CN106840573A - A kind of Flush Airdata Sensing System scaling method - Google Patents
A kind of Flush Airdata Sensing System scaling method Download PDFInfo
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- CN106840573A CN106840573A CN201611180132.2A CN201611180132A CN106840573A CN 106840573 A CN106840573 A CN 106840573A CN 201611180132 A CN201611180132 A CN 201611180132A CN 106840573 A CN106840573 A CN 106840573A
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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
Abstract
The present invention relates to a kind of Flush Airdata Sensing System scaling method, belong to flush airdata sensing system technical field, the wind tunnel test scaling method is demarcated using supersonic wind tunnel to Flush Airdata Sensing System.The step waveform and position of intersecting point of Mach number are demarcated using stration technique measurement, size is compared according to the contracting that measurement result designs Flush Airdata Sensing System wind tunnel model, installation site and the experiment angle of attack, test model is ensured in wind-tunnel calibration process, and residing flow field position can avoid the influence of step ripple all the time.The method also specify mould processing precision, and pressure tap installs perpendicularity, many requirements such as model installation level and pressure measurement pipeline sealing detection.Demarcate Flush Airdata Sensing System and obtain real certainty of measurement.The system calibrating result high precision of the method, efficiency high and reliability are high.
Description
Technical field
Demarcated the present invention relates to Flush Airdata Sensing System and designed, more particularly to flush airdata sensing system
System wind tunnel test scaling method, belongs to flush airdata sensing system technical field.
Background technology
Flush airdata sensing system (Flush Air Data Sensing, FADS) system, by pressure sensor battle array
The pressure distribution of row measurement aircraft surface, the flight such as static pressure, Mach number, the angle of attack, yaw angle is obtained by special algorithm indirectly
Atmosphere data.FADS systems are that supersonic aircraft obtains main path of the flight atmosphere data as flight control input, special
It is not particularly important for the supersonic aircraft of air suction type.
FADS system calibratings include that wind tunnel test and flight test are demarcated, but because flight test general technical is very multiple
Miscellaneous, research fund is expensive, target range difficult coordination and experiment preparatory period are long etc., so carrying out flight test demarcates difficulty very
Greatly.Therefore ground wind tunnel test turns into FADS system calibrating technical ways.It is a pole that the wind tunnel test of FADS systems is demarcated
Its fine special test, is influenceed by many factors such as flow field quality, modelling processing and installations.
FADS system main operational principles are the pressure distributions that aircraft surface is measured by array of pressure sensors, are passed through
Special algorithm obtains aircraft to flow atmosphere data indirectly.Therefore system calibrating primary key technical problems be stablized,
Uniform high-quality Flow Field in Wind Tunnel, it is ensured that the pressure value of measuring point is not influenceed ability accurate calibration by extraneous other factorses on model
The certainty of measurement of FADS systems.Failing to exclude extraneous other factorses interference, i.e., cannot accurate calibration FADS systems accurately survey
Accuracy of measurement, will cause FADS system developments to fail.For domestic existing type of production wind-tunnel, Flow Field in Wind Tunnel Quality Design is typically each
Designed according to national military standard technical standard, mainly meet the routine test mission requirements such as aircraft dynamometry and pressure measurement, wind-tunnel
Most of position flow field quality is cannot to meet the similar special test of FADS system calibratings in test section.Therefore wind-tunnel is completed
Experimental Calibration must carry out in-depth analysis research to Flow Field in Wind Tunnel structure, avoid various interference and find suitable FADS system calibratings
Flow field regions.Influence flow field quality mainly by two aspect influence factors of step ripple and wind tunnel wall interference in wind tunnel test.Step ripple
The gap docked with test section by the jet pipe of wind-tunnel produces expansion wave system to constitute, it is impossible to which eliminating the effects of the act to avoid.Hole wall is done
It is to get to the reflection of hole wall by test model head base body shock wave to cause to disturb, can only be by designing a model blockage ratio and Control experiment most
The big angle of attack is influenceed with reducing its.Both the above factor can influence the pressure value on FADS system pressure tap array layouts, cause
There is deviation in algorithm calculation result, has a strong impact on FADS system calibrating certainties of measurement.Second key technical problems is that model sets
Meter and processing, it has to be warranted that the site error of pressure tap, pressure tap and wall perpendicularity, it is ensured that the installation knot of model joint
Structure intensity, in case the buffeting of supersonic speed high frequency produces loosening to cause measurement error in process of the test.3rd key technical problems are
The installation accuracy control of test model, for the axisymmetric model of air-breathing missile, model changes the outfit and is easiest to circumferential deviation occur,
The angle of attack and sideslip measurement error are significantly affected generation.Therefore must be carried out accordingly according to certain standard after model is installed
Detection and fine setting.
