CN106840574A - A kind of device for wind-tunnel dynamic derivative forced vibration tests - Google Patents
A kind of device for wind-tunnel dynamic derivative forced vibration tests Download PDFInfo
- Publication number
- CN106840574A CN106840574A CN201611192367.3A CN201611192367A CN106840574A CN 106840574 A CN106840574 A CN 106840574A CN 201611192367 A CN201611192367 A CN 201611192367A CN 106840574 A CN106840574 A CN 106840574A
- Authority
- CN
- China
- Prior art keywords
- pitching
- angle
- inner core
- angle mechanism
- wind
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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
Abstract
A kind of device for wind-tunnel dynamic derivative forced vibration tests, including dynamic scale, supporting mechanism, yaw angle mechanism and roll angle mechanism.Dynamic scale is connected in yaw angle mechanism by supporting mechanism, roll angle mechanism is also connected in yaw angle mechanism, and by the relative position and angle between the cooperation adjustment yaw angle mechanism and roll angle mechanism between yaw angle mechanism and roll angle mechanism, meet the experimental test demand under the different angles of attack, yaw angle and roll angle operating mode.The present invention can carry out continuous rotary motion in the case where frequency or frequency sweep mode is determined by servomotor output torque drive power transmission shaft, by eccentric cam and the groove fit of dynamic scale, complete forms of motion conversion, realize simple harmonic quantity forced vibration.The present invention is rational in infrastructure compact, has the advantages that normal direction carries big, high precision, has major application to be worth in field of aerospace.
Description
Technical field
The present invention relates to a kind of device for wind-tunnel dynamic derivative forced vibration tests, belong to wind tunnel test technical field.
Background technology
When Design of Flight Control is carried out with space vehicle dynamic attributional analysis, flight force and moment is with aerodynamic derivative shape
Formula occurs, i.e., quiet, dynamic stability derivative, because mechanism of production is complicated, generally obtains above-mentioned parameter using forced vibration wind tunnel test.
Dynamic derivative wind tunnel test obtains dynamic derivative using model vibration come the rigid motion mode of simulated flight device.With
The development of high-speed aircraft, guided missile, rocket and reentry vehicle, flight quality and dynamic stability problem are increasingly taken seriously, dynamic to lead
Number experiment also becomes more and more important.Particularly supersonic speed, high-supersonic speed range and significantly disturbance and on a large scale motor-driven bar
Experiment and e measurement technology under part, so whole forced vibration tests device is necessary to optimize design.
According to the wind tunnel test mission requirements of the symmetrical aircraft in new face, one side aircraft normal load is big, to solve
Load and Rigidity Matching problem, development of new forced vibration tests technology is forming the dynamic test ability of the symmetrical aircraft in face.
On the other hand, it is desirable to while the static derivative and dynamic derivative of accurate measurement aircraft.Current forced vibration tests device normal direction is carried
Lotus bearing capacity is not high, and torque output member is installed and fixation is undesirable, not enough on test accuracy, while also lacking reality
The ability that now the experiment angle of attack, yaw angle and roll angle are superimposed.
The characteristics of symmetrical aircraft in new face, is mainly normal load much larger than transverse load, for this reason, it may be necessary to a kind of new
Forced vibration tests device solves the above problems, and can carry out the dynamic wind tunnel test of this class aircraft.
The content of the invention
Technology solve problem of the invention is：Overcome the deficiencies in the prior art, there is provided one kind is forced for wind-tunnel dynamic derivative
The device of vibration test.Increase the rigidity and bearing capacity of supporting mechanism using unique mentality of designing and structure type, really
Protect experiment vibration frequency and amplitude is controllable accurate, realize determining frequency, the high accuracy simple harmonic quantity forced vibration of amplitude.
Technical solution of the invention is：
A kind of device for wind-tunnel dynamic derivative forced vibration tests, including：Dynamic scale, supporting mechanism, yaw angle machine
Structure and roll angle mechanism, dynamic scale are connected in yaw angle mechanism by supporting mechanism, and roll angle mechanism is also connected to break away
In the mechanism of angle, and adjusted between yaw angle mechanism and roll angle mechanism by the cooperation between yaw angle mechanism and roll angle mechanism
Relative position and angle, realize the experimental test under the different angles of attack, yaw angle and roll angle operating mode.
Supporting mechanism includes：Allotment bar, eccentric cam, power transmission shaft, check ring, elastic washer and angular contact bearing；
Allotment bar is tubular structure, and front end is coordinated with dynamic scale by circular conical surface, and afterbody is with yaw angle mechanism by circle
Cone match；
Power transmission shaft is arranged on inside allotment bar, and power transmission shaft two ends are each provided with mounting groove, check ring, elastic washer and angle
Contact bearing is arranged on the mounting groove of power transmission shaft, axial location and rotation for adjusting power transmission shaft；The head of power transmission shaft leads to
Eccentric cam connection dynamic scale is crossed, the continuous convert rotational motion of power transmission shaft is the reciprocally swinging of dynamic scale.
