CN209014243U - Airfoil dynamic experiment amplitude angle regulating mechanism - Google Patents
Airfoil dynamic experiment amplitude angle regulating mechanism Download PDFInfo
- Publication number
- CN209014243U CN209014243U CN201821590491.XU CN201821590491U CN209014243U CN 209014243 U CN209014243 U CN 209014243U CN 201821590491 U CN201821590491 U CN 201821590491U CN 209014243 U CN209014243 U CN 209014243U
- Authority
- CN
- China
- Prior art keywords
- sliding block
- concussion
- connecting rod
- rotary body
- regulating mechanism
- 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.)
- Expired - Fee Related
Links
Abstract
A kind of Airfoil dynamic experiment amplitude angle regulating mechanism, based on crank and rocker mechanism, the accurate adjusting at amplitude angle when realizing aerofoil profile model pitching concussion by adjusting slide position and length of connecting rod.Driving motor at the top of wind-tunnel provides power resources for whole device, the crank device of the regulating mechanism is set to drive rocker arm pitching concussion by connecting rod while moving in a circle around motor shaft; rocker arm is connected with concussion axis; and then concussion axis to be driven to carry out periodical pitching concussion along axial; and test aerofoil profile model used and pass through that dynamic experiment is dedicated to turn window and concussion axis connection by auricle, it is final to realize that aerofoil profile model carries out periodicity pitching concussion with particular amplitude angle and moves.The utility model can be aeroperformance assessment of the aerofoil profile of high maneuverability aircraft under various amplitude corner condition for accurate reliable experimental data, and provide foundation for its optimization design.
Description
Technical field
The present invention relates to aerospace wing tunnel test apparatus fields, specially a kind of to be suitable for the continous way transonic wind tunnel wing
Type dynamic experiment amplitude angle regulating mechanism.
Background technique
Helicopter is to drive helicopter rotor system to work using turboshaft engine, to generate lift, thrust and control
The aircraft of power, in civil field and military field using very extensive, the performance superiority and inferiority of rotor system directly determines directly
The flying quality and security performance of the machine of liter, and the dynamic characteristic for the aerofoil profile that the aerodynamic characteristic of lifting airscrew is used with it ceases manner of breathing
It closes, the unsteady dynamic stall phenomenon that pitching concussion of the aerofoil profile under various amplitude corner condition generates is to rotor aerodynamics, behaviour
Vertical characteristic, component life have vital influence.Rotor system at work, due to rotor blade wave and periodically
The influence of displacement, retreating blade is smaller relative to speed of incoming flow, and for balance paddle disk torque, the retreating blade angle of attack is usually larger,
Therefore easily cause dynamic stall phenomenon, and advancing blade is larger with respect to speed of incoming flow, easily generates shock wave, when shock wave is stronger
Shock wave-boundary-layer interference phenomenon will be generated, dynamic stall caused by also inducing leading edge to separate in the lesser situation of the angle of attack.
Therefore, during helicopter rotor system periodicity displacement the size at amplitude angle directly affect rotor-blade airfoil dynamic it is special
Property.
Currently, the size for amplitude angle is still not perfect to the research of aerofoil profile dynamic stall phenomenon, especially in the big angle of attack
Under the conditions of the mechanism study of dynamic characteristic be still left to be desired.It and is one by the continous way transonic wind tunnel that axial flow compressor drives
The reverse-flow type transonic aerodynamics experiment porch that kind can be continuously long-running, flow field quality and conventional efficient are much higher than
Conventional intermittent wind tunnel, and for aerofoil profile with the dynamic experiment of the periodical pitching concussion of certain amplitude angle progress, to wind-tunnel
The field quality of stream and continue working duration require it is higher, therefore in continous way transonic wind tunnel carry out various amplitude angle to aerofoil profile
The experimental study that dynamic characteristic influences has very important significance, and can be the pneumatic Performance Evaluation of dynamic of high speed aerofoil profile,
Optimization design provides accurate reliable experimental data.
