CN110990951A - Helicopter appearance design method - Google Patents
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Abstract
The invention belongs to the field of helicopter appearance and discloses a helicopter appearance design method, which comprises the following steps: determining the primary shape of the maximum longitudinal section contour line and the cross section contour line of the helicopter profile, and determining the initial parameter matrix t of the maximum longitudinal section contour line1And an initial parameter matrix t of the cross-sectional profile2(ii) a According to the main intersection data of the helicopter and the constraint function Y of the helicopter profileSAnd constraint matrix t of helicopter profileS(ii) a Calculating the aerodynamic characteristics of the initial shape of the helicopter and establishing a helicopter shape optimization proxy model; obtaining an optimized parameter matrix t of the maximum longitudinal section contour line1OAnd an optimized parameter matrix t of the cross-sectional profile2O(ii) a Solving a type function, a contour function and a main function of the optimized helicopter appearance, and further drawing a final helicopter appearance; can accurately represent the theoretical appearance of the helicopter, shorten the period of appearance design, save cost and improve the engineering qualityIn the design, the method has great application advantages.
Description
Technical Field
The invention relates to the field of helicopter appearance, in particular to a helicopter appearance design method.
Background
At present, the theoretical appearance of a helicopter is usually designed by adopting CATIA software, and the preliminary theoretical appearance is modified and perfected by combining CFD calculation analysis results and helicopter model wind tunnel test results, but the wind tunnel test has high cost and long period, and the obtained optimal appearance of the helicopter is not necessarily the optimal appearance of the helicopter. The parameterized rapid design of the theoretical appearance of the helicopter is very necessary.
Disclosure of Invention
Aiming at the problems of the background art, the invention aims to provide a helicopter appearance design method, which improves the helicopter appearance design precision, obtains the appearance meeting the constraint condition in a short time and saves the development cost.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
A helicopter profile design method, said method comprising:
the first step is as follows: determining the primary Shape of the maximum longitudinal section contour line and the cross section contour line of the helicopter Shape, and determining the initial parameter matrix t of the maximum longitudinal section contour line by adopting a CST (Class-Shape-Transformation) parameterization method1And an initial parameter matrix t of the cross-sectional profile2；
The second step is that: determining a constraint function Y of the helicopter profile according to the main intersection data of the helicopterSAnd constraint matrix t of helicopter profileS；
The third step: determining the initial shape of the helicopter according to the initial shapes of the maximum longitudinal section contour line and the cross section contour line, and calculating the aerodynamic characteristics of the initial shape of the helicopter;
the fourth step: establishing a helicopter appearance optimization proxy model;
the fifth step: initial parameter matrix t according to maximum longitudinal section contour line1Initial parameter matrix t of cross section contour line2Constraint function Y of helicopter profileSAnd a constraint matrix tSAnd the helicopter appearance optimization proxy model obtains the optimization parameters of the maximum longitudinal section contour line by adopting a genetic optimization algorithmMatrix t1OAnd an optimized parameter matrix t of the cross-sectional profile2O；
And a sixth step: optimization parameter matrix t according to maximum longitudinal section contour line1OAnd an optimized parameter matrix t of the cross-sectional profile2OSolving a type function, a profile function and a main function of the optimized helicopter appearance by adopting a CST parameterization method, and further drawing the final helicopter appearance; the type function is used for representing the symmetry of the helicopter appearance, the contour function is used for representing the contour line shape of the helicopter appearance, and the main function is used for representing the overall characteristics of the helicopter appearance.
The technical scheme of the invention has the characteristics and further improvements that:
(a) the second step is specifically as follows:
(1) determining intersection point data of a rotor system, a transmission system, a power system and an undercarriage of the helicopter;
(2) determining a constraint function Y of the shape of the helicopter according to intersection point data of a rotor system, a transmission system, a power system and an undercarriage of the helicopterSAnd constraint matrix t of helicopter profileS。
(b) The third step is specifically:
(1) determining the initial shape of the helicopter according to the initial shapes of the maximum longitudinal section contour line and the cross section contour line, and drawing the initial shape of the helicopter by adopting a generative curved surface design module in CATIA software;
(2) and calculating the aerodynamic characteristics of the initial profile of the helicopter by using CFD (computational Fluid dynamics) aerodynamic calculation software.
(c) The fourth step is specifically as follows:
(1) constraint function Y in helicopter formSAnd constraint matrix t of helicopter profileSWithin the range of (3), constructing a sample design set P of the appearance of the helicopter; the sample design set P comprises various helicopter appearances and a parameter matrix corresponding to each helicopter appearance;
(2) calculating the aerodynamic characteristics of each helicopter shape in the sample design set P by adopting CFD;
(3) and establishing a helicopter shape optimization proxy model according to the various helicopter shapes, the parameter matrix corresponding to each helicopter shape and the aerodynamic characteristics of each helicopter shape.
