercept line as a Dirichlet boundary condition:
v is the range of nodes in the direction of the B spline surface column; c (C) 1 (u)、C 2 (u)、C 3 (u) and C 4 (u) B-spline forms of key stubs, respectively;and->And respectively take values for four boundary lines.
The invention provides a method and a device for generating transition of an aircraft air inlet curved surface, wherein the method comprises the steps of customizing an air inlet key intercept line in a B spline form, and controlling points and control points of the air inlet key intercept lineA node; the key stubs comprise an inlet stub, a middle stub and an outlet stub; c for the key section line of the air inlet channel 2 Smoothly constraining to obtain the position of a control point of a key section line of the air inlet channel; constructing an air inlet curved surface Laplacian equation according to the position of a control point of an air inlet key section line; calculating the position of a key limit control point according to the Laplacian equation of the curved surface of the air inlet channel; and fitting and transiting the curved surface of the air inlet channel according to the position of the key limit control point. According to the method, the transition curved surface can be obtained only by providing key limit control point information; avoiding conversion into an array point format specified by UG software, directly importing key limit control point information into the UG software, and generating a three-dimensional curved surface according to discrete control points; and the parameterization is adopted to carry out fine design on the curved surface of the air inlet channel, and the trend of the pipeline, the area of each section and the width of the pipeline are precisely controlled.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it will be obvious to those skilled in the art that other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a flow chart of a method for generating curved transition of an aircraft inlet according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of an aircraft air inlet curved surface transition generation method according to an embodiment of the present invention;
FIG. 3 is a block diagram of a B-spline closed curve C according to an embodiment of the present invention 2 Smooth flow diagram intent;
FIG. 4 is a schematic diagram of mapping parameter domain to physical isoparameter according to an embodiment of the present invention;
FIG. 5 is a graph of the boundary condition results of Dirichlet based on B-spline form provided by an embodiment of the present invention;
FIG. 6 is a schematic diagram of the calculation result of the Laplace equation according to the embodiment of the present invention;
fig. 7 is a schematic structural diagram of an aircraft inlet curved transition generating device according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 and fig. 2, an embodiment of the present invention provides a method for generating curved transition of an aircraft air intake duct, including:
step 101, customizing a B spline type air inlet channel key intercept line and control points and nodes of the air inlet channel key intercept line; the critical stubs include an inlet stub, a middle stub, and an outlet stub.
The control points and nodes of the inlet and middle stubs and the control points and nodes of the outlet stubs are custom B-spline form.
102, performing C on the key intercept line of the air inlet channel 2 And (5) carrying out smooth constraint to obtain the position of a control point of the key section line of the air inlet channel.
As shown in fig. 3, the inlet key-section curve degree is increased, i.e., the curve degree of the inlet section, the middle section, and the outlet section is increased. The degree of the (p+1 order) p-th order B spline curve with N control points is doubled, and N=2n+2 control points and m=n+p+1 node vectors are obtained.
C, according to the initial control point and the end control point of the key section line of the air inlet channel after the curve degree is increased 2 Smooth constraint:
wherein C' (0) is the first derivative of the starting control point; c' (0) is the second derivative of the starting control point; c' (1) is the first derivative of the ending control point; c' (1) is the second derivative of the ending control point; given n+1 control points are P 0 ，P 1 ，P 2 ，...，P n ；P 0 A value that is the starting control point; p (P) n A value that is an end control point; u (u) p+1 P+1st node; p (P) n-1 A value of the n-1 th control point;is P 0 Is a second derivative of (2); />Is P 2 Is the zero-order derivative of (2); />Is P 0 Is the first derivative of (a); p (P) 1 (1) Is P 1 Is the first derivative of (a); />Is P 0 Is the zero-order derivative of (2); p (P) 1 (0) Is P 1 Is a zero-order derivative of (c).
And step 103, constructing an air inlet curved surface Laplacian equation according to the position of the control point of the key section line of the air inlet.
