CN202041365U - Support frame for wind tunnel test model - Google Patents
Support frame for wind tunnel test model Download PDFInfo
- Publication number
- CN202041365U CN202041365U CN2011201394892U CN201120139489U CN202041365U CN 202041365 U CN202041365 U CN 202041365U CN 2011201394892 U CN2011201394892 U CN 2011201394892U CN 201120139489 U CN201120139489 U CN 201120139489U CN 202041365 U CN202041365 U CN 202041365U
- Authority
- CN
- China
- Prior art keywords
- model
- wind tunnel
- flange
- wind
- tunnel
- 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 - Lifetime
Links
Images
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model relates to a support frame for a wind tunnel test model. The upper junction surface and the lower junction surface of a force balance are respectively connected with a support beam top plate and a force platform. Two variable-attack angle mechanisms are respectively arranged at the top ends of support pillars respectively located at the outer sides of the two side walls of the middle part of a wind tunnel test section. The side wall of a wind tunnel at an equal altitude with the centre lines of flange spline shafts of the variable-attack angle mechanisms is symmetrically provided with via holes of the flange spline shafts; one ends of the flange spline shafts are located in the wind tunnel after passing through the via holes on the side wall of the wind tunnel, and the other ends of the flange spline shafts are connected with the variable-attack angle mechanisms outside the wind tunnel. Two variable-sideslip angle mechanisms are located in the wind tunnel and are fixed on flange plates at the end faces of the flange spline shafts located in the wind tunnel through sliding plates. Sliding flanges of the two variable-sideslip angle mechanisms are connected with the wingtips of an airplane model through model connecting pieces. The support frame for the wind tunnel test model is suitable for airplane air-drop airborne wind tunnel drop tests and fuselage, high lift device and afterbody drag wind tunnel tests. The support frame for the wind tunnel test model has the characteristics of simple structure, convenience in use and reliable test data.
Description
Technical field
The present invention relates to aircraft surface experimental technique fields such as aircraft, is the indispensable equipment that carries out the meticulous measurement of aircraft resistance, the mobile noiseless simulation of aircraft surface, the airborne wind-tunnel drop-test of airplane air dropping.
Background technology
Technology related to the present invention is that abdominal support, back support, the afterbody of model in wind tunnel supports and messenger wire (bracing cable) supports measuring system.When carrying out the meticulous measurement of aircraft drag, the airborne wind-tunnel drop-test of air-drop, airframe, high lift device, afterbody drag wind-tunnel investigation, mobile most important around fuselage, wing (band high lift device) inner segment and empennage, but above-mentioned model supporting way all can disturb the mobile generation of these parts, thereby influences the reliability of test findings; When particularly carrying out the airborne wind-tunnel drop-test research of airplane air dropping, above-mentioned support also can tangle model or have a strong impact on the drop from the air movement locus of object model of air-drop.
In Jap.P. JP09203685A, the model supporting mechanism of model test of Vibration in a kind of wind-tunnel is disclosed, test model is placed on the wind-tunnel middle part perpendicular to flow level, and two wing tips of model are connected on two axles of model supporting mechanism.Two axles of model supporting mechanism stretch out outside the hole from the cinclides of wind-tunnel both sides, one of them is free to rotate and move up and down with bearings, another axle is supported on former and later two actuators, but the twisting vibration of actuator aggregate motion implementation model and upper and lower translation vibration.But this supporting mechanism can not the implementation model angle of attack and the variation of yaw angle, and can not directly measure six aerodynamic force components that act on the model.
Summary of the invention
For overcome exist in the prior art or the mobile generation of air-flow disturbed, thereby influence the reliability of test findings, perhaps can not the implementation model angle of attack and the variation of yaw angle, and can not directly measure the deficiency that acts on six aerodynamic force components on the model, the present invention proposes a kind of model in wind tunnel bracing frame.
