CN206876373U - The surface pressure measurement device of aircraft slat covering - Google Patents
The surface pressure measurement device of aircraft slat covering Download PDFInfo
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- CN206876373U CN206876373U CN201720418678.0U CN201720418678U CN206876373U CN 206876373 U CN206876373 U CN 206876373U CN 201720418678 U CN201720418678 U CN 201720418678U CN 206876373 U CN206876373 U CN 206876373U
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Abstract
The utility model discloses a kind of surface pressure measurement device of aircraft slat covering.Surface pressure measurement device of the present utility model includes flexible pad and pressure signal collector, the inside of flexible pad is disposed with a series of measuring pressure passages being separated from each other, one end of every measuring pressure passage is the pressure tap positioned at the upper surface of flexible pad, the other end is that the measuring pressure passage positioned at a side of flexible pad exports, pressure signal collector has the multiple interfaces being adapted with measuring pressure passage outlet, and measuring pressure passage is exported for being connected correspondingly with interface.The surface pressure measurement device of aircraft slat covering of the present utility model, it is simple to operate and detachable, repeatable to utilize, additionally it is possible at utmost to ensure the accuracy and validity of measurement data.
Description
Technical field
It the utility model is related to the technical field of the surface pressure measurement of aircraft, more particularly to a kind of aircraft slat covering
Surface pressure measurement device.
Background technology
At present, some experiments including aircraft icing mnncl tcst technology become more and more important, and test parameters is surveyed
The accurate and reasonability of amount is the important guarantee of test reliability, and one of importance relates to the survey of surface pressing
Amount.By taking the correlation test of anti-icing system as an example, no matter in anti-icing system icing tunnel authorization experiment, Flight Test, in order to verify
Anti-icing system performance, it is necessary to simulate and obtain the covering pressure and temperature data of the anti-icing leading edge of system, it is necessary to as far as possible as much as possible
The measurement apparatus for reducing Test Data Collecting installs influence of the method to interior flow field additional, so as to keep interior flow field uniformity.
However, according to related wind tunnel test both domestic and external and flight test, protected to match wing Flow Field outside aerodynamic characteristic
Hold consistent, it is necessary to verify its consistency by the leading edge surface for measuring slat pressure (Cp).At present, the Cp being widely adopted is surveyed
Weight testing method is to arrange row's pressure tap by the measurement section of the slat covering in test model aircraft, while in slat
Portion is corresponding in turn to each pressure tap and arranges that row's measuring pressure passage is finally drawn to pressure tester by lid altogether, obtains pressure letter
Number.
It is this to arrange pressure tap in skin-surface while the Cp measuring methods of measuring pressure passage are arranged inside slat, can not
Flow field heat transfer characteristic, the flow field Temperature Distribution of wing anti-ice system icing mnncl tcst model can be influenceed with avoiding, so as to cause
The Temperature Distribution numerical value of the anti-icing leading edge of the wing anti-ice system of icing mnncl tcst measurement is deviated.Moreover, this be arranged in
Measuring pressure passage arrangement inside the slat covering of narrow space, very high, measuring pressure passage and pressure tap are required to processing technology
Interface position metal stresses be present, Aircraft Flight Test experiment during wing be in harsh vibration condition, measuring pressure passage
It is easy to fall off to cause part gathered data invalid.
It would therefore be highly desirable to propose that a kind of flow field that is new, can not influenceing aircraft testing model is distributed and dismounts simplicity
Surface pressure measurement device.
Utility model content
The technical problems to be solved in the utility model is to overcome the survey of aircraft slat surface pressing of the prior art
Amount method, flow field distribution, the flow field heat transfer characteristic of aircraft can be influenceed, causes measurement result deviation, and to processing technology
It is required that too high, and the defects of measuring pressure passage easily comes off and influences measurement data validity, a kind of aircraft slat covering is proposed
Surface pressure measurement device.
