CN108984862A - A kind of aerodynamic characteristic CFD calculated result modification method - Google Patents
A kind of aerodynamic characteristic CFD calculated result modification method Download PDFInfo
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- CN108984862A CN108984862A CN201810677100.6A CN201810677100A CN108984862A CN 108984862 A CN108984862 A CN 108984862A CN 201810677100 A CN201810677100 A CN 201810677100A CN 108984862 A CN108984862 A CN 108984862A
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Abstract
The present invention relates to helicopter Pneumatic Calculation technical field, in particular to a kind of aerodynamic characteristic CFD calculated result modification method includes the steps of determining that plus reequips the aerodynamic configuration and installation site of hung outside helicopter equipment；Calculate the aerodynamic characteristic data for adding repacking forebody；Judge the accuracy and reliability of CFD calculation method；To the aerodynamic characteristic data for adding repacking rear body；When adding the aerodynamic characteristic for fuselage CFD calculated value after repacking to meet the index request of resistance, pitching moment and yawing, carry out in next step；Helicopter fuselage aerodynamic characteristic data after obtaining plus reequiping.Compared with helicopter model wind tunnel test, this method can rapidly calculate the helicopter fuselage aerodynamic characteristic data after adding repacking, to which the time for making helicopter obtain aerodynamic characteristic data reduces by 70% or more, also, this method facilitate Helicopter flight performance, flight quality, rotor load and flight load etc. it is subsequent calculate everything goes well with your work promote.
Description
Technical field
The present invention relates to helicopter Pneumatic Calculation technical field, in particular to a kind of aerodynamic characteristic CFD calculated result amendment
Method.
Background technique
Helicopter fuselage aerodynamic characteristic data are to carry out the meter such as flying quality, flight quality, rotor load and flight load
The design of calculation inputs, and is the important foundation data in helicopter development process.Helicopter fuselage aerodynamic characteristic data are obtained at present
Mainly there are wind tunnel test and CFD to calculate two methods.Wherein wind tunnel test needs to design and produce helicopter model early period, coordinate etc.
It to wind tunnel test time etc., cannot rapidly modify to aerodynamic configuration during test, the period is long, and cost
It is relatively high.And with the development of the progress of computer technology and numerical computation method, CFD calculating speed is getting faster, and calculates knot
The accuracy and reliability of fruit is also higher and higher.
Many research and development institutions and company can be reduced gone straight up in this way using the thinking development helicopter of " machine is many types of " at present
Machine development cost accelerates development progress.It is installed additional on basic model helicopter and modified segment equipment is pneumatic to the fuselage of helicopter
Characteristic has bigger influence, and adds the lead time of remodeling helicopter shorter, therefore carry out wind-tunnel examination without the time cycle
It tests.
Summary of the invention
The object of the present invention is to provide a kind of aerodynamic characteristic CFD calculated result modification methods, to solve existing helicopter
Aerodynamic characteristic for fuselage data capture method it is existing at least one the problem of.
The technical scheme is that
A kind of aerodynamic characteristic CFD calculated result modification method, includes the following steps:
Step 1: determining plus reequiping the aerodynamic configuration and installation site of hung outside helicopter equipment；
Step 2: carrying out CFD calculating to the helicopter fuselage aerodynamic characteristic before described plus repacking, forebody is reequiped to adding
Aerodynamic characteristic data；
Step 3: the CFD calculated result before repacking will be added to compare and analyze with wind tunnel test value, the calculating side CFD is judged
The accuracy and reliability of method；If accurate and reliable, carry out in next step；Otherwise, return step two improve CFD calculation method；
Step 4: reequiping the pneumatic of rear body to adding to adding the helicopter fuselage aerodynamic characteristic after repacking to carry out CFD calculating
Performance data；
Step 5: whether the aerodynamic characteristic for fuselage CFD calculated value after judgement plus repacking meets resistance, pitching moment and yaw
The index request of torque；If satisfied, then carrying out next step data correction；If not satisfied, then comparative analysis adds the CFD of repacking front and back
Calculated value, the aerodynamic configuration and installation site of Optimal improvements plug-in device, until meeting index request；
Step 6: according to add repacking front and back aerodynamic characteristic for fuselage CFD calculate between difference, in conjunction with add repacking before going straight up to
Machine aerodynamic characteristic for fuselage wind tunnel test data obtain adding the helicopter fuselage aerodynamic characteristic data after repacking.