Because domestic FADS system researches are started late, specific standard has not yet been formed to system calibrating method, lack system
The Specifications that system is demarcated.
The content of the invention
The present invention is in order to overcome the shortcomings of existing Wind Tunnel Technique condition, it is proposed that a kind of Flush Airdata Sensing System
Scaling method, can be with the certainty of measurement of accurate calibration system.
The object of the invention is achieved by following technical solution：
A kind of Flush Airdata Sensing System scaling method is provided, is comprised the following steps：
(1) parameter of supersonic wind tunnel, jet pipe length L1mm, sectional dimension B1mm × B1mm, test Mach number Ma are obtained
It is 2.0~4.0, aircraft prototype length is L2mm, and equivalent diameter is Dmm；According to experiment demand estimate range of angles of attack for-α~
α；
(2) when measuring Mach number 2~4 using stration technique, the position of the angle of up/down steps ripple and upper and lower ripple intersection point is surveyed
Amount intersection point constitutes the cone in region with nozzle section, is flowed along wind-tunnel apart from nozzle entry sectional position size X1mm, upper and lower ripple
The median plane in direction is isosceles triangle, base angle 2 and apex angle α 3；
(3) the ratio value Sc of modulus type contracting ratio is 1；
(4) as step ripple intersection point X1<During 1/2L1mm, jet pipe back segment is selected as pilot region, strut lengths L0Calculate public
Formula is：
As step ripple intersection point X1 >=1/2L1mm, leading portion pilot region, strut lengths L are selected0Computing formula is：
L0≥(Sc.D/2)/tan((arctan(B1/(L1-L3))×180/π-α)×π/180)+L3-L4-100
It is L3mm that wherein attack angle mechanism turns the heart apart from nozzle exit, and attack angle mechanism is with strut connector apart from nozzle exit
L4mm；
(5) if the length L of the pole for calculating0Effective range is not at, then readjusts step range of angles of attack and contracting
The ratio value of ratio, takes Sc=Sc-0.1 or α=α -2, return to step (4)；If L0In effective range, it is determined that α, Sc and L0；
(6) according to the dimensioned dummy vehicle after the ratio value Sc contractings ratio of contracting ratio, according to L0Processing pole；
(7) Flush Airdata Sensing System is arranged on inside dummy vehicle, dummy vehicle is pacified by pole
On attack angle mechanism；
(8) blasting is carried out in the range of Mach number 2~4, attack angle mechanism runs in the range of-α to α, it is embedded big
Destiny measures static pressure, Mach number, the angle of attack and the yaw angle of dummy vehicle according to sensor-based system；By flush airdata sensing system system
The static pressure of the dummy vehicle that the static pressure of the dummy vehicle of unified test, Mach number, the angle of attack and sideslip angular amount and wind tunnel system are measured,
Mach number, the angle of attack compare with yaw angle, judge whether airdata sensing system measurement is accurate.
Preferably, the length L of pole0Effective range be more than 0.1L1, and less than 0.6L1.
Preferably, judge whether accurate specific method is for Flush Airdata Sensing System measurement：Static pressure error≤
500Pa, Mach number error≤0.1, angle of attack error≤0.5 °, sideslip angle error≤0.5 ° then judges that embedded atmosphere data is passed
Sensing system measurement is accurate；If wherein thering is parameter error to exceed threshold range, judge that Flush Airdata Sensing System should
Parameter measurement error precision is not up to design requirement.