In order to meet the design requirement of high maneuverability aerofoil profile, primary means air technology developed country, the world carries out earlier
The correlative study of various amplitude corner condition Airfoil dynamic stall.Early in late 1970s, McCroskey et al. is not for
Carry out a large amount of wind- tunnel investigation with rotor-blade airfoil, tentatively discloses the parameters pair such as mean angle of attack, amplitude angle, reduced frequency
The influence of aerofoil profile dynamic stall characteristic；The country under various amplitude corner condition aerofoil profile dynamic stall characteristic correlative study carry out compared with
In evening, Northwestern Polytechnical University Xia Yushun, Xi Zhongxiang, Zhou Ruixing et al. are in " NACA0012 aerofoil profile dynamic stall characteristic and pressure testing method
Research " aviation journal, volume 1996 the 17th, A1 phase P26-311000-6893 discloses and carries out in NF-3 wind-tunnel
The dynamic stall correlative study under various amplitude corner condition of NACA0012 aerofoil profile obtains the dynamic stall of more complete aerofoil profile
When pressure distribution.Its test mechanism is as shown in figure 13, and wherein the amplitude of model can be different on turntable by changing sliding block
Radial coupled position is adjusted, and shares 3 positions, can make to realize 5 °, 8 °, 10 ° of amplitude angle.
Both at home and abroad for the experimental study of dynamic stall characteristic under aerofoil profile various amplitude corner condition mostly all in low-speed wind tunnel
Expansion is no longer satisfied the following high maneuverability aircraft to the design requirement of novel airfoil, and this kind of amplitude angle adjusts machine
Structure there are installation and debugging difficulty it is higher, adjustable range is smaller, and angle adjustable is less the problems such as.
Summary of the invention
To overcome, installation and debugging difficulty existing in the prior art is higher, adjustable range is smaller and angle adjustable is less
Deficiency, the invention proposes a kind of Airfoil dynamic experiment amplitude angle regulating mechanisms.
The present invention includes two connecting rods, rocker arm, crank and rotation axis；Wherein, pass through length tune between two connecting rods
Save screw rod connection.The crank is located at one end of the connecting rod after connection, and the lantern ring of connecting rod is sleeved on to the lantern ring of the sliding block of crank
On bar, and it is mutually perpendicular to the center line of the connecting rod and the center line of sliding block；Another end cap of two connecting rods upon connection
In the rotation axis.One end of rocker arm is also sleeved in the rotation axis；The other end of the rocker arm is set with and is fixed on
Support one end of the concussion axis of testpieces.
The crank includes threaded rod, rotary body, sliding block and sliding block pressing plate.The rotary body is sleeved on the electricity of driving motor
On arbor, the rotary body is enable to rotate by center of rotation of the motor shaft.It is respectively fixed with end cap at the both ends of the rotary body,
The both ends of the threaded rod are separately mounted in the centre bore of the end cap.The slide block set of square-outside and round-inside is mounted in the threaded rod
On.There is the collar shank of protrusion in one side surface of the sliding block, and makes to be rotatably assorted between the collar shank and lantern ring.In the cunning
The sliding block pressing plate of strip is laid in the upper surface of block, so that the sliding block pressing plate is pressed on the upper surface of the sliding block by screw.
The a rotating body has the square cavity extended along the rotary body length direction；It is used at the top of the square cavity
Place the groove of sliding block pressing plate.The screw hole of multiple perforation rotor cases is provided on the groove.The one of the rotary body
There is convex block in the side surface of a long side, and there is the threaded hole for connecting motor shaft at the center of the convex block；The threaded hole and rectangular sky
Chamber perforation, and it is mutually perpendicular to the center line of the threaded hole and the geometric center lines of the square cavity length direction.With it is convex
The side surface of another long side of the symmetrical rotary body of block is provided with the aperture of bar shaped, which is the cunning of the collar shank on sliding block
Road；Effective removable length of the collar shank slideway is 0~36mm.
The shape of the sliding block is rectangular, and makes clearance fit between the sliding block and the square cavity of rotary body.In the cunning
There is the threaded hole with shaft at the center of block.There is the collar shank of protrusion in one side surface of the sliding block.
One end of the connecting rod is welded with lantern ring, and the axis of the lantern ring centre bore is vertical with the axial space of the connecting rod；
The internal diameter of the lantern ring is slightly larger than the outer diameter of collar shank on the outer diameter or sliding block of rotation axis joined together, make each lantern ring respectively with
It is rotatably assorted between the rotation axis or collar shank.There is tapped blind hole at the center of the connecting rod the other end face, and the screw thread is blind
Hole is with length adjustment screw rod by being threadedly engaged.The length of the connecting rod is 980mm.