(d) The CST parameterization method in the first step comprises the following steps:
(1) defining a constraint function YSAnd type function
And defining a contour function S (lambda) by adopting a weighted sum of m-order polynomials;
(2) according to a constraint function YSAnd type function
And the contour function S (lambda) calculates a parameter matrix t;
wherein, λ is x/f, x is the horizontal axis coordinate of the outline point of the helicopter, M1And M2A range of types characterizing the outline profile.
(e) Constraint function YSThe method specifically comprises the following steps: y iss＝Y(λ)
And λ is x/f, x is the horizontal axis coordinate of the helicopter outline point, and f is the length of the helicopter outline.
(f) Type function
Comprises the following steps:
wherein M is1And M2A range of types characterizing the outline profile.
(g) The contour function S (λ) is defined using a weighted sum of m-th order polynomials:
where t ═ tiAnd (i ═ 0, 1, …, m) } is a parameter matrix of the profile function S (λ), and m is the order of the parameter matrix t.
(h) According to a constraint function YSAnd type function
And the contour function S (lambda) calculates a parameter matrix t, which is specifically as follows:
t＝(t0,t1,…,tm)
(t0,t1,…,tm)＝(ε(λ0),ε(λ1),…,ε(λm))·G＝(ε(x0/f),ε(x1/f),…,ε(xm/f))·G
the physical meaning of ε (λ) is the ratio of the ordinate y of the helicopter outline point to the length f of the helicopter outline, (x)0,x1,…,xm) The horizontal axis coordinate of m +1 points on the outline of the helicopter is represented;
and delta epsilon is the thickness step difference value of the tail part of the helicopter.
The invention has the beneficial effects that: the invention adopts a CST parameterization method, combines constraint conditions of overall arrangement and aerodynamic characteristics, carries out parameterization design on the appearance of the helicopter, and can accurately draw the shapes of the maximum longitudinal section contour line and the cross section contour line of the helicopter to obtain the optimized appearance of the helicopter; on the basis of CST parameterization method, a constraint function Y is addedSThe method can accurately represent the theoretical appearance of the helicopter, shorten the period of appearance design, save the cost and have great application advantages in engineering design.
Drawings
FIG. 1 is a schematic diagram of a maximum longitudinal section profile provided by an embodiment of the present invention;
FIG. 2 is a schematic illustration of a cross-sectional profile provided by an embodiment of the present invention;
fig. 3 is a schematic view of a CST parameterized form design process according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
A method for designing the shape of helicopter with accurate CST parameterization features that the CST parameterization method and the constraint function Y of helicopter are usedSCoupling, designing main characteristic contour lines of the helicopter, and combining CATIA software to carry out parametric modeling on the outline curved surface of the helicopter. In the CST parameterization method, a type function is mainly used
A contour function S (lambda) and a main function epsilon (lambda), and a constraint function Y is defined according to the constraint condition of the overall arrangement of the helicopterS。
Ys＝Y(λ)
λ＝x/f
Wherein x is the coordinate of the horizontal axis of the outline point, y is the coordinate of the vertical axis of the outline point, f is the length of the outline, and Delta epsilon is the thickness step value of the tail part of the outline.
Defining type functions
As follows:
wherein M is1And M2A range of types characterizing the outline profile.
Defining a profile function S (λ) using a weighted sum of m-th order polynomials:
where t ═ tiAnd (i ═ 0, 1, …, m) } is a parameter matrix of the profile function S (λ), and m is the order of the parameter matrix t.
The parameter matrix t ═ t (t) is obtained by the following matrix equation0,t1,…,tm)：
(t0,t1,…,tm)＝(ε(λ0),ε(λ1),…,ε(λm))·G＝(ε(x0/f),ε(x1/f),…,ε(xm/f))·G
The method comprises the following steps:
the first step is as follows: determining the initial parameter matrix t of the maximum longitudinal section contour line, the preliminary shape of the cross section contour line and the maximum longitudinal section contour line of the helicopter profile1And an initial parameter matrix t of the cross-sectional profile2。
① the maximum longitudinal section contour shape of the helicopter profile is designed by CST parameterization method, see figure 1.
② the cross-sectional contour of the helicopter profile is designed using the CST parameterization method, see FIG. 2.