Preferably, dummy vehicle is processed according to Sc, each dimension precision requirement in dummy vehicle surface reaches ± 0.02mm,
Dummy vehicle surface pressure tap status requirement：Pressure measurement hole site circumference deviation positioned at dummy vehicle summit is less than 0.1mm,
The error of perpendicularity≤3 ', the position axial error for playing pressure tap on wall is less than 0.1mm, and circumferential error is less than 0.1mm, processes survey
Behind pressure hole, dummy vehicle surface is polished.
Preferably, dummy vehicle is arranged on upper rear horizontal gradient error≤3 ' of pole.
Preferably, pressure measurement pipeline is installed, load cell goes out installed in flight model table through pressure-measuring pipe pass in pressure tap
Face, after dummy vehicle installation, 105kPa~130kPa is pressurized to pressure tap, and Flush Airdata Sensing System is anti-
Between seasonable≤0.5s, stabilization time >=3s；Negative pressure is to 90kPa~5kPa, SRT≤0.5s.
The present invention has the following advantages that compared with prior art：
(1) installation site (length of pole) and size by adjusting dummy vehicle of the invention, avoids step ripple
Interference, obtain uniform flow field, it is ensured that the quality of wind tunnel test.The system calibrating result high precision of the method, efficiency high and
Reliability is high.
(2) size and range of angles of attack by adjusting dummy vehicle of the invention, avoids wind tunnel wall interference, further improves
Test accuracy, it is ensured that the confidence level of experiment.
(3) invention provides for model accuracy and the sealing detection standard of pressure measurement pipeline, it is ensured that the reliability of experiment.
Brief description of the drawings
Fig. 1 is the original dimension schematic diagram of dummy vehicle in the embodiment of the present invention；
Fig. 2 is FADS systems and wind-tunnel peg model scheme of installation in the embodiment of the present invention；
Fig. 3 is experiment schematic diagram of the invention.
Specific embodiment
Referring to Fig. 1, FADS systems are arranged on inside flight model, and P1 to P9 is the pressure measurement pipeline of FADS systems, and pressure measurement is passed
Sensor goes out installed in flight model surface, measurement surface pressure through pressure-measuring pipe pass.Flight model is arranged on wind-tunnel by pole
In test section, referring to Fig. 2.Flight model is arranged on attack angle mechanism by pole, around angle of attack machine under the control of attack angle mechanism
The heart that turns of structure rotates, and the scope rotated during experiment is that range of angles of attack is-α~α.
Supersonic wind tunnel step waveform and position of intersecting point are measured using stration technique, as shown in figure 3, conventional method is used
Dummy vehicle, due to not accounting for the influence of step ripple, in the sphere of action in step ripple, cause demarcate fail, this
Invention considers the influence of step ripple, and dummy vehicle is placed in outside the sphere of action of step ripple, it is ensured that wind tunnel test is demarcated
Process model avoids step ripple, is calculated using step ripple position of intersecting point and obtains model contracting than ratio value and strut lengths.Specific bag
Include the following steps：
(1) parameter of supersonic wind tunnel, jet pipe length L1mm, sectional dimension B1mm × B1mm, test Mach number Ma are obtained
It is 2.0~4.0；Aircraft prototype length is L2mm, and equivalent diameter is Dmm；According to experiment demand estimate range of angles of attack for-α~
α；
(2) when measuring Mach number 2~4 using stration technique, the angle of up/down steps ripple and the position of upper and lower ripple intersection point are obtained
Put, apart from nozzle entry sectional position size X1mm, upper and lower ripple constitutes the cone in region with nozzle section to measurement intersection point, along wind-tunnel
The median plane of direction of flow is isosceles triangle, base angle 2 and apex angle α 3；
(3) the ratio value Sc of modulus type contracting ratio is 1；
(4) as step ripple intersection point X1<During 1/2L1mm, jet pipe back segment is selected as pilot region, strut lengths L0Calculate public
Formula is：
As step ripple intersection point X1 >=1/2L1mm, leading portion pilot region, strut lengths L are selected0Computing formula is：
L0≥(Sc.D/2)/tan((arctan(B1/(L1-L3))×180/π-α)×π/180)+L3-L4-100
It is L3mm that wherein attack angle mechanism turns the heart apart from nozzle exit, and attack angle mechanism is with strut connector apart from nozzle exit
L4mm；
