CN106840574B - 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
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- CN106840574B CN106840574B CN201611192367.3A CN201611192367A CN106840574B CN 106840574 B CN106840574 B CN 106840574B CN 201611192367 A CN201611192367 A CN 201611192367A CN 106840574 B CN106840574 B CN 106840574B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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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 cooperation adjustment yaw angle mechanism between yaw angle mechanism and roll angle mechanism and relative position and angle between roll angle mechanism, meet the experimental test demand under the different angles of attack, yaw angle and roll angle operating condition.The present invention can drive transmission shaft to carry out continuous rotation movement, be cooperated by eccentric cam and the groove of dynamic scale in the case where determining frequency or frequency sweep mode by servo motor output torque, complete forms of motion conversion, realize simple harmonic quantity forced vibration.Structure of the invention is rationally compact, has many advantages, such as that normal direction carrying is big, precision is high, has major application value in field of aerospace.
Description
Technical field
The present invention relates to a kind of devices for wind-tunnel dynamic derivative forced vibration tests, belong to wind tunnel test technical field.
Background technique
When carrying out Design of Flight Control and space vehicle dynamic attributional analysis, flight force and moment is with aerodynamic derivative shape
Formula occurs, i.e., quiet, dynamic stability derivative, due to mechanism of production complexity, usually obtains above-mentioned parameter using forced vibration wind tunnel test.
Dynamic derivative wind tunnel test obtains dynamic derivative using model oscillation 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 test also becomes more and more important.Especially supersonic speed, high-supersonic speed range and significantly disturbance and on a large scale motor-driven item
Test and measuring technique under part, so it is necessary to optimize for entire forced vibration tests device.
According to the wind tunnel test mission requirements of the symmetrical aircraft in novel face, one side aircraft normal load is big, to solve
Load and Rigidity Matching problem, development of new forced vibration tests technology is with the dynamic test ability of forming face symmetrical flight device.
On the other hand, it is desirable that while the static derivative and dynamic derivative of precise measurement aircraft.Current forced vibration tests device normal direction carries
Lotus bearing capacity is not high, and torque output member installation and fixation are undesirable, insufficient on test accuracy, while also lacking reality
Now test the ability of the angle of attack, yaw angle and roll angle superposition.
The characteristics of symmetrical aircraft in novel face, mainly normal load was much larger than transverse load, for this reason, it may be necessary to a kind of novel
Forced vibration tests device solves the above problems, and is able to carry out the dynamic wind tunnel test of this kind of aircraft.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of 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
It protects test vibration frequency and amplitude is controllably accurate, realize the high-precision simple harmonic quantity forced vibration for determining frequency, amplitude.
The technical solution of the invention is as follows:
A kind of device for wind-tunnel dynamic derivative forced vibration tests, comprising: 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 condition.
Supporting mechanism includes: allotment bar, eccentric cam, transmission shaft, check ring, elastic washer and angular contact bearing；
Allotment bar is that tubular structure, front end and dynamic scale are cooperated by circular conical surface, and tail portion and yaw angle mechanism pass through circle
Cone match；
Transmission shaft is arranged inside allotment bar, and both ends of the drive shaft is each provided with mounting groove, check ring, elastic washer and angle
Contact bearing is arranged on the mounting groove of transmission shaft, for adjusting axial position and the rotation of transmission shaft；The head of transmission shaft is logical
Eccentric cam connection dynamic scale is crossed, the continuous rotation conversion of motion of transmission shaft is the reciprocally swinging of dynamic scale.
Yaw angle mechanism includes: bent sting, shaft coupling, retarder mounting base, retarder, servo motor and motor cover board；
Bent sting includes two parts, respectively supporing shell and angle board, and angle board is located in supporing shell, and angle
It is distributed with multiple angle adjustment holes on plate, supporing shell is hollow cylindrical, shaft coupling, retarder mounting base, retarder and is watched
It takes motor to be connected in turn, be arranged inside supporing shell, the transmission shaft of supporting mechanism connects retarder by shaft coupling；
Observation window is provided in supporing shell, for observing the connection of the transmission shaft and retarder.