The present invention includes force balance, power platform, brace summer, two support posts, change angle of attack mechanism, change yaw angle mechanism and model web members, wherein:
Force balance is positioned at brace summer, and the last joint face of this force balance is connected with the lower surface of brace summer top board, and the following joint face of this force balance is connected with the upper surface of power platform.The power platform moves along the direction identical with air-flow by steamboat.Two support posts lay respectively at the outside, two side, test chamber middle part, and are fixed on the two ends of brace summer.Two become the top that angle of attack mechanism is installed in support post respectively.With the wind tunnel side wall of the flange splined shaft center line equal-height position that becomes angle of attack mechanism on the via hole that has the flange splined shaft of symmetry, the via hole that one end of flange splined shaft passes on the wind tunnel side wall is positioned at wind-tunnel, and the other end of flange splined shaft is connected with wind-tunnel change angle of attack mechanism outward.Two change yaw angle mechanisms are positioned at wind-tunnel, are fixed on by slide plate on the ring flange of the flange splined shaft end face that is positioned at wind-tunnel.Two slip flanges that become yaw angle mechanism link to each other with the wing tip of model aircraft by the model web member.
Described change yaw angle mechanism comprises slide plate and slip flange.The pilot hole when being distributed with model aircraft difference yaw angle on the described slide plate and the connecting hole of flange splined shaft.Described slip flange is made up of positioning disk and moment adjusting lever, is being evenly equipped with the hole that cooperates with pilot hole on the slide plate on the card of slip flange positioning disk, and the moment adjusting lever is fixed on the side panel face of slip flange positioning disk.There is the installed surface of model web member the end of moment adjusting lever.
One end of described model web member is useful on the pin shaft hole of coupling torque adjusting lever, and the other end of model web member has the U-shaped clip slot, and the connecting hole of model aircraft is arranged on described U-shaped clip slot wallboard.U-shaped clip slot on the model web member has the inclination angle, and this inclination angle is consistent with the inclination angle of model aircraft wing tip.
Four jiaos of described power platform floor all have gathering sill, are used for cooperating with ground guidepost.Steamboat is positioned at the lower surface of four jiaos of base plates.Top board is used to install force balance.
There is the installing plate of support post at the two ends of described brace summer.The brace summer top board is positioned at brace summer upper surface center.
Use when of the present invention, by power platform, force balance, brace summer, two support posts, change angle of attack mechanism, change yaw angle mechanism, model web member model aircraft is supported in the wind-tunnel, the aerodynamic force that air-flow affacts on the model aircraft in the wind-tunnel can be measured with the force balance the hole outside, the preceding more accurate measurement of simple component resistance balance of platform of can also exerting oneself of the suffered resistance of model aircraft; Become angle of attack mechanism and become yaw angle mechanism and realize aspect, the i.e. variation of the angle of attack and yaw angle.When carrying out the airborne wind-tunnel drop-test of airplane air dropping, in the model aircraft of hollow, launch the airborne object model of air-drop with throwing mechanism, and with the movement locus of the airborne object model of camera record air-drop.
The present invention has been put into main support measurement component outside the wind-tunnel, the support that back support commonly used, abdominal support and afterbody support when having avoided wind tunnel test disturbs, and can be according to the yaw angle of testing requirements, the pilot hole of corresponding yaw angle is corresponding on slip flange and the slide plate, has realized the adjustment of yaw angle.Use the present invention, near the no any model of model aircraft fuselage, wing (comprising high lift device) inner segment and empennage is supported disturb, efficiently solve supporting mechanism, improved the reliability of test figure the disturbance that air-flow produces.The present invention is suitable for the airborne wind-tunnel drop-test of airplane air dropping, airframe, high lift device, afterbody drag wind tunnel test; The measuring system that supports this wind tunnel test wing tip model both can realize the airplane air dropping wind-tunnel drop-test of drop from the air, and the aerodynamic characteristics that can drop from the air to airplane air dropping easily be studied again, and both can carry out synchronously.