Constructing B-spline parameter domains as shown in FIG. 4To physical Domain->Parameter mapping:
wherein, if d is 1, the parameter range of the B spline curve is (0, 1), and if d is 2, the parameter range of the B spline curve is the rectangular area (0, 1) formed together 2 ；For B-splineThe functional expression corresponds tou is the range of nodes in the direction of the B-spline surface row, i.e., Ω=C (u), +.>U is; c (u) andall are B spline function expressions; n (N) i,p (u) is a bernstein basis function; p (P) i Is the value of the ith control point; span is the space that is stretched; b spline function->Is N i,p (u) according to P i For linear combination of weight values, i.e. B-spline function N i,p (u) tensed corresponding function space.
Constructing a B spline surface S (u, v):
the physical domain and the parameter domain of the B-spline surface S (u, v) are the same, namelyAs shown in fig. 5, a laplace equation of the B-spline surface S (u, v) in the physical domain Ω is constructed, and the key intercept is taken as the dirichlet boundary condition:
v is the range of nodes in the direction of the B spline surface column; c (C) 1 (u)、C 2 (u)、C 3 (u) and C 4 (u) B-spline forms of key stubs, respectively;and->And respectively take values for four boundary lines.
And 104, calculating the position of a key limit control point according to the Laplacian equation of the curved surface of the air inlet channel.
And 105, performing fitting transition on the curved surface of the air inlet channel according to the positions of the key limit control points.
As shown in fig. 6, key limit control point positions are obtained, modeling is performed by using UG software, and fitting transition is performed on the curved surface of the air inlet channel.
Based on the same inventive concept, the embodiment of the invention also provides an aircraft air inlet curved surface transition generating device, and because the principle of solving the problem of the device is similar to that of the aircraft air inlet curved surface transition generating method, the implementation of the device can refer to the implementation of the aircraft air inlet curved surface transition generating method, and the repetition is omitted.
An embodiment of the present invention provides an aircraft air inlet curved surface transition generating device, as shown in fig. 7, including:
the self-defining module 10 is used for self-defining the inlet channel key intercept line in the form of B spline and the control point and node of the inlet channel key intercept line; the critical stubs include an inlet stub, a middle stub, and an outlet stub.
A smoothness constraint module 20 for performing C on the key section line of the air inlet 2 And (5) carrying out smooth constraint to obtain the position of a control point of the key section line of the air inlet channel.
The construction module 30 is configured to construct a laplace equation of the curved surface of the air inlet according to the position of the control point of the key intercept of the air inlet.
The calculating module 40 is configured to calculate the position of the critical limit control point according to the laplace equation of the curved surface of the air inlet.
The fitting transition module 50 is configured to perform fitting transition on the curved surface of the air inlet according to the position of the key limit control point.
Optionally, the smoothness constraint module includes:
the curve degree increasing unit is used for increasing the degree of the key section curve of the air inlet channel, and increasing the degree of the p times of B spline curve with N control points by one time to obtain n=2n+2 control points and m=n+p+1 node vectors;
the smooth constraint unit is used for carrying out C according to the initial control point and the final control point of the key intercept of the air inlet channel after the curve degree is increased 2 Smooth constraint:
wherein C' (0) is the first derivative of the starting control point; c' (0) is the second derivative of the starting control point; c' (1) is the first derivative of the ending control point; c' (1) is the second derivative of the ending control point; given n+1 control points are P 0 ，P 1 ，P 2 ，...，P n ；P 0 A value that is the starting control point; p (P) n A value that is an end control point; u (u) p+1 P+1st node; p (P) n-1 A value of the n-1 th control point;is P 0 Is a second derivative of (2); />Is P 2 Is the zero-order derivative of (2); />Is P 0 Is the first derivative of (a); p (P) 1 (1) Is P 1 Is the first derivative of (a); />Is P 0 Is the zero-order derivative of (2); p (P) 1 (0) Is P 1 Is a zero-order derivative of (c).
