CN105677945A - Multiple-condition propulsion performance optimum design method of composite material propeller - Google Patents

Abstract

The present invention relates to a multiple-condition propulsion performance optimum design method of a composite material propeller, and aims at solving the problem that an existing composite material propeller design method is imperfect. The multiple-condition propulsion performance optimum design method comprises the steps of (1) starting; (2) determining a pitch value pi<0> of the composite material propeller at a design advance of J<0>; (3) determining [theta]0.75R at a 0.75R position when the design advance is J<1>; (4) calculating [alpha]0.75R; (5) determining a geometrical pitch angle [theta]1 of the composite material propeller at the 0.75R position when the design advance is J<1>; (6) determining a geometrical pitch angle [theta]1 of the composite material propeller when the design advance is J<1>; (7) selecting a ply orientation angle and sequence of a composite material; (8) designing initial geometry of the composite material propeller; (9) calculating a geometrical pitch angle [theta]1' of the composite material propeller when the design advance is J<1>; and (10) determining the pitch angle |[theta]1'-[theta]1|, if |[theta]1'-[theta]1| >= 0.1 DEG, executing the step (7), and if |[theta]1'-[theta]1| < 0.1 DEG, over. The multiple-condition propulsion performance optimum design method is applied to the propeller field.

Description

A kind of multi-state propulsive performance Optimization Design of composite propeller

Technical field

The present invention relates to the multi-state propulsive performance Optimization Design of composite propeller.

Background technology

Traditional metal airscrew is in the design process with the propulsive performance under the conventional operating mode of decision design for target, and this target determines the basic offset of metal airscrew, and the propulsive performance under other operating modes cannot realize further optimizing design. And composite propeller is due to its special Torsion Coupling effect, it is possible to by designing the laying of composite, carry out multiple-objection optimization, it is achieved the design object that metal airscrew cannot realize.

The method for designing of composite propeller is different from traditional metal airscrew, and the method for designing of metal airscrew is no longer satisfied with composite propeller. The research of current composite propeller is also in the starting stage, composite Materials Design process is mainly based upon conventional metals propeller, based on the offset parameter of metal airscrew, by designing the laying of composite, realize propulsive efficiency under design conditions identical with metal oar, or be better than the target of metal oar. But, propeller, in real navigation process, also has other running working conditions, and particularly with the naval vessel having lowsteaming demand, therefore only optimizing composite propeller is inadequate in the propulsive performance of design conditions. If the propulsive performance under other operating modes can be improved again in the propulsive performance under ensureing design conditions simultaneously, then can effectively improve the comprehensive propulsive performance of composite propeller, improve the service efficiency of main frame, reach energy-conservation effect, extend the hours underway on naval vessel.

Summary of the invention

The invention aims to solve the existing incomplete problem of composite propeller method for designing, and propose the multi-state propulsive performance Optimization Design of a kind of composite propeller.

Above-mentioned goal of the invention is achieved through the following technical solutions:

Step one, beginning;

Step 2, determine composite propeller design into speed J⁰Under pitch p_i ⁰, wherein i=1,2 ... n, n are the radial direction radius number of composite propeller, and value is positive integer;

Step 3, employing panel method determine that metal airscrew is designing into fast as J¹Time, the incoming flow angle, θ of 0.75R place blade section_0.75R;

Step 4, calculate the incoming flow angle of attack of metal airscrew main blade 0.75R place blade section maximum propulsive efficiency_0.75R;

Step 5, determine that according to step 3 and step 4 metal airscrew is designing into speed as J¹Time, 0.75R place blade section reaches the geometric pitch angle θ of maximum propulsive efficiency₁;

Step 6, determine according to step 5 composite propeller designing into speed J¹, arrive the geometric pitch angle θ higher than metal airscrew propulsive efficiency₁;

Step 7, choose according to step 2 composite plys angle and order;

Step 8, design the initial geometry of composite propeller according to step 7;

Step 9, according to step 8 calculate composite propeller entering speed J¹Time geometric pitch angle θ₁';

Step 10, judge the angle of pitch according to step 6 and step 9 | θ₁′-θ₁|, if | θ₁′-θ₁| >=0.1 °, then perform step 7; If | θ₁′-θ₁| < 0.1 °, then terminate.

