CN112052528B - Method for designing aerodynamic profile of novel rotor blade of helicopter - Google Patents
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Abstract
The invention belongs to the technical field of aerodynamic design of helicopters, and discloses a method for designing the aerodynamic shape of a novel rotor blade of a helicopter. Aiming at the increasingly urgent requirements of the existing helicopter models and the next generation helicopter models on low-noise and high-performance rotors, an optimization target is formulated, optimization parameters and ranges are determined based on the past engineering design experience and a large number of pneumatic layout parameter sensitivity analysis results, an optimization method based on a proxy model and a genetic algorithm is adopted, multi-wheel rotor pneumatic layout optimization iterative design and calculation are carried out, and a novel rotor pneumatic appearance design scheme meeting performance requirements is obtained.
Description
Technical Field
The invention belongs to the technical field of aerodynamic design of helicopters, and particularly relates to a design method for aerodynamic appearance of a novel rotor blade of a helicopter.
Background
The rotor blade has a plurality of aerodynamic parameters such as airfoil configuration, torsion distribution, chord length distribution, blade tip form and the like, and the rotor has a plurality of design targets such as hovering efficiency in a hovering flight state, forward flight lift-drag ratio in a horizontal forward flight state, aerodynamic noise in an inclined descending flight state and the like, so that the rotor blade aerodynamic layout design is a multi-parameter and multi-target optimization iterative process. In the process of the aerodynamic layout optimization design of the rotor blades, a manual 'sea calculation' method is often adopted for screening, a large amount of calculation is carried out on a single parameter or a limited combination of two or three parameters, a better parameter is selected for solidification, and then other parameters are optimized.
Disclosure of Invention
The purpose of the invention is as follows: the novel rotor blade aerodynamic configuration of the helicopter is designed by a set of new optimized flow, the hovering efficiency and the forward flying lift-drag ratio of the rotor are improved while the aerodynamic noise of the rotor is reduced, and the requirements of the helicopter on silence and high performance are met.
The technical scheme of the invention is as follows:
a method for designing the aerodynamic profile of a helicopter's new rotor blade, said method comprising the steps of:
the method comprises the following steps: according to the design requirements of the helicopter, setting a rotor wing optimization target and giving design constraints;
step two: setting blade optimization design parameters and ranges;
step three: giving a sample point by an optimization method based on the agent model;
step four: aerodynamic layout parameters such as airfoil position, torsion distribution, chord length distribution and the like are given based on the blade parametric model;
step five: generating a blade grid suitable for the shape of the advanced blade;
step six: solving a rotor flow field to give the hovering and forward flying performances of the rotor;
step seven: taking load information obtained by flow field calculation as input, performing rotor aerodynamic noise evaluation, and giving a rotor noise level;
step eight: if the aerodynamic performance and the noise level of the rotor meet the index requirements, the optimization is stopped; if the index requirements are not met, generating a new sample point by using an optimization method by taking the pneumatic performance and the noise level as response values; and repeating the fourth step to the seventh step to carry out sample point optimization iteration.
Further, the rotor optimization goal in the first step is: rotor aerodynamic performance and aerodynamic noise level.
Further, rotor aerodynamic performance includes: hovering efficiency of the rotor at typical takeoff weight, forward flight lift-drag ratio of the rotor at maximum cruising speed.
Furthermore, the rotor wing aerodynamic noise selects an observation point in a noise concentration area as a noise reduction target area, and the average value of the area is taken as a response value.
Further, the blade optimization design parameters include: the airfoil comprises a radial position of an airfoil with the thickness of 9 percent, a torsion starting position of 'zero', a chord length at a linear forward-swept starting position, a chord length at a backward-swept starting position, a chord length of a blade tip, a distance from a trailing edge point to a horizontal trailing edge line at 1.0R, a lower reverse starting position of the blade tip and a lower reverse angle.
Further, the range of blade optimization design parameters includes:
9% thickness airfoil radial position range: 0.8R to 1R;
"zero" twist start position range: 0.9R to 1R;
chord length range at the straight line forward sweep start position: 1.03 to 1.1C;
straight forward sweep start position range: 0.7R to 0.8R;
chord length range at the sweep start position: 1.1 to 1.3C;
sweep home position range: 0.83R-0.95R;
blade tip chord length range: 0.333-0.5C;
1.0R range of distance from trailing edge point to horizontal trailing edge line: 0C to 0.5C;
lower tip reverse start position range: 0.93R-0.97R;
range of anhedral angles: 0 degree to 20 degrees;
wherein, R is the rotor radius, and C is the chord length of the blade at the position of 0.25R relative radius.
Further, the optimized weight coefficients of hovering efficiency of the rotor under a typical takeoff weight, forward flight lift-drag ratio of the rotor under a maximum cruising speed state and aerodynamic noise are respectively as follows: 0.25, 0.5.
Further, in the sixth step, a CFD method based on the RANS master control equation is adopted to solve the rotor flow field.
The invention has the beneficial effects that: the CFD numerical calculation method is adopted to calculate the aerodynamic shape scheme of the novel rotor blade of the helicopter, the aerodynamic performance and the noise level of the rotor are evaluated, and the result shows that compared with a reference rotor, the aerodynamic performance of the optimized rotor is partially improved, and the maximum noise reduction amplitude can reach 2 dB.
Drawings
FIG. 1 is a schematic view of a rotor aerodynamic noise concentration zone;
FIG. 2 is a flow chart of a method for designing the aerodynamic profile of a novel rotor blade of a helicopter;
fig. 3 is a schematic view of the aerodynamic profile of a novel rotor blade of a helicopter according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Aiming at the increasingly urgent requirements of the existing helicopter models and the next generation helicopter models on low-noise and high-performance rotors, an optimization target is formulated, optimization parameters and ranges are determined based on the past engineering design experience and a large number of pneumatic layout parameter sensitivity analysis results, an optimization method based on a proxy model and a genetic algorithm is adopted, multi-wheel rotor pneumatic layout optimization iterative design and calculation are carried out, and a novel rotor pneumatic appearance design scheme meeting performance requirements is obtained.
A method for designing the aerodynamic profile of a helicopter's new rotor blade, as shown in fig. 2, said method comprising the steps of:
the method comprises the following steps: and (4) establishing an optimization target and giving design constraints.
And (4) formulating a rotor wing optimization target according to the design requirements of the helicopter model. The aerodynamic noise level of the rotor is reduced while the aerodynamic performance of the rotor is improved by taking the aerodynamic parameters and the aerodynamic noise of the rotor as design targets. The aerodynamic parameters of the rotor wing are specifically hovering efficiency of the rotor wing under a typical takeoff weight and a forward flight lift-drag ratio of the rotor wing under a maximum cruising speed state, wherein observation points in a noise concentration area are selected as noise reduction target areas for aerodynamic noise of the rotor wing, an average value of the areas is taken as a response value, and a schematic diagram of the aerodynamic noise concentration area of the rotor wing is given in fig. 1. The weighting coefficients of the three optimization objectives are 0.25, 0.25 and 0.5 respectively.
Step two: and establishing blade optimization design parameters and ranges.
According to the preliminary analysis of the design parameters of the reference paddle, selecting 10 paddle appearance parameter variables for optimization design: the radial position of the airfoil with the thickness of 9 percent is optimized within the range of 0.8R-1R; the zero torsion starting position is optimized within the range of 0.9R-1R;
the chord length at the forward sweeping starting position of the straight line is in the optimized range of 1.03-1.1C; the linear forward-swept initial position is optimized within the range of 0.7R-0.8R; the chord length at the sweepback initial position is in an optimized range of 1.1-1.3 ℃; the sweep-back initial position is optimized within the range of 0.83R-0.95R; the blade tip chord length is in the optimized range of 0.333-0.5 ℃; the distance from the trailing edge point at the 1.0R position to the horizontal trailing edge line is in the optimized range of 0C-0.5C; the optimization range of the lower reverse starting position of the blade tip is 0.93R-0.97R; the down-reflecting angle is optimized within the range of 0-20 degrees. R is the radius of the rotor wing, and C is the chord length at the initial position of the main wing section of the blade.
Step three: and giving a sample point by an optimization method based on the proxy model.
Step four: and pneumatic layout parameters such as airfoil position, torsion distribution, chord length distribution and the like are given based on the paddle parametric model, and the chord length of the optimization scheme is correspondingly scaled in order to ensure that the equivalent real degree of the tension is consistent with the reference rotor wing.
Step five: and generating a blade grid suitable for the shape of the advanced blade according to the aerodynamic layout parameters.
Step six: and (3) solving the rotor flow field by adopting a CFD (computational fluid dynamics) method based on an RANS (random access storage system) main control equation according to the blade grids to obtain blade surface load data, rotor hovering efficiency and forward flight lift-drag ratio.
Step seven: and taking blade surface load data obtained by rotor flow field calculation as input, performing rotor aerodynamic noise evaluation, and giving out a rotor noise level.
Step eight: and (4) generating a new sample point by using an optimization method by taking the rotor wing aerodynamic parameters and the noise level as response values.
Step nine: and repeating the third step to the eighth step.
Step ten: and after a certain amount of sample point optimization iteration is carried out, if the aerodynamic performance and the noise level of the rotor meet the index requirements, the optimization is stopped, otherwise, the optimization is continued.