Yaw angle mechanism includes：Bent sting, shaft coupling, decelerator mounting seat, decelerator, servomotor and motor cover plate；
Bent sting includes two parts, respectively supports housing and angle board, and angle board is located on support housing, and angle
It is distributed with multiple angle adjustment holes on plate, support housing is hollow cylindrical, shaft coupling, decelerator mounting seat, decelerator and watches
Take motor to be connected in turn, be arranged on support enclosure interior, the power transmission shaft of supporting mechanism passes through shaft coupling connection reducer；
Observation window is provided with support housing, the connection for observing the power transmission shaft and decelerator.
The angle of regulation range of angle board is 0 °~16 °.
Roll angle mechanism one end is U-shaped structure, and multiple connecting holes are distributed with above, and roll angle mechanism is mounted in yaw angle mechanism
Angle board on, coordinated by the angle adjustment holes on the connecting hole in roll angle mechanism and angle board, and then adjust roll angle
Position of the mechanism relative to yaw angle mechanism and angle；The other end of roll angle mechanism is diametrically with 30 °, 45 °, 60 ° and 90 °
Angle set keyway, with wind-tunnel tulwar coordinate after, realize different roll angles.
Dynamic scale, supporting mechanism and yaw angle mechanism are on same axis.
Dynamic scale includes：Pitching balance inner core, pitching balance outer wall, rotating shaft, strain beam, housing screw, sliding bearing；
Pitching balance inner core includes head circular conical surface section, non-uniform beam, coordinates section and drives beam, and non-uniform beam is used to measure
Five component aerodynamic loadings, to coordinate and be provided with manhole and rectangular through-hole in section, and pitching balance outer wall is tubular structure, including sky
The heart coordinates section and afterbody circular conical surface section, and manhole and rectangular through-hole are provided with hollow cooperation section；
Pitching balance inner core is arranged on the outer pars intramuralis of pitching balance, and sliding bearing is enclosed within outside rotating shaft, and through pitching day
Manhole on flat outer wall and pitching balance inner core, pitching balance outer wall and pitching balance inner core are combined together, strain
Beam passes through the rectangular through-hole on pitching balance outer wall and pitching balance inner core, the corner for measuring pitching balance inner core；Compress
Be fixed on pitching balance outer wall for strain beam and rotating shaft by screw.
Pitching balance inner core drive beam be located at pitching balance outer wall hollow cooperation intersegmental part, and it is hollow coordinate section it is interior
Footpath more than the maximum radial dimension for driving beam, the internal diameter of hollow cooperation section than driving the big at least 10mm of the maximum radial dimension of beam,
Pitching balance inner core rotates around the axis, and rotational steps are not less than 1 °, and the head circular conical surface section of pitching balance inner core is 1:10 circular cones
Face, the afterbody circular conical surface section of pitching balance outer wall is 1:10 circular conical surfaces.
Set fluted on the driving beam rear part end face of pitching balance inner core, for driving pitching balance inner core to revolve around the shaft
Turn, realize pitching simple harmonic motion；The calibration center of pitching balance inner core non-uniform beam and the center superposition of rotating shaft, as measurement base
It is accurate.
The non-uniform beam of pitching balance inner core is stretch section, and maximum is respectively subjected to 10000N normal force and 120Nm pitching power
Square load, the maximum gauge of pitching balance outer wall is less than 51mm, and sliding bearing uses copper master alloy inlaid solid lubrication bearing.
Compared with the prior art, the invention has the advantages that：
(1) present invention improves the load carrying capacity of forced vibration device, can bear larger normal load；
(2) in technical solution of the present invention, the torque output devices such as decelerator, servomotor can effectively be fixed, it is to avoid dress
The vibration effect output effect put, improves test accuracy；
(3) can realize that wind-tunnel tulwar adjusts the angle of attack, yaw angle mechanism changes the given rolling of yaw angle and roll angle mechanism
Corner, meets the experimental test demand under the different angles of attack, yaw angle and roll angle operating mode.
(4) present invention proposes the dynamic pitching balance design thought of uniqueness, breaches traditional tandem formula balance
Method for designing so that dynamic scale overall volume is small, reduces balance diameter, and it is long that inside and outside fabricated structure then shortens balance
Degree, balance deformation is small, improves the rigidity and bearing capacity of balance.
(5) in technical solution of the present invention, dynamic scale calibration center overlaps with rotating shaft, improves the essence of dynamic scale measurement
Degree.The strain beam of dynamic scale can be dismounted independently.Only need the thickness for changing strain beam to carry out Matching Model in ground is debugged to carry
Lotus, without repeated removal, effective lifting test efficiency.
(6) present invention is combined using modular form, and wind tunnel model, dynamic scale and supporting mechanism etc. are carried out
Series connection, model and dynamic scale measuring cell are changed according to different demands, device is had more versatility.Relative to existing
Technology, test accuracy of the invention is higher, and assembly difficulty is lower.The present invention can be widely applied to big load wind tunnel test
In, with good practicality and promotional value.
