CN105043713B - A kind of nacelle outer surface method for testing pressure - Google Patents
A kind of nacelle outer surface method for testing pressure Download PDFInfo
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- CN105043713B CN105043713B CN201510350503.6A CN201510350503A CN105043713B CN 105043713 B CN105043713 B CN 105043713B CN 201510350503 A CN201510350503 A CN 201510350503A CN 105043713 B CN105043713 B CN 105043713B
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Abstract
The invention discloses a kind of nacelle outer surface method for testing pressure.Nacelle outer surface method for testing pressure includes：The pressure data of the outer surface of nacelle to be measured is obtained by Fluid Mechanics Computation method；The test model of nacelle to be measured is tested by manometric test, so as to obtain the outer surface pressure data of test model；Judge in the experimental model in manometric test, layouted with whether having at pressure jump position；If it is not, then choose Fluid Mechanics Computation method in the position corresponding with the pressure jump position in manometric test at pressure data, using the pressure data as the pressure jump position in manometric test pressure data；So as to by being integrated with the pressure data at pressure jump position in the pressure data at other places of layouting in manometric test and Fluid Mechanics Computation method, so as to obtain whole nacelle outer surface pressure data.The nacelle outer surface pressure data for obtaining in this way, pressure data is accurately and reliably.
Description
Technical field
The present invention relates to strength of aircraft experimental technique field, more particularly to a kind of nacelle outer surface method for testing pressure.
Background technology
The pressure distribution of the nacelle outer surface of current aircraft is generally tried using CFD (Fluid Mechanics Computation) methods or pressure measurement
The method tested is determined.
It is excessive or in the case that yaw angle is slightly larger in aircraft angle of attack however, when being calculated using CFD approach, show
Local Discrete and the inaccurate problem of integral result are shown.
And use manometric test method, generally need proportionally to be reduced due to model, it may appear that nacelle it is too small and
Layout limited problem, i.e., can not typically be layouted at pressure jump under lip and the wing, cause this part of important pressure point
Cloth can not be obtained.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
Overcome it is an object of the invention to provide a kind of nacelle outer surface method for testing pressure or at least mitigate existing skill
At least one drawbacks described above of art.
To achieve the above object, the present invention provides a kind of nacelle outer surface method for testing pressure.The nacelle appearance face pressure
Force test method includes：By Fluid Mechanics Computation method, each position to the outer surface of the nacelle to be measured calculates,
So as to the pressure data at each position for the outer surface for obtaining nacelle to be measured；By manometric test to the experiment mould of nacelle to be measured
Type is tested, the pressure data of the nacelle outer surface at place so that each for obtaining the test model is layouted；To calculating fluid
The pressure data obtained in mechanics method and manometric test is analyzed calculating, so as to obtain nacelle appearance surface pressure with flow direction
Changing Pattern, and along the fluid flow to nacelle to be measured same position at section in Pressure Variation；Sentence
The position with pressure jump of the nacelle to be measured in data obtained by disconnected Fluid Mechanics Computation method and maximum pressure point
Position at test data whether have position with pressure jump and the maximum of nacelle to be measured in value, and manometric test
Whether have at pressure spot and layout；If it is, the number pressure of the pressure jump position in directly choosing the manometric test
According to；If it is not, then carrying out following step：The position and maximum for choosing the pressure jump in the Fluid Mechanics Computation method are pressed
The pressure data at other places of layouting in the pressure data in force, and selection manometric test and position of layouting, both are entered
Row is integrated, so as to obtain whole nacelle outer surface pressure data.
Preferably, to choose by the Fluid Mechanics Computation method with the pressure data at pressure jump position
With in maximum pressure position and the manometric test closest at the pressure jump position and maximum pressure position number pressure
According to being modified so that at pressure jump position and maximum pressure position pressure data it is prominent closest to the pressure with it
Smooth continuous pressure data is formed between pressure data at change position.
Preferably, the Fluid Mechanics Computation method includes：Nacelle to be measured is divided into multiple annular cross-sections along its axial direction,
The point of equal amount is equably taken in each annular cross-section, and tries to achieve the pressure data of each annular cross-section respectively.
Preferably, according to corresponding to the pressure jump position it is the annular cross-section in the Fluid Mechanics Computation method
Quantity, choose the pressure data of corresponding each annular cross-section in the Fluid Mechanics Computation method.