Invention effect

On the basis of original metal airscrew, utilize the designability of composite, a kind of composite propeller is designed in conjunction with the mode of initial geometry by designing laying angle, and make this propeller all have higher propulsive efficiency with other operating modes one or more under design conditions, it is achieved the high efficiency of composite propeller. Ensure design into speed propulsive performance efficient while, make naval vessel still show higher propulsive performance when other regimes. The material that propeller uses is composite (carbon fiber or glass fibre).

A kind of multi-state propulsive performance Optimization Design of composite propeller, relate to the Optimization Design of a kind of propeller, multi-state refers to comprise design conditions (designing into speed) and one or more operating mode (entering speed) except design conditions, and propeller adopts composite (carbon fiber or glass fibre). Based on the offset parameter of metal airscrew, determine composite propeller geometrical pitch under design conditions, Design by Surface Panel Method is utilized to go out the composite propeller geometrical pitch having higher propulsive performance (propulsive efficiency) under one or more operating mode except design conditions, by the initial geometry designs of composite propeller and material laying angle design, composite propeller is made to realize expection pitch distribution under hydrodynamic(al) load force.

The geometrical pitch of higher propulsive efficiency can be reached by designing multi-state composite propeller in advance, composite Torsion Coupling characteristic is utilized to make it under corresponding water dynamic load effect, predetermined torsional deflection occur, it is achieved the purpose that composite propeller multi-state propulsive performance promotes.

By predefined composite propeller geometrical pitch value under design conditions and other operating modes, composite propeller is made not only to have higher propulsive efficiency under design conditions, under other running working conditions, all there is the propulsive efficiency higher than metal airscrew, improve the comprehensive propulsive performance of composite propeller.

Judge the angle of pitch | θ₁′-θ₁|, if | θ₁′-θ₁| >=0.1 °, then choose composite plys angle and order; Design the initial geometry of composite propeller; Calculate composite propeller and enter speed J¹Time geometric pitch angle θ₁'; Change composite plys angle and order, recalculate the initial geometry of composite propeller; If | θ₁′-θ₁| < 0.1 °, then terminate.

Accompanying drawing explanation

Fig. 1 is flow chart of the present invention;

Fig. 2 is angle schematic diagram between metal airscrew main blade 0.75R place's blade section and incoming flow.

Detailed description of the invention

Detailed description of the invention one: present embodiment is described in conjunction with Fig. 1, the multi-state propulsive performance Optimization Design of a kind of composite propeller of present embodiment, specifically prepare according to following steps:

Step one, beginning;

Step 2, determine composite propeller design into speed J⁰Under pitch p_i ⁰, wherein i=1,2 ... n, n are the radial direction radius number of composite propeller, and value is positive integer;

Step 3, employing panel method determine that metal airscrew is designing into fast as J¹Time, the incoming flow angle, θ of 0.75R place blade section_0.75R;

Step 4, calculate the incoming flow angle of attack of metal airscrew main blade 0.75R place blade section maximum propulsive efficiency_0.75R;

Step 5, determine that according to step 3 and step 4 metal airscrew is designing into speed as J¹Time, 0.75R place blade section reaches the geometric pitch angle θ of maximum propulsive efficiency₁;

Step 6, determine according to step 5 composite propeller designing into speed J¹, arrive the geometric pitch angle θ higher than metal airscrew propulsive efficiency₁;

Step 7, choose according to step 2 composite plys angle and order;

Step 8, design the initial geometry of composite propeller according to step 7;

Step 9, according to step 8 calculate composite propeller entering speed J¹Time geometric pitch angle θ₁';

Step 10, judge the angle of pitch according to step 6 and step 9 | θ₁′-θ₁|, if | θ₁′-θ₁| >=0.1 °, then perform step 7; If | θ₁′-θ₁| < 0.1 °, then terminate;

Multi-state refers to comprise design conditions (designing into speed) and one or more operating mode (entering speed) except design conditions, multiple refers to two or more.