Description of drawings
Accompanying drawing 1 is the structural representation of model in wind tunnel bracing frame, and wherein a is a side view, and b is a front view;
Accompanying drawing 2 is power platform synoptic diagram, and wherein a is a front view, and b is a vertical view, and c is that A is to view;
Accompanying drawing 3 is brace summer synoptic diagram, and wherein a is a front view, and b is a vertical view;
Accompanying drawing 4 is support post structural representations, and wherein a is a front view, and b is a side view;
Accompanying drawing 5 is to become the yaw angle structural scheme of mechanism, and wherein a is a vertical view, and b is that A is to partial view;
Accompanying drawing 6 is model web member structural representations, and wherein a is a vertical view, and b is a side view;
Accompanying drawing 7 is skateboard synoptic diagram, and wherein a is a front view, and b is a side view;
Accompanying drawing 8 is slip flange structural representations, and wherein a is a side view, and b is a front view, and c is a vertical view.Wherein,
1. force balance 2. brace summers 3. support posts 4. become angle of attack mechanism 5. flange splined shafts
6. become yaw angle mechanism 7. model web members, 8. model aircrafts, 9. wind-tunnel, 10. resistance balances
11. power platform 12. motors 13. speed reduction units 14. gear pairs 15. worm screws
16. turbine 17. worm shaft bearings 18. worm bearings 19. female splined shafts 20. turbine bearings
21. turboshaft bearing 22. slide plates 23. slip flanges 24. bearing pins 25. screws
26. steamboat 27. steamboat pressing plates 28. gathering sills
Embodiment
Present embodiment is a kind of model in wind tunnel bracing frame.Present embodiment both can be used for the aerodynamic force that the survey aircraft model is subjected in wind-tunnel, also can launch the airborne object model of air-drop with throwing mechanism in the model aircraft of hollow, and drop the movement locus of airborne object model with camera record.
Present embodiment comprises force balance 1, simple component resistance balance 10, power platform 11, brace summer 2, support post 3, becomes angle of attack mechanism 4, becomes yaw angle mechanism 6 and model web member 7.Becoming angle of attack mechanism 4 is made up of motor 12, speed reduction unit 13, gear pair 14, worm screw 15, turbine 16, female splined shaft 19, turbine bearing 20, turboshaft bearing 21, flange splined shaft 5, worm bearing 18, worm shaft bearing 17 and some screws; Becoming yaw angle mechanism 6 is made up of slide plate 22, slip flange 23, bearing pin 24 and some screws 25.
Brace summer 2 is the steel design part, be a rectangle frame structure below, go up and be another rectangle frame, respectively there is the rectangle frame connection up and down of 3 short columns front and back, and be added with oblique reinforcement, there is a top board at the middle part on the last rectangle frame, one installing plate is each side arranged, the center has 16 around the uniform through hole in center on the top board of middle part, its position, size are corresponding with 16 through holes of force balance 1 upper surface, 4 threaded holes uniform around the center are arranged on two installing plates, corresponding with 4 through holes below the support post 3 respectively.Brace summer 2 be anchored to measure on the balance 1 and and balance top with 16 screw retention.Two support posts 3 are the steel design part, and 4 through holes uniform around the center are all arranged below, and its position and size are corresponding with 4 threaded holes of both sides installing plate above the brace summer 2.Supporting upright support 3 tops has the turboshaft bearing 21 that change angle of attack mechanism 4 is installed, and the upper outside face is processed with the screw hole that motor 12, speed reduction unit 13, gear pair 14, worm screw 15 are installed.
Become angle of attack mechanism 4 and adopt prior art, drive female splined shaft 19 by motor 12, speed reduction unit 13, gear pair 14, worm screw 15, turbine 16 and form.Turbine 16 is installed in female splined shaft 19 outer ends, and female splined shaft 19 is supported on the support post 3 by turbine bearing 20, turboshaft bearing 21.Flange splined shaft 5 is the combination that is threaded the flange and a splined shaft in hole, and the splined hole of its splined shaft and female splined shaft 19 forms little clearance fit, and the flange threaded hole is corresponding with number with the step through-hole position at slide plate 22 middle parts.Flange splined shaft 5 passes wind-tunnel 9 areoles in the wind-tunnel 9 and inserts female splined shaft 19, leaves the gap and seal with soft materials such as sponges between flange splined shaft 5 and wind-tunnel 9 areoles, and flange splined shaft 5 passes the aperture of the diameter of axle of hole wall less than wind tunnel side wall.The top, side that worm bearing 18 and the worm shaft bearing 17 of worm screw 15 through two ends is installed in support post 3 and and turbine 16 cooperations, a gear in the end mounting teeth wheel set 14 of worm screw 15, another gear in the gear pair 14 is installed on the output shaft of reducer casing 13, two gearing mesh.Motor 12 and reducer casing 13 also are installed in support post 3 sides, be positioned at worm screw 15 below.