(5) if the length L of the pole for calculating0Effective range is not at, then readjusts step range of angles of attack, take Sc
=Sc-0.1 or α=α -2, return to step (4)；If L0In effective range, it is determined that α, Sc and L0；The length L of pole0's
Effective range is that, more than 0.1L1, and less than 0.6L1, if not in effective range, model cannot normal mounting；
(6) dummy vehicle is processed according to Sc, according to L0Processing pole；
(7) Flush Airdata Sensing System is arranged on inside dummy vehicle, and dummy vehicle is installed by pole
On attack angle mechanism；
(8) blasting is carried out in the range of Mach number 2~4, attack angle mechanism runs in the range of-α to α, it is embedded big
Destiny measures static pressure, Mach number, the angle of attack and the yaw angle of dummy vehicle according to sensor-based system；Airdata sensing system is surveyed
Static pressure, the Mach of the dummy vehicle that the static pressure of dummy vehicle, Mach number, the angle of attack and sideslip angular amount and wind tunnel system are measured
Number, the angle of attack compare with yaw angle, judge whether airdata sensing system measurement is accurate.Judge that airdata sensing system is surveyed
Whether accurate specific method is amount：Static pressure error≤500Pa, Mach number error≤0.1, angle of attack error≤0.5 °, yaw angle
Error≤0.5 °, then judge that airdata sensing system measurement is accurate；If wherein thering is parameter error to exceed threshold range, sentence
Disconnected airdata sensing system parameter measurement is not up to design requirement.
Dummy vehicle is processed according to Sc, each dimension precision requirement in dummy vehicle surface reaches ± 0.02mm, aircraft
Model surface pressure tap status requirement：Pressure measurement hole site circumference deviation positioned at dummy vehicle summit is less than 0.1mm, perpendicularity
Error≤3 ', the position axial error for playing pressure tap on wall is less than 0.1mm, and circumferential error is less than 0.1mm, processes pressure tap
Afterwards, dummy vehicle surface is polished.Dummy vehicle is arranged on upper rear horizontal gradient error≤3 ' of pole.To ensure adding for model
Work and installation quality, improve certainty of measurement.
Pressure measurement pipeline is installed, load cell goes out installed in flight model surface, flight through pressure-measuring pipe pass in pressure tap
After device model installation, 105kPa~130kPa, Flush Airdata Sensing System reaction time are pressurized to pressure tap
≤ 0.5s, stabilization time >=3s；Negative pressure is to 90kPa~5kPa, SRT≤0.5s, it is ensured that pressure measurement pipeline do not block,
It is air tight.
With reference to specific embodiment, the present invention is described in further detail：
Embodiment 1
The present embodiment describes specific implementation process of the present invention in detail by taking the Mach number 2 of rating test as an example：
(1) supersonic wind tunnel jet pipe length is 2400mm, and sectional dimension is 1200mm × 1200mm, and model length is
871mm, model maximum gauge is 268mm.It is L3=800mm, the distance spray of angle of attack joint that attack angle mechanism turns the heart apart from nozzle exit
The distance of pipe outlet is L4=114mm.The range of angles of attack that experiment is estimated is α=- 12 °~12 °.
(2) the step wave structure using Mach number 2 in stration technique measurement supersonic nozzle and the position of upper and lower ripple intersection point,
Measurement position of intersecting point size X1=1050mm, with the coverage of this determination step ripple.Because position of intersecting point is apart from attack angle mechanism
Turn the heart farther out, if the leading portion of selected jet pipe cannot meet as trial zone is estimated experiment range of angles of attack, therefore selected supersonic speed
The wind-tunnel stream that back segment (1050mm~2400mm) Delta Region of wind tunnel nozzle is demarcated as Flush Airdata Sensing System
Field areas, is 2=60.3 ° of base angle for calculating triangular domain high with X1.Range of angles of attack α=- 12 °~12 ° are estimated according to experiment, is attacked
Angle mechanism turns heart L3=800mm, step ripple intersection point X1=1050mm, 2=60.3 ° and α 3=of step ripple Delta Region base angle
59.4°；
(3) the length L0=300mm (wherein Ma=2) of the ratio value Sc=0.8 of model contracting ratio and installation pole.Pole is long
Spend for attack angle mechanism joint with model bottom apart from size.Ensure in process of the test, all of angle of attack state drag is equal
Step ripple can be avoided, and ensures the point on model surface apart from step ripple proximal most position >=100mm.