Detailed description of the invention two: present embodiment and detailed description of the invention one the difference is that: described step 2 being determined, composite propeller designs into speed J⁰Under pitch p_i ⁰, wherein i=1,2 ... n, n are the radial direction radius number of composite propeller; Detailed process is:

Parameter based on the geometry offset of metal airscrew, the design of metal airscrew enters speed for J⁰, radially pitch is p_i ⁰, wherein i=1,2 ... n, n are the radial direction radius number of metal airscrew; By the radial direction pitch p of metal airscrew_i ⁰It is defined as composite propeller to design into speed J⁰Under pitch p_i ⁰(composite propeller is designing into fast as J⁰Time twist deformation after pitch be p_i ⁰)。

Other step and parameter and detailed description of the invention one are identical.

Detailed description of the invention three: present embodiment and detailed description of the invention one or two the difference is that: described step 3 adopts panel method determine metal airscrew designing into speed be J¹Time, the incoming flow angle of 0.75R place blade section guide margin leading edge; Detailed process is:

Based on green theorem, Fortran language is utilized to write metal airscrew panel method program, the solving model according to metal airscrew velocity field

Solve metal airscrew velocity field 4 π V (p), solve the disturbance velocity V (p) in basin, metal airscrew place according to metal airscrew velocity field 4 π V (p);

Wherein, p is arbitrfary point, flow field, and V (p) is the disturbance velocity in basin, metal airscrew place, and Q is the point on propeller surface,For perturbation potential,Jump for velocity potential, V₀For speed of incoming flow, n_QFor Q point normal vector, R_pQFor the distance between a p and some Q, s_sFor propeller blade face, s_wFor propeller tailwater system, S is integration face, Q₁For the point on tailwater system,For a Q₁Normal vector,For for putting p and some Q₁Between distance;

Utilize the solving model of metal airscrew velocity field, solve to be different from and design into speed J⁰Enter speed J¹The speed of incoming flow of the lower main blade of metal airscrew

Wherein, P_0.75RFor metal airscrew main blade 0.75R place blade section guide margin leading edge, R is radius, whereinV_xFor entering speed for J¹Time metal airscrew main blade 0.75R place x-axis speed of incoming flow, V_yFor entering speed for J¹Time metal airscrew main blade 0.75R place y-axis speed of incoming flow, V_zFor entering speed for J¹Time metal airscrew main blade 0.75R place z-axis speed of incoming flow; The coordinate system at metal airscrew place is cartesian coordinate system, and rotating shaft is defined as x-axis, and x-axis forward is speed of incoming flow direction, and the axle at the main blade place of propeller is y-axis, and coordinate system observes right-hand rule;

Speed is entered for J according to what solve¹The speed of incoming flow of the lower main blade of metal airscrewUtilize formulaCalculate metal airscrew designing into fast as J¹Time, the incoming flow angle, θ of 0.75R place blade section guide margin leading edge_0.75R。

Other step and one of parameter and detailed description of the invention one to two are identical.

Detailed description of the invention four: one of present embodiment and detailed description of the invention one to three the difference is that: described step 4 calculates the incoming flow angle of attack of metal airscrew main blade 0.75R place blade section maximum propulsive efficiency; Detailed process is:

Commercial CFD code is utilized to set up the geometric model (airfoil type of metal airscrew main blade 0.75R place blade section guide margin leading edge, two bubble faces) and divide fluid computational fields grid, solve metal airscrew main blade 0.75R place blade section guide margin leading edge lift coefficient C under different incoming flow angle of attack_LWith resistance coefficient C_D, it is depicted as lift-drag ratio curve C_L/C_D-α, lift-drag ratio C_L/C_DMore big, the propulsive efficiency of metal airscrew main blade 0.75R place blade section is more high, lift-drag ratio curve C_L/C_DIncoming flow angle of attack that-α peak is corresponding and the incoming flow angle of attack of metal airscrew main blade 0.75R place blade section guide margin leading edge maximum propulsive efficiency_0.75R。

Other step and one of parameter and detailed description of the invention one to three are identical.

