CN110132526A - A kind of low disturbing pulse type shock tunnel strain type face frictional resistance balance - Google Patents
A kind of low disturbing pulse type shock tunnel strain type face frictional resistance balance Download PDFInfo
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- CN110132526A CN110132526A CN201910455333.6A CN201910455333A CN110132526A CN 110132526 A CN110132526 A CN 110132526A CN 201910455333 A CN201910455333 A CN 201910455333A CN 110132526 A CN110132526 A CN 110132526A
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- sensor
- frictional resistance
- outer housing
- disturbing pulse
- type face
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present embodiments relate to a kind of low disturbing pulse type shock tunnel strain type face frictional resistance balances, it include: sensor outer housing and sensor measurement structure, the sensor measurement structure is through setting inside sensor outer housing, sensor measurement structure is measured by balance malformation caused by gas current friction power, and reflects air-flow along the shearing force size of body surface.The embodiment of the present invention measures the balance malformation as caused by gas current friction power using strain gauge, applied to impulse type wind-tunnel, to reflect air-flow along the shearing force size on object surface, available high accurancy and precision force measurements, and oval type face air flow contacts face design, and air-flow barrier grid are designed, the interference that incoming flow generates sensor is effectively reduced, the research for hypersonic frictional resistance measuring technique is even more to be of great significance.
Description
Technical field
The present embodiments relate to aeromechanics technology fields more particularly to a kind of low disturbing pulse type shock tunnel to answer
Modification face frictional resistance balance.
Background technique
The frictional resistance of aircraft surface is the important component of aircraft resistance, and skin friction resistance greatly limits
The performance of hypersonic aircraft, relevant experimental study show to the hypersonic aircraft for using airbreathing motor
For, frictional resistance can account for the 50% of its drag overall, also have similar ratio in the high lifting body aircraft such as Waverider aircraft
Example.Important component of the frictional resistance as resistance will reduce first in the design of entire hypersonic aircraft,
And drag reduction work must be set up accurately measuring frictional resistance, so for hypersonic frictional resistance measuring technique
Research is even more to be of great significance.
Summary of the invention
In consideration of it, to solve above-mentioned technical problem or partial technical problems, the embodiment of the present invention provide a kind of low interference arteries and veins
Stamp shock tunnel strain type face frictional resistance balance.
In a first aspect, the embodiment of the present invention provides a kind of low disturbing pulse type shock tunnel strain type face frictional resistance balance, packet
It includes:
Sensor outer housing and sensor measurement structure, the sensor measurement structure is through setting in sensor outer housing
Portion, sensor measurement structure are measured by balance malformation caused by gas current friction power, and reflect air-flow along object
The shearing force size in body surface face.
In a possible embodiment, the sensor measurement structure includes that the sensor airflow of sensor outer housing connects
Contacting surface bottom end and is inserted into the support rod of sensor outer housing and is attached at sensor airflow contact surface center, the support
Bar bottom end is attached by ballistic measurement unit with hold-down support.
In a possible embodiment, the sensor airflow contact surface is oval sensor airflow contact surface.
In a possible embodiment, the sensor outer housing surface setting is multiple is located at oval sensor airflow
Air-flow below contact surface obstructs grid, enters inside sensor outer housing to reduce air-flow.
In a possible embodiment, the sensor outer housing surface setting is multiple is located at oval sensor airflow
Air-flow immediately below contact surface obstructs grid.
In a possible embodiment, the air-flow barrier grid are 2~6.
In a possible embodiment, the oval sensor airflow contact surface is plane or type face.
In a possible embodiment, the sensor outer housing top uses and oval sensor airflow contact surface
Same high accuracy install planar structure, the planar structure are round or ellipse.
In a possible embodiment, the border width of the planar structure is H, and border width H > D/2, wherein
D is length of the oval sensor airflow contact surface in direction of flow.
In a possible embodiment, the wind-tunnel shock loading impingement of the ballistic measurement unit measures single
The structural vibration frequency f that member generates meets following formula, f >=2/t, and t is the efficiency test time of impulse type wind-tunnel in formula.
In a possible embodiment, efficiency test time t is determined by wind tunnel operation index.