The both ends of the length adjustment screw rod are oppositely oriented external screw thread；Have six in the middle part of the length adjustment screw rod
The boss of side, is respectively installed with clamp nut on the threaded rod of the boss two sides.
There is through-hole at the both ends of the rocker arm, and the through-hole of one end is rotatably assorted with rotation axis.The through-hole of the other end with
Axis cooperation is shaken, and passes through screws tighten.The center line of rocker arm both ends through-hole is parallel to each other；Rocker arm both ends through-hole
Center is away from for 210mm.
The present invention is expanded Planar Crank-and-rocker Mechanism for space song by rotation axis in the limited wind tunnel reservoir structure room in space
Handle rocker device takes full advantage of the space of wind-tunnel solution longitudinal direction in interior, and can reduce the length of concussion axis；Pass through simultaneously
Locking nut fixes sliding block, when the sliding block being made to be moved to any position on threaded rod, will not all generate opposite fortune therebetween
It is dynamic, therefore the present invention overcomes existing amplitude angle regulating mechanisms during pitching concussion that mechanical noise and mechanical oscillation are excessive
Defect；The present invention realizes the continuously adjustable of amplitude angle angle by changing slide position, and adjustable range is 0 ° to 10 °, overcomes
The deficiency that existing amplitude angle regulating mechanism adjustable range is small, angle adjustable is few.Based on These characteristics, the present invention can be high motor-driven
Property aircraft aeroperformance assessment of the aerofoil profile under various amplitude corner condition for accurate reliable experimental data, and optimize for it
Design provides foundation.
To verify effect of the invention, real-time angle of attack data: sample frequency 20KHz are acquired, when acquisition is a length of
1.024s, aerofoil profile oscillation frequency are 11.05Hz, and mean angle of attack is 10 °, and amplitude angle is 5 °.Amplitude angular amplitude error be ±
0.21 °, meet requirement of the continous way transonic wind tunnel aerofoil profile dynamic test to amplitude angle degree of regulation.
The present invention realizes the pitching of aerofoil profile model based on crank and rocker mechanism, by adjusting slide position and length of connecting rod
The accurate adjusting at amplitude angle when concussion.Driving motor at the top of wind-tunnel provides power resources for entire mechanism, runs in mechanism
Rocker arm pitching concussion is driven by connecting rod while crank moves in a circle around motor shaft in journey, rocker arm is connected with concussion axis, into
And concussion axis is driven to carry out periodical pitching concussion along axial, and test aerofoil profile model used and dynamic experiment is passed through by auricle
Dedicated to turn window and concussion axis connection, final realization aerofoil profile model carries out periodical pitching concussion movement with particular amplitude angle.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention.
Fig. 2 is the main view of rotary body.
Fig. 3 is the A-A direction view of Fig. 2.
Fig. 4 is the top view of Fig. 2.
Fig. 5 is the main view of crank.
Fig. 6 is the A-A direction view of Fig. 5.
Fig. 7 is the top view of Fig. 5.
The main view of Fig. 8 connecting rod.
Fig. 9 is the top view of Fig. 8.
Figure 10 is the main view of rocker arm.
Figure 11 is the top view of Figure 10.
Figure 12 is the connection schematic diagram of the present invention with driving motor and concussion axis.
Figure 13 is the structural schematic diagram of NF-3 amplitude angle regulating mechanism in the prior art.
In figure: 1. cranks；2. connecting rod；3. length adjustment screw rod；4. rotation axis；5. rocker arm；6. threaded rod；7. rotary body；
8. sliding block；9. sliding block pressing plate；10. shaking axis；11. motor shaft；12. aerofoil profile model；13. end cap.
Specific embodiment
The present embodiment is a kind of continous way transonic wind tunnel Airfoil dynamic experiment amplitude angle regulating mechanism, including two connecting rods
2, Rocker arm 5, crank 1 and rotation axis 4；Wherein, it is connected between two connecting rods by length adjustment screw rod 3.The crank position
The lantern ring of connecting rod is sleeved on the collar shank of sliding block 8 of crank 1 by one end of the connecting rod after connection, and makes the connecting rod
The center line of center line and sliding block is mutually perpendicular to；The other end of two connecting rods upon connection is sleeved in the rotation axis 4.It shakes
One end of arm 5 is also sleeved in the rotation axis；The other end of the rocker arm is set with and is fixed on the concussion axis of support testpieces
10 one end.
Crank 1 includes threaded rod 6, rotary body 7, sliding block 8 and sliding block pressing plate 9.The rotary body 7 is sleeved on driving motor
On motor shaft 11, the rotary body is enable to rotate by center of rotation of the motor shaft.It is respectively fixed at the both ends of the rotary body 7
The both ends of end cap 13, the threaded rod are separately mounted in the centre bore of the end cap by screw thread, and are fastened by nut.Outside
The sliding block 8 of square inner circle is sleeved on the threaded rod, when threaded rod rotation, the sliding block is driven to move along the threaded rod.
There is the collar shank of protrusion in one side surface of the sliding block 8, for connecting the lantern ring of connecting rod；The outer diameter of the collar shank is slightly less than set
The internal diameter of ring makes to be rotatably assorted therebetween.The sliding block pressing plate 9 of strip is laid in the upper surface of the sliding block 8, passes through spiral shell
The upper surface for making the sliding block pressing plate be pressed on the sliding block is followed closely, to limit the play of the sliding block.
The shape of the rotary body 7 is square.There is the rectangular sky extended along the rotary body length direction in a rotating body
Chamber；There is the groove for placing sliding block pressing plate 9 at the top of the square cavity.Multiple perforation rotary bodies 7 are provided on the groove
The screw hole of shell.There is convex block in the side surface of a long side of the rotary body, the center of the convex block has for connecting motor shaft
12 threaded hole；The threaded hole and square cavity penetrate through, and make the center line of the threaded hole and the square cavity length side
To geometric center lines be mutually perpendicular to.Opening for bar shaped is provided in the side surface of another long side of the rotary body symmetrical with convex block
Hole, the aperture are the slideway of the collar shank on sliding block 8；Effective removable length of the collar shank slideway is 0~36mm.
The shape of the sliding block 8 is rectangular, and makes clearance fit between the sliding block and the square cavity of rotary body.In the cunning
There is the threaded hole cooperated with threaded rod 6 at the center of block.There is the collar shank of protrusion in one side surface of the sliding block.
Sliding block pressing plate 9 is strip, and the groove at the top of outer dimension and the square cavity is adapted.
The structure of described two connecting rods 2 is identical, and the present embodiment is described for one of those.The one of the connecting rod
End is welded with lantern ring, and the axis of the lantern ring centre bore is vertical with the axial space of the connecting rod；The internal diameter of the lantern ring is bigger
In the outer diameter of collar shank on the outer diameter or sliding block of rotation axis 4 joined together, make each lantern ring respectively with the rotation axis or collar shank
Between be rotatably assorted.There is tapped blind hole at the center of the connecting rod the other end face, and the tapped blind hole and length adjustment screw rod 3 are logical
It crosses and is threadedly engaged.The length of the connecting rod is 980mm.
The both ends of the length adjustment screw rod 3 are oppositely oriented external screw thread；Have in the middle part of the length adjustment screw rod
The boss of six sides is respectively installed with clamp nut on the threaded rod of the boss two sides.When length adjustment screw rod both ends point
After not screwing in the tapped blind hole of each connecting rod end face, fastened by the clamp nut.
The Rocker arm 5 is lath-shaped.There is through-hole at the both ends of the rocker arm, and the through-hole of one end is matched with the rotation of rotation axis 4
It closes.The through-hole and concussion axis 10 of the other end cooperate, and pass through screws tighten.The center line of rocker arm both ends through-hole is mutually flat
Row；The center of rocker arm both ends through-hole is away from for 210mm.
When work, which realizes aerofoil profile mould based on crank and rocker mechanism, by adjustment slide position and length of connecting rod
The accurate adjusting at amplitude angle when type pitching concussion.Driving motor at the top of wind-tunnel provides power resources for entire mechanism, in mechanism
Rocker arm pitching concussion, rocker arm and concussion axis phase are driven by connecting rod while crank moves in a circle around motor shaft in operational process
Connect, and then drive concussion axis along the periodical pitching concussion of axial progress, and tests aerofoil profile model used by auricle across dynamic
State experiment is dedicated to turn window and concussion axis connection, and final realization aerofoil profile model is carried out periodically with the amplitude angle within the scope of 0 ° to 10 °
Pitching concussion movement.