The utility model is that solve above-mentioned technical problem by following technical proposals：
The utility model provides a kind of surface pressure measurement device of aircraft slat covering, and its feature is that it includes
Flexible pad and pressure signal collector, the inside of the flexible pad are disposed with a series of measuring pressure passages being separated from each other, every
One end of measuring pressure passage is the pressure tap positioned at the upper surface of the flexible pad, and the other end is positioned at a side of the flexible pad
The measuring pressure passage outlet in face, length direction arrangement of the pressure tap along the flexible pad, the pressure signal collector have
With multiple interfaces for being adapted of measuring pressure passage outlet, the measuring pressure passage export for correspondingly with the interface phase
Connection.
It is preferred that the upper surface of the flexible pad have it is roughly the same with the upper surface of the aircraft slat covering coarse
Degree.
It is preferred that the pressure tap is arranged to, and when the upper surface of the flexible pad is in flat state, the pressure tap
It is arranged along a straight line as a row.
It is preferred that the side for the flexible pad that the measuring pressure passage outlet is pointed to positioned at the straight line.
It is preferred that the straight line is, when the upper surface of the flexible pad is in flat state the flexible pad along its
The center line of length direction extension.
It is preferred that the pressure tap is distributed as, in the center section of the row pressure tap, distribution is more intensive, and at it
Remaining part point distribution is more sparse.
It is preferred that all or part of measuring pressure passage is arranged to substantially L-shaped, wherein the portion being connected with the pressure tap
Divide and extend approximately along perpendicular to the direction of the straight line, the part being connected with measuring pressure passage outlet is approximately along parallel to institute
State the direction extension of straight line.
It is preferred that the aircraft slat covering is the slat covering of aircraft testing model.
It is preferred that the diameter of the pressure tap is between 0.5mm and 1mm.
On the basis of common sense in the field is met, above-mentioned each optimum condition, can be combined, produce the utility model respectively compared with
Good example.
Positive effect of the present utility model is：
The surface pressure measurement device of aircraft slat covering of the present utility model, the major part of measurement apparatus are dismantled and assembled outer
Put, in test and can enough directly attaches slat skin-surface and installed, simple to operate and detachable, repeatable to utilize.Together
When, the external and internal compositionses of aircraft testing model will not be destroyed according to surface pressure measurement of the present utility model, can at utmost be protected
Hinder the accuracy and validity of measurement data, and also there is the advantages of high practicality, saving human cost and financial cost, and
It can be applied in the experiment on icing mnncl tcst model and the aircraft wing surface of other variforms.
Brief description of the drawings
Fig. 1 is the schematic diagram of the surface pressure measurement device of the aircraft slat covering of the preferred embodiment of the utility model one.
Fig. 2A is the pressure measurement in the surface pressure measurement device of the aircraft slat covering of the preferred embodiment of the utility model one
The schematic diagram of the preferred arrangement of hole and measuring pressure passage.
Fig. 2 B are the survey in the surface pressure measurement device of the aircraft slat covering of another preferred embodiment of the utility model
The schematic diagram that the another kind of pressure hole and measuring pressure passage is preferably arranged.
Fig. 3 is that the surface pressure measurement device of the aircraft slat covering of the preferred embodiment of the utility model one is in measurement shape
Schematic diagram under state.
Embodiment
With reference to Figure of description, further preferred embodiment of the present utility model is described in detail, following
It is described as exemplary, is not limitation of the utility model, any other still falls within of the present utility model similar to situation
Among protection domain.
In following specific descriptions, the term of directionality, such as "left", "right", " on ", " under ", "front", "rear", etc.,
Direction described in refer to the attached drawing uses.The part of embodiment of the present utility model can be placed in a variety of different directions, direction
The term of property is for illustrative purposes and nonrestrictive.
With reference to shown in figure 1, filled according to the surface pressure measurement of the aircraft slat covering 2 of the preferred embodiment of the utility model one
Put, including flexible pad 1 and pressure signal collector, the inside of flexible pad 1 are disposed with a series of measuring pressure passages being separated from each other,
One end of every measuring pressure passage is the pressure tap 11 positioned at the upper surface of flexible pad 1, and the other end is positioned at a side of flexible pad 1
The measuring pressure passage outlet in face, pressure tap 11 arrange that pressure signal collector has to go out with measuring pressure passage along flexible pad length direction
Multiple interfaces that mouth is adapted, measuring pressure passage are exported for being connected correspondingly with interface.Pressure tap 11 said here
Arrange that expression is that each pressure tap 11 is arranged in along the diverse location of flexible pad length direction along flexible pad length direction,
The distance of the side at both ends of i.e. each pressure tap 11 to flexible pad length direction is different, but is not intended to limit the cloth of pressure tap
Put and strictly arrange along a straight line.And measuring pressure passage is then arranged as in other words longitudinally prolonging at least partially along the length direction of flexible pad
Stretch.In this embodiment, aircraft slat covering 2 can refer to the slat covering 2 for being exclusively used in the model aircraft of a certain experiment.