Preferably, the nacelle is the nacelle being connected with aircraft.
Preferably, at least a portion of the outer surface of the nacelle is under the wing of the aircraft.
Preferably, it is corresponding with the pressure jump position in the manometric test in the Fluid Mechanics Computation method
Pressure jump position the pressure data number pressure that at least includes at the pressure jump position at the maximum pressure point that is subject to
According to.
Nacelle outer surface method for testing pressure in the present invention is by choosing being tried with pressure measurement in Fluid Mechanics Computation method
Pressure data at pressure jump position in testing at corresponding position, using the pressure data as the pressure in manometric test
The pressure data of power mutated site；So as to by the pressure data in manometric test and Fluid Mechanics Computation method with pressure
The pressure data of power variant positions is integrated, so as to obtain whole nacelle outer surface pressure data.In this way
The nacelle outer surface pressure data for arriving, pressure data accurately and reliably, relative to prior art, goes out when solving using CFD approach
Existing use CFD approach, while also solving the problems, such as to occur that nacelle is too small and layouts limited using manometric test method.
Brief description of the drawings
Fig. 1 is the schematic flow sheet of nacelle outer surface according to an embodiment of the invention method for testing pressure.
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Face is described in detail with reference to accompanying drawing to embodiments of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
Nacelle outer surface of the invention method for testing pressure includes：
By Fluid Mechanics Computation method, each position to the outer surface of nacelle to be measured calculates, so as to be treated
Pressure data at each position for the outer surface for surveying nacelle；
The test model of nacelle to be measured is tested by manometric test, the place so that each for obtaining test model is layouted
Nacelle outer surface pressure data；
Pressure data to being obtained in Fluid Mechanics Computation method and manometric test is analyzed calculating, so as to obtain cabin
External surface pressure with flow direction Changing Pattern, and along fluid flow to nacelle to be measured same position at section in pressure
Power Changing Pattern；
Judge nacelle to be measured in the data obtained by Fluid Mechanics Computation method position with pressure jump and
Whether test data has the position with pressure jump of the nacelle to be measured in value, and manometric test at the position of maximum pressure point
Put and maximum pressure point at whether have layout；If it is, directly choosing the pressure jump position in manometric test
Pressure data；If it is not, then carrying out following step：
The position of the pressure jump in selection Fluid Mechanics Computation method and the pressure data of maximum pressure point, Yi Jixuan
The pressure data at other places of layouting in manometric test and position of layouting are taken, both are integrated, so as to obtain whole cabin
External surface pressure data.
Advantageously, to choose by Fluid Mechanics Computation method with the pressure data at pressure jump position and
Carried out with the pressure data of maximum pressure position closest at the pressure jump position in maximum pressure position and manometric test
Amendment so that at pressure jump position and maximum pressure position pressure data with it closest to the pressure jump position
Smooth continuous pressure data is formed between the pressure data at place.
It is understood that Fluid Mechanics Computation method includes：Nacelle to be measured is divided into multiple ring-types along its axial direction to cut open
Face, equably takes the point of equal amount in each annular cross-section, and tries to achieve the pressure data of each annular cross-section respectively.
Advantageously, the quantity of the annular cross-section in the Fluid Mechanics Computation method according to corresponding to pressure jump position,
Choose the pressure data of corresponding each annular cross-section in Fluid Mechanics Computation method.
Advantageously, the pressure corresponding with the pressure jump position in manometric test in Fluid Mechanics Computation method
The pressure data of mutated site at least includes the pressure data at pressure jump position at the maximum pressure point that is subject to.
It is understood that nacelle is the nacelle being connected with aircraft.
Advantageously, at least a portion of the outer surface of nacelle is under the wing of aircraft.So, it is covered by the wing of aircraft
The region of lid must be pressure jump position, and the position is difficult to be tested by test method, that is, be particularly well-suited to this hair
Bright nacelle outer surface method for testing pressure.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, do not make the essence of the essence disengaging various embodiments of the present invention technical scheme of appropriate technical solution
God and scope.