Brief description of the drawings
Fig. 1 is the structural representation for wind-tunnel dynamic derivative forced vibration device of the invention；
Fig. 2 is the structural representation of the supporting mechanism of Fig. 1；
Fig. 3 is the part composition schematic diagram of the yaw angle mechanism of Fig. 1；
Fig. 4 is the roll angle mechanism structure schematic diagram of Fig. 1；
Fig. 5 is the structural representation of the dynamic scale of Fig. 1；
Fig. 6 is the sectional view of Fig. 5；
Fig. 7 is the part composition schematic diagram of Fig. 5.
Specific embodiment
Specific embodiment of the invention is further described in detail below in conjunction with the accompanying drawings.
On the one hand the wind tunnel test task of the new symmetrical aircraft in face requires to form the dynamic test energy of the symmetrical aircraft in face
Power solves the problems, such as load and Rigidity Matching, while being capable of the static derivative and dynamic derivative of accurate measurement aircraft.The present invention is proposed
A kind of device for wind-tunnel dynamic derivative forced vibration tests, improves normal load ability to bear and test measurement is accurate
Degree, while the experimental test demand under the different angles of attack, yaw angle and roll angle operating mode can be met.
As shown in figure 1, the present invention proposes a kind of device for wind-tunnel dynamic derivative forced vibration tests, including：Dynamic
Balance 1, supporting mechanism 15, yaw angle mechanism 16 and roll angle mechanism 17, dynamic scale 1 are connected to sideslip by supporting mechanism 15
In angle mechanism 16, roll angle mechanism 17 is also connected in yaw angle mechanism 16, and by yaw angle mechanism 16 and roll angle mechanism
Relative position and angle between cooperation adjustment yaw angle mechanism 16 and roll angle mechanism 17 between 17, realize the different angles of attack,
Experimental test under yaw angle and roll angle operating mode.
As shown in Fig. 2 supporting mechanism 15 includes：Allotment bar 2, eccentric cam 6, power transmission shaft 7, check ring 12, cushion
Circle 13 and angular contact bearing 14；
Allotment bar 2 is tubular structure, and front end is coordinated with dynamic scale 1 by circular conical surface, and afterbody leads to yaw angle mechanism 16
Cross circular conical surface cooperation；Increase the contact area between coordinating, reduce the gap of mechanical structure.
Power transmission shaft 7 is arranged on inside allotment bar 2, and the two ends of power transmission shaft 7 are each provided with mounting groove, check ring 12, cushion
Circle 13 and angular contact bearing 14 are arranged on the mounting groove of the power transmission shaft 7, axial location and rotation for adjusting power transmission shaft 7
Turn；Elastic washer 13 is that power transmission shaft 7 is axially leaving certain adjustment threshold degree, reduces installation difficulty, it is to avoid parts were assembled
The offset issue of axial dimension in journey.The head of power transmission shaft 7 by eccentric cam 6 connect dynamic scale 1, power transmission shaft 7 it is continuous
Convert rotational motion is the reciprocally swinging of dynamic scale 1, effective motion conversion is realized, needed for reproduction aircraft elevating movement
Forced vibration state.
As shown in figure 3, yaw angle mechanism 16 includes：Bent sting 3, shaft coupling 8, decelerator mounting seat 9, decelerator 10, watch
Take motor 11 and motor cover plate 4；
Bent sting 3 includes two parts, respectively supports housing 18 and angle board 19, angle board 19 to be located at support housing 18
On, and multiple angle adjustment holes are distributed with angle board 19, support housing 18 is hollow cylindrical, and shaft coupling 8, decelerator is installed
Seat 9, decelerator 10 and servomotor 11 are connected in turn, and are arranged on inside support housing 18, the supporting mechanism 15
Power transmission shaft 7 passes through the connection reducer 10 of shaft coupling 8；Be fixed on decelerator 10 on support housing 18 by decelerator mounting seat 9, reduces
Gap is installed, the component vibration caused by forced vibration tests is reduced, so as to reduce the interference of mechanical noise, experiment essence is improved
Degree.
Observation window is provided with support housing 18, the connection for observing power transmission shaft 7 and decelerator 10.Can finely tune simultaneously
The axial location of power transmission shaft 7, it is ensured that the eccentric cam 6 of the head of power transmission shaft 7 can coordinate with pitching balance inner core 20.
The angle of regulation range of angle board 19 is 0 °~16 °, and increased the experiment in wind tunnel test to yaw angle operating mode needs
Ask, it is also possible to adjust the direction of yaw angle mechanism 16 for pitch orientation, for increasing the experiment angle of attack, complete big angle of attack wind tunnel test
Demand.
