CN110489939A - A kind of optimization method of Design of Propeller, optimization device and readable storage medium storing program for executing - Google Patents
A kind of optimization method of Design of Propeller, optimization device and readable storage medium storing program for executing Download PDFInfo
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- CN110489939A CN110489939A CN201910998909.3A CN201910998909A CN110489939A CN 110489939 A CN110489939 A CN 110489939A CN 201910998909 A CN201910998909 A CN 201910998909A CN 110489939 A CN110489939 A CN 110489939A
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Abstract
This application provides a kind of optimization method of Design of Propeller, optimization device and readable storage medium storing program for executing, the optimization method includes: from the design data of the propeller to be optimized got, determine the initial propeller pitch angle at each propeller-blade section and initial chord length, and it is directed to each propeller-blade section, determine propeller pitch angle value interval and chord length value interval；Based on according to the division propeller pitch angle and division chord length in propeller pitch angle value interval and each propeller parameter group of chord length value interval generation, determine multiple lift resistance ratios, using the corresponding propeller pitch angle and chord length for dividing propeller pitch angle and division chord length as propeller to be optimized at the section of maximum lift-drag ratio in multiple lift resistance ratios, in this way, the corresponding propeller pitch angle of maximum lift-drag ratio and chord length can be selected on each propeller-blade section, propeller can be made to obtain maximum lift on each propeller-blade section, by the smallest resistance, determine the optimized parameter of Design of Propeller, help to improve the accuracy of Design of Propeller.
Description
Technical field
This application involves vehicle technology fields, optimization method, optimization device more particularly, to a kind of Design of Propeller
And readable storage medium storing program for executing.
Background technique
With the rapid development of science and technology, aviation industry also get up therewith by fast development, and aircraft, unmanned plane etc. are them
In a research direction, in the Design and manufacturing process of aircraft and unmanned plane, as the propulsive force of aircraft flight, propeller is set
Meter is very important a ring, in order to improve the aerodynamic quality of aircraft and unmanned plane, for rationally setting for properller
Meter, is vital.
At this stage when carrying out the design of properller, the design side proposed in its document Angelo is relatively mostly used
Method, inputs propeller parameter, and the parameter value calculation propeller for being directly based upon input according to formula is right on each propeller-blade section
The design parameter answered constructs Design of Propeller model.The final design result of this algorithm is directly determined by formula, is directed to
Model propeller design perfect condition, the position of the propeller of practical application is not necessarily it is most suitable, for example,
Design parameter ideally in practical applications, at the different location on different propellers and each propeller, is managed
Design parameter in the case of thinking can not be such that the performance of each propeller reaches most preferably, influence the accurate of properller design
Property.
Summary of the invention
In view of this, a kind of optimization method for being designed to provide Design of Propeller of the application, optimization device and readable
Storage medium, initial propeller pitch angle and initial chord length at each propeller-blade section, determine propeller pitch angle value interval with
And chord length value interval, and from propeller pitch angle value interval and chord length value interval determine the maximum propeller pitch angle of lift resistance ratio and
Chord length can select the corresponding propeller pitch angle of maximum lift-drag ratio and chord length on each propeller-blade section, propeller can be made to exist
Maximum lift is obtained on each propeller-blade section, by the smallest resistance, is determined the optimized parameter of Design of Propeller, is helped
In the accuracy for improving Design of Propeller.
The embodiment of the present application provides a kind of optimization method of Design of Propeller, and the optimization method includes:
From the design data of the propeller to be optimized got, determine the propeller to be optimized at each propeller-blade section
Initial propeller pitch angle and initial chord length；
The spiral shell to be optimized is determined based on default pitch angle offset and the initial propeller pitch angle for each propeller-blade section
The propeller pitch angle value interval of paddle is revolved, and based on default chord length offset and the initial chord length, determines the spiral to be optimized
The chord length value interval of paddle；
For each propeller-blade section, it is based on the propeller pitch angle value interval and the chord length value interval, is generated described to be optimized
The corresponding multiple propeller parameter groups of propeller, wherein each propeller parameter group includes that a division propeller pitch angle and one draw
Divide chord length；
Based on the division propeller pitch angle in each propeller parameter group and chord length is divided, determines that the propeller to be optimized is corresponding more
A lift resistance ratio；
For each propeller-blade section, the corresponding target spiral shell of the maximum target lift resistance ratio of lift resistance ratio is selected from the multiple lift resistance ratio
Paddle parameter group is revolved, and using the division propeller pitch angle in the target propeller parameter group and divides chord length as the spiral to be optimized
Propeller pitch angle and chord length of the paddle at the section.
Further, the optimization method determines the propeller pitch angle value interval by following steps:
The product for determining default bias coefficient of discharge and the default pitch angle offset is first interval endpoint adjusted value；
By the initial propeller pitch angle and the first interval endpoint adjusted value and value and the initial propeller pitch angle and described the
Numerical intervals between the difference of one interval endpoint adjusted value are determined as the propeller pitch angle value interval.
Further, the optimization method determines the chord length value interval by following steps:
Product based on the default bias coefficient of discharge Yu the default chord length offset is determined as the adjustment of second interval endpoint
Value；
The difference for determining preset constant and second interval endpoint adjusted value is first end point regulation coefficient, and is determined described default normal
Several and second interval endpoint adjusted value and value is the second endpoint regulation coefficient；
By the product and the initial chord length of the initial chord length and the first end point regulation coefficient and second endpoint
Numerical intervals between the product of regulation coefficient are determined as the chord length value interval.
Further, described to be directed to each propeller-blade section, it is based on the propeller pitch angle value interval and chord length value area
Between, generate the corresponding multiple propeller parameter groups of the propeller to be optimized, comprising:
It is to divide step-length with the default pitch angle offset, obtains multiple division pitches in the propeller pitch angle value interval
Angle, and be to divide step-length with the default chord length offset, obtain multiple division chord lengths in the chord length value interval；
Each is divided into propeller pitch angle and each divides chord length permutation and combination, generates multiple propeller parameter groups.
Further, the optimization method determines lift resistance ratio by following steps:
Obtain the lift coefficient corresponding with chord length is divided of the division propeller pitch angle in each propeller parameter group and resistance coefficient；
The ratio of the lift coefficient Yu the resistance coefficient is determined, for the corresponding lift resistance ratio of propeller parameter group.