The second step is that: determining a constraint function Y of a helicopter profileSAnd constraint matrix t of helicopter profileS。
① determining the principal intersection data of the helicopter;
the distance between the rotor blade and the tail rotor blade of the helicopter is determined by combining the rotor blade disc load, the rotor diameter, the rotor tip speed, the rotor blade number, the rotor solidity, the rotor blade chord length, the rotor shaft forward rake angle, the tail rotor blade disc load, the tail rotor diameter, the tail rotor tip speed, the tail rotor blade number, the tail rotor solidity and the tail rotor blade chord length of the helicopter, so that intersection point data of a rotor system, a transmission system and a power system of the helicopter are obtained.
And determining intersection point data of the landing gear of the helicopter by combining a front shroud angle, a longitudinal wheel track, longitudinal distances from the front wheels and the main wheels to the gravity center, a transverse wheel track and a side shroud angle of the helicopter.
② determining constraint function Y of helicopter configuration according to intersection data of helicopter rotor system, transmission system, power system and landing gearSAnd constraint matrix t of helicopter profileS；
Constraint matrix t of helicopter profileS＝(tSZ,tSL,tSW,tSQ)；
Determining a constraint matrix t according to the requirements of overall arrangement of the helicopterSZSatisfy tSZMIN≤tSZ≤tSZMAXWherein t isSZMINLower limit, t, required for overall helicopter layoutSZMAXThe upper limit required for overall arrangement of the helicopter;
determining a constraint matrix t according to the ground clearance requirement of the helicopterSLSatisfy tSLMIN≤tSL≤tSLMAXWherein t isSLMINLower limit for helicopter ground clearance requirement, tSLMAXAn upper limit for helicopter ground clearance requirements;
determining a constraint matrix t according to the requirement of the appearance shape of the helicopterSWSatisfy tSWMIN≤tSW≤tSWMAXWherein t isSWMINLower limit, t, for the design of helicopterSWMAXThe upper limit of the helicopter appearance modeling requirement is set;
determining a constraint matrix t according to the requirements of the aerodynamic characteristics of the helicopterSQSatisfy tSQMIN≤tSQ≤tSQMAXWherein t isSQMINLower limit for the aerodynamic characteristics of the helicopter, tSQMAXThe upper limit of the requirements for the aerodynamic characteristics of the helicopter;
constraint function of helicopter profile
Where v is the order of the constraint function of the helicopter profile.
The third step: determining the aerodynamic characteristics of the initial profile of the helicopter.
① determining the initial shape of the helicopter according to the initial shapes of the maximum longitudinal section contour line and the cross section contour line;
and according to the preliminary shapes of the maximum longitudinal section contour line and the cross section contour line determined in the first step, drawing the initial appearance of the helicopter by adopting a generative curved surface design module in CATIA software.
② use CFD to calculate the aerodynamic properties of the initial profile.
The fourth step: and establishing a helicopter appearance optimization proxy model.
① constraint function Y in helicopter formSAnd constraint matrix t of helicopter profileSWithin the range of (3), constructing a sample design set P of the appearance of the helicopter; the sample design set P comprises various helicopter appearances and a parameter matrix corresponding to each helicopter appearance;
② calculating aerodynamic characteristics of each helicopter configuration in the sample design set P using CFD;
③, establishing a helicopter shape optimization proxy model according to the various helicopter shapes and the parameter matrix corresponding to each helicopter shape and the aerodynamic characteristics of each helicopter shape.
Specifically, a helicopter shape optimization proxy model is established by combining ISIGHT platform optimization software according to various helicopter shapes and parameter matrixes corresponding to the helicopter shapes and the aerodynamic characteristics of the helicopter shapes.
The fifth step: initial parameter matrix t according to maximum longitudinal section contour line1Initial parameter matrix t of cross section contour line2Constraint function Y of helicopter profileSAnd a constraint matrix tSAnd the helicopter appearance optimization proxy model obtains the optimization parameter matrix t of the maximum longitudinal section contour line by adopting a genetic optimization algorithm1OAnd an optimized parameter matrix t of the cross-sectional profile2O。
And a sixth step: optimization parameter matrix t according to maximum longitudinal section contour line1OAnd an optimized parameter matrix t of the cross-sectional profile2OSolving a type function, a profile function and a main function of the optimized helicopter appearance by adopting a CST parameterization method, and further drawing the final helicopter appearance; the type function is used for representing the symmetry of the helicopter appearance, the contour function is used for representing the contour line shape of the helicopter appearance, and the main function is used for representing the overall characteristics of the helicopter appearance.