The critical part that becomes yaw angle mechanism 6 is slide plate 22, slip flange 23 and bearing pin 24.But slide plate 22 middle parts have and the corresponding sunk screw step through-hole of the ring flange threaded hole of flange splined shaft 5, be processed with the threaded hole that is connected with the flange 23 that slides (accompanying drawing 5 only provides crab angle and is-10 ° ,-6 °, 0 °, 6 °, 10 ° threaded hole, can increase and decrease as required) corresponding to different yaw angles thereon.Slip flange 23 is welded to form by the flange that has through hole and a tilting cylinder, processes platform up and down in the termination of cylinder, and perpendicular to platform and cylinder axis pin hole processing, pin-and-hole and bearing pin 24 form little clearance fit.Model web member 7 is the part of crooking one's arm, one end is processed with the through hole that forms little clearance fit with bearing pin 24, one end is " U " clevis groove that two wallboards are formed, and is processed with 6 through holes perpendicular to " U " clevis groove two wallboards, and 6 through holes are corresponding with 6 through holes of model aircraft 8 wing tip portions.Bearing pin 24 diameters are slightly less than the pin-and-hole aperture of slip flange 23 and model web member 7.Model aircraft 8 wing tips are processed into flat board, processing and model web member 7 corresponding 6 through holes on the flat board, and the wing tip flat board can be inserted into " U " clevis groove of model web member 7.
When using present embodiment, by power platform 11, force balance 1, brace summer 2, two support posts 3, change angle of attack mechanism 4, change yaw angle mechanism 6, model web member 7 model aircraft 8 is supported in the wind-tunnel 9, the aerodynamic force that air-flow affacts on the model aircraft 8 in the wind-tunnel can be measured with the force balance the hole outside 1, the preceding simple component resistance balance 10 more accurate measurements (accompanying drawing 1) of platform 11 of can also exerting oneself of model aircraft 8 suffered resistances; Become angle of attack mechanism 4 and become the variation that yaw angle mechanism 6 (accompanying drawings 5) are realized aspect (angle of attack and yaw angle); When carrying out the airborne wind-tunnel drop-test of airplane air dropping, in the model aircraft 8 of hollow, launch the airborne object model of air-drop with throwing mechanism, and with the movement locus of the airborne object model of camera record air-drop.
Power platform 11 is supported on the floor by four steamboats 26, gathering sill 28 block be contained in ground totally 12 guideposts in case power platform 11 only with the wind hole axis move forward and backward.In the race of the power that the is installed in platform 11 of steamboat 26, make steamboat 26 expose anchorage force platform 11 and it can be moved forward and backward from power platform 11 lower surfaces from top compressing with steamboat pressing plate 27; Unclamp steamboat pressing plate 27 steamboats and regain, power platform 11 falls earthward and can not move.Resistance balance 10 is loaded on power platform 11 dead aheads, and linking to each other with the ground point of fixity in power platform 11 dead aheads is used for measuring more accurately the resistance component.Force balance 1 for 16 screw retention to the upper mounting plate of power platform 11, be used to measure the aerodynamic force that acts on the model aircraft 8; Force balance 1 can lockedly only be the part of support component when carrying out the airborne drop-test research of airplane air dropping; Brace summer 2 is installed on the force balance 1, and upper surface of rectangle frame middle part top board lower surface and force balance 1 cooperates on it, and 16 through hole correspondences are also used bolt.Two support posts 3 are installed on the installing plate at rectangle frame two ends on the brace summer 2, and 4 through holes below it are corresponding with 4 threaded holes on the installing plate of two ends and be screwed, and stand on the outer both sides of wind-tunnel 9 sidewalls.The turbine bearing 20 that becomes angle of attack mechanism 4 is installed in the turboshaft bearing 21 at the top of two support posts 3, and female splined shaft 19 is loaded on the turbine bearing 20.