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, cooperated by angle adjustment holes on the connecting hole and angle board in roll angle mechanism, and then adjust roll angle
Position and angle of the mechanism relative to yaw angle mechanism；The other end of roll angle mechanism is radially with 30 °, 45 °, 60 ° and 90 °
Angle be arranged keyway, with wind-tunnel tulwar cooperation 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, shaft, strain beam, housing screw, sliding bearing；
Pitching balance inner core includes head circular conical surface section, non-uniform beam, cooperation section and driving beam, and non-uniform beam is for measuring
Five component aerodynamic loadings cooperate and are provided with circular through hole and rectangular through-hole in section, and pitching balance outer wall is tubular structure, including sky
The heart cooperates section and tail portion circular conical surface section, is provided with circular through hole and rectangular through-hole in hollow cooperation section；
Pars intramuralis is arranged outside pitching balance in pitching balance inner core, and sliding bearing sleeve passes through pitching day outside shaft
Pitching balance outer wall and pitching balance inner core are combined together by the circular through hole on flat outer wall and pitching balance inner core, strain
Beam passes through the rectangular through-hole on pitching balance outer wall and pitching balance inner core, for measuring the corner of pitching balance inner core；It compresses
Strain beam and shaft are fixed on pitching balance outer wall by screw.
The driving beam of pitching balance inner core is located at the hollow cooperation intersegmental part of pitching balance outer wall, and hollow cooperation section is interior
Diameter be greater than driving beam maximum radial dimension, it is hollow cooperation section internal diameter than driving beam maximum radial dimension greatly at least 10mm,
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 cone
Face, the tail portion circular conical surface section of pitching balance outer wall are 1:10 circular conical surface.
Be arranged on the driving beam tail end face of pitching balance inner core it is fluted, for driving pitching balance inner core to revolve around the shaft
Turn, realizes pitching simple harmonic motion；The calibration center of pitching balance inner core non-uniform beam is overlapped with the center of shaft, as measurement base
It is quasi-.
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 are 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 retarder, servo motor can be effectively fixed, avoid filling
The vibration set influences output effect, improves test accuracy；
(3) wind-tunnel tulwar may be implemented and adjust 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 condition.
(4) the invention proposes unique dynamic pitching balance design thought, traditional tandem formula balance is breached
Design method reduces balance diameter, it is long that inside and outside fabricated structure then shortens balance so that dynamic scale overall volume is small
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 is overlapped with shaft, improves the essence of dynamic scale measurement
Degree.The strain beam of dynamic scale can be dismounted independently.The thickness for only needing to change strain beam in the debugging of ground carrys out Matching Model and carries
Lotus is not necessarily to 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 replaces model and dynamic scale measuring cell according to different demands, makes device with 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, there is good practicability and promotional value.
Detailed description of the invention
Fig. 1 is the structural schematic diagram for wind-tunnel dynamic derivative forced vibration device of the invention；
Fig. 2 is the structural schematic diagram 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 schematic diagram of the dynamic scale of Fig. 1；
Fig. 6 is the cross-sectional view of Fig. 5；
Fig. 7 is the part composition schematic diagram of Fig. 5.
Specific embodiment
A specific embodiment of the invention is further described in detail with reference to the accompanying drawing.
On the one hand the wind tunnel test task of the novel symmetrical aircraft in face requires the dynamic test energy of forming face symmetrical flight device
Power solves the problems, such as load and Rigidity Matching, while capableing of the static derivative and dynamic derivative of precise measurement aircraft.The present invention proposes
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 can satisfy the experimental test demand under the different angles of attack, yaw angle and roll angle operating condition.
As shown in Figure 1, the invention proposes a kind of devices for wind-tunnel dynamic derivative forced vibration tests, comprising: 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 passes through yaw angle mechanism 16 and roll angle mechanism
Between 17 cooperation adjustment yaw angle mechanism 16 and roll angle mechanism 17 between relative position and angle, realize the different angles of attack,
Experimental test under yaw angle and roll angle operating condition.
As shown in Fig. 2, supporting mechanism 15 includes: allotment bar 2, eccentric cam 6, transmission shaft 7, check ring 12, elastic cushion
Circle 13 and angular contact bearing 14；
Allotment bar 2 is that tubular structure, front end and dynamic scale 1 are cooperated by circular conical surface, and tail portion and yaw angle mechanism 16 are logical
Cross circular conical surface cooperation；Increase the contact area between cooperation, reduces the gap of mechanical structure.