Optionally, during the grid dividing of the step 2, mesh refinement is carried out to presumptive area, is counted later
It calculates and obtains the aerodynamic characteristic data of fuselage.
Optionally, during the grid dividing of the step 4, near the presumptive area and plug-in device
Region carries out mesh refinement, is calculated later and obtains the aerodynamic characteristic data of fuselage.
Invention effect:
Aerodynamic characteristic CFD calculated result modification method of the invention, the helicopter after capable of rapidly calculating plus reequiping
Aerodynamic characteristic for fuselage data, so that the time for making helicopter obtain aerodynamic characteristic data reduces by 70% or more；Helicopter is facilitated to fly
Row performance, flight quality, rotor load and flight load etc. it is subsequent calculate everything goes well with your work promote；And it is possible to according to helicopter
The variation of development demand and state of the art rapidly obtains the aerodynamic characteristic data adjusted after aerodynamic configuration, is hung outside helicopter
The aerodynamic configuration of equipment and the Optimal improvements of installation site pass through technical support.
Detailed description of the invention
Fig. 1 is the schematic diagram of aerodynamic characteristic CFD calculated result modification method of the present invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
1 pair of aerodynamic characteristic CFD calculated result modification method of the invention is described in further details with reference to the accompanying drawing.
The present invention provides a kind of aerodynamic characteristic CFD calculated result modification method, by straight before and after conversion unit to adding
The CFD that liter machine carries out aerodynamic characteristic for fuselage is calculated, in conjunction with the wind tunnel test data added before repacking, after obtaining plus reequiping
Helicopter fuselage aerodynamic characteristic data, to rapidly promote model development process.
It can specifically include following steps:
Step 1: determining plus reequiping the aerodynamic configuration and installation site of hung outside helicopter equipment.Aerodynamic configuration and installation
Position has bigger influence to the aerodynamic drag of helicopter.The aerodynamic configuration of plug-in device is streamlined as far as possible, while and machine
Body has a smooth surface transition.It, will be plug-in by reasonable general layout and coordination under the premise of meeting the realization of plug-in device function
Equipment is mounted on the place smaller to air flow effect.
Step 2: reequiping the pneumatic of forebody to adding to adding the helicopter fuselage aerodynamic characteristic before repacking to carry out CFD calculating
Performance data；Further, during the grid dividing that CFD is calculated, it is that mesh refinement is carried out to presumptive area, is counted later
It calculates and obtains the aerodynamic characteristic data of fuselage.Wherein, preferably presumptive area refers on fuselage that aerodynamic configuration is more complicated and wake zone
Domain.
Step 3: the CFD calculated result before repacking will be added to compare and analyze with wind tunnel test value, the calculating side CFD is judged
The accuracy and reliability of method；If accurate and reliable, carry out in next step；Otherwise, return step two improve CFD calculation method.Tool
Body, the numerical value of comparative analysis includes resistance coefficient, pitching moment coefficient, yawing moment coefficient.
Step 4: reequiping the pneumatic of rear body to adding to adding the helicopter fuselage aerodynamic characteristic after repacking to carry out CFD calculating
Performance data；Equally, during the grid dividing that CFD is calculated, it is that mesh refinement is carried out to presumptive area, is calculated later
And obtain the aerodynamic characteristic data of fuselage.Wherein, preferably the region near above-mentioned presumptive area and plug-in device is carried out
Mesh refinement is calculated later and obtains the aerodynamic characteristic data of fuselage.
Step 5: aerodynamic characteristic for fuselage CFD calculated value and index of correlation requirement after comparison plus repacking；After judgement plus repacking
Aerodynamic characteristic for fuselage CFD calculated value whether meet the index request of resistance, pitching moment and yawing；If satisfied, then into
Row next step data correction；If not satisfied, then comparative analysis adds the CFD calculated value of repacking front and back, Optimal improvements plug-in device
Aerodynamic configuration and installation site, until meeting index request.
Step 6: according to add repacking front and back aerodynamic characteristic for fuselage CFD calculate between difference, in conjunction with add repacking before going straight up to
Machine aerodynamic characteristic for fuselage wind tunnel test data obtain adding the helicopter fuselage aerodynamic characteristic data after repacking；It is specific to use following public affairs
Formula:
F=F1+F2-F3；
Wherein, the helicopter fuselage aerodynamic characteristic data after F is indicated plus reequiped；Wind tunnel test number before F1 is indicated plus reequiped
According to；CFD calculates data after F2 is indicated plus reequiped；F3 adds CFD before repacking to calculate data.