The embodiment of the present application also provides a kind of optimization device of Design of Propeller, the optimization device includes:
First determining module, for from the design data of the propeller to be optimized got, determining the propeller to be optimized
Initial propeller pitch angle and initial chord length at each propeller-blade section；
Second determining module determines mould based on default pitch angle offset and described first for being directed to each propeller-blade section
The initial propeller pitch angle that block determines determines the propeller pitch angle value interval of the propeller to be optimized, and based on default chord length offset
And the initial chord length that first determining module determines, determine the chord length value interval of the propeller to be optimized；
Generation module, for be directed to each propeller-blade section, based on second determining module determine propeller pitch angle value interval and
The chord length value interval that second determining module determines generates the corresponding multiple propeller parameters of the propeller to be optimized
Group, wherein each propeller parameter group includes a division propeller pitch angle and a division chord length；
Third determining module, for based on the division propeller pitch angle in each propeller parameter group and dividing chord length, determine it is described to
Optimize the corresponding multiple lift resistance ratios of propeller；
Selecting module selects to rise from multiple lift resistance ratios that the third determining module determines for being directed to each propeller-blade section
Hinder more corresponding than maximum target lift resistance ratio target propeller parameter group, and by the division paddle in the target propeller parameter group
The propeller pitch angle and chord length of elongation and division chord length as the propeller to be optimized at the section.
Further, second determining module determines the propeller pitch angle value interval by following steps:
The product for determining default bias coefficient of discharge and the default pitch angle offset is first interval endpoint adjusted value；
By the initial propeller pitch angle and the first interval endpoint adjusted value and value and the initial propeller pitch angle and described the
Numerical intervals between the difference of one interval endpoint adjusted value are determined as the propeller pitch angle value interval.
Further, second determining module determines the chord length value interval by following steps:
Product based on the default bias coefficient of discharge Yu the default chord length offset is determined as the adjustment of second interval endpoint
Value；
The difference for determining preset constant and second interval endpoint adjusted value is first end point regulation coefficient, and is determined described default normal
Several and second interval endpoint adjusted value and value is the second endpoint regulation coefficient；
By the product and the initial chord length of the initial chord length and the first end point regulation coefficient and second endpoint
Numerical intervals between the product of regulation coefficient are determined as the chord length value interval.
Further, the generation module is determined for being directed to each propeller-blade section based on second determining module
Propeller pitch angle value interval and the chord length value interval that determines of second determining module, it is corresponding to generate the propeller to be optimized
Multiple propeller parameter groups when, be used for:
It is to divide step-length with the default pitch angle offset, obtains multiple division pitches in the propeller pitch angle value interval
Angle, and be to divide step-length with the default chord length offset, obtain multiple division chord lengths in the chord length value interval；
Each is divided into propeller pitch angle and each divides chord length permutation and combination, generates multiple propeller parameter groups.
Further, the third determining module determines lift resistance ratio by following steps:
Obtain the lift coefficient corresponding with chord length is divided of the division propeller pitch angle in each propeller parameter group and resistance coefficient；
The ratio of the lift coefficient Yu the resistance coefficient is determined, for the corresponding lift resistance ratio of propeller parameter group.
The embodiment of the present application also provides a kind of electronic equipment, comprising: processor, memory and bus, the memory are deposited
Contain the executable machine readable instructions of the processor, when electronic equipment operation, the processor and the memory it
Between by bus communication, the optimization of such as above-mentioned Design of Propeller is executed when the machine readable instructions are executed by the processor
The step of method.
The embodiment of the present application also provides a kind of computer readable storage medium, is stored on the computer readable storage medium
Computer program, when which is run by processor the step of the execution such as optimization method of above-mentioned Design of Propeller.
Optimization method, optimization device and the readable storage medium storing program for executing of Design of Propeller provided by the embodiments of the present application, from acquisition
To propeller to be optimized design data in, determine initial propeller pitch angle of the propeller to be optimized at each propeller-blade section
With initial chord length；For each propeller-blade section, based on default pitch angle offset and the initial propeller pitch angle, determine it is described to
Optimize the propeller pitch angle value interval of propeller, and based on default chord length offset and the initial chord length, determines described to excellent
Change the chord length value interval of propeller；For each propeller-blade section, it is based on the propeller pitch angle value interval and the chord length value
Section generates the corresponding multiple propeller parameter groups of the propeller to be optimized, wherein each propeller parameter group includes one
Divide propeller pitch angle and a division chord length；Based on the division propeller pitch angle in each propeller parameter group and chord length is divided, determines institute
State the corresponding multiple lift resistance ratios of propeller to be optimized；For each propeller-blade section, lift resistance ratio is selected from the multiple lift resistance ratio
The corresponding target propeller parameter group of maximum target lift resistance ratio, and by the division propeller pitch angle in the target propeller parameter group
Propeller pitch angle and chord length with division chord length as the propeller to be optimized at the section.
In this way, according to the initial propeller pitch angle of each propeller-blade section, initial chord length and default pitch angle offset and in advance
If chord length offset, propeller pitch angle value interval and chord length value interval are determined, according to propeller pitch angle value interval and chord length
Multiple division propeller pitch angles and multiple division chord lengths in value interval, determine multiple propeller parameter groups, and calculate each
The corresponding lift resistance ratio of a propeller parameter group will divide propeller pitch angle and divide string in the maximum propeller parameter group of lift resistance ratio
It is long, it is determined as the propeller pitch angle and chord length of corresponding propeller-blade section, can selects maximum lift-drag ratio corresponding on each propeller-blade section
Propeller pitch angle and chord length, propeller can be made to obtain maximum lift on each propeller-blade section, by the smallest resistance,
The optimized parameter for determining Design of Propeller helps to improve the accuracy of Design of Propeller.
To enable the above objects, features, and advantages of the application to be clearer and more comprehensible, preferred embodiment is cited below particularly, and cooperate
Appended attached drawing, is described in detail below.
Detailed description of the invention
Technical solution in ord to more clearly illustrate embodiments of the present application, below will be to needed in the embodiment attached
Figure is briefly described, it should be understood that the following drawings illustrates only some embodiments of the application, therefore is not construed as pair
The restriction of range for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 is the system construction drawing under a kind of possible application scenarios；
Fig. 2 is a kind of flow chart of the optimization method of Design of Propeller provided by the embodiment of the present application；
Fig. 3 is propeller schematic diagram；
Fig. 4 is propeller-blade section 3B parameter schematic diagram in a rotational direction in Fig. 3；
Fig. 5 is the flow chart of the optimization method for the Design of Propeller that another embodiment of the application provides；
Fig. 6 is a kind of structural schematic diagram for optimizing device provided by the embodiment of the present application；
Fig. 7 is the structural schematic diagram of a kind of electronic equipment provided by the embodiment of the present application.
