CN108267293A - A kind of embedded horizontal tail aerodynamics force measurement device - Google Patents
A kind of embedded horizontal tail aerodynamics force measurement device Download PDFInfo
- Publication number
- CN108267293A CN108267293A CN201810365630.7A CN201810365630A CN108267293A CN 108267293 A CN108267293 A CN 108267293A CN 201810365630 A CN201810365630 A CN 201810365630A CN 108267293 A CN108267293 A CN 108267293A
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- Prior art keywords
- horizontal tail
- force measurement
- measurement device
- aerodynamics force
- embedded
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- 238000005259 measurement Methods 0.000 title claims abstract description 37
- 238000009434 installation Methods 0.000 claims abstract description 33
- 239000011888 foil Substances 0.000 claims abstract description 16
- 238000012545 processing Methods 0.000 claims abstract description 4
- 241000237509 Patinopecten sp. Species 0.000 claims description 8
- 235000020637 scallop Nutrition 0.000 claims description 8
- 238000005096 rolling process Methods 0.000 abstract description 6
- 230000035945 sensitivity Effects 0.000 abstract description 3
- 230000007812 deficiency Effects 0.000 abstract 1
- 238000012360 testing method Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000007916 tablet composition Substances 0.000 description 1
Classifications
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses a kind of embedded horizontal tail aerodynamics force measurement devices, including fixing end and horizontal tail installation end, the fixing end includes connecting rod and fixed tablet, shear groove is provided between connecting rod and fixed tablet, the fixing end and horizontal tail installation end are an integrated steel-structure, ellbeam is played by processing to be formed between fixed tablet and horizontal tail installation end, several foil gauges are provided on the bullet ellbeam and in shear groove.Bridge measurement of the present invention all using shear strain responsive type resistance strain gage, reduces the amplitude of deformation of measuring device under Aerodynamic force action, ensure that the joint gap of measuring device and model；Rolling moment is measured using shear groove, chip measuring device rolling moment component sensitivity output deficiency is overcome, improves the accuracy of the component measurement.Meanwhile the measuring device can be as needed, quickly, conveniently, accurately replaces adjustment horizontal tail setting angle.
Description
Technical field
The present invention relates to aircraft wind tunnel test field of measuring technique, more particularly to measurement aircraft horizontal tail aerodynamic force
A kind of embedded horizontal tail aerodynamics force measurement device.
Background technology
The horizontal tail of aircraft is to adjust the important component of flight attitude, the peace under installation site and different flight state
Dress angle is intended to be studied in advance by wind tunnel test.And it is current, the horizontal tail aerodynamics force measurement device that domestic majority wind-tunnel is equipped with is
Chip measuring device, as Hu Guofeng TH2002A monoblock types balance design calculates report Sichuan：Chinese aerodynamic investigation with
Centre of development fragrant wind-tunnel balance Beijing of velocity air dynamic study 2009.03, He De of institute：National Defense Industry Press
2001.05.Mainly include：Fixing end, measuring cell and model end, the fixing end are used to fix entire measuring device；It is described
Model end is used to fix horizontal tail；The measuring cell is placed between fixing end and model end, and is integral thin-slab structure, is passed through
Foil gauge is pasted in thin sheet surface for measuring the aerodynamic force of horizontal tail.This chip horizontal tail measuring device is widely used to the country
More wind-tunnel.But the device has as a drawback that：Rigidity is small, and rigidity is intersected, the rolling moment of horizontal tail measure accuracy compared with
Difference.Therefore, it designs a kind of rigidity greatly and can accurately measure the measuring device of horizontal tail aerodynamic force, be beneficial to improve horizontal tail experiment
Identification capacity, the horizontal tail design for aircraft provide strong wind tunnel test data supporting.
Invention content
The purpose of the present invention is being directed to the problem of above-mentioned, a kind of embedded horizontal tail aerodynamics force measurement device is proposed, to carry
The safety of high aircraft horizontal tail wind tunnel test and the accuracy of test data.
To achieve these goals, the present invention adopts the following technical scheme that：
A kind of embedded horizontal tail aerodynamics force measurement device, including fixing end and horizontal tail installation end, the fixing end includes connecting rod
With fixed tablet, it is whole for one to be provided with shear groove, the fixing end and horizontal tail installation end between connecting rod and fixed tablet
Body steel construction plays ellbeam between fixed tablet and horizontal tail installation end by processing to be formed, on the bullet ellbeam and in shear groove
It is provided with several foil gauges.
In the above-mentioned technical solutions, there are three joint faces for tool between the fixed tablet and horizontal tail installation end, symmetrical
Two joint faces are machined with spring beam, another joint face is fixed between tablet and horizontal tail installation end and do not contacted.
In the above-mentioned technical solutions, the foil gauge played on ellbeam and in shear groove is shear strain responsive type resistance
Foil gauge.
In the above-mentioned technical solutions, the bullet ellbeam includes elastic I-beam and elastic X-shaped beam.
In the above-mentioned technical solutions, the bullet ellbeam either all elastic I-beams or all elastic X-shaped beams or
Person's elasticity I-beam and elastic X-shaped beam are used in mixed way.
In the above-mentioned technical solutions, the spring beam on two joint faces is symmetrical arranged, and the type and quantity of spring beam are right
Claim.
In the above-mentioned technical solutions, it is provided with attachment lug between the both sides of the connecting rod and fixed tablet.
In the above-mentioned technical solutions, shaft mounting hole is provided on the attachment lug, peace is become for connecting by shaft
Fill angle apparatus.
In the above-mentioned technical solutions, the end set of the connecting rod has fixed hole, and the fixed hole passes through fixation
Connector is connect with becoming installation angle apparatus.
In the above-mentioned technical solutions, become on installation angle apparatus and be provided with scallop hole, angle apparatus and engaging lug are installed by change
Piece mutually rotates and changes scallop hole and the position of fixed hole in connecting rod, and then changes the established angle of horizontal tail.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
Bridge measurement all using shear strain responsive type resistance strain gage, reduces the deformation of measuring device under Aerodynamic force action
Amplitude ensure that the joint gap of measuring device and model；Rolling moment is measured using shear groove, chip is overcome and measures dress
It is insufficient to put rolling moment component sensitivity output, improves the accuracy of the component measurement.Meanwhile the measuring device can be according to need
Will, adjustment horizontal tail setting angle quickly, conveniently, is accurately replaced, the aircraft horizontal tail aerodynamic force for different installation forms, which compares, to be carried
Identification platform is supplied.
Description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is a kind of front view of embedded horizontal tail aerodynamics force measurement device of the present invention；
Fig. 2 is a kind of stereogram of embedded horizontal tail aerodynamics force measurement device shown in Fig. 1；
Fig. 3 is a kind of strain gauge adhesion location drawing of embedded horizontal tail aerodynamics force measurement device shown in Fig. 1；
Fig. 4 is a kind of foil gauge group bridge schematic diagram of embedded horizontal tail aerodynamics force measurement device shown in Fig. 1；
Fig. 5 is a kind of stereogram of embedded horizontal tail aerodynamics force measurement device shown in Fig. 1（Band becomes installation angle apparatus peace tail mould
Type）；
Fig. 6 is a kind of side view of embedded horizontal tail aerodynamics force measurement device shown in Fig. 1（Band becomes installation angle apparatus peace tail mould
Type）；
Wherein：1 it is extension bar, 2 be shear groove, 3 be attachment lug, 4 is fixed tablet, 5 be I-beam, and 6 be horizontal tail installation end, 7
It is X-shaped beam；
Number in Fig. 3, Fig. 4 is the number of foil gauge.
Specific embodiment
All features or disclosed all methods disclosed in this specification or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Embodiment 1
As shown in Figure 1 and Figure 2, a kind of measurement horizontal tail jet power unit having the following structure of the present invention and solve,
The embedded horizontal tail aerodynamics force measurement device includes：Connecting rod, shear groove, attachment lug, fixed tablet, elastic I-beam, bullet
Property X-shaped beam, horizontal tail installation end, the connecting rod, shear groove, attachment lug, fixed tablet composition fixing end, the elasticity I
The spring beam of ellbeam, elastic X-shaped beam composition, the fixing end with horizontal tail installation end in addition to being connect by spring beam, other parts
It does not contact, horizontal tail model on the horizontal tail installation end is installed, is pasted in the elasticity I-beam, elastic X-shaped beam and shear groove
Foil gauge, the connecting rod are connect with attachment lug by shaft with support element and change installation angle apparatus.
As shown in figure 3,32 foil gauges are respectively adhered on four elastic elastic X-shaped beams 7 of I-beams 5, two, during stickup
Ensure that foil gauge is symmetrical on each elastic I-beam 5, elastic X-shaped beam 7, and the lead-out wire of every foil gauge connects with measure traverse line
It connects, and forms the foil gauge group bridge such as Fig. 4, every group of electric bridge output difference voltage signal, on force sensor for multiple components calibrated mount
It is demarcated, obtains component signal and the relationship of component loaded load, obtain the calibration equation coefficient of measuring device.Wind tunnel test
When, according to the voltage output value of the five component measurements device that calibration equation and data collecting system measure, by resolving
Obtain the aerodynamic loading that model is subject to.The voltage and the functional relation of calibration load that static calibration obtains, it is possible to be put down
Aerodynamic loading suffered by tail.The relationship of each component signal and each group bridge output signal is：
Lift (Y)=B1+B2+B3+B4
Resistance (X)=B5+B6
Pitching (Mx)=B7+B8
Rolling (Mz)=B2+B4-B1-B2
Yaw (My)=B5-B6
B1~B8 groups bridge uses 4 bridges, and each group bridge Output Voltage Formula is as follows：
Wherein：For the output signal of electric bridge,；
K is the sensitivity coefficient of foil gauge,；
For a group bridge driving voltage,；
The strain generated for foil gauge each on each group of bridge.
Fig. 5 is the stereogram that apparatus of the present invention band becomes installation angle apparatus peace tail model, and horizontal tail model is by fixing on tablet
Two aerofoil profile shape cover boards and the horizontal tail ends of horizontal tail installation end both sides collectively constitute, to simulate true horizontal tail shape.Meanwhile
Cover board peace tail end can also prevent air-flow from entering the elastic I-beam 5 of the device and elastic X-shaped beam 7, avoid air-flow to measurement result
Bring interference.Become installation angle apparatus to be made of support end, scallop hole and measuring device connecting pin, support end becomes installation to fixed
Angle apparatus, measuring device connecting pin is hinged with attachment lug 3, by changing scallop hole and the fixed hole on 1 end of connecting rod
Link position, and then change horizontal tail established angle.The horizontal tail established angle that the position of scallop hole can be tested as needed is set
Meter processing.
Fig. 6 is the side view that apparatus of the present invention band becomes installation angle apparatus peace tail model.
Embodiment 2
Compared with Example 1, it removes and becomes outside installation angle apparatus difference, the other structures of embedded horizontal tail aerodynamics force measurement device are equal
It is identical.It can be the structures such as the jack of other forms, groove to become installation angle apparatus.
Embodiment 3
Embodiment 1 is compared, and removes that the support element become on installation angle apparatus is different outer, embedded horizontal tail aerodynamics force measurement device its
His structure is identical.Support element can be also designed according to the form of scallop hole, so as to can not only realize that horizontal tail is installed
The variation at angle can also be achieved the variation of horizontal tail device roll angle, yaw angle.
It may be noted that the invention can be not only used for horizontal tail, it may also be used for the aerodynamics force measurement of other flat appearance devices；No
It can only be used to aerodynamics force measurement, it may also be used for the measurement of other stress forms.
The invention is not limited in aforementioned specific embodiments.The present invention, which expands to, any in the present specification to be disclosed
The step of new feature or any new combination and any new method or process disclosed or any new combination.
Claims (10)
1. a kind of embedded horizontal tail aerodynamics force measurement device, it is characterised in that including fixing end and horizontal tail installation end, the fixation
End includes connecting rod and fixed tablet, and shear groove, the fixing end and horizontal tail peace are provided between connecting rod and fixed tablet
Dress end is an integrated steel-structure, and ellbeam is played by processing to be formed between fixed tablet and horizontal tail installation end, on the bullet ellbeam
With several foil gauges are provided in shear groove.
A kind of 2. embedded horizontal tail aerodynamics force measurement device according to claim 1, it is characterised in that the fixed tablet
Joint face, symmetrical two joint faces to be machined with spring beam there are three tools between horizontal tail installation end, another joint face is consolidated
It allocates and is not contacted between plate and horizontal tail installation end.
3. a kind of embedded horizontal tail aerodynamics force measurement device according to claim 1, it is characterised in that on the bullet ellbeam
It is shear strain responsive type resistance strain gage with the foil gauge in shear groove.
A kind of 4. embedded horizontal tail aerodynamics force measurement device according to claim 2, it is characterised in that the bullet ellbeam packet
Include elastic I-beam and elastic X-shaped beam.
5. a kind of embedded horizontal tail aerodynamics force measurement device according to claim 3, it is characterised in that it is described bullet ellbeam or
Either all elastic X-shaped beams or elastic I-beam and elastic X-shaped beam are used in mixed way all elastic I-beams of person.
6. according to a kind of any embedded horizontal tail aerodynamics force measurement devices of claim 2-4, it is characterised in that two companies
Spring beam in junction is symmetrical arranged, and the type and quantity of spring beam are symmetrical.
7. a kind of embedded horizontal tail aerodynamics force measurement device according to claim 1, it is characterised in that the connecting rod
Attachment lug is provided between both sides and fixed tablet.
A kind of 8. embedded horizontal tail aerodynamics force measurement device according to claim 6, it is characterised in that the attachment lug
On be provided with shaft mounting hole, by shaft for connect become installation angle apparatus.
9. a kind of embedded horizontal tail aerodynamics force measurement device according to claim 6, it is characterised in that the connecting rod
End set has fixed hole, and the fixed hole is connect by fixedly connected part with becoming installation angle apparatus.
10. a kind of embedded horizontal tail aerodynamics force measurement device according to claim 7 or 8, it is characterised in that become established angle
Scallop hole is provided on device, installing angle apparatus by change with attachment lug mutually rotates and change scallop hole and connecting rod
The position of upper fixed hole, and then change the established angle of horizontal tail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810365630.7A CN108267293B (en) | 2018-04-23 | 2018-04-23 | Embedded horizontal tail aerodynamic force measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810365630.7A CN108267293B (en) | 2018-04-23 | 2018-04-23 | Embedded horizontal tail aerodynamic force measuring device |
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| Publication Number | Publication Date |
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| CN108267293A true CN108267293A (en) | 2018-07-10 |
| CN108267293B CN108267293B (en) | 2023-11-17 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920932A (en) * | 2019-12-04 | 2020-03-27 | 中国直升机设计研究所 | Method and device for determining load spectrum of helicopter stabilizing surface mounting structure |
| CN113670560A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN114001915A (en) * | 2021-11-02 | 2022-02-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Plate type hinge moment balance |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN113670560A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN113670560B (en) * | 2021-10-21 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN114001915A (en) * | 2021-11-02 | 2022-02-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Plate type hinge moment balance |
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