As shown in figure 4, the one end of roll angle mechanism 17 is U-shaped structure, multiple connecting holes, roll angle mechanism 17 are distributed with above
On the angle board 19 of yaw angle mechanism 16, by the angular adjustment on the connecting hole in roll angle mechanism 17 and angle board 19
Hole coordinates, and then adjusts position and angle of the roll angle mechanism 17 relative to yaw angle mechanism 16；Roll angle mechanism 17 it is another
End diametrically sets keyway with 30 °, 45 °, 60 ° and 90 ° of angle, after coordinating with wind-tunnel tulwar, realizes different roll angles,
So as to increase attainable operating condition of test number.
Dynamic scale 1, supporting mechanism 15 are on same axis with yaw angle mechanism 16, and structure is carried out by tandem
Combination, with good globality.
As shown in Fig. 5,6,7, dynamic scale 1 includes：Pitching balance inner core 20, pitching balance outer wall 21, rotating shaft 22, strain
Beam 23, housing screw 24, sliding bearing 25；
Pitching balance inner core 20 includes head circular conical surface section, non-uniform beam, coordinates section and drives beam, and non-uniform beam is used to survey
Five component aerodynamic loadings are measured, is coordinated and manhole and rectangular through-hole is provided with section, pitching balance outer wall 21 is tubular structure, bag
Hollow cooperation section and afterbody circular conical surface section are included, manhole and rectangular through-hole are provided with hollow cooperation section；
Pitching balance inner core 20 is arranged on inside pitching balance outer wall 21, and sliding bearing 25 is enclosed within outside rotating shaft 22, and is worn
The manhole crossed on pitching balance outer wall 21 and pitching balance inner core 20, by pitching balance outer wall 21 and pitching balance inner core 20
It is combined together, strain beam 23 is used through the rectangular through-hole on pitching balance outer wall 21 and pitching balance inner core 20, rectangular configuration
In ensuring that strain beam 23 can completely follow pitching balance inner core 20 to be moved, the corner of pitching balance inner core 20 is measured；
Be fixed on pitching balance outer wall 21 for strain beam 23 and rotating shaft 22 by housing screw 24, for suppressing the strain beam in motion process
23 and the cross stream component that is subject to of rotating shaft 22.
The beam that drives of pitching balance inner core 20 is located at the hollow cooperation intersegmental part of pitching balance outer wall 21, and hollow cooperation section
Internal diameter more than the maximum radial dimension for driving beam, the internal diameter of hollow cooperation section is bigger at least than driving the maximum radial dimension of beam
10mm, is that enough spaces are reserved in the pitching simple harmonic motion of pitching balance inner core 20, it is to avoid pitching balance inner core 20 is being moved through
Collided with pitching balance outer wall 21 in journey.Pitching balance inner core 20 22 is rotated around the shaft, and rotational steps are not less than 1 °, so that
The situation of change of aerodynamic loading can be more accurately obtained, is conducive to improving measurement accuracy.The head of pitching balance inner core 20
Circular conical surface section is 1:10 circular conical surfaces, the afterbody circular conical surface section of pitching balance outer wall 21 is 1:10 circular conical surfaces, using 1:10 circular cone
Face is attached the contact area that can increase between part, makes connection even closer, reduces caused by mechanical structure gap
Influence.
Set fluted on the driving beam rear part end face of pitching balance inner core 20, for driving pitching balance inner core 20 to rotate
Axle 22 rotates, and realizes pitching simple harmonic motion；The calibration center of the non-uniform beam of pitching balance inner core 20 and the center of rotating shaft 22
Overlap, as measuring basis, improve certainty of measurement, make structure compacter.
The non-uniform beam of pitching balance inner core 20 is stretch section, and maximum is respectively subjected to 10000N normal force and 120Nm pitching
Torque load, the range can meet the loading demands of the symmetrical aircraft in new face, it is ensured that pitching balance inner core 20 has enough
Rigidity.The maximum gauge of pitching balance outer wall 21 is less than 51mm, the overall volume of the dynamic pitching balance of limitation；Therefore in new face
The less situation of symmetrical flight device test model can complete to install, simultaneously because the small volume of dynamic pitching balance can also
Other dynamic test models are matched, can be increased and be applied range.Sliding bearing 25 uses copper master alloy inlaid solid lubrication bearing,
The bearing long service life, lubricant is added without the later stage, makes dynamic pitching balance within the service life time limit without repeating to tear open
Dress.
Operation principle：
According to the demand of different tests operating mode, change the angle conditions angle of attack of wind-tunnel tulwar；Change the upper angle of bent sting 3
The relative position of the connecting hole in the angle adjustment holes of plate 19 and roll angle mechanism 17, and then adjust yaw angle β；Change roll angle
Keyway in mechanism 17 to coordinate with wind-tunnel tulwar, adjusts roll angle；Multiple angles regulation can combine realization, meet multi-pose
The requirement of angle combination.