Specific embodiment
To keep the purposes, technical schemes and advantages of the embodiment of the present application clearer, below in conjunction with the embodiment of the present application
Middle attached drawing, the technical scheme in the embodiment of the application is clearly and completely described, it is clear that described embodiment is only
It is some embodiments of the present application, instead of all the embodiments.The application being usually described and illustrated herein in the accompanying drawings is real
The component for applying example can be arranged and be designed with a variety of different configurations.Therefore, below to the application's provided in the accompanying drawings
The detailed description of embodiment is not intended to limit claimed scope of the present application, but is merely representative of the selected reality of the application
Apply example.Based on embodiments herein, those skilled in the art are obtained every without making creative work
A other embodiments, shall fall in the protection scope of this application.
Firstly, the application application scenarios applicatory are introduced.The application can be applied to vehicle technology field, lead to
Cross by each propeller-blade section initial propeller pitch angle and initial chord length is based on default pitch angle offset and default chord length is inclined
Shifting amount is divided into propeller pitch angle value interval and chord length value interval, in the propeller pitch angle value interval and chord length value interval
Mark off multiple division propeller pitch angles and multiple division chord lengths, each division propeller pitch angle of permutation and combination and each division string
Length forms multiple propeller parameter groups, by the division propeller pitch angle in the maximum propeller parameter group of lift resistance ratio and divides chord length work
For the propeller pitch angle and chord length of corresponding section, the accuracy of Design of Propeller is improved.Referring to Fig. 1, Fig. 1 is a kind of possible application
System construction drawing under scene.As shown in fig. 1, the system comprises design data generating means and optimization device, wherein institutes
Design data generating means are stated for generating the parameter value of design propeller, wherein the parameter value includes the paddle for propeller
Blade section quantity and propeller pitch angle and chord length on each propeller-blade section, the optimization device are getting the spiral shell to be optimized
Revolve paddle design data after, determine each section initial propeller pitch angle and initial chord length, to the initial paddle of each section
Elongation and initial chord length optimize.
It has been investigated that relatively mostly using Angelo institute in its document when carrying out the design of properller at this stage
The design method of proposition inputs propeller parameter, is directly based upon the parameter value calculation propeller of input at each according to formula
Corresponding design parameter on propeller-blade section constructs Design of Propeller model.The final design result of this algorithm is direct by formula
It determines, is directed to the perfect condition of model propeller design, the position of the propeller of practical application is not necessarily
It is most suitable, for example, design parameter ideally is in practical applications, on different propellers and each propeller
At different location, design parameter ideally can not be such that the performance of each propeller reaches most preferably, influence aircraft spiral
The accuracy of paddle design.
Based on this, the embodiment of the present application provides a kind of optimization method of Design of Propeller, according to each propeller-blade section
Initial propeller pitch angle, initial chord length and default pitch angle offset and default chord length offset, determine propeller pitch angle value area
Between and chord length value interval, according to multiple division propeller pitch angles in propeller pitch angle value interval and chord length value interval and more
A division chord length determines multiple propeller parameter groups, and calculates each corresponding lift resistance ratio of propeller parameter group, by a liter resistance
Than dividing propeller pitch angle in maximum propeller parameter group and dividing chord length, it is determined as the propeller pitch angle chord of corresponding propeller-blade section
It is long, the corresponding propeller pitch angle of maximum lift-drag ratio and chord length can be selected on each propeller-blade section, propeller can be made every
Maximum lift is obtained on one propeller-blade section, by the smallest resistance, the optimized parameter of Design of Propeller is determined, facilitates
Improve the accuracy of Design of Propeller.
Referring to Fig. 2, Fig. 2 is a kind of flow chart of the optimization method of Design of Propeller provided by the embodiment of the present application.
As shown in Figure 2, the optimization method of Design of Propeller provided by the embodiments of the present application, comprising:
Step 201, from the design data of the propeller to be optimized got, determine the propeller to be optimized in each blade
Initial propeller pitch angle and initial chord length at section.
In the step, aerofoil profile according to the to be optimized propeller of the propeller to be optimized when design is obtained, with
And the design data that the propeller needs environment at military service etc. to set, it is theoretical based on momentum theory and foline, it will be described
Propeller to be optimized is divided into multiple propeller-blade sections, and calculates and determine that the propeller to be optimized is first at each propeller-blade section
Beginning propeller pitch angle and initial chord length.
Wherein, the design data include the airscrew diameter of propeller to be optimized, propeller blade number, hub diameter,
Speed of incoming flow, design speed, target pulling force, atmospheric density, atmosphere viscosity etc..
Referring to Fig. 3, Fig. 3 is propeller schematic diagram, as shown in figure 3, it is directed to the propeller,It is A point apart from spiral shell
Revolve the distance of paddle rotation center；For propeller radius, cut-off rule 3b is based on along radial direction on propeller blade by spiral shell
Rotation paddle is divided into several propeller-blade sections 3B；Please refer to Fig. 4, Fig. 4 is that propeller-blade section 3B joins in a rotational direction in Fig. 3
Number schematic diagram, the chord length B of propeller-blade section 3B；The relative wind that incoming flow angle δ ' is propeller-blade section 3B closes speed and propeller hub Plane of rotation
Between angle；Angle of attack α ' it is that the relative wind of propeller-blade section 3B closes the angle of speed and wing chord (different from fuselage axis)；Paddle
Elongation θ refers to the angle of blade tip aerofoil profile string and Plane of rotation.
It, can be based on Angelo in its document when calculating initial propeller pitch angle and the initial chord length at each propeller-blade section
The calculation formula of middle proposition is solved, and first passes through equation calculation median parameter value K of the Angelo in its document, calculating side
Journey is as follows:
(1)
Wherein,For the design pulling force of propeller,For atmospheric density,For the inflow velocity perpendicular to propeller plan,For propeller radius,It is intermediate variable, without specific physical significance.