(4) strut lengths L0=300mm, and in effective range, processing experiment model and pole.Mould processing surface
Each dimension precision requirement is reached within ± 0.02mm, pressure tap status requirement on model：The circumferential deviation in the position on summit≤
0.1mm, the error of perpendicularity≤3 ' play the position axial error≤0.1mm, circumferential error≤0.1mm of pressure tap on wall.Process
After pressure tap, dummy vehicle surface is polished.
(5) after model is arranged on pole above, its horizontal vertical degree error≤3 ' is detected, failing to reaching the level of requirement
The error of perpendicularity, it is necessary to which the roll angle to model is not adjusted, untill horizontal vertical degree error reaches requirement.
(6) after model installation, capable detection is sealed into pressure measurement pipeline.Specific requirement for suppress 105kPa~
130kPa, system reading reaction time≤0.5s, stabilization time >=3s；Negative pressure is to 90kPa~5kPa, system reading reaction time
≤0.5s.Blow every time after wind to being detected according to step (6), reached requirement and then continue blowing.If not up to obtain
Existing gas leakage or clogging, then need opening model to carry out malfunction elimination, overhauls pipeline.
(7) wind tunnel test blowing.
This method is shown in Table 1 with the contrast of conventional scaling method measurement error.Can be drawn from table and use this method
The systematic measurement error of demarcation improves a lot, and static pressure measurement error is reduced to 490Pa, Mach number measurement error by 3000Pa
0.05 is reduced to by 0.15, the angle of attack is reduced to 0.5 ° by 2.5 °, and yaw angle is reduced to 0.5 ° by 1.2 °.The measurement essence of system calibrating
Degree reaches technical requirement.
The contrast (Ma=2) of this method of table 1 and conventional scaling method measurement error
Embodiment 2
(1) supersonic wind tunnel jet pipe length is 2400mm, and sectional dimension is 1.2m × 1.2m, and model length is 871mm, mould
Type maximum gauge is 268mm.It is 800mm, distance of the angle of attack joint apart from nozzle exit that attack angle mechanism turns the heart apart from nozzle exit
It is 114mm.The range of angles of attack that experiment is estimated is α=- 12 °~12 °.
(2) the step wave structure using Mach number 3 in stration technique measurement supersonic nozzle and the position of upper and lower ripple intersection point,
Measurement position of intersecting point size X1=2300mm, with the coverage of this determination step ripple.Because position of intersecting point is apart from attack angle mechanism
Turn that the heart is nearer, thus selected supersonic wind tunnel jet pipe leading portion (0mm~2300mm) Delta Region as embedded atmosphere data
The Flow Field in Wind Tunnel region that sensor-based system is demarcated, is 2=75.4 ° of base angle for calculating triangular domain high with X1.The angle of attack is estimated according to experiment
Scope α=- 12 °~12 °, attack angle mechanism turns heart L3=800mm, step ripple intersection point X1=1690mm, step ripple Delta Region bottom
3=39 ° of angle α 2=70.5 ° and apex angle α；
(3) meet during length L0=1300mm (the wherein Ma=3) of model contracting ratio Sc=0.8 and installation pole and require.
Strut lengths are for attack angle mechanism joint with model bottom apart from size.Ensure in process of the test, under all of angle of attack state
Model can avoid step ripple, and ensure the point on model surface apart from step ripple proximal most position >=100mm.
Processing experiment model and pole, carry out wind tunnel test after installation.
Calibration result is shown in Table 2, and this scaling method, the measurement error high precision of demarcation can be drawn from table.