Transmission shaft 7 is arranged inside allotment bar 2, and 7 both ends of transmission shaft are each provided with mounting groove, check ring 12, elastic cushion
Circle 13 and angular contact bearing 14 are arranged on the mounting groove of the transmission shaft 7, for adjusting axial position and the rotation of transmission shaft 7
Turn；In axial direction, there are certain adjustment threshold degree for transmission shaft 7 for elastic washer 13, reduce installation difficulty, components is avoided to assemble
The offset issue of axial dimension in journey.The head of transmission shaft 7 by eccentric cam 6 connect dynamic scale 1, transmission shaft 7 it is continuous
Rotary motion is converted into the reciprocally swinging of dynamic scale 1, realizes effective movement conversion, reappears needed for aircraft pitching movement
Forced vibration state.
As shown in figure 3, yaw angle mechanism 16 includes: bent sting 3, shaft coupling 8, retarder mounting base 9, retarder 10, watches
Take motor 11 and motor cover board 4；
Bent sting 3 includes two parts, and respectively supporing shell 18 and angle board 19, angle board 19 is located at supporing shell 18
On, and multiple angle adjustment holes are distributed on angle board 19, supporing shell 18 is hollow cylindrical, shaft coupling 8, retarder installation
Seat 9, retarder 10 and servo motor 11 are connected in turn, and are arranged inside supporing shell 18, the supporting mechanism 15
Transmission shaft 7 connects retarder 10 by shaft coupling 8；Retarder 10 is fixed in supporing shell 18 by retarder mounting base 9, is reduced
Gap is installed, component vibration caused by reducing because of forced vibration tests improves test essence to reduce the interference of mechanical noise
Degree.
It is provided with observation window in supporing shell 18, for observing the connection of transmission shaft 7 Yu retarder 10.It can finely tune simultaneously
The axial position of transmission shaft 7 guarantees that the eccentric cam 6 on 7 head of transmission shaft can cooperate with pitching balance inner core 20.
The angle of regulation range of angle board 19 is 0 °~16 °, and increasing in wind tunnel test needs the test of yaw angle operating condition
It asks, also the direction of adjustable yaw angle mechanism 16 is pitch orientation, for increasing the test angle of attack, complete big angle of attack wind tunnel test
Demand.
As shown in figure 4,17 one end of roll angle mechanism 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, pass through the angular adjustment on the connecting hole and angle board 19 in roll angle mechanism 17
Hole cooperation, and then adjust position and angle of the roll angle mechanism 17 relative to yaw angle mechanism 16；Roll angle mechanism 17 it is another
Keyway is arranged radially with 30 °, 45 °, 60 ° and 90 ° of angle in end, after the cooperation of wind-tunnel tulwar, realizes different roll angles,
To increase achievable operating condition of test number.
Dynamic scale 1, supporting mechanism 15 and yaw angle mechanism 16 are on same axis, and structure is carried out by tandem
Combination has good globality.
As shown in Fig. 5,6,7, dynamic scale 1 includes: pitching balance inner core 20, pitching balance outer wall 21, 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, cooperation section and driving beam, and non-uniform beam is for surveying
Five component aerodynamic loadings are measured, cooperates and is provided with circular through hole and rectangular through-hole in section, pitching balance outer wall 21 is tubular structure, packet
Hollow cooperation section and tail portion circular conical surface section are included, is provided with circular through hole and rectangular through-hole in hollow cooperation section；
Pitching balance inner core 20 is arranged inside pitching balance outer wall 21, and 25 sets of sliding bearing outside shaft 22, and are worn
The circular through hole on pitching balance outer wall 21 and pitching balance inner core 20 is crossed, by pitching balance outer wall 21 and pitching balance inner core 20
It is combined together, strain beam 23 passes through the rectangular through-hole on pitching balance outer wall 21 and pitching balance inner core 20, and rectangular configuration is used
In ensuring that strain beam 23 can follow pitching balance inner core 20 to be moved completely, the corner of pitching balance inner core 20 is measured；
Strain beam 23 and shaft 22 are fixed on pitching balance outer wall 21 by housing screw 24, for inhibiting the strain beam in motion process
23 and the cross stream component that is subject to of shaft 22.
The driving beam 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 be greater than driving beam maximum radial dimension, it is hollow cooperation section internal diameter than driving beam maximum radial dimension greatly at least
10mm reserves enough spaces for the pitching simple harmonic motion of pitching balance inner core 20, pitching balance inner core 20 is avoided to be moved through
It collides in journey with pitching balance outer wall 21.22 rotation around the shaft of pitching balance inner core 20, rotational steps are not less than 1 °, thus
The situation of change of acquisition aerodynamic loading that can be more accurate, is conducive to improving measurement accuracy.The head of pitching balance inner core 20
Circular conical surface section is 1:10 circular conical surface, and the tail portion circular conical surface section of pitching balance outer wall 21 is 1:10 circular conical surface, using the circular cone of 1:10
Face is attached the contact area that can increase between component, make to connect it is even closer, reduce because of mechanical structure gap caused by
It influences.
