CN108984862B - Pneumatic characteristic CFD calculation result correction method - Google Patents
Pneumatic characteristic CFD calculation result correction method Download PDFInfo
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Abstract
The invention relates to the technical field of helicopter aerodynamic computation, in particular to a method for correcting a computational result of aerodynamic Characteristics (CFD), which comprises the following steps: determining the aerodynamic shape and the installation position of the modified helicopter plug-in equipment; calculating aerodynamic characteristic data of the fuselage before modification; judging the accuracy and reliability of the CFD calculation method; adding aerodynamic characteristic data of the modified body; carrying out the next step under the condition that the CFD calculated value of the aerodynamic characteristics of the modified machine body meets the index requirements of resistance, pitching moment and yawing moment; and obtaining the aerodynamic characteristic data of the modified helicopter body. Compared with a wind tunnel test of a helicopter model, the method can quickly calculate the aerodynamic characteristic data of the body of the modified helicopter, so that the time for the helicopter to obtain the aerodynamic characteristic data is reduced by more than 70 percent, and the method is convenient for the subsequent calculation work of the flight performance, the flight quality, the rotor load, the flight load and the like of the helicopter to be smoothly promoted.
Description
Technical Field
The invention relates to the technical field of helicopter aerodynamic computation, in particular to a method for correcting a computational result of aerodynamic Characteristics (CFD).
Background
The aerodynamic characteristic data of the helicopter body is the design input for calculating the flight performance, the flight quality, the rotor load, the flight load and the like, and is important basic data in the development process of the helicopter. At present, two methods of wind tunnel test and CFD calculation are mainly used for obtaining the aerodynamic characteristic data of the helicopter body. The helicopter model needs to be designed and manufactured in the early stage of the wind tunnel test, waiting time of the wind tunnel test is coordinated, the pneumatic appearance cannot be rapidly modified in the test process, the period is long, and the cost is high. With the progress of computer technology and the development of numerical calculation methods, the CFD calculation speed is faster and faster, and the accuracy and reliability of the calculation result are higher and higher.
At present, many research and development mechanisms and companies develop helicopters by adopting the idea of 'one helicopter with multiple types', so that the development cost of the helicopters can be reduced, and the development progress is accelerated. The basic helicopter is provided with a part of equipment which is additionally arranged and modified to have a larger influence on the aerodynamic characteristics of the helicopter body, and the modified helicopter has a shorter development period, so that a wind tunnel test is not carried out in a time period.
Disclosure of Invention
The invention aims to provide a method for correcting a calculation result of aerodynamic characteristics CFD (computational fluid dynamics) so as to solve at least one problem of the existing method for acquiring the aerodynamic characteristics data of a helicopter body.
The technical scheme of the invention is as follows:
a pneumatic characteristic CFD calculation result correction method comprises the following steps:
determining the aerodynamic shape and the installation position of an additionally modified helicopter plug-in device;
secondly, CFD calculation is carried out on the aerodynamic characteristics of the helicopter body before modification until the aerodynamic characteristics of the helicopter body before modification are added;
step three, comparing and analyzing the CFD calculation result before modification with the wind tunnel test value, and judging the accuracy and reliability of the CFD calculation method; if the accuracy and reliability are high, the next step is carried out; otherwise, returning to the step two, and improving the CFD calculation method;
step four, CFD calculation is carried out on the aerodynamic characteristics of the modified helicopter body, and the CFD calculation is added to the aerodynamic characteristics data of the modified helicopter body;
judging whether the CFD calculated value of the aerodynamic characteristics of the modified fuselage meets the index requirements of resistance, pitching moment and yawing moment; if so, carrying out the next step of data correction; if the external hanging equipment does not meet the index requirement, comparing CFD calculated values before and after analysis and modification, and optimizing and improving the pneumatic appearance and the installation position of the external hanging equipment until the index requirement is met;
and step six, according to the difference between the CFD calculation of the aerodynamic characteristics of the helicopter body before and after the addition and modification, combining the wind tunnel test data of the aerodynamic characteristics of the helicopter body before the addition and modification to obtain the aerodynamic characteristic data of the helicopter body after the addition and modification.
Optionally, in the mesh division process in the second step, mesh encryption is performed on the predetermined area, and then calculation is performed to obtain the aerodynamic characteristic data of the fuselage.
Optionally, in the grid division process in the fourth step, grid encryption is performed on the predetermined area and the area near the plug-in device, and then calculation is performed to obtain the aerodynamic characteristic data of the fuselage.
The invention has the following effects:
the method for correcting the calculation result of the aerodynamic characteristic CFD can quickly calculate the aerodynamic characteristic data of the body of the modified helicopter, so that the time for the helicopter to obtain the aerodynamic characteristic data is reduced by more than 70%; the subsequent calculation work of the helicopter, such as the flight performance, the flight quality, the rotor load, the flight load and the like, is facilitated to be smoothly promoted; and moreover, according to the development requirements and the change of the technical state of the helicopter, the aerodynamic characteristic data after the aerodynamic profile is adjusted can be quickly obtained, and the optimization and improvement of the aerodynamic profile and the installation position of the helicopter plug-in equipment are supported by the technology.
Drawings
FIG. 1 is a schematic diagram of the result correction method of the aerodynamic CFD calculation of the present invention.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. 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. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
The method for correcting the result of the calculation of the aerodynamic characteristics CFD according to the present invention will be described in further detail with reference to fig. 1.
The invention provides a method for correcting a computational result of aerodynamic Characteristics (CFD), which is characterized in that CFD calculation of the aerodynamic characteristics of a helicopter body is carried out before and after modification equipment is added, and wind tunnel test data before modification is combined to obtain the aerodynamic characteristics data of the helicopter body after modification, so that the model development process is rapidly promoted.
The method specifically comprises the following steps:
step one, determining the aerodynamic shape and the installation position of the modified helicopter plug-in equipment. The aerodynamic profile and the mounting position have a relatively large influence on the aerodynamic resistance of the helicopter. The aerodynamic appearance of the plug-in device is streamline as much as possible, and simultaneously, the plug-in device is in smooth transition with the surface of the machine body. On the premise of realizing the functions of the plug-in equipment, the plug-in equipment is arranged in a place with less influence on air flow through reasonable overall arrangement and coordination.
Step two, CFD calculation is carried out on the aerodynamic characteristics of the helicopter body before modification until the aerodynamic characteristics of the helicopter body before modification are added; further, in the meshing process of the CFD calculation, the predetermined area is subjected to mesh encryption, and then calculation is performed to obtain the aerodynamic characteristic data of the body. Wherein, the preferred predetermined area refers to the area with more complex aerodynamic shape and wake flow on the fuselage.
Step three, comparing and analyzing the CFD calculation result before modification with the wind tunnel test value, and judging the accuracy and reliability of the CFD calculation method; if the accuracy and reliability are high, the next step is carried out; otherwise, returning to the step two, and improving the CFD calculation method. Specifically, the values of the comparative analysis include a drag coefficient, a pitch moment coefficient, and a yaw moment coefficient.
Step four, CFD calculation is carried out on the aerodynamic characteristics of the modified helicopter body, and the CFD calculation is added to the aerodynamic characteristics data of the modified helicopter body; similarly, in the meshing process of the CFD calculation, the predetermined area is subjected to mesh encryption, and then calculation is performed to obtain the aerodynamic characteristic data of the body. Preferably, the predetermined area and the area near the plug-in device are subjected to grid encryption, and then calculation is performed to obtain the aerodynamic characteristic data of the body.
Step five, comparing the CFD calculated value of the aerodynamic characteristics of the modified body with the requirements of related indexes; judging whether the CFD calculated value of the aerodynamic characteristics of the modified fuselage meets the index requirements of resistance, pitching moment and yawing moment; if so, carrying out the next step of data correction; if the external hanging equipment does not meet the index requirement, comparing CFD calculated values before and after analysis and modification, and optimizing and improving the pneumatic appearance and the installation position of the external hanging equipment until the external hanging equipment meets the index requirement.