The motor 12, speed reduction unit 13, gear pair 14, worm screw 15, the turbine 16 that become angle of attack mechanism 4 are installed in support post 3 upper side.Turbine 16 is installed in female splined shaft 19 outer ends.Flange splined shaft 5 passes in the wind-tunnel 9 in the splined hole that wind-tunnel 9 areoles insert female splined shaft 19 and realizes connecting inside and outside the hole, between flange splined shaft 5 and wind-tunnel 9 areoles, leave the gap and with soft materials such as sponge sealings, flange splined shaft 5 passes the aperture of the diameter of axle of hole wall less than wind-tunnel 9 sidewalls.The top, side that worm bearing 18 and the worm shaft bearing 17 of worm screw 15 through two ends is installed in support post 3 and and turbine 16 cooperations, a gear in the end mounting teeth wheel set 14 of worm screw 15, another gear in the gear pair 14 is installed on the output shaft of reducer casing 13, two gearing mesh.Motor 12 and reducer casing 13 also are installed in support post 3 sides, be positioned at worm screw 15 below.Motor 12 drives female splined shaft 19 by speed reduction unit 13, gear pair 14, worm screw 15, turbine 16 and flange splined shaft 5 rotates and final model aircraft 8 angle of attack variation that realize.
But the ring flange threaded hole of flange splined shaft 5 is corresponding with the sunk screw through hole at slide plate 22 middle parts that become yaw angle mechanism 6, and with 6 screw retention.According to the yaw angle of testing requirements, one group of threaded hole of corresponding yaw angle (10 ° ,-6 °, 0 °, 6 °, 10 °) is corresponding and be screwed on the through hole of slip flange 23 flanges and the slide plate 22.The end overlap joint that the platform of a tilting cylinder termination of slide plate 22 and model web member 7 have through hole, the through hole alignment of the through hole of platform and model web member 7, and connect with bearing pin 24, tighten with nut bearing pin 24 terminations, and slide plate 22 and model web member 7 can rotate mutually.The dull and stereotyped insertion of model aircraft 8 wing tips model web member 7 one ends two wallboards are formed " U " the clevis groove, with 6 bolts model aircraft 8 wing tips flat board is connected with model web member 7.Change requirement according to the test yaw angle, slip flange 23 an end on the slide plate 22 forward, an end moves the screw hole correspondence of corresponding yaw angle on flange through hole and slide plate 22 backward, can realize the yaw angles variation with screw 25 with slide plate 22 and slip flange 23 are fixing.When adjusting model aircraft 8 yaw angles, unclamp bearing pin 24 nuts, slip flange 23 can rotate around bearing pin 24 with model web member 7, and pin diameter is slightly less than the pin-and-hole aperture of slip flange 23 and model web member 7, adjusts yaw angle rear pin shaft end and locks with nut.The relative position relation of having represented slide plate 22 when yaw angle is respectively-10 °, 0 °, 10 °, slip flange 23 and model web member 7 in the accompanying drawing 5 (a).
Claims (5)
1. model in wind tunnel bracing frame, comprise force balance (1), power platform (11), brace summer (2), two support posts (3), become angle of attack mechanism (4), become yaw angle mechanism (6) and model web member (7), it is characterized in that, force balance (1) is positioned at brace summer (2), and the last joint face of this force balance (1) is connected with the lower surface of brace summer (2) top board, and the following joint face of this force balance (1) is connected with the upper surface of power platform (11); Power platform (11) moves along the direction identical with air-flow by steamboat (26); Two support posts (3) lay respectively at the outside, two side, wind-tunnel (9) test section middle part, and are fixed on the two ends of brace summer (2); Two become the top that angle of attack mechanism (4) is installed in support post (3) respectively; With the wind tunnel side wall of flange splined shaft (5) the center line equal-height position that becomes angle of attack mechanism (4) on the via hole that has flange splined shaft (5) of symmetry, the via hole that one end of flange splined shaft (5) passes on the wind tunnel side wall is positioned at wind-tunnel (9), and the other end of flange splined shaft (5) is connected with wind-tunnel (9) change angle of attack mechanism (4) outward; Two change yaw angle mechanisms (6) are positioned at wind-tunnel (9), are fixed on by slide plate (22) on the ring flange of flange splined shaft (5) end face that is positioned at wind-tunnel (9); Two slip flanges (23) that become yaw angle mechanism (6) link to each other with the wing tip of model aircraft (8) by model web member (7).
2. model in wind tunnel bracing frame according to claim 1 is characterized in that, becomes yaw angle mechanism (6) and comprises slide plate (22) and slip flange (23); The pilot hole when being distributed with the different yaw angle of model aircraft (8) on the described slide plate (22) and the connecting hole of flange splined shaft (5); Described slip flange (23) is made up of positioning disk and moment adjusting lever, is being evenly equipped with the hole that cooperates with pilot hole on the slide plate (22) on the card of slip flange (23) positioning disk, and the moment adjusting lever is fixed on the side panel face of slip flange (23) positioning disk; There is the installed surface of model web member (7) end of moment adjusting lever.
3. model in wind tunnel bracing frame according to claim 1, it is characterized in that, one end of model web member (7) is useful on the pin shaft hole of coupling torque adjusting lever, and the other end of model web member (7) has the U-shaped clip slot, and the connecting hole of model aircraft (8) is arranged on described U-shaped clip slot wallboard; U-shaped clip slot on the model web member (7) has the inclination angle, and this inclination angle is consistent with the inclination angle of model aircraft (8) wing tip.
4. model in wind tunnel bracing frame according to claim 1 is characterized in that four jiaos of power platform (11) base plate all have gathering sill (28), are used for cooperating with ground guidepost; Steamboat (26) is positioned at the lower surface of four jiaos of base plates; Top board is used to install force balance (1).
5. model in wind tunnel bracing frame according to claim 1 is characterized in that there is the installing plate of support post (3) at the two ends of brace summer (2); Brace summer (2) top board is positioned at brace summer (2) upper surface center.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201394892U CN202041365U (en) | 2011-05-05 | 2011-05-05 | Support frame for wind tunnel test model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201394892U CN202041365U (en) | 2011-05-05 | 2011-05-05 | Support frame for wind tunnel test model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202041365U true CN202041365U (en) | 2011-11-16 |
Family
ID=44968803
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201394892U Expired - Lifetime CN202041365U (en) | 2011-05-05 | 2011-05-05 | Support frame for wind tunnel test model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202041365U (en) |
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN102494866A (en) * | 2011-12-13 | 2012-06-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Framework-type support component for wind tunnel test model |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
| 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 |
| CN103076152A (en) * | 2012-12-31 | 2013-05-01 | 中国人民解放军国防科学技术大学 | Gesture adjusting device for model with four degrees of freedom for hypersonic speed pulse wind tunnel |
| CN103115746A (en) * | 2013-01-21 | 2013-05-22 | 中国科学院力学研究所 | Shock tunnel module support device |
| CN103852237A (en) * | 2014-03-24 | 2014-06-11 | 西北工业大学 | Supporting and protecting device for high-speed wind tunnel plasma flow control experiment |
| CN103852238A (en) * | 2014-03-24 | 2014-06-11 | 西北工业大学 | Wind tunnel test section aerofoil rapid mounting device |
| CN104019959A (en) * | 2014-05-30 | 2014-09-03 | 西南交通大学 | Variable attack angel apparatus for wind tunnel test of aircraft engine model |
| CN104809943A (en) * | 2015-05-18 | 2015-07-29 | 中国人民解放军海军工程大学 | Wing lift and drag experimental device |
| CN104819822A (en) * | 2015-04-20 | 2015-08-05 | 中国科学院力学研究所 | Support system of hypersonic propulsion wind tunnel model |
| CN104931228A (en) * | 2015-06-26 | 2015-09-23 | 空气动力学国家重点实验室 | Double-body super-high aspect ratio aircraft wind tunnel force measurement test supporting device |
| CN105571812A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Universal rectifying device for low-speed flutter model |
| CN105716827A (en) * | 2014-12-03 | 2016-06-29 | 中航通飞研究院有限公司 | Amphibious aircraft blown flap wind tunnel test model |
| CN108132132A (en) * | 2017-12-22 | 2018-06-08 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of High Speed Train Models wind tunnel test standard roadbed |
| CN109916589A (en) * | 2019-03-27 | 2019-06-21 | 西北工业大学 | Pressure variation characteristic test method in a kind of carrier large sized object air-drop cabin |
| CN109974963A (en) * | 2019-04-16 | 2019-07-05 | 山东交通学院 | A kind of sailing boat wind tunnel experiment device |
| CN110261575A (en) * | 2019-05-24 | 2019-09-20 | 中国石油大学(北京) | For simulating the experimental rig and method of multilayer reason rock sample |
| CN110514385A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of undercarriage aerodynamic noise test support device |
| CN111307400A (en) * | 2020-03-31 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Back support device for wind tunnel ground effect test |
| CN112345195A (en) * | 2020-11-17 | 2021-02-09 | 中国航天空气动力技术研究院 | Test device for high-speed wind tunnel ultra-large attack angle multi-frequency compound motion |
| CN113358320A (en) * | 2021-08-10 | 2021-09-07 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring force of interference of jet flow of upstream air for high-speed wind tunnel |
| CN114935441A (en) * | 2022-05-13 | 2022-08-23 | 中国空气动力研究与发展中心超高速空气动力研究所 | Model supporting device connected to quick release device and capable of changing attack angle and sideslip angle |
| CN117740312A (en) * | 2024-02-21 | 2024-03-22 | 中国空气动力研究与发展中心空天技术研究所 | Detachable reference suspension system suitable for high-speed wind tunnel large-scale heavy model test |
-
2011
- 2011-05-05 CN CN2011201394892U patent/CN202041365U/en not_active Expired - Lifetime
Cited By (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288381B (en) * | 2011-05-05 | 2013-04-17 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN102494866A (en) * | 2011-12-13 | 2012-06-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Framework-type support component for wind tunnel test model |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
| CN102818692B (en) * | 2012-08-17 | 2015-04-22 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
| 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 |
| CN103076152B (en) * | 2012-12-31 | 2015-04-15 | 中国人民解放军国防科学技术大学 | Gesture adjusting device for model with four degrees of freedom for hypersonic speed pulse wind tunnel |
| CN103076152A (en) * | 2012-12-31 | 2013-05-01 | 中国人民解放军国防科学技术大学 | Gesture adjusting device for model with four degrees of freedom for hypersonic speed pulse wind tunnel |
| CN103115746A (en) * | 2013-01-21 | 2013-05-22 | 中国科学院力学研究所 | Shock tunnel module support device |
| CN103852238A (en) * | 2014-03-24 | 2014-06-11 | 西北工业大学 | Wind tunnel test section aerofoil rapid mounting device |
| CN103852237A (en) * | 2014-03-24 | 2014-06-11 | 西北工业大学 | Supporting and protecting device for high-speed wind tunnel plasma flow control experiment |
| CN103852237B (en) * | 2014-03-24 | 2016-03-30 | 西北工业大学 | For the support protecting appts of high-speed wind tunnel plasma flow control experiment |
| CN104019959A (en) * | 2014-05-30 | 2014-09-03 | 西南交通大学 | Variable attack angel apparatus for wind tunnel test of aircraft engine model |
| CN104019959B (en) * | 2014-05-30 | 2016-08-17 | 西南交通大学 | A kind of aircraft engine model wind tunnel test attack angle changing device |
| CN105571812A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Universal rectifying device for low-speed flutter model |
| CN105571812B (en) * | 2014-10-11 | 2017-12-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general fairing of low-speed flutter model |
| CN105716827A (en) * | 2014-12-03 | 2016-06-29 | 中航通飞研究院有限公司 | Amphibious aircraft blown flap wind tunnel test model |
| CN105716827B (en) * | 2014-12-03 | 2018-04-24 | 中航通飞研究院有限公司 | Amphibious aircraft blown flap model in wind tunnel |
| CN104819822A (en) * | 2015-04-20 | 2015-08-05 | 中国科学院力学研究所 | Support system of hypersonic propulsion wind tunnel model |
| CN104809943A (en) * | 2015-05-18 | 2015-07-29 | 中国人民解放军海军工程大学 | Wing lift and drag experimental device |
| CN104931228B (en) * | 2015-06-26 | 2017-07-07 | 空气动力学国家重点实验室 | A kind of super high-aspect-ratio aircraft force test in wind tunnel support meanss of binary |
| CN104931228A (en) * | 2015-06-26 | 2015-09-23 | 空气动力学国家重点实验室 | Double-body super-high aspect ratio aircraft wind tunnel force measurement test supporting device |
| CN108132132A (en) * | 2017-12-22 | 2018-06-08 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of High Speed Train Models wind tunnel test standard roadbed |