The contrast (Ma=3) of this method of table 2 and conventional scaling method measurement error
The above, optimal specific embodiment only of the invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
Should all be included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (6)
1. a kind of Flush Airdata Sensing System scaling method, it is characterised in that comprise the following steps：
(1) parameter of supersonic wind tunnel is obtained, jet pipe length L1mm, sectional dimension B1mm × B1mm, test Mach number Ma are 2.0
~4.0, aircraft prototype length is L2mm, and equivalent diameter is Dmm；Range of angles of attack is estimated for-α~α according to experiment demand；
(2) when measuring Mach number 2~4 using stration technique, the position of the angle of up/down steps ripple and upper and lower ripple intersection point, measurement is handed over
Apart from nozzle entry cross-sectional distance X1mm, upper and lower ripple constitutes the cone in region with nozzle section to point, along wind-tunnel direction of flow
Heart face is isosceles triangle, base angle 2 and apex angle α 3；
(3) the ratio value Sc of modulus type contracting ratio is 1；
(4) as step ripple intersection point X1<During 1/2L1mm, jet pipe back segment is selected as pilot region, strut lengths L0Computing formula is：
When step ripple intersection point apart from nozzle entry section apart from X1 >=1/2L1mm, leading portion pilot region, strut lengths L are selected0
Computing formula is：
L0≥(Sc.D/2)/tan((arctan(B1/(L1-L3))×180/π-α)×π/180)+L3-L4-100
It is L3mm that wherein attack angle mechanism turns the heart apart from nozzle exit, and attack angle mechanism is with strut connector apart from nozzle exit L4mm；
(5) if the length L of the pole for calculating0Effective range is not at, then readjusts the ratio of step range of angles of attack and contracting ratio
Example value, takes Sc=Sc-0.1 or α=α -2, return to step (4)；If L0In effective range, it is determined that α, Sc and L0；
(6) according to the dimensioned dummy vehicle after the ratio value Sc contractings ratio of contracting ratio, according to L0Processing pole；
(7) Flush Airdata Sensing System is arranged on inside dummy vehicle, dummy vehicle is arranged on by pole
On attack angle mechanism；
(8) blasting is carried out in the range of Mach number 2~4, attack angle mechanism runs in the range of-α to α, embedded big destiny
According to the static pressure of sensor-based system measurement dummy vehicle, Mach number, the angle of attack and yaw angle；Flush Airdata Sensing System is surveyed
The static pressure of dummy vehicle, Mach number, static pressure, the Mach of the angle of attack and sideslip angular amount and the dummy vehicle of wind tunnel system measurement
Number, the angle of attack compare with yaw angle, judge whether airdata sensing system measurement is accurate.
2. a kind of Flush Airdata Sensing System scaling method according to claim 1, it is characterised in that pole
Length L0Effective range be more than 0.1L1, and less than 0.6L1.
3. a kind of Flush Airdata Sensing System scaling method according to claim 1, it is characterised in that judge embedding
Whether accurate specific method is to enter the measurement of formula airdata sensing system：Static pressure error≤500Pa, Mach number error≤0.1,
Angle of attack error≤0.5 °, sideslip angle error≤0.5 ° then judges that Flush Airdata Sensing System measurement is accurate；If wherein
There is parameter error to exceed threshold range then, judge that the Flush Airdata Sensing System parameter measurement error precision is not up to and set
Meter is required.
4. a kind of Flush Airdata Sensing System scaling method according to claim 1, it is characterised in that according to Sc
Processing dummy vehicle, each dimension precision requirement in dummy vehicle surface reaches ± 0.02mm, dummy vehicle surface pressure tap
Status requirement：Pressure measurement hole site circumference deviation positioned at dummy vehicle summit is less than 0.1mm, and the error of perpendicularity≤3 ' play wall
The position axial error of upper pressure tap is less than 0.1mm, and circumferential error is less than 0.1mm, after processing pressure tap, to dummy vehicle
Surface polishes.
5. a kind of Flush Airdata Sensing System scaling method according to claim 1, it is characterised in that aircraft
Model is arranged on upper rear horizontal gradient error≤3 ' of pole.
6. a kind of Flush Airdata Sensing System scaling method according to claim 4, it is characterised in that pressure tap
Interior installation pressure measurement pipeline, load cell goes out installed in flight model surface, dummy vehicle installation through pressure-measuring pipe pass
Afterwards, 105kPa~130kPa, Flush Airdata Sensing System reaction time≤0.5s, stabilization time are pressurized to pressure tap
≥3s；Negative pressure is to 90kPa~5kPa, SRT≤0.5s.
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| CN111157759A (en) * | 2019-12-24 | 2020-05-15 | 太原航空仪表有限公司 | Fixed differential pressure type attack angle sensor and use method |
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