(2)
Wherein,For blade the piece number,For propeller radius,For revolution speed of propeller,It is certain point in propeller rotation
The distance of the heart,It can be the variable along propeller radius direction herein for intermediate variable.
(3)
Median parameter value K is calculated in joint type (1), formula (2) and formula (3).If propeller is based on foline theory to be divided into
A propeller-blade section is directed to progress numerical value calculating at each section.
According to median parameter value K, propeller is calculated at the incoming flow angle of everywhere based on formula (4):
(4)
Wherein,For propeller everywhere incoming flow angle.
Further, the maximum angle of attack of lift resistance ratio is set along the angle of attack of radius everywhere by propeller, then pitch at this
AngleForWithThe sum of, the chord length B at this can be calculated by formula (5):
(5)
Wherein,For the lift coefficient under the maximum lift-drag ratio angle of attack at the position,For the resistance coefficient under the angle of attack.
Place's propeller to be optimized can be calculated in each paddle by the formula that above-mentioned Angelo is recorded in its document in this way
Initial propeller pitch angle and initial chord length at blade section.
Step 202 is directed to each propeller-blade section, based on default pitch angle offset and the initial propeller pitch angle, determines
The propeller pitch angle value interval of the propeller to be optimized, and based on default chord length offset and the initial chord length, determine institute
State the chord length value interval of propeller to be optimized.
In the step, for each propeller-blade section, i.e., the section divided by foline theory, on each section
For the corresponding initial propeller pitch angle of the section and default pitch angle offset, a propeller pitch angle value interval is determined, and according to
The corresponding initial chord length of the section and default chord length offset determine the chord length value interval of corresponding section, and so on, really
Determine the corresponding propeller pitch angle value interval of whole propeller-blade section and chord length value interval.
It wherein, can be according to the initial of each propeller-blade section for default pitch angle offset and default chord length offset
Propeller pitch angle and initial chord length determine, can also determine according to the design data of propeller to be optimized with reference to history design data；And
And default pitch angle offset for each propeller-blade section and default chord length offset can be unified numerical value, be also possible to
It is determined according to the specific value of the initial propeller pitch angle of each propeller-blade section and initial chord length.
Step 203 is directed to each propeller-blade section, is based on the propeller pitch angle value interval and the chord length value interval, raw
At the corresponding multiple propeller parameter groups of the propeller to be optimized, wherein each propeller parameter group includes a division paddle
Elongation and a division chord length.
In the step, on each propeller-blade section, marked off in the propeller pitch angle value interval that step 202 determines multiple
Propeller pitch angle is divided, while marking off multiple chord lengths in the chord length value interval that step 202 determines, and each based on what is marked off
A division chord length and each division propeller pitch angle generate multiple propeller parameter groups.
Wherein, the quantity of division can choose due to the difference required Section Design for each section, is having
In body implementation process, the quantity of division is more, and the result after calculation processing is finer.
Step 204, based in each propeller parameter group division propeller pitch angle and divide chord length, determine the spiral shell to be optimized
Revolve the corresponding multiple lift resistance ratios of paddle.
In the step, according to the division propeller pitch angle in each propeller parameter group and chord length is divided, is determined and corresponding spiral shell
Revolve the lift resistance ratio for dividing propeller pitch angle and dividing chord length in paddle parameter group.
Wherein, lift resistance ratio is aircraft in flight course, in the lift of the same angle of attack and the ratio of resistance, is also possible to
The lift coefficient of the same angle of attack and the ratio of resistance coefficient, the relating to parameters such as value and the aircraft angle of attack, flying speed, with aircraft
Flying speed is at curved line relation.
Step 205 is directed to each propeller-blade section, and the maximum target lift resistance ratio of lift resistance ratio is selected from the multiple lift resistance ratio
Corresponding target propeller parameter group, and using the division propeller pitch angle in the target propeller parameter group and chord length is divided as institute
State propeller pitch angle and chord length of the propeller to be optimized at the section.
In the step, lift resistance ratio is found based in the calculated multiple lift resistance ratios of step 204 for each propeller-blade section
Maximum target lift resistance ratio, and determine the division propeller pitch angle in the corresponding target propeller parameter group of target lift resistance ratio and division
Chord length, by target propeller parameter group division propeller pitch angle and divide chord length be determined as propeller to be optimized at the section
Propeller pitch angle and chord length, and so on, determine the propeller pitch angle and chord length of each propeller-blade section.
Wherein, the aerodynamic quality of the bigger aircraft for indicating design of lift resistance ratio is better, so needing in each paddle
The design considerations of the corresponding propeller pitch angle of maximum lift-drag ratio and chord length as the propeller-blade section is selected at blade section.
The optimization method of Design of Propeller provided by the embodiments of the present application, from the design number of the propeller to be optimized got
In, initial propeller pitch angle and initial chord length of the propeller to be optimized at each propeller-blade section are determined；For each blade
Section determines the propeller pitch angle value of the propeller to be optimized based on default pitch angle offset and the initial propeller pitch angle
Section, and based on default chord length offset and the initial chord length, determine the chord length value interval of the propeller to be optimized；
For each propeller-blade section, it is based on the propeller pitch angle value interval and the chord length value interval, generates the spiral to be optimized
The corresponding multiple propeller parameter groups of paddle, wherein each propeller parameter group includes a division propeller pitch angle and a division string
It is long；Based on the division propeller pitch angle in each propeller parameter group and chord length is divided, determines that the propeller to be optimized is corresponding more
A lift resistance ratio；For each propeller-blade section, select the maximum target lift resistance ratio of lift resistance ratio corresponding from the multiple lift resistance ratio
Target propeller parameter group, and using the division propeller pitch angle in the target propeller parameter group and chord length is divided as described to excellent
Change propeller pitch angle and chord length of the propeller at the section.
In this way, according to the initial propeller pitch angle of each propeller-blade section, initial chord length and default pitch angle offset and in advance
If chord length offset, propeller pitch angle value interval and chord length value interval are determined, according to propeller pitch angle value interval and chord length
Multiple division propeller pitch angles and multiple division chord lengths in value interval, determine multiple propeller parameter groups, and calculate each
The corresponding lift resistance ratio of a propeller parameter group will divide propeller pitch angle and divide string in the maximum propeller parameter group of lift resistance ratio
It is long, it is determined as the propeller pitch angle and chord length of corresponding propeller-blade section, can selects maximum lift-drag ratio corresponding on each propeller-blade section
Propeller pitch angle and chord length, propeller can be made to obtain maximum lift on each propeller-blade section, by the smallest resistance,
The optimized parameter for determining Design of Propeller helps to improve the accuracy of Design of Propeller.