Detailed description of the invention five: one of present embodiment and detailed description of the invention one to four the difference is that: in described step 5 according to step 3 and step 4 determine metal airscrew designing into speed be J¹Time, 0.75R place blade section reaches the geometric pitch angle of maximum propulsive efficiency; Detailed process is:

Metal airscrew is designing into fast as J¹Time, between metal airscrew main blade 0.75R place's blade section and incoming flow, there is angle α_0.75RTime, 0.75R place blade section reaches maximum propulsive efficiency, then 0.75R place blade section reaches the geometric pitch angle of maximum propulsive efficiency is θ₁=θ_0.75R+α_0.75R, such as Fig. 2.

Detailed description of the invention six: one of present embodiment and detailed description of the invention one to five the difference is that: according to step 5, described step 6 determines that composite propeller is designing into speed J¹Time, arrive and designing into fast as J higher than metal airscrew¹Time, 0.75R place blade section reaches the geometric pitch angle θ of maximum propulsive efficiency₁; Detailed process is:

Entering speed for J¹Time, when the geometric pitch angle that the geometric pitch angle of 0.75R place blade section after composite propeller deforms reaches maximum propulsive efficiency with metal oar is identical, composite propeller reaches to be higher than the propulsive efficiency of virgin metal propeller, and namely composite propeller is entering speed for J¹Time the target angle of pitch be θ₁。

Other step and one of parameter and detailed description of the invention one to five are identical.

Detailed description of the invention seven: one of present embodiment and detailed description of the invention one to six the difference is that: described step 7 is chosen composite plys angle and order according to step 2;Detailed process is:

Choose composite plys angle and order is It is 0 ° for composite plys angle,It is 45 ° for composite plys angle,It is 90 ° for composite plys angle, []_sFor symmetric layups.

Other step and one of parameter and detailed description of the invention one to six are identical.

Detailed description of the invention eight: one of present embodiment and detailed description of the invention one to seven the difference is that: described step 8 is designed the initial geometry of composite propeller according to step 7; Detailed process is:

First choose the model that geometry is composite propeller 1 of metal airscrew, solve composite propeller fluid and structural simulation Equation for Calculating go out composite propeller model 1 at J according to the laying angle in step 7 and order⁰Under blade deflection 1, by the negative value maps of blade deflection 1 to composite propeller model 1 blade, obtain new composite propeller model 2, again calculate composite propeller spiral shell model 2 at J⁰Under blade deflection 2, extract the pitch after now composite propeller deforms, compare pitch now whether equal to radially pitch p_i ⁰If equal to, then composite propeller model 2 is defined as the initial geometry of composite propeller, if be not equal to, then again the negative value maps of blade deflection 2 to composite propeller model 2 will obtain new composite propeller model 3, again calculate composite propeller model 3 at J⁰Under blade deflection 3, extract the pitch after now composite propeller deforms, compare pitch now whether equal to radially pitch p_i ⁰If equal to, then composite propeller model 3 is defined as the initial geometry of composite propeller, if be not equal to, then again the negative value maps of blade deflection 3 to composite propeller model 3 will obtain new composite propeller model 4, repeat new composite propeller model 3 to the process of new composite propeller model 4 until at J⁰Pitch and p after lower composite propeller model n deformation_i ⁰Identical, now model n is defined as the initial geometry of composite propeller;

Composite propeller fluid and structural simulation equation is $\&lsqb;M\&rsqb;\left\{\stackrel{\&CenterDot;\&CenterDot;}{u}\right\}+\&lsqb;C\&rsqb;\left\{\stackrel{\&CenterDot;}{u}\right\}+\&lsqb;K\&rsqb;\left\{u\right\}=\left\{F_{ce}\right\}+\left\{F_{co}\right\}+\left\{F_h\right\},$

Wherein, [M] is mass matrix, and [C] is damping matrix, and [K] is stiffness matrix,For vector acceleration,For velocity vector, { u} is motion vector, F_ceFor centrifugal force, F_coFor Coriolis force, F_hFor external force.