Step six, according to the difference between the CFD calculation of the aerodynamic characteristics of the helicopter body before and after the modification, combining the wind tunnel test data of the aerodynamic characteristics of the helicopter body before the modification to obtain the aerodynamic characteristic data of the modified helicopter body; the following formula is specifically adopted:
F＝F1+F2-F3；
wherein F represents the aerodynamic characteristic data of the modified helicopter body; f1 represents wind tunnel test data before refitting; f2 denotes CFD calculation data after modification; f3 plus pre-retrofit CFD calculation data.
Compared with a wind tunnel test of a helicopter model, the method can quickly calculate the aerodynamic characteristic data of the body of the modified helicopter, so that the time for the helicopter to obtain the aerodynamic characteristic data is reduced by more than 70%. The subsequent calculation work of the helicopter, such as the flight performance, the flight quality, the rotor load, the flight load and the like, is facilitated to be smoothly promoted. And the aerodynamic characteristic data after the aerodynamic profile is adjusted can be quickly obtained according to the development requirements and the change of the technical state of the helicopter. The method is technically supported for optimizing and improving the aerodynamic appearance and the mounting position of the helicopter plug-in equipment.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (3)
1. A method for correcting a calculation result of aerodynamic Characteristics (CFD) is characterized by comprising the following steps:
determining the aerodynamic shape and the installation position of an additionally modified helicopter plug-in device;
secondly, CFD calculation is carried out on the aerodynamic characteristics of the helicopter body before modification to obtain the aerodynamic characteristic data of the helicopter body before modification;
step three, comparing and analyzing the CFD calculation result before modification with the wind tunnel test value, and judging the accuracy and reliability of the CFD calculation method; if the accuracy and reliability are high, the next step is carried out; otherwise, returning to the step two, and improving the CFD calculation method;
step four, CFD calculation is carried out on the aerodynamic characteristics of the modified helicopter body to obtain the aerodynamic characteristic data of the modified helicopter body;
judging whether the CFD calculated value of the aerodynamic characteristics of the modified fuselage meets the index requirements of resistance, pitching moment and yawing moment; if so, carrying out the next step of data correction; if the external hanging equipment does not meet the index requirement, comparing CFD calculated values before and after analysis and modification, and optimizing and improving the pneumatic appearance and the installation position of the external hanging equipment until the index requirement is met;
and step six, according to the difference between the CFD calculation of the aerodynamic characteristics of the helicopter body before and after the addition and modification, combining the wind tunnel test data of the aerodynamic characteristics of the helicopter body before the addition and modification to obtain the aerodynamic characteristic data of the helicopter body after the addition and modification.
2. The aerodynamic characteristic CFD calculation result correction method according to claim 1, wherein in the meshing process of the second step, the predetermined area is meshed and encrypted, and then calculation is performed to obtain the aerodynamic characteristic data of the body.
3. The aerodynamic characteristic CFD calculation result correction method according to claim 2, wherein in the meshing process of the fourth step, the predetermined area and the area near the plug-in device are meshed and encrypted, and then calculation is performed to obtain aerodynamic characteristic data of the body.
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| CN109900486B (en) * | 2019-03-04 | 2020-12-08 | 北京空天技术研究所 | Method for acquiring thermal aerodynamic performance of aircraft with flight |
| CN111581722B (en) * | 2020-04-30 | 2021-12-03 | 中国直升机设计研究所 | Wing body fused transportation helicopter short wing shape design method |
| CN112199904B (en) * | 2020-09-25 | 2022-06-24 | 中国直升机设计研究所 | Helicopter component load severe state selection and evaluation method |
| CN112182754B (en) * | 2020-09-25 | 2022-11-04 | 中国直升机设计研究所 | Method for calculating aerodynamic resistance of surface projection of helicopter body |
| CN112651075B (en) * | 2020-10-30 | 2022-11-04 | 中国直升机设计研究所 | Design method of spoiler for weakening tail screen movement of helicopter |
| CN114611437B (en) * | 2022-05-09 | 2022-08-09 | 上海华模科技有限公司 | Method and device for establishing aircraft pneumatic model database based on CFD technology |
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