Be arranged on the driving beam tail end face of pitching balance inner core 20 it is fluted, for driving pitching balance inner core 20 to rotate
Axis 22 rotates, and realizes pitching simple harmonic motion；The calibration center of 20 non-uniform beam of pitching balance inner core and the center of shaft 22
It is overlapped, as measuring basis, improves measurement accuracy, keep structure more compact.
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 satisfy the loading demands of the symmetrical aircraft in novel face, and it is enough to guarantee that pitching balance inner core 20 has
Rigidity.The maximum gauge of pitching balance outer wall 21 is less than 51mm, limits the overall volume of dynamic pitching balance；Therefore in novel face
The lesser situation of symmetrical flight device test model can be completed to install, simultaneously because the small volume of dynamic pitching balance can also be with
Other dynamic test models are matched, can be increased using range.Sliding bearing 25 uses copper master alloy inlaid solid lubrication bearing,
The bearing long service life adds lubricant without the later period, tears dynamic pitching balance within the service life time limit without repeating open
Dress.
Working principle:
According to the demand of different tests operating condition, change the angle conditions angle of attack of wind-tunnel tulwar；Change 3 upper angle of bent sting
The angle adjustment holes of plate 19 and the relative position of the connecting hole in roll angle mechanism 17, and then adjust yaw angle β；Change roll angle
Keyway in mechanism 17 to cooperate with wind-tunnel tulwar, adjusts roll angle；Multiple angles adjusting can be implemented in combination, and meet multi-pose
The requirement of angle combination.
After setting test attitude angle, starting servo motor 11 carries out continuous rotation movement output torque, passes through retarder 10
It is transmitted to transmission shaft 7 with shaft coupling 8, then is transferred to eccentric cam 6.By on eccentric cam 6 and 1 tail end face of dynamic scale
Movement, is converted to the reciprocating motion in pitch orientation by groove cooperation.To drive the driving beam of pitching balance inner core 20 to rotate
Axis 22 rotates, and realizes the whole pitching simple harmonic motion of pitching balance inner core 20, while strain beam 23 being driven to synchronize movement, surveys
Measure the movement angle of pitching balance inner core 20.
Embodiment
Most prior art can only all be tested by wind-tunnel tulwar to adjust the variation of angle of attack, and operating condition of test changes
Become very limited, and very high to the dependence of wind-tunnel tulwar, it, can shadow significantly if the tulwar regulating power of test air tunnel is lower
Ring operating condition of test number and experiment quantity.The forced vibration tests device may be implemented wind-tunnel tulwar and adjust angle of attack, yaw angle
Mechanism changes yaw angle β and roll angle mechanism gives the different attitude angle variation of tri- kinds of roll angle K, 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 approximate relationship below under small amplitude forced vibration:
β=K*sin α
In conjunction with the relational expression of three, can be solved under the operating condition of combination of two under another attitude angle as a result, for more
State complex wind tunnel test and multimode motion theory verification test, have widened the application range of device, and the practicality also compares
Existing device is high.
Claims (8)
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 on yaw angle mechanism (16), and passes through yaw angle mechanism (16) and rolling
Cooperation adjustment yaw angle mechanism (16) between angle mechanism (17) and relative position and angle between roll angle mechanism (17), it is real
Experimental test under the existing different angles of attack, yaw angle and roll angle operating condition；
The supporting mechanism (15) includes allotment bar (2), eccentric cam (6), transmission shaft (7), check ring (12), elastic washer
(13) and angular contact bearing (14)；
The allotment bar (2) is tubular structure, and front end and dynamic scale (1) are cooperated by circular conical surface, tail portion and yaw angle mechanism
(16) cooperated by circular conical surface,
Transmission shaft (7) setting is internal in allotment bar (2), and transmission shaft (7) both ends are each provided with mounting groove, check ring (12), bullet
Property washer (13) and angular contact bearing (14) be arranged on the mounting groove of the transmission shaft (7), for adjusting the axis of transmission shaft (7)
To position and rotation；The head of transmission shaft (7) passes through eccentric cam (6) connection dynamic scale (1), the continuous rotation of transmission shaft (7)
Transhipment turn turns to the reciprocally swinging of dynamic scale (1)；
Yaw angle mechanism (16) includes bent sting (3), shaft coupling (8), retarder mounting base (9), retarder (10), servo motor
(11) and motor cover board (4)；
Bent sting (3) includes two parts, and respectively supporing shell (18) and angle board (19), angle board (19) is located at supporting shell
On body (18), and multiple angle adjustment holes are distributed on angle board (19), supporing shell (18) is hollow cylindrical, shaft coupling
(8), retarder mounting base (9), retarder (10) and servo motor (11) are connected in turn, and are arranged in supporing shell (18)
The transmission shaft (7) of inside, the supporting mechanism (15) passes through shaft coupling (8) connection retarder (10)；
Supporing shell is provided with observation window on (18), for observing the connection of the transmission shaft (7) Yu retarder (10).
2. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 1, it is characterised in that: angle
The angle of regulation range of plate (19) is 0 °~16 °.
3. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 1, it is characterised in that: 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 by the connecting hole on roll angle mechanism (17) with the angle adjustment holes on angle board (19)
It closes, and then adjusts the position and angle of roll angle mechanism (17) relative to yaw angle mechanism (16)；Roll angle mechanism (17) it is another
Keyway is arranged radially with 30 °, 45 °, 60 ° and 90 ° of angle in one end, after the cooperation of wind-tunnel tulwar, realizes different rollings
Angle.
4. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 1, it is characterised in that: described
Dynamic scale (1), supporting mechanism (15) and yaw angle mechanism (16) are on same axis.
5. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 1, it is characterised in that: described
Dynamic scale (1) includes: pitching balance inner core (20), pitching balance outer wall (21), shaft (22), strain beam (23), compresses spiral shell
Follow closely (24), sliding bearing (25)；
Pitching balance inner core (20) includes head circular conical surface section, non-uniform beam, cooperation section and driving beam, and non-uniform beam is for measuring
Five component aerodynamic loadings cooperate and are provided with circular through hole and rectangular through-hole in section, and pitching balance outer wall (21) is tubular structure, packet
Hollow cooperation section and tail portion circular conical surface section are included, is provided with circular through hole and rectangular through-hole in hollow cooperation section；
Pitching balance inner core (20) setting is internal in pitching balance outer wall (21), and sliding bearing (25) is covered in shaft (22) outside,
And the circular through hole on pitching balance outer wall (21) and pitching balance inner core (20) is passed through, by pitching balance outer wall (21) and pitching
Balance inner core (20) is combined together, and strain beam (23) passes through the square on pitching balance outer wall (21) and pitching balance inner core (20)
Shape through-hole, for measuring the corner of pitching balance inner core (20)；Housing screw (24) is fixed by strain beam (23) and shaft (22)
On pitching balance outer wall (21).
6. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 5, 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 internal diameter of hollow cooperation section is big
In the maximum radial dimension of driving beam, maximum radial dimension greatly at least 10mm of the internal diameter than driving beam of hollow cooperation section, pitching
Balance inner core (20) rotates around the shaft (22), 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 surface, the tail portion circular conical surface section of pitching balance outer wall (21) are 1:10 circular conical surface.
7. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 5, it is characterised in that: pitching
Be arranged on the driving beam tail end face of balance inner core (20) it is fluted, for drive pitching balance inner core (20) around the shaft (22) revolve
Turn, realizes pitching simple harmonic motion；The calibration center of pitching balance inner core (20) non-uniform beam and the center weight of shaft (22)
It closes, as measuring basis.
8. a kind of device for wind-tunnel dynamic derivative forced vibration tests according to claim 5, it is characterised in that: pitching
The non-uniform beam of balance inner core (20) is stretch section, and maximum is respectively subjected to 10000N normal force and 120Nm pitching moment load, institute
The maximum gauge for stating pitching balance outer wall (21) is less than 51mm, and sliding bearing (25) uses copper master alloy inlaid solid lubrication axis
It holds.
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| CN201611192367.3A CN106840574B (en) | 2016-12-21 | 2016-12-21 | A kind of device for wind-tunnel dynamic derivative forced vibration tests |
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| CN201611192367.3A CN106840574B (en) | 2016-12-21 | 2016-12-21 | A kind of device for wind-tunnel dynamic derivative forced vibration tests |
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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 |
|---|
| SDM标模大攻角动导数试验;赵忠良等;《航空学报》;19980331;第19卷(第2期);第137-138页，图1-2 |
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