Fig. 3 shows an embodiment of the aerodynamic profile of a novel helicopter rotor blade designed by the method, having an unconventional blade shape and a three-dimensional tip.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A design method for aerodynamic profile of novel rotor blade of helicopter is characterized in that: the method comprises the following steps:
the method comprises the following steps: setting a rotor wing optimization target according to the design requirements of the helicopter;
step two: setting blade optimization design parameters and ranges;
step three: giving a sample point by an optimization method based on the agent model;
step four: giving aerodynamic layout parameters based on a blade parametric model, wherein the aerodynamic layout parameters at least comprise: airfoil position, twist distribution, chord length distribution;
step five: generating a blade grid suitable for the shape of the blade according to the pneumatic layout parameters;
step six: performing rotor flow field solving according to the generated blade grids, and calculating blade surface load data and rotor aerodynamic parameters;
step seven: according to blade surface load data obtained by rotor flow field calculation, rotor aerodynamic noise evaluation is carried out, and rotor noise level is given;
step eight: if the rotor wing pneumatic parameters and the noise level meet the optimization target, stopping optimization; if the requirement of the index is not met, the aerodynamic parameters and the noise level of the rotor wing are used as response values, and the third step to the seventh step are repeated to carry out optimization iteration of the sample points.
2. The method of claim 1, wherein said method comprises the steps of: the rotor wing optimization target in the step one is as follows: a target rotor aerodynamic parameter and a target aerodynamic noise level.
3. The method of claim 2, wherein said method comprises the steps of: the rotor aerodynamic parameters include: hovering efficiency of the rotor at typical takeoff weight, forward flight lift-drag ratio of the rotor at maximum cruising speed.
4. The method of claim 2, wherein said method comprises the steps of: and (3) selecting an observation point in a noise concentration area as a noise reduction target area by rotor aerodynamic noise, and taking the average value of the area as a response value.
5. The method of claim 1, wherein said method comprises the steps of:
the blade optimization design parameters include: the airfoil comprises a radial position of an airfoil with the thickness of 9 percent, a torsion starting position of 'zero', a chord length at a linear forward-swept starting position, a chord length at a backward-swept starting position, a chord length of a blade tip, a distance from a trailing edge point to a horizontal trailing edge line at 1.0R, a lower reverse starting position of the blade tip and a lower reverse angle.
6. The method of claim 5, wherein said method comprises the steps of: the range of blade optimum design parameters includes:
9% thickness airfoil radial position range: 0.8R to 1R;
"zero" twist start position range: 0.9R to 1R;
chord length range at the straight line forward sweep start position: 1.03 to 1.1C;
straight forward sweep start position range: 0.7R to 0.8R;
chord length range at the sweep start position: 1.1 to 1.3C;
sweep home position range: 0.83R-0.95R;
blade tip chord length range: 0.333-0.5C;
1.0R range of distance from trailing edge point to horizontal trailing edge line: 0C to 0.5C;
lower tip reverse start position range: 0.93R-0.97R;
range of anhedral angles: 0 degree to 20 degrees;
wherein, R is the rotor radius, and C is the chord length of the blade at the position of 0.25R relative radius.
7. A method of designing the aerodynamic profile of a helicopter new rotor blade according to claim 3 wherein: the optimized weight coefficients of the hovering efficiency of the rotor under the typical takeoff weight, the forward flight lift-drag ratio of the rotor under the maximum cruising speed state and the aerodynamic noise are respectively as follows: 0.25, 0.5.
8. The method of claim 1, wherein said method comprises the steps of: and in the sixth step, solving the rotor flow field by adopting a CFD method based on an RANS main control equation.
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| CN113353285B (en) * | 2021-07-13 | 2022-06-10 | 南京航空航天大学 | Method and system for determining rotor wing profile |
| CN117725688A (en) * | 2024-02-18 | 2024-03-19 | 中国空气动力研究与发展中心计算空气动力研究所 | Design method, system and pneumatic appearance of multi-laser system low acoustic explosion high lift-drag ratio appearance |
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| WO2009022033A1 (en) * | 2007-08-16 | 2009-02-19 | Indra Sistemas, S.A. | Method for real-time simulation of a helicopter rotor |
| CN102663195A (en) * | 2012-04-17 | 2012-09-12 | 北京航空航天大学 | Design method for reducing vibration and dynamic stress level of rotor blade |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009022033A1 (en) * | 2007-08-16 | 2009-02-19 | Indra Sistemas, S.A. | Method for real-time simulation of a helicopter rotor |
| CN102663195A (en) * | 2012-04-17 | 2012-09-12 | 北京航空航天大学 | Design method for reducing vibration and dynamic stress level of rotor blade |
Non-Patent Citations (5)
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