In work, by the length of the accurate controls connecting rod of length adjustment screw rod, and pass through locking nut for length tune
Section screw rod is locked, it is ensured that the length of entire connecting rod is remaining constant in dynamic experiment mechanism operational process, simultaneously
The length of connecting rod also determines therewith.Connecting rod is rotatably assorted by cylindrical hole with sliding block rotary body lateral ends and is connect, and the other end is logical
Rotation axis is crossed to connect by bearing.The length of the connecting rod is, when sliding block axis is overlapped and rocker arm with motor rotation axis axis
The length of connecting rod when keeping horizontal.
Rotation axis connects connecting rod and rocker arm by bearing, is spatial crank rocker machine by Planar Crank-and-rocker Mechanism topology
Structure can effectively utilize space, reduce the length of concussion axis, while the friction avoided when rocker arm is directly connected to connecting rod is damaged
It loses, the length of rotation axis is according to the end face and sliding block of concussion axis and rocker arm connection side in level between rotary body end face outside
Projector distance on direction determines.
Locking nut of the sliding block outside rotary body makes screw rod adjust position needed for experiment in sliding block for fixing sliding block
It postpones and is no longer able to turn；Locking pin at the top of rotary body passes through rotary body surface and is deep into rotary body cavity and on sliding block pressing plate
Surface holds out against fixation, and sliding block pressing plate lower surface is adjacent to sliding block upper surface, and stiction is leaned between sliding block pressing plate and sliding block
Ensure that slide position is kept fixed during entirely experiment mechanism operation.The collar shank of the sliding block other side is matched with link rotatable
Close connection.
Claims (7)
1. a kind of Airfoil dynamic experiment amplitude angle regulating mechanism, which is characterized in that including two connecting rods, rocker arm, crank and rotation
Axis；Wherein, it is connected between two connecting rods by length adjustment screw rod；The crank is located at one end of the connecting rod after connection,
The lantern ring of connecting rod is sleeved on the collar shank of the sliding block of crank, and make the connecting rod center line and sliding block center line it is mutual
Vertically；The other end of two connecting rods upon connection is sleeved in the rotation axis；One end of rocker arm is also sleeved on the rotation
On axis；The other end of the rocker arm is set with and is fixed on one end of the concussion axis of support testpieces.
2. Airfoil dynamic experiment amplitude as described in claim 1 angle regulating mechanism, which is characterized in that the crank includes screw thread
Bar, rotary body, sliding block and sliding block pressing plate；The rotary body is sleeved on the motor shaft of driving motor, enable the rotary body with
The motor shaft is center of rotation rotation；It is respectively fixed with end cap at the both ends of the rotary body, the both ends of the threaded rod are pacified respectively
In the centre bore of the end cap；The slide block set of square-outside and round-inside is on the threaded rod；One side surface of the sliding block has
The collar shank of protrusion, and make to be rotatably assorted between the collar shank and lantern ring；Strip is laid in the upper surface of the sliding block
Sliding block pressing plate, so that the sliding block pressing plate is pressed on the upper surface of the sliding block by screw.
3. Airfoil dynamic experiment amplitude as claimed in claim 2 angle regulating mechanism, which is characterized in that a rotating body has edge should
The square cavity that rotary body length direction extends；There is the groove for placing sliding block pressing plate at the top of the square cavity；Described
The screw hole of multiple perforation rotor cases is provided on groove；There is convex block in the side surface of a long side of the rotary body, this is convex
There is the threaded hole for connecting motor shaft at the center of block；The threaded hole and square cavity penetrate through, and make the center of the threaded hole
The geometric center lines of line and the square cavity length direction are mutually perpendicular to；In another length of the rotary body symmetrical with convex block
The side surface on side is provided with the aperture of bar shaped, which is the slideway of the collar shank on sliding block；The effective of collar shank slideway can
Movable length is 0~36mm.
4. Airfoil dynamic experiment amplitude as claimed in claim 2 angle regulating mechanism, which is characterized in that the shape of the sliding block is side
Shape, and make clearance fit between the sliding block and the square cavity of rotary body；There is the spiral shell with shaft at the center of the sliding block
Pit；There is the collar shank of protrusion in one side surface of the sliding block.
5. Airfoil dynamic experiment amplitude as described in claim 1 angle regulating mechanism, which is characterized in that weld one end of the connecting rod
There is lantern ring, the axis of the lantern ring centre bore is vertical with the axial space of the connecting rod；The internal diameter of the lantern ring, which is slightly larger than, is matched
The outer diameter of collar shank, rotates each lantern ring between the rotation axis or collar shank respectively on the outer diameter or sliding block of the rotation axis of conjunction
Cooperation；There is tapped blind hole at the center of the connecting rod the other end face, which is matched with length adjustment screw rod by screw thread
It closes；The length of the connecting rod is 980mm.