Compared with helicopter model wind tunnel test, this method can rapidly calculate the helicopter fuselage gas after adding repacking
Dynamic characteristic data, so that the time for making helicopter obtain aerodynamic characteristic data reduces by 70% or more.Facilitate Helicopter flight performance,
Flight quality, rotor load and flight load etc. it is subsequent calculate everything goes well with your work promote.And demand can be developed according to helicopter
With the variation of state of the art, the aerodynamic characteristic data adjusted after aerodynamic configuration are rapidly obtained.For the gas of hung outside helicopter equipment
The Optimal improvements of dynamic shape and installation site pass through technical support.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (3)
1. a kind of aerodynamic characteristic CFD calculated result modification method, which comprises the steps of:
Step 1: determining plus reequiping the aerodynamic configuration and installation site of hung outside helicopter equipment；
Step 2: carrying out CFD calculating to the helicopter fuselage aerodynamic characteristic before described plus repacking, the pneumatic of forebody is reequiped to adding
Performance data；
Step 3: the CFD calculated result before repacking will be added to compare and analyze with wind tunnel test value, CFD calculation method is judged
Accuracy and reliability；If accurate and reliable, carry out in next step；Otherwise, return step two improve CFD calculation method；
Step 4: to adding the helicopter fuselage aerodynamic characteristic after repacking to carry out CFD calculating, to the aerodynamic characteristic for adding repacking rear body
Data；
Step 5: whether the aerodynamic characteristic for fuselage CFD calculated value after judgement plus repacking meets resistance, pitching moment and yawing
Index request；If satisfied, then carrying out next step data correction；If not satisfied, then comparative analysis adds the CFD of repacking front and back to calculate
Value, the aerodynamic configuration and installation site of Optimal improvements plug-in device, until meeting index request；
Step 6: according to the difference added between the aerodynamic characteristic for fuselage CFD calculating of repacking front and back, in conjunction with the helicopter machine added before reequiping
Body aerodynamic characteristic wind tunnel test data obtain adding the helicopter fuselage aerodynamic characteristic data after repacking.
2. aerodynamic characteristic CFD calculated result modification method according to claim 1, which is characterized in that in the step 2
Grid dividing during, to presumptive area carry out mesh refinement, calculated later and obtain the aerodynamic characteristic data of fuselage.
3. aerodynamic characteristic CFD calculated result modification method according to claim 2, which is characterized in that in the step 4
Grid dividing during, near the presumptive area and plug-in device region carry out mesh refinement, counted later
It calculates and obtains the aerodynamic characteristic data of fuselage.
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Cited By (6)
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| CN109900486A (en) * | 2019-03-04 | 2019-06-18 | 北京空天技术研究所 | A kind of winged hot aeroperformance acquisition methods of aircraft of band |
| CN111581722A (en) * | 2020-04-30 | 2020-08-25 | 中国直升机设计研究所 | Wing body fused transportation helicopter short wing shape design method |
| CN112199904A (en) * | 2020-09-25 | 2021-01-08 | 中国直升机设计研究所 | Helicopter component load severe state selection and evaluation method |
| CN112651075A (en) * | 2020-10-30 | 2021-04-13 | 中国直升机设计研究所 | Design method of spoiler for weakening tail screen movement of helicopter |
| CN114611437A (en) * | 2022-05-09 | 2022-06-10 | 上海华模科技有限公司 | Method and device for establishing aircraft pneumatic model database based on CFD technology |
| 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 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109900486A (en) * | 2019-03-04 | 2019-06-18 | 北京空天技术研究所 | A kind of winged hot aeroperformance acquisition methods of aircraft of band |
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| CN112199904A (en) * | 2020-09-25 | 2021-01-08 | 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 |
| CN112651075A (en) * | 2020-10-30 | 2021-04-13 | 中国直升机设计研究所 | Design method of spoiler for weakening tail screen movement of helicopter |
| CN114611437A (en) * | 2022-05-09 | 2022-06-10 | 上海华模科技有限公司 | Method and device for establishing aircraft pneumatic model database based on CFD technology |
| 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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| CN108984862B (en) | 2021-05-07 |
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