Referring to Fig. 5, Fig. 5 is the flow chart of the optimization method for the Design of Propeller that another embodiment of the application provides.Such as
Shown in Fig. 5, the optimization method of Design of Propeller provided by the embodiments of the present application, comprising:
Step 501, from the design data of the propeller to be optimized got, determine the propeller to be optimized in each blade
Initial propeller pitch angle and initial chord length at section.
Step 502 is directed to each propeller-blade section, based on default pitch angle offset and the initial propeller pitch angle, determines
The propeller pitch angle value interval of the propeller to be optimized, and based on default chord length offset and the initial chord length, determine institute
State the chord length value interval of propeller to be optimized.
Step 503, with the default pitch angle offset be divide step-length, obtain more in the propeller pitch angle value interval
A division propeller pitch angle, and be to divide step-length with the default chord length offset, obtain multiple strokes in the chord length value interval
Divide chord length.
In the step, using default pitch angle offset as the division step-length for dividing propeller pitch angle value interval, in propeller pitch angle
Multiple division propeller pitch angles are marked off in value interval, and according to the method described above, be to divide step-length with default chord length offset, in string
Multiple division chord lengths are marked off in long value interval.
Wherein, the propeller pitch angle quantity that divides divided in propeller pitch angle value interval is drawn with what is divided in chord length value interval
Point chord length quantity can be consistent.
For example, being directed to a certain propeller-blade section, initial propeller pitch angle is 5 °, and initial chord length is 10, and default pitch angle offset is
0.5 °, presetting chord length offset is 5%, and therefore, the propeller pitch angle value interval got with this condition is (4.5 °, 5.5 °), string
Long value interval is (9.5,10.5), with 0.5 ° of default pitch angle offset to divide step-length, is in propeller pitch angle value interval
It is respectively 4.5 °, 5 °, 5.5 ° that three division propeller pitch angles are obtained in (4.5 °, 5.5 °)；It is to divide step with default chord length offset 5%
It is long, it is to obtain three division chord lengths 9.5,10,10.5 in (9.5,10.5) in chord length value interval.
Each is divided propeller pitch angle and each division chord length permutation and combination by step 504, generates multiple propellers ginsengs
Array.
In the step, after obtaining multiple division propeller pitch angles and multiple division chord lengths by step 503, for each stroke
Divide propeller pitch angle and each division chord length, carries out permutation and combination, form multiple propeller parameter groups.
For example, corresponding to above-described embodiment, after propeller pitch angle value interval is divided, obtaining three division propeller pitch angles is respectively
4.5 °, 5 °, 5.5 ° obtain three division chord lengths 9.5,10,10.5 after dividing chord length value interval, are based on each
It divides propeller pitch angle and each divides chord length, obtain nine propeller parameter groups, (4.5 °, 9.5), (4.5 °, 10), (4.5 °,
10.5), (5 °, 9.5), (5 °, 10), (5 °, 10.5), (5.5 °, 9.5), (5.5 °, 10), (5.5 °, 10.5).
Step 505, based in each propeller parameter group division propeller pitch angle and divide chord length, determine the spiral shell to be optimized
Revolve the corresponding multiple lift resistance ratios of paddle.
Step 506 is directed to each propeller-blade section, and the maximum target lift resistance ratio of lift resistance ratio is selected from the multiple lift resistance ratio
Corresponding target propeller parameter group, and using the division propeller pitch angle in the target propeller parameter group and chord length is divided as institute
State propeller pitch angle and chord length of the propeller to be optimized at the section.
Wherein, step 501 to step 503 and step 505 to the description of step 506 is referred to step 201 to step
202 and step 204 to the description of step 205, and identical technical effect can be reached, this not repeated them here.
Further, determine the propeller pitch angle value interval by following steps: determine default bias coefficient of discharge with it is described
The product of default pitch angle offset is first interval endpoint adjusted value；By the initial propeller pitch angle and the first interval endpoint
Adjusted value and value and the numerical intervals between the initial propeller pitch angle and the difference of the first interval endpoint adjusted value, really
It is set to the propeller pitch angle value interval.
In the step, the default propeller pitch angle for the natural environment setting being on active service according to history design data or propeller is obtained
Offset, and the value interval divided as needed numerical intervals size setting offset coefficient of discharge, by pitch angle offset with
The product of offset coefficient of discharge is set as first interval endpoint adjusted value, the difference of initial propeller pitch angle and first interval endpoint adjusted value
And initial propeller pitch angle and first interval endpoint adjusted value and value determination numerical intervals, as corresponding propeller pitch angle value area
Between.
For example, initial pitch angle value is 5 ° on a certain propeller-blade section, presetting pitch angle offset is 0.5 °, is determining paddle
Can be just with 0.5 ° for first interval endpoint adjusted value when elongation value interval, i.e., offset coefficient of discharge is 1 at this time, is based on this, really
Fixed propeller pitch angle value interval is (4.5 °, 5.5 °)；In actual optimization demand, need to look for most in bigger numerical intervals
Good propeller pitch angle, adjustable offset coefficient of discharge, it is assumed that offset coefficient of discharge is 2, propeller pitch angle value interval determining at this time be (4 °,
6 °).
Further, the chord length value interval is determined by following steps: based on the default bias coefficient of discharge and institute
The product for stating default chord length offset is determined as second interval endpoint adjusted value；Determine preset constant and second interval endpoint tune
The difference of whole value is first end point regulation coefficient, and determine the preset constant and second interval endpoint adjusted value and value be the
Two endpoint regulation coefficients；By the product and the initial chord length of the initial chord length and the first end point regulation coefficient and institute
The numerical intervals between the product of the second endpoint regulation coefficient are stated, the chord length value interval is determined as.
In the step, the default chord length for obtaining the natural environment setting being on active service according to history design data or propeller is inclined
Shifting amount, and the numerical intervals size setting offset coefficient of discharge of the value interval divided as needed, and the offset coefficient of discharge
It is that the offset coefficient of discharge of setting is consistent with propeller pitch angle interval division, so as to subsequent divided chord length quantity and division propeller pitch angle quantity phase
Together.The product of default chord length offset and offset coefficient of discharge is determined as second interval endpoint adjusted value, because default chord length is inclined
Shifting amount generally exists with percents, so needing in two endpoint values for determining chord length value interval by second interval
Endpoint adjusted value and constant 1 make and and make it is poor, then by with value and the product and difference of default chord length offset and default string
Numerical intervals between the product of long offset are as chord length value interval.