After setting experiment attitude angle, starting servomotor 11 carries out continuous rotary motion output torque, by decelerator 10
Power transmission shaft 7 is delivered to shaft coupling 8, then is transferred to eccentric cam 6.By on eccentric cam 6 and the tail end face of dynamic scale 1
Groove fit, will move the reciprocating motion be converted in pitch orientation.So as to the driving beam for driving pitching balance inner core 20 rotates
Axle 22 rotates, and realizes the pitching simple harmonic motion of the entirety of pitching balance inner core 20, while driving strain beam 23 to synchronize motion, surveys
The movement angle of amount pitching balance inner core 20.
Embodiment
Most prior art can only all be tested by change of the wind-tunnel tulwar to adjust angle of attack, and operating condition of test changes
Become very limited and very high to the dependence of wind-tunnel tulwar, if the tulwar regulating power of test air tunnel is relatively low, can shadow significantly
Ring operating condition of test number and experiment quantity.The forced vibration tests device can realize wind-tunnel tulwar regulation angle of attack, yaw angle
Mechanism changes the different attitude angle changes of yaw angle β roll angle Ks tri- kind given with roll angle mechanism, therefore can cover major part
The duty requirements of dynamic test, can provide enough test datas.
In addition, the angle of attack, yaw angle and roll angle have the relation below approximate under small amplitude forced vibration：
β=K*sin α
With reference to the relational expression of three, the result under another attitude angle can be solved under the operating mode of combination of two, for many
State complex wind tunnel test and multimode motion theory checking test, have widened the range of application of device, and its practicality also compares
Existing device is high.
Claims (10)
1. a kind of device for wind-tunnel dynamic derivative forced vibration tests, it is characterised in that：Including dynamic scale (1), support machine
Structure (15), yaw angle mechanism (16) and roll angle mechanism (17), dynamic scale (1) are connected to yaw angle by supporting mechanism (15)
In mechanism (16), roll angle mechanism (17) is also connected in yaw angle mechanism (16), and by yaw angle mechanism (16) and rolling
Cooperation between angle mechanism (17) adjusts the relative position and angle between yaw angle mechanism (16) and roll angle mechanism (17), real
Experimental test under the existing different angles of attack, yaw angle and roll angle operating mode.
2. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 1, it is characterised in that：It is described
Supporting mechanism (15) includes allotment bar (2), eccentric cam (6), power transmission shaft (7), check ring (12), elastic washer (13) and angle
Contact bearing (14)；
The allotment bar (2) is tubular structure, and front end is with dynamic scale (1) by circular conical surface cooperation, afterbody and yaw angle mechanism
(16) coordinated by circular conical surface,
Power transmission shaft (7) is arranged on allotment bar (2) inside, and power transmission shaft (7) two ends are each provided with mounting groove, check ring (12), bullet
Property packing ring (13) and angular contact bearing (14) are arranged on the mounting groove of the power transmission shaft (7), the axle for adjusting power transmission shaft (7)
To position and rotation；The head of power transmission shaft (7) connects dynamic scale (1), the continuous rotation of power transmission shaft (7) by eccentric cam (6)
The dynamic reciprocally swinging for being converted into dynamic scale (1) of transhipment.
3. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 2, it is characterised in that：Break away
Angle mechanism (16) includes bent sting (3), shaft coupling (8), decelerator mounting seat (9), decelerator (10), servomotor (11) and electricity
Cover plate (4)；
Bent sting (3) includes two parts, respectively supports housing (18) and angle board (19), and angle board (19) is positioned at supporting shell
Multiple angle adjustment holes are distributed with body (18), and on angle board (19), support housing (18) is hollow cylindrical, shaft coupling
(8), decelerator mounting seat (9), decelerator (10) and servomotor (11) are connected in turn, and are arranged on support housing (18)
Inside, the power transmission shaft (7) of the supporting mechanism (15) is by shaft coupling (8) connection reducer (10)；
Observation window is provided with support housing (18), the connection for observing the power transmission shaft (7) and decelerator (10).
4. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 3, it is characterised in that：Angle
The angle of regulation range of plate (19) is 0 °~16 °.
5. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 3, it is characterised in that：It is described
Roll angle mechanism (17) one end is U-shaped structure, and multiple connecting holes are distributed with above, and roll angle mechanism (17) is mounted in yaw angle mechanism
(16) on angle board (19), matched somebody with somebody with the angle adjustment holes on angle board (19) by the connecting hole in roll angle mechanism (17)
Close, and then adjust the position of roll angle mechanism (17) relative to yaw angle mechanism (16) and angle；Roll angle mechanism (17) it is another
One end diametrically sets keyway with 30 °, 45 °, 60 ° and 90 ° of angle, after coordinating with wind-tunnel tulwar, realizes different rollings
Angle.
6. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 1, it is characterised in that：It is described
Dynamic scale (1), supporting mechanism (15) are with yaw angle mechanism (16) on same axis.
7. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 1, it is characterised in that：It is described
Dynamic scale (1) includes：Pitching balance inner core (20), pitching balance outer wall (21), rotating shaft (22), strain beam (23), compression spiral shell
Nail (24), sliding bearing (25)；
Pitching balance inner core (20) is including head circular conical surface section, non-uniform beam, cooperation section and drives beam, and non-uniform beam is used to measure
Five component aerodynamic loadings, to coordinate and be provided with manhole and rectangular through-hole in section, and pitching balance outer wall (21) is tubular structure, bag
Hollow cooperation section and afterbody circular conical surface section are included, manhole and rectangular through-hole are provided with hollow cooperation section；
Pitching balance inner core (20) is arranged on pitching balance outer wall (21) inside, and sliding bearing (25) is enclosed within rotating shaft (22) outside,
And through the manhole on pitching balance outer wall (21) and pitching balance inner core (20), by pitching balance outer wall (21) and pitching
Balance inner core (20) is combined together, and strain beam (23) is through the square on pitching balance outer wall (21) and pitching balance inner core (20)
Shape through hole, the corner for measuring pitching balance inner core (20)；Housing screw (24) is fixed by strain beam (23) and rotating shaft (22)
On pitching balance outer wall (21).
8. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 7, it is characterised in that：Pitching
The driving beam of balance inner core (20) is located at the hollow cooperation intersegmental part of pitching balance outer wall (21), and the hollow internal diameter for coordinating section is big
In the maximum radial dimension for driving beam, the internal diameter of hollow cooperation section is than driving the big at least 10mm of the maximum radial dimension of beam, pitching
(22) rotate balance inner core (20) around the shaft, and rotational steps are not less than 1 °, and the head circular conical surface section of pitching balance inner core (20) is
1:10 circular conical surfaces, the afterbody circular conical surface section of pitching balance outer wall (21) is 1:10 circular conical surfaces.
9. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 7, it is characterised in that：Pitching
Set fluted on the driving beam rear part end face of balance inner core (20), (22) revolve around the shaft for driving pitching balance inner core (20)
Turn, realize pitching simple harmonic motion；The calibration center of pitching balance inner core (20) non-uniform beam is heavy with the center of rotating shaft (22)
Close, as measuring basis.
10. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 7, it is characterised in that：Bow
Look up to heaven flat inner core (20) non-uniform beam for stretch section, maximum is respectively subjected to 10000N normal force and 120Nm pitching moment load,
The maximum gauge of the pitching balance outer wall (21) is less than 51mm, and sliding bearing (25) uses copper master alloy inlaid solid lubrication axle
Hold.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611192367.3A CN106840574B (en) | 2016-12-21 | 2016-12-21 | A kind of device for wind-tunnel dynamic derivative forced vibration tests |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611192367.3A CN106840574B (en) | 2016-12-21 | 2016-12-21 | A kind of device for wind-tunnel dynamic derivative forced vibration tests |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106840574A true CN106840574A (en) | 2017-06-13 |
| CN106840574B CN106840574B (en) | 2019-02-15 |
Family
ID=59136007
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611192367.3A Active CN106840574B (en) | 2016-12-21 | 2016-12-21 | A kind of device for wind-tunnel dynamic derivative forced vibration tests |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106840574B (en) |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107450601A (en) * | 2017-08-02 | 2017-12-08 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of change yaw angle mechanism suitable for high-speed wind tunnel |
| CN107860545A (en) * | 2017-12-04 | 2018-03-30 | 中国航空工业集团公司沈阳空气动力研究所 | The six degree of freedom system of large-scale transonic wind tunnel big load model captive trajectory testing |
| CN107966264A (en) * | 2017-11-09 | 2018-04-27 | 中国航天空气动力技术研究院 | One kind is used for hypersonic wind tunnel rolling forced vibration dynamic derivative experimental rig |
| CN107966265A (en) * | 2017-11-09 | 2018-04-27 | 中国航天空气动力技术研究院 | One kind is used for hypersonic wind tunnel pitching yaw forced vibration dynamic derivative experimental rig |
| CN108120581A (en) * | 2017-12-11 | 2018-06-05 | 中国航天空气动力技术研究院 | Rotary missile pitching dynamic derivative high wind tunnel testing device and method |
| CN108195545A (en) * | 2017-12-05 | 2018-06-22 | 中国航天空气动力技术研究院 | Slender bodies aircraft elastic model vibration testing device |
| CN108760230A (en) * | 2018-03-30 | 2018-11-06 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of mounting device and installation method of model in wind tunnel |