Technical solution provided in an embodiment of the present invention discloses a kind of low disturbing pulse type shock tunnel strain type face frictional resistance
Balance measures the balance malformation as caused by gas current friction power using strain gauge, is applied to impulse type wind-tunnel, from
And reflect air-flow along the shearing force size on object surface, available high accurancy and precision force measurements, and oval type face
The design of air flow contacts face, and air-flow barrier grid are designed, the interference that incoming flow generates sensor is effectively reduced, rubs for hypersonic
The research for wiping drag measurement technology is even more to be of great significance.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The some embodiments recorded in inventive embodiments can also obtain according to these attached drawings for those of ordinary skill in the art
Obtain other attached drawings
Fig. 1 is that a kind of low disturbing pulse type shock tunnel strain type face frictional resistance balance of the embodiment of the present invention is integrally-built
Schematic top plan view；
Fig. 2 is a kind of sensor measurement structural schematic diagram of the embodiment of the present invention；
Fig. 3 is a kind of sensor outer housing schematic diagram of internal structure of the embodiment of the present invention；
Fig. 4 is a kind of sensor outer housing cross section structure schematic diagram of the embodiment of the present invention.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art
Every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
In order to facilitate understanding of embodiments of the present invention, it is further explained below in conjunction with attached drawing with specific embodiment
Bright, embodiment does not constitute the restriction to the embodiment of the present invention.
As shown in Figure 1, for a kind of low disturbing pulse type shock tunnel strain type face frictional resistance provided by the embodiment of the present invention
The integrally-built schematic top plan view of balance, a kind of low disturbing pulse type shock tunnel strain type face frictional resistance balance, comprising:
Sensor outer housing 1 and sensor measurement structure 2, the sensor measurement structure 2 is through setting in sensor outer housing 1
Inside, sensor measurement structure 2 are measured by balance malformation caused by gas current friction power, and reflect air-flow along
The shearing force size of body surface.
The sensor measurement structure 2 includes the sensor airflow contact surface 201 of sensor outer housing 1, the sensor gas
Bottom end and the support rod 202 of insertion sensor outer housing 1 are attached at stream 201 center of contact surface, and 202 bottom end of support rod is logical
Overbump formula measuring unit 203 is attached with hold-down support 204, as shown in Figure 2.The wherein sensor airflow contact surface
201 be oval sensor airflow contact surface 201.
Traditional frictional resistance balance mostly use it is round or rectangular, there are air-flows contact surface side structure is had an impact it is biggish
Problem, in the case of identical contact area (identical shearing force), the air flow contacts face 201 of ellipsoidal structure effectively reduces side
Front face area, to reduce the influence of air-flow impingement measuring unit 203.
Multiple air-flow resistances for being located at oval 201 lower section of sensor airflow contact surface are arranged in 1 surface of sensor outer housing
Barrier 3 enters inside sensor outer housing 1 to reduce air-flow.Wherein, it is preferred that 1 surface of the sensor outer housing setting is multiple
Air-flow immediately below oval sensor airflow contact surface 201 obstructs grid 3, and the air-flow barrier grid 3 can be 2~6.
Wherein 1 schematic diagram of internal structure of sensor outer housing is as shown in Figure 3.
By CFD (Fluid Mechanics Computation) numerical simulation, the elliptical-shaped contact face compared to round (contact area is identical),
Since side section area is reduced and increases air-flow barrier grid 3, incoming flow significantly reduces (i.e. interference caused by sensor
Incoming flow is impacted sensors sides and is influenced).
The ellipse sensor airflow contact surface 201 is plane or type face, to cooperate the frictional resistance of complex appearance aircraft
Measurement demand.
1 top of sensor outer housing uses and the same high accuracy install plane of oval sensor airflow contact surface 201
Structure, the planar structure are round or ellipse.Wherein 1 cross section structure schematic diagram of sensor outer housing is as shown in Figure 4.
The border width of the planar structure is H, and border width H > D/2, and wherein D is oval sensor airflow contact
Length of the face 201 in direction of flow.
The wherein experience based on CFD numerical simulation result and machining, if the border width is too small, installation accuracy
It is measured etc. then will affect frictional resistance the problem of causing, which is the experience provided based on numerical simulation and machining empirical analysis
Value, guarantee measurement be normally carried out, and the edge designs be sensor installation after flow transition section, the purpose is to reduce by
The influence that frictional resistance measurement is generated after installation error generates step.
Measuring unit structure is by finite element structure design optimization, to meet the hypersonic shock wave wind of the high enthalpy of short test period
Hole frictional resistance measures test requirements document, and the wind-tunnel shock loading impingement measuring unit 203 of the ballistic measurement unit 203 generates
Structural vibration frequency f meet following formula, f >=2/t Hz, t is the efficiency test time of impulse type wind-tunnel, effective examination in formula
Time t is tested to be determined by wind tunnel operation index.
By the above-mentioned description to technical solution provided in an embodiment of the present invention, a kind of low disturbing pulse type shock wave is disclosed
Wind-tunnel strain type face frictional resistance balance measures the balance malformation as caused by gas current friction power using strain gauge, answers
For impulse type wind-tunnel, to reflect air-flow along the shearing force size on object surface, available high accurancy and precision dynamometry knot
Fruit, and oval type face air flow contacts face design, and air-flow barrier grid are designed, it can effectively reduce what incoming flow generated sensor
Interference, the research for hypersonic frictional resistance measuring technique are even more to be of great significance.
The function of modules and the realization process of effect are specifically detailed in the above method and correspond to step in above-mentioned apparatus
Realization process, details are not described herein.
Professional should further appreciate that, described in conjunction with the examples disclosed in the embodiments of the present disclosure
Unit and algorithm steps, can be realized with electronic hardware, computer software, or a combination of the two, hard in order to clearly demonstrate
The interchangeability of part and software generally describes each exemplary composition and step according to function in the above description.
These functions are implemented in hardware or software actually, the specific application and design constraint depending on technical solution.
Professional technician can use different methods to achieve the described function each specific application, but this realization
It should not be considered as beyond the scope of the present invention.
The step of method described in conjunction with the examples disclosed in this document or algorithm, can be executed with hardware, processor
The combination of software module or the two is implemented.Software module can be placed in random access memory (RAM), memory, read-only memory
(ROM), electrically programmable ROM, electrically erasable ROM, register, hard disk, moveable magnetic disc, CD-ROM or technical field
In any other form of storage medium well known to interior.
Above-described specific embodiment has carried out further the purpose of the present invention, technical scheme and beneficial effects
It is described in detail, it should be understood that being not intended to limit the present invention the foregoing is merely a specific embodiment of the invention
Protection scope, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should all include
Within protection scope of the present invention.
Claims (11)
1. a kind of low disturbing pulse type shock tunnel strain type face frictional resistance balance characterized by comprising sensor outer housing and biography
Sensor measurement structure, for the sensor measurement structure through being arranged inside sensor outer housing, sensor measurement structure passes through gas
Balance malformation caused by stream frictional force measures, and reflects air-flow along the shearing force size of body surface.
2. low disturbing pulse type shock tunnel strain type face according to claim 1 frictional resistance balance, which is characterized in that described
Sensor measurement structure includes the sensor airflow contact surface of sensor outer housing, bottom end at sensor airflow contact surface center
Be attached with the support rod of insertion sensor outer housing, the support rod bottom end by ballistic measurement unit and hold-down support into
Row connection.
3. low disturbing pulse type shock tunnel strain type face according to claim 2 frictional resistance balance, which is characterized in that described
Sensor airflow contact surface is oval sensor airflow contact surface.
4. low disturbing pulse type shock tunnel strain type face according to claim 3 frictional resistance balance, which is characterized in that described
Multiple air-flow barrier grid being located at below oval sensor airflow contact surface are arranged in sensor outer housing surface, to reduce air-flow
Into inside sensor outer housing.
5. low disturbing pulse type shock tunnel strain type face according to claim 4 frictional resistance balance, which is characterized in that described
Multiple air-flow barrier grid being located at immediately below oval sensor airflow contact surface are arranged in sensor outer housing surface.
6. according to the described in any item low disturbing pulse type shock tunnel strain type face frictional resistance balances of claim 4 to 5, feature
It is, the air-flow barrier grid are 2~6.
7. low disturbing pulse type shock tunnel strain type face according to claim 3 frictional resistance balance, which is characterized in that described
Oval sensor airflow contact surface is plane or type face.
8. low disturbing pulse type shock tunnel strain type face according to claim 3 frictional resistance balance, which is characterized in that described
Sensor outer housing top uses and the same high accuracy install planar structure of oval sensor airflow contact surface, the planar structure
For round or ellipse.
9. low disturbing pulse type shock tunnel strain type face according to claim 8 frictional resistance balance, which is characterized in that described
The border width of planar structure is H, and border width H > D/2, and wherein D is oval sensor airflow contact surface in direction of flow
Length.
10. low disturbing pulse type shock tunnel strain type face according to claim 2 frictional resistance balance, which is characterized in that institute
It states the structural vibration frequency f that the wind-tunnel shock loading impingement measuring unit of ballistic measurement unit generates and meets following formula, f >=
2/t, t is the efficiency test time of impulse type wind-tunnel in formula.
11. low disturbing pulse type shock tunnel strain type face according to claim 10 frictional resistance balance, which is characterized in that institute
Efficiency test time t is stated to be determined by wind tunnel operation index.
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| CN201910455333.6A CN110132526B (en) | 2019-05-29 | 2019-05-29 | Low-interference pulse type shock tunnel strain profile friction drag balance |
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| CN201910455333.6A CN110132526B (en) | 2019-05-29 | 2019-05-29 | Low-interference pulse type shock tunnel strain profile friction drag balance |
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| CN110132526B CN110132526B (en) | 2020-09-15 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110954291A (en) * | 2019-12-05 | 2020-04-03 | 中国科学院力学研究所 | Assembled high-precision fiber grating friction resistance balance |
| CN111189611A (en) * | 2020-03-13 | 2020-05-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test method based on strain type two-component surface friction resistance measuring balance |
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