Optionally, the building module includes:
a first construction unit for constructing B-spline parameter domainTo physical Domain->Parameter mapping:
wherein, if d is 1, the parameter range of the B spline curve is (0, 1), and if d is 2, the parameter range of the B spline curve is the rectangular area (0, 1) formed together 2 ；Is a B spline function expression, which corresponds tou is the range of nodes in the direction of the B-spline surface row, i.e., Ω=C (u), +.>U is; c (u) andall are B spline function expressions; n (N) i,p (u) is a bernstein basis function; p (P) i Is the value of the ith control point; span is the space that is stretched;
a second construction unit for constructing a B-spline surface S (u, v):
a third construction unit for generating a B-spline surface S (u, v) with the same physical domain and parameter domain, i.eIn the case of (a), constructing a Laplace equation of the B-spline surface S (u, v) in the physical domain omega, andthe critical intercept line serves as a dirichlet boundary condition:
v is the range of nodes in the direction of the B spline surface column; c (C) 1 (u)、C 2 (u)、C 3 (u) and C 4 (u) B-spline forms of key stubs, respectively;and->And respectively take values for four boundary lines.
For more specific working procedures of the above modules, reference may be made to the corresponding contents disclosed in the foregoing embodiments, and no further description is given here.
The invention has been described in detail in connection with the specific embodiments and exemplary examples thereof, but such description is not to be construed as limiting the invention. It will be understood by those skilled in the art that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, and these fall within the scope of the present invention. The scope of the invention is defined by the appended claims.

Claims (2)

1. The method for generating the curved surface transition of the air inlet passage of the aircraft is characterized by comprising the following steps of:
101, customizing control points and nodes of an inlet channel key intercept line and an inlet channel key intercept line in a B spline form; the key stubs comprise an inlet stub, a middle stub and an outlet stub;
102, performing C on the key intercept line of the air inlet channel 2 Smoothly constraining to obtain the position of a control point of a key section line of the air inlet channel;
103, constructing an air inlet curve Laplacian equation according to the position of a control point of an air inlet key section line;
104, calculating the position of a key limit control point according to the Laplacian equation of the curved surface of the air inlet channel;
105, fitting and transiting the curved surface of the air inlet channel according to the position of the key limit control point;
wherein step 102 comprises:
the degree of a key section curve of an air inlet channel is improved, the degree of a p-degree B spline curve with N control points is doubled, and N=2n+2 control points and m=n+p+1 node vectors are obtained;
c, according to the initial control point and the end control point of the key section line of the air inlet channel after the curve degree is increased 2 Smooth constraint:
wherein C' (0) is the first derivative of the starting control point; c' (0) is the second derivative of the starting control point; c' (1) is the first derivative of the ending control point; c' (1) is the second derivative of the ending control point; given n+1 control points are P 0 ，P 1 ，P 2 ，...，P n ；P 0 A value that is the starting control point; p (P) n A value that is an end control point; u (u) p+1 P+1st node; p (P) n-1 A value of the n-1 th control point;is P 0 Is a second derivative of (2); />Is P 2 Is the zero-order derivative of (2); />Is P 0 Is the first derivative of (a); p (P) 1 (1) Is P 1 Is the first derivative of (a); />Is P 0 Is the zero-order derivative of (2); p (P) 1 (0) Is P 1 Is the zero-order derivative of (2);
step 103 comprises:
construction of B-spline parameter DomainTo physical Domain-> Parameter mapping:
wherein, if d is 1, the parameter range of the B spline curve is (0, 1), and if d is 2, the parameter range of the B spline curve is the rectangular area (0, 1) formed together 2 ；Is a B spline function expression, which corresponds to +.>u is the range of nodes in the direction of the B-spline surface row, i.e., Ω=C (u), +.>U is; c (u) and->All are B spline function expressions; n (N) i,p (u) is a bernstein basis function; p (P) i Is the value of the ith control point; span is the space that is stretched;
constructing a B spline surface S (u, v):
the physical domain and the parameter domain of the B-spline surface S (u, v) are the same, namelyConstructing a Laplacian equation of the B spline surface S (u, v) in a physical domain omega, and taking a key intercept as a Dirichlet boundary condition:
v is the range of nodes in the direction of the B spline surface column; c (C) 1 (u)、C 2 (u)、C 3 (u) and C 4 (u) B-spline forms of key stubs, respectively;and->And respectively take values for four boundary lines.