With reference to shown in figure 3, when carrying out the surface pressure measurement of flank covering, flexible pad 1 is sticked to slat covering 2
Leading edge surface, incoming flow to pressure signal collector by measuring pressure passage via pressure tap 11, gathered by pressure signal collector
Air pressure in each bar measuring pressure passage.By the flexible feature of flexible pad 1, it is brought into close contact to surface to be measured.Measuring pressure passage
It can be shaped in during the processing and manufacturing of flexible pad 1 among flexible pad 1.
According to preferred embodiment of the present utility model, the upper surface of flexible pad 1 has the upper table with aircraft slat covering
The roughly the same roughness in face, so as to the upper surface of more preferable simulation slat covering.It is highly preferred that flexible pad 1 is uniform in thickness
Laminated structure, and in brim-portion thickness gradual change to close to zero.Thus the thickness rank of the edge part of flexible pad 1 is reduced
Jump.
According to preferred embodiment of the present utility model, pressure tap 11 is arranged to, when the upper surface of flexible pad 1 is in plane
During state, pressure tap 11 is arranged along a straight line as a row.The side for the flexible pad 1 that measuring pressure passage outlet is pointed to positioned at straight line.For example,
In preferred embodiment with reference to shown in figure 1, the center line that pressure tap 11 extends along its length along flexible pad 1 is arranged as one
Row.The arrangement shape arrangement of pressure tap 11, is advantageous to more easily obtain the surface to be measured under airflow function according to measurement result
Pressure distribution.
With reference to shown in figure 1, Fig. 2A, according to preferred embodiment of the present utility model, as shown in Figure 1 along a straight line
The pressure tap 11 of single-row arrangement, can further have following distribution：In the center section of a row pressure tap 11, distribution is more intensive,
It is and more sparse in the remainder distribution close to both ends.The distribution of this pressure tap 11 is substantially corresponding to the examination such as wind tunnel test
The distribution of pressure tap in testing.In many experiments, the arrangement of pressure tap typically need to be more intensive in slat leading edge neighbouring position,
More toward slat it is tangential backward, spacing is bigger.And the pressure tap 11 in above-mentioned preferred embodiment of the present utility model is distributed, i.e.,
It can be well adapted in these experiments, and be easy to more easily to obtain in test surface to be measured (such as model aircraft
Slat leading edge surface) on along specific direction pressure gradient be distributed.
With reference to shown in figure 2A, in some preferred embodiments, whole measuring pressure passages 12 are arranged to substantially L-shaped, wherein
Extend with the part that pressure tap 11 is connected approximately along perpendicular to the direction of straight line along the arrangement of pressure tap 11, with measuring pressure passage 12
The part being connected is exported approximately along the direction parallel to straight line along the arrangement of pressure tap 11 to extend.Pressure tap 11 may be arranged to
The center line extended along its length along flexible pad 1 is distributed, and the measuring pressure passage 12 of L-shaped can as shown in Figure 2 A, by perpendicular to this
Center line and the part composition parallel to the center line.
With reference to shown in figure 2B, according to another preferred embodiment of the present utility model, can use with above-mentioned embodiment
The equivalent distribution mode of pressure tap 11 of straight line arrangement pressure tap 11 is set.In view of carried out in stable aerodynamics
Experiment in, the parallel lines of general slat costa are approximate isobar, can be approximately considered two on this parallel lines
The pressure that measuring point measures is equal.Therefore,, can be upper with reference to shown in figure 2B according to another preferred embodiment of the present utility model
On the basis of the embodiment for stating the pressure tap 11 of straight line arrangement, by pressure tap 11, horizontal direction is staggeredly arranged along figure,
And then measuring pressure passage 12 can be arranged simply to the measuring pressure passage 12 of the linear along the length direction extension of flexible pad 1.