For example, initial chord length is 10 on a certain propeller-blade section, presetting chord length offset is 5%, when the offset coefficient of discharge
When being 1, second interval endpoint adjusted value is 0.05, and further, first end point regulation coefficient is 0.95, the second endpoint adjustment system
Number is 1.05, is based on this, and determining chord length value value interval is (9.5,10.5)；In actual optimization demand, need more
Big numerical intervals look for best propeller pitch angle, adjustable offset coefficient of discharge, it is assumed that offset coefficient of discharge is 2, second interval end
Point adjusted value is 0.1, and further, first end point regulation coefficient is 0.9, and the second endpoint regulation coefficient is 1.1, is based on this, really
Fixed chord length value interval is (9,11).
Further, determine lift resistance ratio by following steps: obtain division propeller pitch angle in each propeller parameter group and
Divide the corresponding lift coefficient of chord length and resistance coefficient；The ratio of the lift coefficient Yu the resistance coefficient is determined, for this
The corresponding lift resistance ratio of propeller parameter group.
In the step, according to the division propeller pitch angle in each propeller parameter group and chord length is divided, is determined in the division paddle
Lift coefficient is determined as corresponding draw with the ratio of resistance coefficient by lift coefficient and resistance coefficient under elongation and division chord length
Divide propeller pitch angle and divides the lift resistance ratio of chord length；Furthermore can also determine the division propeller pitch angle and divide chord length under lift with
And resistance, lift is determined as corresponding division propeller pitch angle with the ratio of resistance and divides the lift resistance ratio of chord length.
The optimization method of Design of Propeller provided by the embodiments of the present application, from the design number of the propeller to be optimized got
In, initial propeller pitch angle and initial chord length of the propeller to be optimized at each propeller-blade section are determined；For each blade
Section determines the propeller pitch angle value of the propeller to be optimized based on default pitch angle offset and the initial propeller pitch angle
Section, and based on default chord length offset and the initial chord length, determine the chord length value interval of the propeller to be optimized；
It is to divide step-length with the default pitch angle offset, obtains multiple division propeller pitch angles in the propeller pitch angle value interval, and
It is to divide step-length with the default chord length offset, obtains multiple division chord lengths in the chord length value interval；By each
It divides propeller pitch angle and each divides chord length permutation and combination, generate multiple propeller parameter groups；Based on each propeller parameter
Division propeller pitch angle and division chord length in group, determine the corresponding multiple lift resistance ratios of the propeller to be optimized；For each blade
Section selects the corresponding target propeller parameter group of the maximum target lift resistance ratio of lift resistance ratio from the multiple lift resistance ratio, and will
Division propeller pitch angle and division chord length in the target propeller parameter group are as the propeller to be optimized at the section
Propeller pitch angle and chord length.
In this way, according to the initial propeller pitch angle of each propeller-blade section, initial chord length and default pitch angle offset and in advance
If chord length offset, propeller pitch angle value interval and chord length value interval are determined, and according to the default pitch angle offset
Multiple divisions in multiple division propeller pitch angles and chord length value interval are obtained in propeller pitch angle value interval with default chord length offset
Propeller pitch angle determines multiple propeller parameter groups, and calculate each according to multiple division propeller pitch angles and multiple division chord lengths
The corresponding lift resistance ratio of propeller parameter group will divide propeller pitch angle and divide chord length in the maximum propeller parameter group of lift resistance ratio,
It is determined as the propeller pitch angle and chord length of corresponding propeller-blade section, the corresponding paddle of maximum lift-drag ratio can be selected on each propeller-blade section
Elongation and chord length can make propeller obtain maximum lift on each propeller-blade section, by the smallest resistance, determine
The optimized parameter of Design of Propeller out helps to improve the accuracy of Design of Propeller.
Referring to Fig. 6, Fig. 6 is a kind of structural schematic diagram for optimizing device provided by the embodiment of the present application, such as institute in Fig. 6
Show, the optimization device 600 includes:
First determining module 610, for from the design data of the propeller to be optimized got, determining the spiral to be optimized
Initial propeller pitch angle and initial chord length of the paddle at each propeller-blade section.
Second determining module 620, for being directed to each propeller-blade section, based on default pitch angle offset and described first
The initial propeller pitch angle that determining module 610 determines determines the propeller pitch angle value interval of the propeller to be optimized, and based on default string
The initial chord length that long offset and first determining module 610 determine, determines the chord length value of the propeller to be optimized
Section.
Generation module 630, for being directed to each propeller-blade section, based on the determining propeller pitch angle of second determining module 620
The chord length value interval that value interval and second determining module 620 determine, it is corresponding more to generate the propeller to be optimized
A propeller parameter group, wherein each propeller parameter group includes a division propeller pitch angle and a division chord length.
Third determining module 640, for determining based on the division propeller pitch angle and division chord length in each propeller parameter group
The corresponding multiple lift resistance ratios of the propeller to be optimized.
Selecting module 650, for being directed to each propeller-blade section, the multiple liters determined from the third determining module 640 hinder
Select the corresponding target propeller parameter group of the maximum target lift resistance ratio of lift resistance ratio than in, and by the target propeller parameter group
In divide propeller pitch angle and divide propeller pitch angle and chord length of the chord length as the propeller to be optimized at the section.
Further, second determining module 620 determines the propeller pitch angle value interval by following steps:
The product for determining default bias coefficient of discharge and the default pitch angle offset is first interval endpoint adjusted value；
By the initial propeller pitch angle and the first interval endpoint adjusted value and value and the initial propeller pitch angle and described the
Numerical intervals between the difference of one interval endpoint adjusted value are determined as the propeller pitch angle value interval.
Further, described second determine that 620 determine the chord length value interval by following steps:
Product based on the default bias coefficient of discharge Yu the default chord length offset is determined as the adjustment of second interval endpoint
Value；
The difference for determining preset constant and second interval endpoint adjusted value is first end point regulation coefficient, and is determined described default normal
Several and second interval endpoint adjusted value and value is the second endpoint regulation coefficient；
By the product and the initial chord length of the initial chord length and the first end point regulation coefficient and second endpoint
Numerical intervals between the product of regulation coefficient are determined as the chord length value interval.