| CN109000881A (en) * | 2018-08-16 | 2018-12-14 | 中国航天空气动力技术研究院 | A kind of rolling forced vibration dynamic derivative experimental rig suitable under Mach number 8.0 |
| CN109506877A (en) * | 2018-12-11 | 2019-03-22 | 中国航天空气动力技术研究院 | It is a kind of sub- across 90 ° of the super wind-tunnel big angle of attack, 360 ° of rolling devices of coupling |
| CN110108440A (en) * | 2019-05-10 | 2019-08-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of wind-tunnel balance attitude-control device |
| CN110940484A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Rolling forced vibration dynamic derivative test device for high-speed flying wing model under large attack angle |
| CN110987354A (en) * | 2019-12-05 | 2020-04-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method based on same |
| RU2736347C1 (en) * | 2020-05-27 | 2020-11-16 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Electromechanical bench |
| CN112268677A (en) * | 2020-10-15 | 2021-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Forced rock test device for high-speed wind tunnel |
| CN112268680A (en) * | 2020-09-17 | 2021-01-26 | 中国航天空气动力技术研究院 | Method for improving test accuracy of rotary balance |
| CN112504614A (en) * | 2020-10-19 | 2021-03-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Rolling reset device for wind tunnel balance calibration |
| CN114061893A (en) * | 2021-12-28 | 2022-02-18 | 中国航天空气动力技术研究院 | Wind tunnel small-amplitude forced pitching oscillation mechanism |
| CN114152404A (en) * | 2022-02-08 | 2022-03-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-precision pitching moment measuring device based on air bearing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01299434A (en) * | 1988-05-27 | 1989-12-04 | Mitsubishi Heavy Ind Ltd | Wind-tunnel test apparatus |
| JPH05322692A (en) * | 1992-05-26 | 1993-12-07 | Mitsubishi Heavy Ind Ltd | Wind tunnel test device |
| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 中国航空工业第一集团公司沈阳空气动力研究所 | Scale measuring device for pitching dynamic derivative experiment |
| CN102998082A (en) * | 2012-10-23 | 2013-03-27 | 绵阳市维博电子有限责任公司 | Device for wind tunnel dynamic derivative pitch vibration test |
| CN204188365U (en) * | 2014-10-11 | 2015-03-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of variable angle of attack supportive device for high-speed wind tunnel flutter model |
| CN105258904A (en) * | 2015-11-02 | 2016-01-20 | 中国航天空气动力技术研究院 | Wind tunnel test method for conical movement stability of rotary missile |
-
2016
- 2016-12-21 CN CN201611192367.3A patent/CN106840574B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01299434A (en) * | 1988-05-27 | 1989-12-04 | Mitsubishi Heavy Ind Ltd | Wind-tunnel test apparatus |
| JPH05322692A (en) * | 1992-05-26 | 1993-12-07 | Mitsubishi Heavy Ind Ltd | Wind tunnel test device |
| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 中国航空工业第一集团公司沈阳空气动力研究所 | Scale measuring device for pitching dynamic derivative experiment |
| CN102998082A (en) * | 2012-10-23 | 2013-03-27 | 绵阳市维博电子有限责任公司 | Device for wind tunnel dynamic derivative pitch vibration test |
| CN204188365U (en) * | 2014-10-11 | 2015-03-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of variable angle of attack supportive device for high-speed wind tunnel flutter model |
| CN105258904A (en) * | 2015-11-02 | 2016-01-20 | 中国航天空气动力技术研究院 | Wind tunnel test method for conical movement stability of rotary missile |
Non-Patent Citations (1)
| Title |
|---|
| 赵忠良等: "SDM标模大攻角动导数试验", 《航空学报》 * |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107450601A (en) * | 2017-08-02 | 2017-12-08 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of change yaw angle mechanism suitable for high-speed wind tunnel |
| CN107966265B (en) * | 2017-11-09 | 2019-07-12 | 中国航天空气动力技术研究院 | One kind yawing forced vibration dynamic derivative experimental rig for hypersonic wind tunnel pitching |
| CN107966264A (en) * | 2017-11-09 | 2018-04-27 | 中国航天空气动力技术研究院 | One kind is used for hypersonic wind tunnel rolling forced vibration dynamic derivative experimental rig |
| CN107966265A (en) * | 2017-11-09 | 2018-04-27 | 中国航天空气动力技术研究院 | One kind is used for hypersonic wind tunnel pitching yaw forced vibration dynamic derivative experimental rig |
| CN107860545A (en) * | 2017-12-04 | 2018-03-30 | 中国航空工业集团公司沈阳空气动力研究所 | The six degree of freedom system of large-scale transonic wind tunnel big load model captive trajectory testing |
| CN107860545B (en) * | 2017-12-04 | 2024-04-12 | 中国航空工业集团公司沈阳空气动力研究所 | Six-degree-of-freedom system for large transonic wind tunnel large load model capture track test |
| CN108195545A (en) * | 2017-12-05 | 2018-06-22 | 中国航天空气动力技术研究院 | Slender bodies aircraft elastic model vibration testing device |
| CN108195545B (en) * | 2017-12-05 | 2019-09-06 | 中国航天空气动力技术研究院 | Slender bodies aircraft elastic model vibration testing device |
| CN108120581A (en) * | 2017-12-11 | 2018-06-05 | 中国航天空气动力技术研究院 | Rotary missile pitching dynamic derivative high wind tunnel testing device and method |
| CN108120581B (en) * | 2017-12-11 | 2020-07-28 | 中国航天空气动力技术研究院 | Rotating missile pitching derivative high-speed wind tunnel test device and method |