Other step and one of parameter and detailed description of the invention one to seven are identical.

Detailed description of the invention nine: one of present embodiment and detailed description of the invention one to eight the difference is that: described step 9 calculates composite propeller according to step 8 and is entering speed J¹Time geometric pitch angle θ₁'; Detailed process is:

According to the initial geometry of the composite propeller obtained in step 8, solve the composite propeller fluid and structural simulation initial geometry of Equation for Calculating composite propeller and entering speed J¹The change value of the blade angle of pitch after deforming, is mapped to composite propeller by angle of pitch change value, extracts the pitch P of 0.75R place blade section₁', calculate pitch angle θ now₁', wherein θ₁'=tan^-1(P₁'/πD)。

Other step and one of parameter and detailed description of the invention one to eight are identical.

Detailed description of the invention ten: one of present embodiment and detailed description of the invention one to nine the difference is that: described step 10 judges the angle of pitch | θ₁′-θ₁|, if | θ₁′-θ₁| >=0.1 °, then perform step 7;If | θ₁′-θ₁| < 0.1 °, then terminate; Detailed process is:

Pitch angle θ in comparison step six and step 9₁' and θ₁If, | θ₁′-θ₁| >=0.1 °, then repeat the step 7 work to step 9, change composite plys angle and order, recalculate the initial geometry of composite propeller; If | θ₁′-θ₁| < 0.1 °, then terminate.

Other step and one of parameter and detailed description of the invention one to nine are identical.

Step 2 to step 6 determines except designing into the angle of pitch under another operating mode except speed, increases other according to demand and designs into speed, repeats the step 7 work to step 8, it is achieved the propulsive performance optimization design of multiple operating modes.

Claims (10)

1. the multi-state propulsive performance Optimization Design of a composite propeller, it is characterised in that the multi-state propulsive performance Optimization Design of a kind of composite propeller specifically carries out according to following steps:

Step one, beginning;

Step 2, determine composite propeller design into speed J⁰Under pitch p_i ⁰, wherein i=1,2 ... n, n are the radial direction radius number of composite propeller, and value is positive integer;

Step 3, employing panel method determine that metal airscrew is designing into fast as J¹Time, the incoming flow angle, θ of 0.75R place blade section_0.75R;

Step 4, calculate the incoming flow angle of attack of metal airscrew main blade 0.75R place blade section maximum propulsive efficiency_0.75R;

Step 5, determine that according to step 3 and step 4 metal airscrew is designing into speed as J¹Time, 0.75R place blade section reaches the geometric pitch angle θ of maximum propulsive efficiency₁;

Step 6, determine according to step 5 composite propeller designing into speed J¹, arrive the geometric pitch angle θ higher than metal airscrew propulsive efficiency₁;

Step 7, choose according to step 2 composite plys angle and order;

Step 8, design the initial geometry of composite propeller according to step 7;

Step 9, according to step 8 calculate composite propeller entering speed J¹Time geometric pitch angle θ₁';

Step 10, judge the angle of pitch according to step 6 and step 9 | θ₁′-θ₁|, if | θ₁′-θ₁| >=0.1 °, then perform step 7; If | θ₁′-θ₁| < 0.1 °, then terminate.

2. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 1, it is characterised in that: described step 2 being determined, composite propeller designs into speed J⁰Under pitch p_i ⁰, wherein i=1,2 ... n, n are the radial direction radius number of composite propeller, and value is positive integer; Detailed process is:

Parameter based on the geometry offset of metal airscrew, the design of metal airscrew enters speed for J⁰, radially pitch is p_i ⁰, wherein i=1,2 ... n, n are the radial direction radius number of metal airscrew, and value is positive integer; By the radial direction pitch p of metal airscrew_i ⁰It is defined as composite propeller to design into speed J⁰Under pitch p_i ⁰。

3. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 2, it is characterised in that: described step 3 adopts panel method determine metal airscrew designing into speed be J¹Time, the incoming flow angle of 0.75R place blade section guide margin leading edge; Detailed process is:

Based on green theorem, Fortran language is utilized to write metal airscrew panel method program, the solving model according to metal airscrew velocity fieldSolve metal airscrew velocity field 4 π V (p), solve the disturbance velocity V (p) in basin, metal airscrew place according to metal airscrew velocity field 4 π V (p);

Wherein, p is arbitrfary point, flow field, and V (p) is the disturbance velocity in basin, metal airscrew place, and Q is the point on propeller surface,For perturbation potential,Jump for velocity potential, V₀For speed of incoming flow, n_QFor Q point normal vector, R_pQFor the distance between a p and some Q, s_sFor propeller blade face, s_wFor propeller tailwater system, S is integration face, Q₁For the point on tailwater system,For a Q₁Normal vector,For for putting p and some Q₁Between distance;

Utilize the solving model of metal airscrew velocity field, solve to be different from and design into speed J⁰Enter speed J¹The speed of incoming flow of the lower main blade of metal airscrew

Wherein, P_0.75RFor metal airscrew main blade 0.75R place blade section guide margin leading edge, R is radius, whereinV_xFor entering speed for J¹Time metal airscrew main blade 0.75R place x-axis speed of incoming flow, V_yFor entering speed for J¹Time metal airscrew main blade 0.75R place y-axis speed of incoming flow, V_zFor entering speed for J¹Time metal airscrew main blade 0.75R place z-axis speed of incoming flow; The coordinate system at metal airscrew place is cartesian coordinate system, and rotating shaft is defined as x-axis, and x-axis forward is speed of incoming flow direction, and the axle at the main blade place of propeller is y-axis, and coordinate system observes right-hand rule;

Speed is entered for J according to what solve¹The speed of incoming flow of the lower main blade of metal airscrewUtilize formulaCalculate metal airscrew designing into fast as J¹Time, the incoming flow angle, θ of 0.75R place blade section guide margin leading edge_0.75R。

4. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 3, it is characterised in that: described step 4 calculates the incoming flow angle of attack of metal airscrew main blade 0.75R place blade section maximum propulsive efficiency; Detailed process is:

Utilize commercial CFD code set up the geometric model of metal airscrew main blade 0.75R place blade section guide margin leading edge and divide fluid computational fields grid, solve metal airscrew main blade 0.75R place blade section guide margin leading edge lift coefficient C under different incoming flow angle of attack_LWith resistance coefficient C_D, it is depicted as lift-drag ratio curve C_L/C_D-α, lift-drag ratio C_L/C_DMore big, the propulsive efficiency of metal airscrew main blade 0.75R place blade section is more high, lift-drag ratio curve C_L/C_DIncoming flow angle of attack that-α peak is corresponding and the incoming flow angle of attack of metal airscrew main blade 0.75R place blade section guide margin leading edge maximum propulsive efficiency_0.75R。

5. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 4, it is characterised in that: in described step 5 according to step 3 and step 4 determine metal airscrew designing into speed be J¹Time, 0.75R place blade section reaches the geometric pitch angle of maximum propulsive efficiency; Detailed process is:

Metal airscrew is designing into fast as J¹Time, between metal airscrew main blade 0.75R place's blade section and incoming flow, there is angle α_0.75RTime, 0.75R place blade section reaches maximum propulsive efficiency, then 0.75R place blade section reaches the geometric pitch angle of maximum propulsive efficiency is θ₁=θ_0.75R+α_0.75R。

6. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 5, it is characterised in that: according to step 5, described step 6 determines that composite propeller is designing into speed J¹Time, arrive and designing into fast as J higher than metal airscrew¹Time, 0.75R place blade section reaches the geometric pitch angle θ of maximum propulsive efficiency₁; Detailed process is:

Entering speed for J¹Time, when the geometric pitch angle that the geometric pitch angle of 0.75R place blade section after composite propeller deforms reaches maximum propulsive efficiency with metal oar is identical, composite propeller reaches to be higher than the propulsive efficiency of virgin metal propeller, and namely composite propeller is entering speed for J¹Time the target angle of pitch be θ₁。

7. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 6, it is characterised in that: described step 7 is chosen composite plys angle and order according to step 2;Detailed process is:

Choose composite plys angle and order is It is 0 ° for composite plys angle,It is 45 ° for composite plys angle,It is 90 ° for composite plys angle, []_sFor symmetric layups.

8. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 7, it is characterised in that: described step 8 is designed the initial geometry of composite propeller according to step 7; Detailed process is:

First choose the model that geometry is composite propeller 1 of metal airscrew, solve composite propeller fluid and structural simulation Equation for Calculating go out composite propeller model 1 at J according to the laying angle in step 7 and order⁰Under blade deflection 1, by the negative value maps of blade deflection 1 to composite propeller model 1 blade, obtain new composite propeller model 2, again calculate composite propeller model 2 at J⁰Under blade deflection 2, extract the pitch after now composite propeller deforms, compare pitch now whether equal to radially pitch p_i ⁰If equal to, then composite propeller model 2 is defined as the initial geometry of composite propeller, if be not equal to, then again the negative value maps of blade deflection 2 to composite propeller model 2 will obtain new composite propeller model 3, again calculate composite propeller spiral shell model 3 at J⁰Under blade deflection 3, extract the pitch after now composite propeller deforms, compare pitch now whether equal to radially pitch p_i ⁰If equal to, then composite propeller model 3 is defined as the initial geometry of composite propeller, if be not equal to, then again the negative value maps of blade deflection 3 to composite propeller model 3 will obtain new composite propeller model 4, repeat new composite propeller model 3 to the process of new composite propeller model 4 until at J⁰Pitch and p after lower composite propeller model n deformation_i ⁰Identical, now composite propeller model n is defined as the initial geometry of composite propeller;

Composite propeller fluid and structural simulation equation is $\&lsqb;M\&rsqb;\left\{\stackrel{\&CenterDot;\&CenterDot;}{u}\right\}+\&lsqb;C\&rsqb;\left\{\stackrel{\&CenterDot;}{u}\right\}+\&lsqb;K\&rsqb;\left\{u\right\}=\left\{F_{ce}\right\}+\left\{F_{co}\right\}+\left\{F_h\right\},$

Wherein, [M] is mass matrix, and [C] is damping matrix, and [K] is stiffness matrix,For vector acceleration,For velocity vector, { u} is motion vector, F_ceFor centrifugal force, F_coFor Coriolis force, F_hFor external force.

9. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 8, it is characterised in that: described step 9 calculates composite propeller according to step 8 and enters speed J¹Time geometric pitch angle θ₁'; Detailed process is:

According to the initial geometry of the composite propeller obtained in step 8, solve the composite propeller fluid and structural simulation initial geometry of Equation for Calculating composite propeller and entering speed J¹The change value of the blade angle of pitch after deforming, is mapped to composite propeller by angle of pitch change value, extracts the pitch P of 0.75R place blade section₁', calculate pitch angle θ now₁', wherein θ₁'=tan^-1(P₁'/πD)。

10. the multi-state propulsive performance Optimization Design of a kind of composite propeller according to claim 9, it is characterised in that: described step 10 judges the angle of pitch | θ₁′-θ₁|, if | θ₁′-θ₁| >=0.1 °, then perform step 7; If | θ₁′-θ₁| < 0.1 °, then terminate; Detailed process is:

Pitch angle θ in comparison step six and step 9₁' and θ₁If, | θ₁′-θ₁| >=0.1 °, then repeat the step 7 work to step 9, change composite plys angle and order, recalculate the initial geometry of composite propeller;If | θ₁′-θ₁| < 0.1 °, then terminate.