CN105910792A - Airplane wind tunnel test model installation device - Google Patents
Airplane wind tunnel test model installation device Download PDFInfo
- Publication number
- CN105910792A CN105910792A CN201610374497.2A CN201610374497A CN105910792A CN 105910792 A CN105910792 A CN 105910792A CN 201610374497 A CN201610374497 A CN 201610374497A CN 105910792 A CN105910792 A CN 105910792A
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- China
- Prior art keywords
- model
- wind tunnel
- connecting rod
- erecting device
- chute
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Classifications
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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
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses an airplane wind tunnel test model installation device, and relates to the technical field of airplane wind tunnel test. The airplane wind tunnel test model installation device comprises a pitch adjusting device (1), a sliding mechanism (2), and a model installation support (4). One end of the pitch adjusting device (1) is connected to the top of a test wind tunnel through a first connecting rod (11), and the other end is connected with a rolling shaft (13) through a second connecting rod (12). The included angle between the first connecting rod (11) and the second connecting rod (12) can be adjusted. The sliding mechanism (2) sleeves the rolling shaft (13), and the sliding mechanism (2) can rotate about the rolling shaft (13). One end of the model installation support (4) is connected with the sliding mechanism (2), and the other end is connected with a test model (5). The airplane wind tunnel test model installation device has the beneficial effect that the degree of freedom of roll and yaw movement of airplanes can be released, and wind tunnel test of an airplane with a flying quality improvement control system is realized.
Description
Technical field
The present invention relates to aircraft wind-tunnel technique field, be specifically related to a kind of aircraft model in wind tunnel and install
Device.
Background technology
At present in field of aviation measurement and test, aircraft wind tunnel test concentrates on the aerodynamic characteristic of test aircraft body, flies
The shifted laterally of machine cannot discharge with yawing rotation degree of freedom, it is impossible to test control system couples spy with aircraft
Property, the wind tunnel test of band control system aircraft is verified and there is no the test device of a kind of effective practicality.
Summary of the invention
It is an object of the invention to provide a kind of aircraft model in wind tunnel erecting device, to solve or at least to alleviate
The problem at least one place in the presence of background technology.
The technical solution used in the present invention is: provides a kind of aircraft model in wind tunnel erecting device, is used for pacifying
Dress test model, described aircraft model in wind tunnel erecting device comprise pitching regulating device, slide mechanism and
Model erection support；One end of described pitching regulating device is connected to the ground of test air tunnel by first connecting rod
On, the other end connects described slide mechanism by second connecting rod；Between described first connecting rod and second connecting rod
Angle can regulate；Described slide mechanism is capable of the lateral sliding of described test model, described is laterally
The line direction of the both sides wing of finger to finger test model；Described model erection support one end is with described slide mechanism even
Connecing, the other end is connected with the abdominal part of described test model.
Preferably, described slide mechanism comprises sliding bottom and slide block, and described sliding bottom is provided with chute,
Can slide in described chute in one end of described slide block, the other end is connected with described model erection support.
Preferably, described chute is set to dovetail groove.
Preferably, the two ends of described chute are provided with buffer unit, and described buffer unit is used for limiting described cunning
The shifted laterally of block.
Preferably, described buffer unit comprises spring and baffle plate, and one end of described spring is fixed with described chute
Connect, the other end of described spring is connected with described baffle plate, described slide block described chute two end-stopping plates it
Between slide.
Preferably, described aircraft model in wind tunnel erecting device also comprises yaw device, described yaw device
One end is connected with described model erection support, and the other end is connected with the slide block on described slide mechanism, described partially
Boat device is capable of the test model rotation around described model erection support.
Preferably, described yaw device comprises inner core and urceolus, and one end of described inner core is connected with described slide block,
Described urceolus is set on described inner core, and described urceolus can rotate around described inner core, and described urceolus is with described
Test model erection support connects.
Preferably, rolling bearing, described inner core and institute it are provided with between the radial direction of described inner core and described urceolus
State and between the axial direction of urceolus, be provided with end face bearing.
Preferably, it is designated as the zero of pitching regulating device during the dead in line of described first connecting rod and second connecting rod
Position, the luffing angle range of accommodation of test model is ± 20 degree.
The beneficial effects of the present invention is:
In the aircraft model in wind tunnel erecting device of the present invention, slide mechanism can be with the side of release test model
To freedom of motion；Yaw device can improve wind-tunnel examination with the yawing rotation degree of freedom of release test model
The emulation tested, can realize the wind tunnel test checking of band control system aircraft.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the aircraft model in wind tunnel erecting device of one embodiment of the invention.