2. The utility model provides an aircraft intake duct curved surface transition generation device which characterized in that includes:
the self-defining module is used for self-defining the key cut-off line of the air inlet channel in the form of B spline and the control point and node of the key cut-off line of the air inlet channel; the key stubs comprise an inlet stub, a middle stub and an outlet stub;
a smooth constraint module for performing C on the key intercept line of the air inlet channel 2 Smoothly constraining to obtain the position of a control point of a key section line of the air inlet channel;
the construction module is used for constructing an air inlet curved surface Laplacian equation according to the position of the control point of the key intercept of the air inlet;
the calculation module is used for calculating the position of the key limit control point according to the Laplacian equation of the curved surface of the air inlet channel;
the fitting transition module is used for performing fitting transition on the curved surface of the air inlet channel according to the position of the key limit control point;
wherein, smooth constraint module includes:
the curve degree increasing unit is used for increasing the degree of the key section curve of the air inlet channel, and increasing the degree of the p times of B spline curve with N control points by one time to obtain n=2n+2 control points and m=n+p+1 node vectors;
the smooth constraint unit is used for carrying out C according to the initial control point and the final control point of the key intercept of the air inlet channel after the curve degree is increased 2 Smooth constraint:
wherein C' (0) is the first derivative of the starting control point; c' (0) is the second derivative of the starting control point; c' (1) is the first derivative of the ending control point; c' (1) is the second derivative of the ending control point; given n+1 control points are P 0 ，P 1 ，P 2 ，...，P n ；P 0 A value that is the starting control point; p (P) n A value that is an end control point; u (u) p+1 P+1st node; p (P) n-1 A value of the n-1 th control point;is P 0 Is a second derivative of (2); />Is P 2 Is the zero-order derivative of (2); />Is P 0 Is the first derivative of (a); p (P) 1 (1) Is P 1 Is the first derivative of (a); />Is P 0 Is the zero-order derivative of (2); p (P) 1 (0) Is P 1 Is the zero-order derivative of (2);
the construction module comprises:
a first construction unit for constructing B-spline parameter domainTo physical Domain-> Parameter mapping:
wherein, if d is 1, the parameter range of the B spline curve is (0, 1), and if d is 2, the parameter range of the B spline curve is the rectangular area (0, 1) formed together 2 ；Is a B spline function expression, which corresponds to +.>u is the range of nodes in the direction of the B-spline surface row, i.e., Ω=C (u), +.>U is; c (u) and->All are B spline function expressions; n (N) i,p (u) is a bernstein basis function; p (P) i Is the value of the ith control point; span is the space that is stretched;
a second construction unit for constructing a B-spline surface S (u, v):
a third construction unit for generating a B-spline surface S (u, v) with the same physical domain and parameter domain, i.eUnder the condition of (a), constructing a Laplace equation of the B spline surface S (u, v) in a physical domain omega, and taking a key intercept line as a Dirichlet boundary condition:
v is the range of nodes in the direction of the B spline surface column; c (C) 1 (u)、C 2 (u)、C 3 (u) and C 4 (u) B-spline forms of key stubs, respectively;and->And respectively take values for four boundary lines.
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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101229849A (en) * 2007-12-28 2008-07-30 北京航空航天大学 Intake oblique cut inlet and method for designing the same
CN110211201A (en) * 2019-05-07 2019-09-06 北京航空航天大学 A kind of B-spline surface method for reconstructing
CN111460716A (en) * 2020-04-01 2020-07-28 江苏理工学院 B-spline free-form surface part structure lightweight method based on genetic algorithm
CN114781078A (en) * 2022-03-11 2022-07-22 南京航空航天大学 Stealth snakelike air inlet channel design method based on matrix transformation

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101229849A (en) * 2007-12-28 2008-07-30 北京航空航天大学 Intake oblique cut inlet and method for designing the same
CN110211201A (en) * 2019-05-07 2019-09-06 北京航空航天大学 A kind of B-spline surface method for reconstructing
CN111460716A (en) * 2020-04-01 2020-07-28 江苏理工学院 B-spline free-form surface part structure lightweight method based on genetic algorithm
CN114781078A (en) * 2022-03-11 2022-07-22 南京航空航天大学 Stealth snakelike air inlet channel design method based on matrix transformation

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
复杂变截面进气道的一种设计方法;周慧晨等;航空动力学报;第24卷(第6期);1357-1363 *

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