Claims (7)
1. a kind of nacelle outer surface method for testing pressure, it is characterised in that methods described includes：
By Fluid Mechanics Computation method, each position to the outer surface of nacelle to be measured calculates, so as to obtain cabin to be measured
Pressure data at each position of the outer surface of body；
The test model of nacelle to be measured is tested by manometric test, the place so that each for obtaining the test model is layouted
Nacelle outer surface pressure data；
Pressure data to being obtained in Fluid Mechanics Computation method and manometric test is analyzed calculating, so as to obtain outside nacelle
Surface pressing with flow direction Changing Pattern, and along the fluid flow to nacelle to be measured same position at section in pressure
Power Changing Pattern；
Judge position with pressure jump and the maximum of nacelle to be measured in the data obtained by Fluid Mechanics Computation method
At the position of pressure spot test data whether have the position with pressure jump of the nacelle to be measured in value, and manometric test with
And at maximum pressure point whether have layout；If it is, the pressure jump position in directly choosing the manometric test
Pressure data；If it is not, then carrying out following step：
Choose position and the pressure data of maximum pressure point of pressure jump in the Fluid Mechanics Computation method, Yi Jixuan
The pressure data at other places of layouting in manometric test and position of layouting are taken, both are integrated, so as to obtain whole institute
State nacelle outer surface pressure data.
2. nacelle outer surface as claimed in claim 1 method for testing pressure, it is characterised in that calculate stream by described to choosing
In mechanics method with the pressure data and maximum pressure position at pressure jump position and the manometric test most
Be modified with the pressure data of maximum pressure position close at the pressure jump position so that at pressure jump position and
The pressure data of maximum pressure position and form smooth company closest between the pressure data at the pressure jump position with it
Continuous pressure data.
3. nacelle outer surface as claimed in claim 1 method for testing pressure, it is characterised in that the Fluid Mechanics Computation method
Including：Nacelle to be measured is divided into multiple annular cross-sections along its axial direction, the point of equal amount is equably taken in each annular cross-section,
And the pressure data of each annular cross-section is tried to achieve respectively.
4. nacelle outer surface as claimed in claim 3 method for testing pressure, it is characterised in that according to the pressure jump position
Corresponding is the quantity of the annular cross-section in the Fluid Mechanics Computation method, in the selection Fluid Mechanics Computation method
The pressure data of corresponding each annular cross-section.
5. nacelle outer surface as claimed in claim 1 method for testing pressure, it is characterised in that the nacelle is to be connected with aircraft
Nacelle.
6. nacelle outer surface as claimed in claim 5 method for testing pressure, it is characterised in that the outer surface of the nacelle is extremely
A few part is under the wing of the aircraft.
7. nacelle outer surface as claimed in claim 1 method for testing pressure, it is characterised in that the Fluid Mechanics Computation method
In the pressure jump position corresponding with the pressure jump position in the manometric test pressure data at least include institute
State the pressure data at the maximum pressure point being subject at pressure jump position.
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| CN201510350503.6A CN105043713B (en) | 2015-06-23 | 2015-06-23 | A kind of nacelle outer surface method for testing pressure |
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| CN201510350503.6A CN105043713B (en) | 2015-06-23 | 2015-06-23 | A kind of nacelle outer surface method for testing pressure |
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| CN105043713A CN105043713A (en) | 2015-11-11 |
| CN105043713B true CN105043713B (en) | 2017-06-16 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109858065B (en) * | 2018-11-23 | 2023-05-05 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for predicting aerodynamic load of external stores of airplane |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1746621A (en) * | 2005-10-11 | 2006-03-15 | 天津大学 | Flow profile measuring device |
| JP2014025395A (en) * | 2012-07-26 | 2014-02-06 | Ihi Corp | Engine duct and aircraft engine |
| CN104071330A (en) * | 2013-03-28 | 2014-10-01 | 波音公司 | Monitoring of high-lift systems for aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8752394B2 (en) * | 2010-03-15 | 2014-06-17 | Rolls-Royce Corporation | Determining fan parameters through pressure monitoring |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1746621A (en) * | 2005-10-11 | 2006-03-15 | 天津大学 | Flow profile measuring device |
| JP2014025395A (en) * | 2012-07-26 | 2014-02-06 | Ihi Corp | Engine duct and aircraft engine |
| CN104071330A (en) * | 2013-03-28 | 2014-10-01 | 波音公司 | Monitoring of high-lift systems for aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 大型客机机舱压力及气密检测设备研制与应用;马敏剑;《液压与气动》;20131231;96-99 * |
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