Fig. 2 is the schematic diagram of slide mechanism in the aircraft model in wind tunnel erecting device shown in Fig. 1.
Wherein, 1-pitching regulating device, 2-slide mechanism, 4-model erection support, 5-test model, 11-
First connecting rod, 12-second connecting rod, 21-sliding bottom, 22-slide block, 211-chute.
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, real below in conjunction with the present invention
Execute the accompanying drawing in example, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings,
The most same or similar label represents same or similar element or has same or like function
Element.Described embodiment is a part of embodiment of the present invention rather than whole embodiments.Lead to below
It is exemplary for crossing the embodiment being described with reference to the drawings, it is intended to be used for explaining the present invention, and it is not intended that right
The restriction of the present invention.Based on the embodiment in the present invention, those of ordinary skill in the art are not making creation
The every other embodiment obtained under property work premise, broadly falls into the scope of protection of the invention.Below in conjunction with
Embodiments of the invention are described in detail by accompanying drawing.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ",
"front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ",
Orientation or the position relationship of the instruction such as " outward " they are based on orientation shown in the drawings or position relationship, merely to
It is easy to describe the present invention and simplification description rather than instruction or the device of hint indication or element must have spy
Fixed orientation, with specific azimuth configuration and operation, therefore it is not intended that limit to scope
System.
As shown in Figure 1 and Figure 2, a kind of aircraft model in wind tunnel erecting device, for installation test model
5, aircraft model in wind tunnel erecting device comprises pitching regulating device 1, slide mechanism 2 and model and installs
Bearing 4.
One end of pitching regulating device 1 is connected on the ground of test air tunnel by first connecting rod 11, another
End connects slide mechanism 2 by second connecting rod 12；Angle between first connecting rod 11 and second connecting rod 12
Can regulate.
In the present embodiment, it is designated as pitch regulation dress during the dead in line of first connecting rod 11 and second connecting rod 12
Putting the zero-bit of 1, the luffing angle range of accommodation of test model is ± 20 degree.As shown in Figure 1, in figure
The angle of pitch of test model 5 is designated as zero-bit, and first connecting rod 11 holding position is constant, and second connecting rod 12 is permissible
Turn clockwise 20 degree；Meanwhile, first connecting rod 11 holding position is constant, and second connecting rod 12 can also be inverse
Hour hands rotate 20 degree.
In the present embodiment, first connecting rod 11 connects by bearing pin is fixing with the connection end of second connecting rod 12,
Bearing pin comprises rotary pin shaft and alignment pin, and first connecting rod 11 is provided with same with the connection end of second connecting rod 12
Axis hole, rotary pin shaft inserts the interior angle as first connecting rod 11 with second connecting rod 12 of coaxial aperture and adjusts rotation
Axle, centered by this rotary shaft, arranges hole, multiple location on an arc section, by adjusting first connecting rod
Position the correspondence position in hole with on second connecting rod 12 on 11, and alignment pin is inserted in hole, location, permissible
Realize the regulation of first connecting rod 11 and second connecting rod 12 angle.
It is understood that hole, described location can also be set to oval centered by the axis of rotary pin shaft
Arc hole, and angle index value is set at the edge of long circular hole.Have an advantage in that, it is possible to achieve first connecting rod
11 with the continuously adjusting of second connecting rod 12 angle.
Slide mechanism 2 is capable of the lateral sliding of test model 5, described laterally refers to test model 5
The line direction of both sides wing.Can with the lateral movement of release test model 5 freely by slide mechanism 2
Degree.
In the present embodiment, slide mechanism 2 comprises sliding bottom 21 and slide block 22, on sliding bottom 21
Being provided with chute 211, can slide in chute 211 in one end of slide block 22, and the other end is installed with model
Bearing 4 connects.Chute 211 is set to dovetail groove, has an advantage in that, slide block 22 registration, favorably
In improving test accuracy.
It is understood that the version of chute 211 can also set according to practical situation.Such as, exist
In one alternative, chute is set to rectangular channel, and slide block is also configured as rectangular block accordingly, at rectangular block
Be provided above limited cover, anti-limited slip block abjection chute, have an advantage in that, simple in construction, easy to process,
Advantageously reduce experimentation cost.
In the present embodiment, the two ends of chute 211 are provided with buffer unit, and buffer unit is used for limiting slide block
The shifted laterally of 22.Concrete, in the present embodiment, buffer unit comprises spring and baffle plate, spring
One end is fixing with chute 211 to be connected, and the other end of spring is connected with baffle plate, and slide block 22 is at chute 211
Slide between two end-stopping plates.Have an advantage in that, when slide block 22 moves to one end of chute 211 and baffle plate
Contact, and compression spring, desirably prevent the damage that test model and assay device are caused by collision.
Model erection support 4 one end is connected with slide mechanism 2, and the other end is connected with the abdominal part of test model 5.
In the present embodiment, aircraft model in wind tunnel erecting device also comprises yaw device 3, yaw device
3 one end are connected with model erection support 4, and the other end is connected with the slide block 22 on slide mechanism 2, driftage
Device 3 is capable of the test model 5 rotation around model erection support 4.
Concrete, in the present embodiment, yaw device 3 comprises inner core and urceolus, one end of inner core and slide block
22 connect, and urceolus is set on inner core, and urceolus can rotate around inner core, and urceolus is installed with test model and propped up
Seat 4 connects.It is provided with rolling bearing between inner core and the radial direction of urceolus, sets between inner core and the axial direction of urceolus
It is equipped with end face bearing.
In the present embodiment, inner core is set to cylindrical two-part with the level stepped sleeve, and inner core is set in cunning
Away from one end of chute 211 on block 22, and the bigger one end of outside diameter is near chute 211；Outer jacket casing
It is located at one end that inner core outside diameter is less, sets between shaft part and the endoporus radial direction of urceolus that inner diameter of steel flue is less
It is equipped with rolling bearing, between inner core and the axial step of urceolus, is provided with end face bearing.Have an advantage in that have
It is beneficial to realize the yawing rotation of test model 5, reduces the resistance of motion between parts, be conducive to improving
Test accuracy.
The aircraft model in wind tunnel erecting device of the present invention, by slide block in slide mechanism 22 at chute 211
Interior slip, it is possible to achieve the shifted laterally of test model 5, can with the lateral movement of release test model certainly
By spending；By the rotation of yaw device, can be with the yawing rotation degree of freedom of release test model, control system
Deflection by Control experiment model 5, it is achieved aerodynamic force and the regulation of pitching moment, by Control experiment mould
The lateral movement of type and yawing rotation, thus the balance of Control experiment model 5, can realize band control system and fly
The wind tunnel test checking of machine.
Last it is noted that above example is only in order to illustrate technical scheme, rather than to it
Limit.Although the present invention being described in detail with reference to previous embodiment, the ordinary skill people of this area
Member is it is understood that the technical scheme described in foregoing embodiments still can be modified by it or right
Wherein portion of techniques feature carries out equivalent；And these amendments or replacement, do not make appropriate technical solution
Essence depart from various embodiments of the present invention technical scheme spirit and scope.
Claims (9)
1. an aircraft model in wind tunnel erecting device, for installation test model (5), its feature exists
In: described aircraft model in wind tunnel erecting device comprises pitching regulating device (1), slide mechanism (2)
And model erection support (4)；
One end of described pitching regulating device (1) is connected to the ground of test air tunnel by first connecting rod (11)
On face, the other end connects described slide mechanism (2) by second connecting rod (12)；Described first connecting rod (11)
And the angle between second connecting rod (12) can regulate；
Described slide mechanism (2) is capable of the lateral sliding of described test model (5), described is laterally
The line direction of the both sides wing of finger to finger test model (5)；
Described model erection support (4) one end is connected with described slide mechanism (2), the other end and described examination
The abdominal part testing model (5) connects.
2. aircraft model in wind tunnel erecting device as claimed in claim 1, it is characterised in that: described
Slide mechanism (2) comprises sliding bottom (21) and slide block (22), and described sliding bottom sets on (21)
Being equipped with chute (211), can slide, separately in described chute (211) in one end of described slide block (22)
One end is connected with described model erection support (4).
3. aircraft model in wind tunnel erecting device as claimed in claim 2, it is characterised in that: described
Chute (211) is set to dovetail groove.
4. aircraft model in wind tunnel erecting device as claimed in claim 3, it is characterised in that: described
The two ends of chute (211) are provided with buffer unit, and described buffer unit is used for limiting described slide block (22)
Shifted laterally.
5. aircraft model in wind tunnel erecting device as claimed in claim 4, it is characterised in that: described
Buffer unit comprises spring and baffle plate, and one end of described spring is fixing with described chute (211) to be connected, institute
The other end stating spring is connected with described baffle plate, and described slide block (22) is at the two ends of described chute (211)
Slide between baffle plate.
6. aircraft model in wind tunnel erecting device as claimed in claim 1, it is characterised in that: described
Aircraft model in wind tunnel erecting device also comprises yaw device (3), described yaw device (3) one end with
Described model erection support (4) connects, and the other end is with the slide block (22) on described slide mechanism (2) even
Connecing, described yaw device (3) is capable of test model (5) around described model erection support (4)
Rotate.
7. aircraft model in wind tunnel erecting device as claimed in claim 6, it is characterised in that: described
Yaw device (3) comprises inner core and urceolus, and one end of described inner core is connected with described slide block (22), institute
Stating urceolus to be set on described inner core, described urceolus can rotate around described inner core, described urceolus and described examination
Test model erection support (4) to connect.
8. aircraft model in wind tunnel erecting device as claimed in claim 7, it is characterised in that: described
Rolling bearing it is provided with, between the axial direction of described inner core and described urceolus between the radial direction of inner core and described urceolus
It is provided with end face bearing.
9. aircraft model in wind tunnel erecting device as claimed in claim 1, it is characterised in that: described
It is designated as the zero of pitching regulating device (1) during the dead in line of first connecting rod (11) and second connecting rod (12)
Position, the luffing angle range of accommodation of test model (5) is ± 20 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610374497.2A CN105910792A (en) | 2016-05-31 | 2016-05-31 | Airplane wind tunnel test model installation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610374497.2A CN105910792A (en) | 2016-05-31 | 2016-05-31 | Airplane wind tunnel test model installation device |
Publications (1)
| Publication Number | Publication Date |
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| CN105910792A true CN105910792A (en) | 2016-08-31 |
Family
ID=56742748
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201610374497.2A Pending CN105910792A (en) | 2016-05-31 | 2016-05-31 | Airplane wind tunnel test model installation device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106525375A (en) * | 2016-10-21 | 2017-03-22 | 国网山东省电力公司电力科学研究院 | Self-adaptation system for detecting anti-wind capability of unmanned plane |
| CN107036781A (en) * | 2017-06-08 | 2017-08-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low resistance Three Degree Of Freedom support meanss based on virtual flight test model |
| CN111551340A (en) * | 2020-05-22 | 2020-08-18 | 中国科学院力学研究所 | Pneumatic force measuring and adjusting device for free jet wind tunnel test model |
| CN114112281A (en) * | 2021-07-28 | 2022-03-01 | 上海华模科技有限公司 | Wind tunnel test device for decoupling measurement of aerodynamic dynamic derivative |
| CN114923656A (en) * | 2022-07-20 | 2022-08-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Rope supporting system for full-aircraft flutter wind tunnel test |
| CN115597820A (en) * | 2022-12-15 | 2023-01-13 | 中国空气动力研究与发展中心超高速空气动力研究所（Cn） | Yaw mechanism of large hypersonic-velocity high-temperature wind tunnel model feeding system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106525375A (en) * | 2016-10-21 | 2017-03-22 | 国网山东省电力公司电力科学研究院 | Self-adaptation system for detecting anti-wind capability of unmanned plane |
| CN107036781A (en) * | 2017-06-08 | 2017-08-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low resistance Three Degree Of Freedom support meanss based on virtual flight test model |
| CN107036781B (en) * | 2017-06-08 | 2023-04-25 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-damping three-degree-of-freedom supporting device based on virtual flight test model |
| CN111551340A (en) * | 2020-05-22 | 2020-08-18 | 中国科学院力学研究所 | Pneumatic force measuring and adjusting device for free jet wind tunnel test model |
| CN114112281A (en) * | 2021-07-28 | 2022-03-01 | 上海华模科技有限公司 | Wind tunnel test device for decoupling measurement of aerodynamic dynamic derivative |
| CN114923656A (en) * | 2022-07-20 | 2022-08-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Rope supporting system for full-aircraft flutter wind tunnel test |
| CN115597820A (en) * | 2022-12-15 | 2023-01-13 | 中国空气动力研究与发展中心超高速空气动力研究所（Cn） | Yaw mechanism of large hypersonic-velocity high-temperature wind tunnel model feeding system |
| CN115597820B (en) * | 2022-12-15 | 2023-03-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Yaw mechanism of large hypersonic-velocity high-temperature wind tunnel model feeding system |
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Application publication date: 20160831 |