The invention adopts a CST parameterization method and combines a constraint function Y of the helicopter appearanceSAnd constraint matrix t of helicopter profileSThe method has the advantages that the parameterized design is carried out on the appearance of the helicopter, the shapes of the maximum longitudinal section contour line and the maximum cross section contour line of the helicopter can be accurately drawn, the optimized appearance of the helicopter is obtained, the period of appearance design is shortened, the cost is saved, and the method has great application advantages in engineering design.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A helicopter profile design method, said method comprising:
the first step is as follows: determining the initial shape of the maximum longitudinal section contour line and the cross section contour line of the helicopter profile, and determining the initial parameter matrix t of the maximum longitudinal section contour line by adopting a CST parameterization method1And an initial parameter matrix t of the cross-sectional profile2；
The second step is that: determining a constraint function Y of the shape of the helicopter according to intersection point data of the helicopterSAnd constraint matrix t of helicopter profileS；
The third step: determining the initial shape of the helicopter according to the initial shapes of the maximum longitudinal section contour line and the cross section contour line, and calculating the aerodynamic characteristics of the initial shape of the helicopter;
the fourth step: establishing a helicopter appearance optimization proxy model;
the fifth step: initial parameter matrix t according to maximum longitudinal section contour line1Initial parameter matrix t of cross section contour line2Constraint function Y of helicopter profileSAnd a constraint matrix tSAnd the helicopter appearance optimization proxy model obtains the optimization parameter matrix t of the maximum longitudinal section contour line by adopting a genetic optimization algorithm1OAnd an optimized parameter matrix t of the cross-sectional profile2O；
And a sixth step: optimization parameter matrix t according to maximum longitudinal section contour line1OAnd an optimized parameter matrix t of the cross-sectional profile2OSolving a type function, a profile function and a main function of the optimized helicopter appearance by adopting a CST parameterization method, and further drawing the final helicopter appearance; the type function is used for representing the symmetry of the helicopter appearance, the contour function is used for representing the contour line shape of the helicopter appearance, and the main function is used for representing the overall characteristics of the helicopter appearance.
2. A helicopter profile design method according to claim 1, characterized in that the second step is specifically:
(1) determining intersection point data of a rotor system, a transmission system, a power system and an undercarriage of the helicopter;
(2) according to the rotor system of a helicopter,Determining the constraint function Y of the helicopter profile from the intersection data of the transmission system, the power system and the landing gearSAnd constraint matrix t of helicopter profileS。
3. A helicopter profile design method according to claim 1, characterized by the third step specifically being:
(1) determining the initial shape of the helicopter according to the initial shapes of the maximum longitudinal section contour line and the cross section contour line, and drawing the initial shape of the helicopter by adopting a generative curved surface design module in CATIA software;
(2) and calculating the aerodynamic characteristics of the initial profile of the helicopter by using CFD aerodynamic calculation software.
4. A helicopter profile design method according to claim 1, characterized in that the fourth step specifically is:
(1) constraint function Y in helicopter formSAnd constraint matrix t of helicopter profileSWithin the range of (3), constructing a sample design set P of the appearance of the helicopter; the sample design set P comprises various helicopter appearances and a parameter matrix corresponding to each helicopter appearance;
(2) calculating the aerodynamic characteristics of each helicopter shape in the sample design set P by adopting CFD;
(3) and establishing a helicopter shape optimization proxy model according to the various helicopter shapes, the parameter matrix corresponding to each helicopter shape and the aerodynamic characteristics of each helicopter shape.
5. A helicopter configuration design method according to claim 1 wherein said CST parameterization in said first step comprises:
(1) defining a constraint function YSAnd type function
And defining a contour function S (lambda) by adopting a weighted sum of m-order polynomials;
(2) according to a constraint function YSAnd type function
And the contour function S (lambda) calculates a parameter matrix t;
wherein, λ is x/f, x is the horizontal axis coordinate of the outline point of the helicopter, M1And M2A range of types characterizing the outline profile.
6. A helicopter profile design method according to claim 5, characterized by the constraint function YSThe method specifically comprises the following steps: y iss＝Y(λ)
And λ is x/f, x is the horizontal axis coordinate of the helicopter outline point, and f is the length of the helicopter outline.
7. A helicopter profile design method according to claim 5, characterized by that type function
Comprises the following steps:
wherein M is1And M2A range of types characterizing the outline profile.
8. A helicopter profile design method according to claim 5, characterized in that the weighted sum of m-th order polynomials is used to define a profile function S (λ) as:
where t ═ tiAnd (i ═ 0, 1, …, m) } is a parameter matrix of the profile function S (λ), and m is the order of the parameter matrix t.
9. A helicopter profile design method according to claims 5-8, characterized by being based on a constraint function YSAnd type function
And the contour function S (lambda) calculates a parameter matrix t, which is specifically as follows:
t＝(t0,t1,…,tm)
the physical meaning of ε (λ) is the ratio of the ordinate y of the helicopter outline point to the length f of the helicopter outline, (x)0,x1,…,xm) The horizontal axis coordinate of m +1 points on the outline of the helicopter is represented;
and delta epsilon is the thickness step difference value of the tail part of the helicopter.
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