6. Airfoil dynamic experiment amplitude as described in claim 1 angle regulating mechanism, which is characterized in that the length adjustment screw rod
Both ends are oppositely oriented external screw thread；There are the boss of six sides, the spiral shell in the boss two sides in the middle part of the length adjustment screw rod
Clamp nut is respectively installed on rasp bar.
7. Airfoil dynamic experiment amplitude as described in claim 1 angle regulating mechanism, which is characterized in that the both ends of the rocker arm have
Through-hole, and the through-hole of one end is rotatably assorted with rotation axis；The through-hole of the other end and concussion axis cooperation, and pass through screws tighten；
The center line of rocker arm both ends through-hole is parallel to each other；The center of rocker arm both ends through-hole is away from for 210mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821590491.XU CN209014243U (en) | 2018-09-28 | 2018-09-28 | Airfoil dynamic experiment amplitude angle regulating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821590491.XU CN209014243U (en) | 2018-09-28 | 2018-09-28 | Airfoil dynamic experiment amplitude angle regulating mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209014243U true CN209014243U (en) | 2019-06-21 |
Family
ID=66834822
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821590491.XU Expired - Fee Related CN209014243U (en) | 2018-09-28 | 2018-09-28 | Airfoil dynamic experiment amplitude angle regulating mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209014243U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109029902A (en) * | 2018-09-28 | 2018-12-18 | 西北工业大学 | Continous way transonic wind tunnel Airfoil dynamic experiment amplitude angle regulating mechanism |
-
2018
- 2018-09-28 CN CN201821590491.XU patent/CN209014243U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109029902A (en) * | 2018-09-28 | 2018-12-18 | 西北工业大学 | Continous way transonic wind tunnel Airfoil dynamic experiment amplitude angle regulating mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103852235B (en) | Continuous wind tunnel aerofoil profile dynamic characteristics tester structure | |
| CN103434637A (en) | Novel aerofoil by utilizing magnus effect | |
| CN109029903A (en) | Continous way transonic wind tunnel Airfoil dynamic experiment mean angle of attack regulating mechanism | |
| CN106347661B (en) | It is a kind of that rotor craft and production method are flutterred based on the miniature of voice coil motor driving | |
| CN109612681A (en) | A kind of aerodynamic interference measurement method of the coaxial rigid rotor model of helicopter | |
| CN106379532A (en) | Flapping-wing flapping angle changing mechanism | |
| CN113267315A (en) | Low-speed wind tunnel direct-drive gust generating device | |
| CN109305331A (en) | It is a kind of with the quadrotor drone that can stack undercarriage | |
| CN109000521A (en) | Rudder wingfold device, micro missile and rudder wingfold method | |
| CN209014243U (en) | Airfoil dynamic experiment amplitude angle regulating mechanism | |
| CN103991540B (en) | A kind of taper rotary flapping wing aircraft | |
| CN109029902A (en) | Continous way transonic wind tunnel Airfoil dynamic experiment amplitude angle regulating mechanism | |
| CN104002968B (en) | A kind of small taper rotary flapping wing aircraft | |
| CN209014244U (en) | A kind of mean angle of attack regulating mechanism of Airfoil dynamic experiment | |
| CN106347657B (en) | A kind of unmanned plane and its working method for geography information exploration | |
| CN2876753Y (en) | Fatique-tester for vertical hinge bearing of rotary swing of helicopter | |
| CN100422711C (en) | Apparatus for fatigue test of horizontal hinge bearing of helicopter | |
| CN107963210A (en) | A kind of fixed wing aircraft of VTOL | |
| CN107826245A (en) | A kind of cross flow fan swing device | |
| CN203864996U (en) | Tapered rotating flapping wing air vehicle | |
| CN207000818U (en) | A kind of VTOL fixed wing aircraft of oil electricity mixing | |
| CN106697273B (en) | Multi-angle adjustable flying robot and working method thereof | |
| CN206068153U (en) | For the unmanned plane of geography information exploration | |
| CN103991546B (en) | A kind of rotary flapping wing thrust generating apparatus | |
| CN103991548B (en) | A kind of rotary flapping wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190621 Termination date: 20210928 |