| CN108760230A (en) * | 2018-03-30 | 2018-11-06 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of mounting device and installation method of model in wind tunnel |
| CN108760230B (en) * | 2018-03-30 | 2023-08-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device and method for installing wind tunnel test model |
| CN109000881A (en) * | 2018-08-16 | 2018-12-14 | 中国航天空气动力技术研究院 | A kind of rolling forced vibration dynamic derivative experimental rig suitable under Mach number 8.0 |
| CN109000881B (en) * | 2018-08-16 | 2020-07-14 | 中国航天空气动力技术研究院 | Rolling forced vibration dynamic derivative test device suitable for Mach number of 8.0 |
| CN109506877A (en) * | 2018-12-11 | 2019-03-22 | 中国航天空气动力技术研究院 | It is a kind of sub- across 90 ° of the super wind-tunnel big angle of attack, 360 ° of rolling devices of coupling |
| CN110108440A (en) * | 2019-05-10 | 2019-08-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of wind-tunnel balance attitude-control device |
| CN110940484A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Rolling forced vibration dynamic derivative test device for high-speed flying wing model under large attack angle |
| CN110940484B (en) * | 2019-11-13 | 2021-11-16 | 中国航天空气动力技术研究院 | Rolling forced vibration dynamic derivative test device for high-speed flying wing model under large attack angle |
| CN110987354B (en) * | 2019-12-05 | 2021-10-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method based on same |
| CN110987354A (en) * | 2019-12-05 | 2020-04-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method based on same |
| RU2736347C1 (en) * | 2020-05-27 | 2020-11-16 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Electromechanical bench |
| CN112268680A (en) * | 2020-09-17 | 2021-01-26 | 中国航天空气动力技术研究院 | Method for improving test accuracy of rotary balance |
| CN112268677A (en) * | 2020-10-15 | 2021-01-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Forced rock test device for high-speed wind tunnel |
| CN112504614A (en) * | 2020-10-19 | 2021-03-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Rolling reset device for wind tunnel balance calibration |
| CN114061893A (en) * | 2021-12-28 | 2022-02-18 | 中国航天空气动力技术研究院 | Wind tunnel small-amplitude forced pitching oscillation mechanism |
| CN114152404A (en) * | 2022-02-08 | 2022-03-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-precision pitching moment measuring device based on air bearing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106840574B (en) | 2019-02-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106840574B (en) | A kind of device for wind-tunnel dynamic derivative forced vibration tests | |
| CN106840590B (en) | A kind of five component dynamic pitching balance of miniaturized large-load integral type | |
| CN109000881B (en) | Rolling forced vibration dynamic derivative test device suitable for Mach number of 8.0 | |
| CN203037441U (en) | Single-component rod low-speed hinge moment measuring device | |
| CN109093379A (en) | Low-pressure turbo unit body Intelligent assembly platform | |
| CN106828843B (en) | A kind of underwater robot attitude regulation mechanism | |
| CN102998082A (en) | Device for wind tunnel dynamic derivative pitch vibration test | |
| CN107966265B (en) | One kind yawing forced vibration dynamic derivative experimental rig for hypersonic wind tunnel pitching | |
| CN102966700B (en) | Filtering drive device with high reliability and precision | |
| CN109029903A (en) | Continous way transonic wind tunnel Airfoil dynamic experiment mean angle of attack regulating mechanism | |
| CN109506877A (en) | It is a kind of sub- across 90 ° of the super wind-tunnel big angle of attack, 360 ° of rolling devices of coupling | |
| CN105258904A (en) | Wind tunnel test method for conical movement stability of rotary missile | |
| CN111664749A (en) | High-dynamic vertical five-axis electric turntable | |
| Yeo et al. | Investigation of rotor performance and loads of a UH-60A individual blade control system | |
| CN109060291B (en) | Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft | |
| CN109297672B (en) | Pitching yawing forced vibration dynamic derivative test device suitable for Mach number of 8.0 | |
| CN104229145A (en) | Lead screw push rod type aircraft head deflection driving device | |
| CN207067174U (en) | A kind of band incubator horizontal single quartz flexible accelerometer test table device | |
| CN105628327A (en) | Steel wire rope transmission type two-shaft rudder deflection control force measurement device | |
| CN203010161U (en) | Three-body frame for magnetically suspended control moment gyro | |
| CN110606222A (en) | Pneumatic characteristic testing device for single rotor system of suspended Mars aircraft | |
| CN115508038A (en) | Test device for high-speed wind tunnel ultra-large attack angle pitching and rolling double-freedom-degree motion | |
| Dong et al. | Analysis on meshing characteristics and transmission error of elliptic gears | |
| CN103389198B (en) | A kind of measurement mechanism for hypersonic wind tunnel rolling dynamic test | |
| CN114166496A (en) | Tilt rotor wing test device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |