CN108267293B - Embedded horizontal tail aerodynamic force measuring device - Google Patents
Embedded horizontal tail aerodynamic force measuring device Download PDFInfo
- Publication number
- CN108267293B CN108267293B CN201810365630.7A CN201810365630A CN108267293B CN 108267293 B CN108267293 B CN 108267293B CN 201810365630 A CN201810365630 A CN 201810365630A CN 108267293 B CN108267293 B CN 108267293B
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- horizontal tail
- elastic
- beams
- measuring device
- fixed
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- 238000009434 installation Methods 0.000 claims abstract description 23
- 238000010008 shearing Methods 0.000 claims abstract description 14
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 3
- 239000010959 steel Substances 0.000 claims abstract description 3
- 238000005259 measurement Methods 0.000 claims description 15
- 238000005096 rolling process Methods 0.000 abstract description 6
- 230000035945 sensitivity Effects 0.000 abstract description 3
- 230000007547 defect Effects 0.000 abstract description 2
- 238000012545 processing Methods 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 230000009286 beneficial effect Effects 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
- 230000005284 excitation Effects 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000003068 static effect Effects 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
Abstract
The invention discloses an embedded horizontal tail aerodynamic force measuring device which comprises a fixed end and a horizontal tail mounting end, wherein the fixed end comprises a connecting rod and a fixed flat plate, a shearing groove is formed between the connecting rod and the fixed flat plate, the fixed end and the horizontal tail mounting end are of an integral steel structure, a bullet-shaped beam is formed between the fixed flat plate and the horizontal tail mounting end through processing, and a plurality of strain gauges are arranged on the bullet-shaped beam and in the shearing groove. The bridge of the invention adopts the shear strain sensitive resistance strain gauge to measure, reduces the deformation amplitude of the measuring device under the aerodynamic force action, and ensures the connection gap between the measuring device and the model; the rolling moment is measured by adopting the shearing groove, so that the defect of insufficient sensitivity output of the rolling moment component of the sheet type measuring device is overcome, and the accuracy of measuring the component is improved. Meanwhile, the measuring device can quickly, conveniently and accurately change and adjust the horizontal tail installation angle according to the needs.
Description
Technical Field
The invention relates to the technical field of aircraft wind tunnel test measurement, in particular to an embedded horizontal tail gas power measuring device for measuring the horizontal tail gas power of an aircraft.
Background
The horizontal tail of the aircraft is an important component for adjusting the flight attitude, and the installation position and the installation angles under different flight states of the aircraft are all studied in advance by wind tunnel tests. At present, most domestic wind tunnels are equipped with a flat tail gas dynamic measuring device which is a sheet type measuring device, such as Hu Guofeng, TH2002A integral balance design calculation report, sichuan: china center of aerodynamic research, development Low speed aerodynamic institute 2009.03, he Dexin, wind tunnel balance, beijing: national defense industry press 2001.05. Mainly comprises: the fixed end is used for fixing the whole measuring device; the model end is used for fixing the horizontal tail; the measuring element is arranged between the fixed end and the model end and is of an integral thin plate structure, and the strain gauge is adhered to the surface of the thin plate to be used for measuring aerodynamic force of the horizontal tail. The sheet type horizontal tail measuring device is widely applied to a plurality of domestic wind tunnels. However, this device has the following drawbacks: the rigidity is small, the rigidity is crossed, and the rolling moment measurement accuracy of the horizontal tail is poor. Therefore, the measuring device with high rigidity and capable of accurately measuring the horizontal tail aerodynamic force is designed, the horizontal tail test identification capacity can be improved, and powerful wind tunnel test data support is provided for the horizontal tail design of an aircraft.
Disclosure of Invention
The invention aims at solving the problems and provides an embedded horizontal tail aerodynamic force measuring device so as to improve the safety of an aircraft horizontal tail wind tunnel test and the accuracy of test data.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the utility model provides an embedded horizontal tail aerodynamic force measuring device, includes stiff end and horizontal tail installation end, the stiff end includes connecting rod and fixed dull and stereotyped, is provided with the shearing recess between connecting rod and the fixed dull and stereotyped, stiff end and horizontal tail installation end are a whole steel construction, form the bullet roof beam through processing between fixed dull and stereotyped and the horizontal tail installation end, be provided with a plurality of strain gauges on the bullet roof beam and in the shearing recess.
In the above technical scheme, three connecting surfaces are arranged between the fixed flat plate and the horizontal tail mounting end, two symmetrical connecting surfaces are provided with elastic beams, and the other connecting surface is not in contact with the fixed flat plate and the horizontal tail mounting end.
In the technical scheme, the strain gauge on the elastic beam and in the shearing groove is a shearing strain sensitive resistance strain gauge.
In the above technical solution, the elastic beams include elastic I-beams and elastic X-beams.
In the above technical solution, the elastic beams are either all elastic I-beams or all elastic X-beams, or the elastic I-beams and the elastic X-beams are mixed.
In the technical scheme, the elastic beams on the two connecting surfaces are symmetrically arranged, and the types and the numbers of the elastic beams are symmetrical.
In the above technical scheme, a connecting lug is arranged between the two sides of the connecting rod and the fixed flat plate.
In the above technical scheme, the connecting lug is provided with a rotating shaft mounting hole, and the connecting lug is used for connecting the variable mounting angle device through a rotating shaft.
In the above technical scheme, the tip of connecting rod is provided with fixed through-hole, fixed through-hole passes through fixed connection spare and becomes the installation angle device and be connected.
In the technical scheme, the fan-shaped hole is formed in the variable mounting angle device, the fan-shaped hole and the connecting lug rotate mutually through the variable mounting angle device, the position of the fixing through hole on the fan-shaped hole and the connecting rod is changed, and then the mounting angle of the horizontal tail is changed.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
the bridge measurement adopts shear strain sensitive resistance strain gauges, so that the deformation amplitude of the measuring device under the action of aerodynamic force is reduced, and the connection gap between the measuring device and the model is ensured; the rolling moment is measured by adopting the shearing groove, so that the defect of insufficient sensitivity output of the rolling moment component of the sheet type measuring device is overcome, and the accuracy of measuring the component is improved. Meanwhile, the measuring device can quickly, conveniently and accurately replace and adjust the horizontal tail installation angle according to the needs, and an identification platform is provided for the horizontal tail aerodynamic force comparison of aircrafts in different installation modes.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
FIG. 1 is a front view of an in-line horizontal tail gas dynamic measurement device of the present invention;
FIG. 2 is a perspective view of an in-line horizontal tail gas power measurement device of FIG. 1;
FIG. 3 is a view of the strain gage attachment location of the in-line horizontal aerodynamic force measurement device of FIG. 1;
FIG. 4 is a schematic view of a strain gage stack of the in-line horizontal aerodynamic force measurement device of FIG. 1;
FIG. 5 is a perspective view of an in-line horizontal tail aerodynamic force measurement device of FIG. 1 (with a variable mounting angle device and a horizontal tail model);
FIG. 6 is a side view of an in-line flat tail aerodynamic measurement device of FIG. 1 (with a variable mounting angle device and flat tail model);
wherein: the connecting rod is 1, the shearing groove is 2, the connecting lug is 3, the fixed plate is 4, the I-shaped beam is 5, the horizontal tail mounting end is 6, and the X-shaped beam is 7;
the numerals in fig. 3 and 4 denote the numbers of the strain gage.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Example 1
As shown in fig. 1 and 2, the present invention provides a device for measuring horizontal aerodynamic force, which has the following structure, and the device for measuring horizontal aerodynamic force comprises: connecting rod, shearing groove, connecting lug, fixed flat board, elasticity I-beam, elasticity X-beam, horizontal tail installation end, the connecting rod, shearing groove, connecting lug, fixed flat board constitute the stiff end, the elasticity roof beam that elasticity I-beam, elasticity X-beam constitute, the stiff end is all contactless except that being connected through the elasticity roof beam with horizontal tail installation end, install the horizontal tail model on the horizontal tail installation end, paste the foil gage on elasticity I-beam, elasticity X-beam and the shearing groove, the connecting rod is connected with support piece and the device of becoming the installation angle through the pivot with connecting lug.
As shown in fig. 3, 32 strain gages are respectively stuck on four elastic I-beams 5 and two elastic X-beams 7, the strain gages are ensured to be symmetrical on each elastic I-beam 5 and each elastic X-beam 7 during sticking, outgoing lines of each strain gage are connected with a measuring wire and form a strain gage group bridge as shown in fig. 4, each group bridge outputs a differential voltage signal, calibration is carried out on a multi-component force sensor calibration frame, the relation between a component signal and a component loading load is obtained, and a calibration formula coefficient of the measuring device is obtained. And in the wind tunnel test, according to a calibration formula and the voltage output value of the five-component measuring device measured by the data acquisition system, the pneumatic load born by the model can be obtained through calculation. And obtaining the pneumatic load borne by the horizontal tail by the functional relation between the voltage obtained by static calibration and the calibration load. The relationship of the component signals to the bridge output signals of each set is:
lift (Y) =b1+b2+b3+b4
Resistance (X) =b5+b6
Pitch (Mx) =b7+b8
Roll (Mz) =b2+b4-B1-B2
Yaw (My) =b5-B6
The group B1-B8 of bridges adopts 4 bridges, and the output voltage formula of each group of bridges is as follows:
wherein:for the output signal of the bridge, ">；
K is the sensitivity coefficient of the strain gauge,；
for group bridge excitation voltage, ">；
The strain created for each strain gauge on each group bridge.
Fig. 5 is a perspective view of the device with a variable mounting angle device and a horizontal tail model, wherein the horizontal tail model consists of two wing-shaped cover plates on a fixed flat plate and horizontal tail ends on two sides of a horizontal tail mounting end, and is used for simulating the appearance of a real horizontal tail. Meanwhile, the cover plate and the flat tail end can also prevent air flow from entering the elastic I-beam 5 and the elastic X-beam 7 of the device, so that the air flow is prevented from interfering a measurement result. The variable installation angle device consists of a supporting end, a fan-shaped hole and a measuring device connecting end, wherein the supporting end is used for fixing the variable installation angle device, the measuring device connecting end is hinged with the connecting lug 3, and the installation angle of the horizontal tail is changed by changing the connection position of the fan-shaped hole and the fixing through hole on the end part of the connecting rod 1. The positions of the fan-shaped holes can be designed and processed according to the horizontal tail installation angle to be tested.
FIG. 6 is a side view of the device of the present invention with a variable mounting angle device and a flat tail model.
Example 2
The other structures of the in-line horizontal aerodynamic force measuring device were the same as those of example 1 except that the variable mounting angle device was different. The variable mounting angle device can be in other forms of jacks, grooves and the like.
Example 3
In comparison to example 1, the other structures of the in-line horizontal aerodynamic measurement device were identical except that the support on the variable mounting angle device was different. The support piece can be designed according to the form of the sector hole, so that the change of the installation angle of the horizontal tail can be realized, and the change of the rolling angle and the yaw angle of the horizontal tail device can be realized.
It should be noted that the invention can be used not only for horizontal tails, but also for aerodynamic measurements of other flat profile devices; the device can be used for aerodynamic force measurement and measurement of other stress forms.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Claims (4)
1. An embedded horizontal tail aerodynamic force measuring device is characterized by comprising a fixed end and a horizontal tail installation end, wherein the fixed end comprises a connecting rod and a fixed flat plate, a shearing groove is arranged between the connecting rod and the fixed flat plate,
the fixed end and the horizontal tail installation end are of an integral steel structure, three connecting surfaces are arranged between the fixed flat plate and the horizontal tail installation end, the two symmetrical connecting surfaces are provided with elastic beams, the other connecting surface is not contacted with the horizontal tail installation end, a plurality of shear strain sensitive resistance strain gauges are arranged on the elastic beams and in the shearing grooves, the elastic beams on the two connecting surfaces are symmetrically arranged, the types and the number of the elastic beams are symmetrical,
connecting lugs are arranged between the two sides of the connecting rod and the fixed flat plate, rotating shaft mounting holes are formed in the connecting lugs, the rotating shaft is used for connecting a variable mounting angle device, fan-shaped holes are formed in the variable mounting angle device, the fan-shaped holes and the connecting lugs rotate mutually through the variable mounting angle device, the positions of the fan-shaped holes and the fixed through holes in the connecting rod are changed, and then the mounting angle of the horizontal tail is changed.
2. An in-line horizontal aerodynamic force measurement device according to claim 1, characterized in that the elastic beams comprise elastic I-beams and elastic X-beams.
3. An in-line horizontal aerodynamic force measuring device according to claim 2, characterized in that the elastic beams are either all elastic I-beams, all elastic X-beams, or a combination of elastic I-beams and elastic X-beams.
4. The embedded horizontal tail gas dynamic force measuring device according to claim 1, wherein the end part of the connecting rod is provided with a fixing through hole, and the fixing through hole is connected with the variable installation angle device through a fixing connecting piece.
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 |
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| 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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| CN108267293A CN108267293A (en) | 2018-07-10 |
| CN108267293B true CN108267293B (en) | 2023-11-17 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920932B (en) * | 2019-12-04 | 2022-04-29 | 中国直升机设计研究所 | Method and device for determining load spectrum of helicopter stabilizing surface mounting structure |
| 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 |
| CN114001915B (en) * | 2021-11-02 | 2023-03-31 | 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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