Further, the generation module 630 is based on second determining module for being directed to each propeller-blade section
The chord length value interval that the 620 propeller pitch angle value intervals determined and second determining module 620 determine, generates described to be optimized
When the corresponding multiple propeller parameter groups of propeller, it is used for:
It is to divide step-length with the default pitch angle offset, obtains multiple division pitches in the propeller pitch angle value interval
Angle, and be to divide step-length with the default chord length offset, obtain multiple division chord lengths in the chord length value interval；
Each is divided into propeller pitch angle and each divides chord length permutation and combination, generates multiple propeller parameter groups.
Further, the third determining module 640 determines lift resistance ratio by following steps:
Obtain the lift coefficient corresponding with chord length is divided of the division propeller pitch angle in each propeller parameter group and resistance coefficient；
The ratio of the lift coefficient Yu the resistance coefficient is determined, for the corresponding lift resistance ratio of propeller parameter group.
The optimization device of Design of Propeller provided by the embodiments of the present application, from the design number of the propeller to be optimized got
In, initial propeller pitch angle and initial chord length of the propeller to be optimized at each propeller-blade section are determined；For each blade
Section determines the propeller pitch angle value of the propeller to be optimized based on default pitch angle offset and the initial propeller pitch angle
Section, and based on default chord length offset and the initial chord length, determine the chord length value interval of the propeller to be optimized；
For each propeller-blade section, it is based on the propeller pitch angle value interval and the chord length value interval, generates the spiral to be optimized
The corresponding multiple propeller parameter groups of paddle, wherein each propeller parameter group includes a division propeller pitch angle and a division string
It is long；Based on the division propeller pitch angle in each propeller parameter group and chord length is divided, determines that the propeller to be optimized is corresponding more
A lift resistance ratio；For each propeller-blade section, select the maximum target lift resistance ratio of lift resistance ratio corresponding from the multiple lift resistance ratio
Target propeller parameter group, and using the division propeller pitch angle in the target propeller parameter group and chord length is divided as described to excellent
Change propeller pitch angle and chord length of the propeller at the section.
In this way, according to the initial propeller pitch angle of each propeller-blade section, initial chord length and default pitch angle offset and in advance
If chord length offset, propeller pitch angle value interval and chord length value interval are determined, according to propeller pitch angle value interval and chord length
Multiple division propeller pitch angles in value interval determine multiple propeller parameter groups, and calculate each with multiple and division chord length
The corresponding lift resistance ratio of a propeller parameter group will divide propeller pitch angle and divide string in the maximum propeller parameter group of lift resistance ratio
It is long, it is determined as the propeller pitch angle and chord length of corresponding propeller-blade section, can selects maximum lift-drag ratio corresponding on each propeller-blade section
Propeller pitch angle and chord length, propeller can be made to obtain maximum lift on each propeller-blade section, by the smallest resistance,
The optimized parameter for determining Design of Propeller helps to improve the accuracy of Design of Propeller.
Referring to Fig. 7, Fig. 7 is the structural schematic diagram of a kind of electronic equipment provided by the embodiment of the present application.Such as institute in Fig. 7
Show, the electronic equipment 700 includes processor 710, memory 720 and bus 730.
The memory 720 is stored with the executable machine readable instructions of the processor 710, when electronic equipment 700 is transported
When row, communicated between the processor 710 and the memory 720 by bus 730, the machine readable instructions are by the place
When managing the execution of device 710, the optimization method of the Design of Propeller in the embodiment of the method as shown in above-mentioned Fig. 2 and Fig. 5 can be executed
The step of, specific implementation can be found in embodiment of the method, and details are not described herein.
The embodiment of the present application also provides a kind of computer readable storage medium, is stored on the computer readable storage medium
Computer program can execute in the embodiment of the method as shown in above-mentioned Fig. 2 and Fig. 5 when the computer program is run by processor
Design of Propeller optimization method the step of, specific implementation can be found in embodiment of the method, and details are not described herein.
It is apparent to those skilled in the art that for convenience and simplicity of description, the system of foregoing description,
The specific work process of device and unit, can refer to corresponding processes in the foregoing method embodiment, and details are not described herein.
In several embodiments provided herein, it should be understood that disclosed systems, devices and methods, it can be with
It realizes by another way.The apparatus embodiments described above are merely exemplary, for example, the division of the unit,
Only a kind of logical function partition, there may be another division manner in actual implementation, in another example, multiple units or components can
To combine or be desirably integrated into another system, or some features can be ignored or not executed.Another point, it is shown or beg for
The mutual coupling, direct-coupling or communication connection of opinion can be through some communication interfaces, device or unit it is indirect
Coupling or communication connection can be electrical property, mechanical or other forms.
The unit as illustrated by the separation member may or may not be physically separated, aobvious as unit
The component shown may or may not be physical unit, it can and it is in one place, or may be distributed over multiple
In network unit.It can select some or all of unit therein according to the actual needs to realize the mesh of this embodiment scheme
's.
It, can also be in addition, each functional unit in each embodiment of the application can integrate in one processing unit
It is that each unit physically exists alone, can also be integrated in one unit with two or more units.
It, can be with if the function is realized in the form of SFU software functional unit and when sold or used as an independent product
It is stored in the executable non-volatile computer-readable storage medium of a processor.Based on this understanding, the application
Technical solution substantially the part of the part that contributes to existing technology or the technical solution can be with software in other words
The form of product embodies, which is stored in a storage medium, including some instructions use so that
One computer equipment (can be personal computer, server or the network equipment etc.) executes each embodiment institute of the application
State all or part of the steps of method.And storage medium above-mentioned includes: USB flash disk, mobile hard disk, read-only memory (Read-Only
Memory, ROM), random access memory (Random Access Memory, RAM), magnetic or disk etc. is various to deposit
Store up the medium of program code.
Finally, it should be noted that embodiment described above, the only specific embodiment of the application, to illustrate the application
Technical solution, rather than its limitations, the protection scope of the application is not limited thereto, although with reference to the foregoing embodiments to this Shen
It please be described in detail, those skilled in the art should understand that: anyone skilled in the art
Within the technical scope of the present application, it can still modify to technical solution documented by previous embodiment or can be light
It is readily conceivable that variation or equivalent replacement of some of the technical features；And these modifications, variation or replacement, do not make
The essence of corresponding technical solution is detached from the spirit and scope of the embodiment of the present application technical solution, should all cover the protection in the application
Within the scope of.Therefore, the protection scope of the application should be subject to the protection scope in claims.