According to preferred embodiment of the present utility model, the diameter of pressure tap 11 can be consistent with the diameter of measuring pressure passage 12,
It can be consistent with the diameter of conventional pressure-measuring pipe, such as can be 0.5mm, 0.7mm or 1.0mm etc., be suitable for carrying out ice wind
Test in hole.
The surface pressure measurement device sketched using aircraft slat covering as above is carried out to the slat of model aircraft below
The installation process during surface pressure measurement of cover portion.
First, flexible pad 1 is attached to the surface to be measured of aircraft slat covering, and causes pressure tap 11 to be positioned at table to be measured
Position to be measured on face and towards the direction of flow of measurement air-flow.Then, measuring pressure passage 12 is exported correspondingly with connecing
Mouth is connected.Measurement air-flow is opened, and the measurement data of each bar measuring pressure passage 12 is gathered using pressure signal collector.Its
In, pressure signal collector and measuring pressure passage 12 export the maintenance lid being mountable to positioned at the lower surface of aircraft slat covering
It is interior.
Also, on this basis, it can fix and seal maintenance lid using fluid sealant.Due under aircraft slat covering
The maintenance lid on surface is in the non-flow field zone of influence, thus placement pressure signal collector will not be made to surface pressure measurement herein
Into influence.
After method described above is installed, the surface pressure measurement device under measuring state or under trystate is big
Cause as shown in Figure 3.
After test measurement terminates, maintenance lid can be first opened, disconnects and takes out pressure signal collector.Then, use is close
Maintenance lid is reinstalled in sealing.So far, you can complete the dismounting of whole measurement apparatus.Thus, surface pressure of the present utility model
Force measuring device is detachable, and reusable.
Although the foregoing describing specific embodiment of the present utility model, it will be appreciated by those of skill in the art that
These are merely illustrative of, and the scope of protection of the utility model is defined by the appended claims.Those skilled in the art
Member can make numerous variations or repair to these embodiments on the premise of without departing substantially from principle of the present utility model and essence
Change, but these changes and modification each fall within the scope of protection of the utility model.
Claims (9)
1. a kind of surface pressure measurement device of aircraft slat covering, it is characterised in that it includes flexible pad and pressure signal
Collector, the inside of the flexible pad are disposed with a series of measuring pressure passages being separated from each other, and one end of every measuring pressure passage is position
Pressure tap in the upper surface of the flexible pad, the other end are that the measuring pressure passage positioned at a side of the flexible pad exports,
Length direction arrangement of the pressure tap along the flexible pad, the pressure signal collector has to be exported with the measuring pressure passage
The multiple interfaces being adapted, the measuring pressure passage are exported for being connected correspondingly with the interface.
2. the surface pressure measurement device of aircraft slat covering as claimed in claim 1, it is characterised in that the flexible pad
Upper surface has the roughness roughly the same with the upper surface of the aircraft slat covering.
3. the surface pressure measurement device of aircraft slat covering as claimed in claim 1, it is characterised in that the pressure tap is set
It is set to, when the upper surface of the flexible pad is in flat state, the pressure tap is arranged along a straight line as a row.
4. the surface pressure measurement device of aircraft slat covering as claimed in claim 3, it is characterised in that the measuring pressure passage
The side for the flexible pad that outlet is pointed to positioned at the straight line.
5. the surface pressure measurement device of aircraft slat covering as claimed in claim 4, it is characterised in that the straight line is,
The center line extended along its length of the flexible pad when the upper surface of the flexible pad is in flat state.
6. the surface pressure measurement device of aircraft slat covering as claimed in claim 3, it is characterised in that the pressure tap point
Cloth is that in the center section of the row pressure tap, distribution is more intensive, and is distributed in remainder more sparse.