| CN109916589A (en) * | 2019-03-27 | 2019-06-21 | 西北工业大学 | Pressure variation characteristic test method in a kind of carrier large sized object air-drop cabin |
| CN109974963B (en) * | 2019-04-16 | 2024-01-26 | 山东交通学院 | Sailing boat wind tunnel experimental device |
| CN109974963A (en) * | 2019-04-16 | 2019-07-05 | 山东交通学院 | A kind of sailing boat wind tunnel experiment device |
| CN110261575A (en) * | 2019-05-24 | 2019-09-20 | 中国石油大学(北京) | For simulating the experimental rig and method of multilayer reason rock sample |
| CN110514385A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of undercarriage aerodynamic noise test support device |
| CN111307400A (en) * | 2020-03-31 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Back support device for wind tunnel ground effect test |
| CN112345195A (en) * | 2020-11-17 | 2021-02-09 | 中国航天空气动力技术研究院 | Test device for high-speed wind tunnel ultra-large attack angle multi-frequency compound motion |
| CN113358320A (en) * | 2021-08-10 | 2021-09-07 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring force of interference of jet flow of upstream air for high-speed wind tunnel |
| CN114935441A (en) * | 2022-05-13 | 2022-08-23 | 中国空气动力研究与发展中心超高速空气动力研究所 | Model supporting device connected to quick release device and capable of changing attack angle and sideslip angle |
| CN114935441B (en) * | 2022-05-13 | 2023-04-25 | 中国空气动力研究与发展中心超高速空气动力研究所 | Model supporting device with changeable attack angle and sideslip angle connected with quick throwing device |
| CN117740312A (en) * | 2024-02-21 | 2024-03-22 | 中国空气动力研究与发展中心空天技术研究所 | Detachable reference suspension system suitable for high-speed wind tunnel large-scale heavy model test |
| CN117740312B (en) * | 2024-02-21 | 2024-05-07 | 中国空气动力研究与发展中心空天技术研究所 | Detachable reference suspension system suitable for high-speed wind tunnel large-scale heavy model test |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202041365U (en) | Support frame for wind tunnel test model | |
| CN102288381B (en) | Wing tip support device for wind tunnel test | |
| CN109612681B (en) | Aerodynamic interference measurement method of coaxial rigid rotor model of helicopter | |
| KR101171608B1 (en) | Apparatus and method for testng rotation of helicopter rotor system | |
| KR20090039563A (en) | Helicopter tail rotor test rig | |
| CN111623951B (en) | Wind tunnel model multi-attitude coupling real-time force measuring device and test method | |
| CN112014058B (en) | Wind tunnel force measurement test device for laminar flow airfoil with high lift-drag ratio and test method thereof | |
| CN214502834U (en) | Unmanned aerial vehicle power test device | |
| CN208795498U (en) | A kind of dynamic attitude-simulating turntable for the test of large scale equipment ground performance | |
| CN102937509A (en) | Comprehensive testing platform of propelling system | |
| CN113720612A (en) | Automatic miniature aviation test bed of adjustment | |
| CN110001328B (en) | Spacecraft simulation device | |
| CN114216688B (en) | Miniature turbine engine thrust measuring device and application method thereof | |
| CN113815513B (en) | Aerodynamic coupling test system for paddle wing of vehicle-mounted variable incidence angle aircraft | |
| Tomin et al. | Design, construction and testing of a 3-component force balance for educational wind tunnels in undergraduate aerodynamics | |
| CN114166496B (en) | Tilt rotor wing test device | |
| CN203615921U (en) | System for measuring control angle of helicopter tail rotor | |
| CN115855432A (en) | Distributed ducted fan combination testing device and testing method | |
| CN212501114U (en) | Unmanned aerial vehicle multi freedom attitude test system | |
| McCluer et al. | Full-span tiltrotor aeroacoustic model (FS TRAM) overview and initial testing | |
| CN115754710A (en) | Coaxial motor testing mechanism and brushless motor | |
| CN215098349U (en) | Ground bench test device for tilt rotor unmanned aerial vehicle | |
| CN112109920A (en) | Unmanned aerial vehicle multi freedom attitude test system | |
| CN209264241U (en) | For improving the device of the thrust test accuracy of ducted fan | |
| RU2681251C1 (en) | Hinge moment of the rejected surface measurement device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20111116 Effective date of abandoning: 20130417 |
|
| RGAV | Abandon patent right to avoid regrant |