Claims (10)
1. a kind of optimization method of Design of Propeller, which is characterized in that the optimization method includes:
From the design data of the propeller to be optimized got, determine the propeller to be optimized at each propeller-blade section
Initial propeller pitch angle and initial chord length；
The spiral shell to be optimized is determined based on default pitch angle offset and the initial propeller pitch angle for each propeller-blade section
The propeller pitch angle value interval of paddle is revolved, and based on default chord length offset and the initial chord length, determines the spiral to be optimized
The chord length value interval of paddle；
For each propeller-blade section, it is based on the propeller pitch angle value interval and the chord length value interval, is generated described to be optimized
The corresponding multiple propeller parameter groups of propeller, wherein each propeller parameter group includes that a division propeller pitch angle and one draw
Divide chord length；
Based on the division propeller pitch angle in each propeller parameter group and chord length is divided, determines that the propeller to be optimized is corresponding more
A lift resistance ratio；
For each propeller-blade section, the corresponding target spiral shell of the maximum target lift resistance ratio of lift resistance ratio is selected from the multiple lift resistance ratio
Paddle parameter group is revolved, and using the division propeller pitch angle in the target propeller parameter group and divides chord length as the spiral to be optimized
Propeller pitch angle and chord length of the paddle at the section.
2. optimization method according to claim 1, which is characterized in that determine propeller pitch angle value area by following steps
Between:
The product for determining default bias coefficient of discharge and the default pitch angle offset is first interval endpoint adjusted value；
By the initial propeller pitch angle and the first interval endpoint adjusted value and value and the initial propeller pitch angle and described the
Numerical intervals between the difference of one interval endpoint adjusted value are determined as the propeller pitch angle value interval.
3. optimization method according to claim 2, which is characterized in that determine chord length value area by following steps
Between:
Product based on the default bias coefficient of discharge Yu the default chord length offset is determined as the adjustment of second interval endpoint
Value；
The difference for determining preset constant and second interval endpoint adjusted value is first end point regulation coefficient, and is determined described default normal
Several and second interval endpoint adjusted value and value is the second endpoint regulation coefficient；
By the product and the initial chord length of the initial chord length and the first end point regulation coefficient and second endpoint
Numerical intervals between the product of regulation coefficient are determined as the chord length value interval.
4. optimization method according to claim 1, which is characterized in that it is described to be directed to each propeller-blade section, it is based on the paddle
Elongation value interval and the chord length value interval generate the corresponding multiple propeller parameter groups of the propeller to be optimized, packet
It includes:
It is to divide step-length with the default pitch angle offset, obtains multiple division pitches in the propeller pitch angle value interval
Angle, and be to divide step-length with the default chord length offset, obtain multiple division chord lengths in the chord length value interval；
Each is divided into propeller pitch angle and each divides chord length permutation and combination, generates multiple propeller parameter groups.
5. optimization method according to claim 1, which is characterized in that determine lift resistance ratio by following steps:
Obtain the lift coefficient corresponding with chord length is divided of the division propeller pitch angle in each propeller parameter group and resistance coefficient；
The ratio of the lift coefficient Yu the resistance coefficient is determined, for the corresponding lift resistance ratio of propeller parameter group.
6. a kind of optimization device of Design of Propeller, which is characterized in that the optimization device includes:
First determining module, for from the design data of the propeller to be optimized got, determining the propeller to be optimized
Initial propeller pitch angle and initial chord length at each propeller-blade section；
Second determining module determines mould based on default pitch angle offset and described first for being directed to each propeller-blade section
The initial propeller pitch angle that block determines determines the propeller pitch angle value interval of the propeller to be optimized, and based on default chord length offset
And the initial chord length that first determining module determines, determine the chord length value interval of the propeller to be optimized；
Generation module, for be directed to each propeller-blade section, based on second determining module determine propeller pitch angle value interval and
The chord length value interval that second determining module determines generates the corresponding multiple propeller parameters of the propeller to be optimized
Group, wherein each propeller parameter group includes a division propeller pitch angle and a division chord length；
Third determining module, for based on the division propeller pitch angle in each propeller parameter group and dividing chord length, determine it is described to
Optimize the corresponding multiple lift resistance ratios of propeller；
Selecting module selects to rise from multiple lift resistance ratios that the third determining module determines for being directed to each propeller-blade section
Hinder more corresponding than maximum target lift resistance ratio target propeller parameter group, and by the division paddle in the target propeller parameter group
The propeller pitch angle and chord length of elongation and division chord length as the propeller to be optimized at the section.
7. optimization device according to claim 6, which is characterized in that second determining module is determined by following steps
The propeller pitch angle value interval:
The product for determining default bias coefficient of discharge and the default pitch angle offset is first interval endpoint adjusted value；
By the initial propeller pitch angle and the first interval endpoint adjusted value and value and the initial propeller pitch angle and described the
Numerical intervals between the difference of one interval endpoint adjusted value are determined as the propeller pitch angle value interval.
8. optimization device according to claim 7, which is characterized in that second determining module is determined by following steps
The chord length value interval:
Product based on the default bias coefficient of discharge Yu the default chord length offset is determined as the adjustment of second interval endpoint
Value；
The difference for determining preset constant and second interval endpoint adjusted value is first end point regulation coefficient, and is determined described default normal
Several and second interval endpoint adjusted value and value is the second endpoint regulation coefficient；
By the product and the initial chord length of the initial chord length and the first end point regulation coefficient and second endpoint
Numerical intervals between the product of regulation coefficient are determined as the chord length value interval.
9. a kind of electronic equipment characterized by comprising processor, memory and bus, the memory are stored with the place
The executable machine readable instructions of device are managed, when electronic equipment operation, by described between the processor and the memory
Bus communication executes the spiral as described in any in claim 1 to 5 when the machine readable instructions are executed by the processor
The step of optimization method of paddle design.
10. a kind of computer readable storage medium, which is characterized in that be stored with computer on the computer readable storage medium
Program executes the excellent of the Design of Propeller as described in any in claim 1 to 5 when the computer program is run by processor
The step of change method.
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