7. the surface pressure measurement device of aircraft slat covering as claimed in claim 4, it is characterised in that all or part of
Measuring pressure passage is arranged to substantially L-shaped, wherein with the part that the pressure tap is connected approximately along perpendicular to the side of the straight line
To extension, with the part that measuring pressure passage outlet is connected approximately along the direction extension parallel to the straight line.
8. the surface pressure measurement device of aircraft slat covering as claimed in claim 1, it is characterised in that the aircraft slat
Covering is the slat covering of aircraft testing model.
9. the surface pressure measurement device of aircraft slat covering as claimed in claim 1, it is characterised in that the pressure tap
Diameter is between 0.5mm and 1mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720418678.0U CN206876373U (en) | 2017-04-20 | 2017-04-20 | The surface pressure measurement device of aircraft slat covering |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720418678.0U CN206876373U (en) | 2017-04-20 | 2017-04-20 | The surface pressure measurement device of aircraft slat covering |
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| Publication Number | Publication Date |
|---|---|
| CN206876373U true CN206876373U (en) | 2018-01-12 |
Family
ID=61344055
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| CN201720418678.0U Active CN206876373U (en) | 2017-04-20 | 2017-04-20 | The surface pressure measurement device of aircraft slat covering |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264832A (en) * | 2017-04-20 | 2017-10-20 | 中国商用飞机有限责任公司 | The surface pressure measurement device and method of aircraft slat covering |
| CN110589020A (en) * | 2019-09-24 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Structure and method for determining influence of surface quality defects of airplane |
| CN110884688A (en) * | 2019-12-13 | 2020-03-17 | 中国空气动力研究与发展中心 | Surface pressure measuring device for hypersonic vehicle and pressure leading pipeline connecting method thereof |
| CN112577896A (en) * | 2020-12-12 | 2021-03-30 | 江西洪都航空工业集团有限责任公司 | Detection device for thin skin bulging phenomenon |
| CN112758348A (en) * | 2020-12-24 | 2021-05-07 | 中国飞行试验研究院 | Pressure distribution measuring device for flight test and pressure measuring belt modification method |
| CN112816126A (en) * | 2020-12-24 | 2021-05-18 | 中国飞行试验研究院 | Intelligent flexible pressure measuring belt for flight test |
| CN113074903A (en) * | 2021-03-25 | 2021-07-06 | 中国石油大学胜利学院 | Pressure testing system and method based on blade icing experiment |
| CN110884688B (en) * | 2019-12-13 | 2024-06-04 | 中国空气动力研究与发展中心 | Surface pressure measuring device of hypersonic vehicle and pressure guiding pipeline connecting method thereof |
-
2017
- 2017-04-20 CN CN201720418678.0U patent/CN206876373U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264832A (en) * | 2017-04-20 | 2017-10-20 | 中国商用飞机有限责任公司 | The surface pressure measurement device and method of aircraft slat covering |
| CN110589020A (en) * | 2019-09-24 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Structure and method for determining influence of surface quality defects of airplane |
| CN110884688A (en) * | 2019-12-13 | 2020-03-17 | 中国空气动力研究与发展中心 | Surface pressure measuring device for hypersonic vehicle and pressure leading pipeline connecting method thereof |
| CN110884688B (en) * | 2019-12-13 | 2024-06-04 | 中国空气动力研究与发展中心 | Surface pressure measuring device of hypersonic vehicle and pressure guiding pipeline connecting method thereof |
| CN112577896A (en) * | 2020-12-12 | 2021-03-30 | 江西洪都航空工业集团有限责任公司 | Detection device for thin skin bulging phenomenon |
| CN112758348A (en) * | 2020-12-24 | 2021-05-07 | 中国飞行试验研究院 | Pressure distribution measuring device for flight test and pressure measuring belt modification method |
| CN112816126A (en) * | 2020-12-24 | 2021-05-18 | 中国飞行试验研究院 | Intelligent flexible pressure measuring belt for flight test |
| CN113074903A (en) * | 2021-03-25 | 2021-07-06 | 中国石油大学胜利学院 | Pressure testing system and method based on blade icing experiment |
| CN113074903B (en) * | 2021-03-25 | 2022-04-22 | 中国石油大学胜利学院 | Pressure testing system and method based on blade icing experiment |
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