CN109297668B - Control surface clearance wind tunnel test simulation device - Google Patents
Control surface clearance wind tunnel test simulation device Download PDFInfo
- Publication number
- CN109297668B CN109297668B CN201811279446.7A CN201811279446A CN109297668B CN 109297668 B CN109297668 B CN 109297668B CN 201811279446 A CN201811279446 A CN 201811279446A CN 109297668 B CN109297668 B CN 109297668B
- Authority
- CN
- China
- Prior art keywords
- model
- torsion spring
- spring plate
- control surface
- main shaft
- 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.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
One end of a model main shaft (3) is fixedly connected with a control surface model (1) through a model fixing flange plate (2); the other end of the model main shaft (3) is fixedly connected with a torsion spring plate (6), the free end of the torsion spring plate (6) is inserted into a groove of the fixed base (10), a gap is reserved between the free end of the torsion spring plate and the groove, the gap is adjustable through a gap control screw/bolt (9) arranged on the fixed base (10), and the control of the torsional rigidity of the model is realized through the bending of the torsion spring plate (6); the deformation of the torsion spring plate (6) is limited by a model protection column (8); the bearing (5) is arranged inside the model fixing sleeve (4), the model main shaft (3) penetrates through the two bearings (5), and the model fixing sleeve (4) is used for fixing the degree of freedom of the main shaft except torsion. The invention realizes the simulation of linear and nonlinear conditions by adjusting the size of the gap.
Description
Technical Field
The invention relates to a wind tunnel test fixing device, and belongs to the field of aerospace engineering.
Background
When the aircraft wing control surface test is carried out, a model is required to be fixed, the safety of the model is required to be guaranteed at the fixed end of the model, the bending rigidity, the torsional rigidity and boundary conditions of some nonlinear gaps of the model are required to be simulated, and the design of the control surface gap wind tunnel test simulation device is based on the consideration of the problems.
As shown in fig. 1, the conventional wind tunnel control surface model fixing device mainly includes: model 1, ring flange 2, model girder 3. The model 1 and the flange plate 2 are fixed, the model main beam 3 is fixedly connected with the flange plate 2, and the bending rigidity and the torsional rigidity are simulated by using the main beam of the model.
The prior wind tunnel control surface model fixing device has the following problems:
(1) because the bending rigidity and the torsional rigidity of the model are simulated by using the same main beam, the bending rigidity and the torsional rigidity are easy to interfere with each other, and the boundary condition model is not easy to be accurate.
(2) The gap nonlinearity phenomenon of the model boundary condition cannot be simulated.
(3) The bending rigidity and the torsional rigidity of the model are simulated by using the same main beam, the design work is difficult to avoid the condition of coupling two data volumes, and the difficulty of designing the main beam is increased.
(4) The girder lacks corresponding spacing and protection device, when the model acutely vibrates, takes place experimental accident easily.
Disclosure of Invention
The invention mainly aims to overcome the defects in the prior art, and provides a control surface clearance wind tunnel test simulation device which simply and effectively realizes the purposes of simulating complex boundary conditions such as nonlinear clearance and the like and completing a wind tunnel test by using a simpler structural form.
The purpose of the invention is realized by the following technical scheme: a wind tunnel test simulation device for a control surface clearance comprises a control surface model, a model fixing flange plate, a model main shaft, two model fixing sleeves, two bearings, a torsion spring plate, a group of model protection columns, a group of clearance control screws/bolts and a fixing base; one end of the model main shaft is fixedly connected with the control surface model through a model fixing flange plate; the other end of the model main shaft is fixedly connected with a torsion spring plate, the free end of the torsion spring plate is inserted into the groove of the fixed base, a gap is reserved between the free end of the torsion spring plate and the groove of the fixed base, the gap is adjustable through a gap control screw/bolt arranged on the fixed base, and the control of the torsional rigidity of the model is realized through the bending of the torsion spring plate; the deformation of the torsion spring plate is limited through the model protection column; the bearing is installed inside the fixed cover of model, and the model main shaft passes two bearings, uses the fixed cover of model to realize the fixed of the degree of freedom beyond the main shaft torsion.
Preferably, the emergency stop pin is included, and when the vibration of the rudder surface model exceeds a threshold value in the test process, the emergency stop pin is started to clamp and fix the torsion spring piece.
Preferably, the gap control screws/bolts are not less than three groups in the axial direction of the torsion spring plate, and the distance a of each group is not less than 1 cm; the gap control screws/bolts are in one group located at the same longitudinal height.
Preferably, the torsion spring plate is positioned by the lowermost group of gap control screws/bolts, or a boss is arranged on one side inside the groove of the fixing base, one side of the torsion spring plate is in contact with the boss, and the other side of the torsion spring plate is tightly pressed and positioned by the lowermost gap control screws/bolts.
Preferably, the gap control screw/bolt head is arc-shaped and symmetrically arranged with respect to the torsion spring plate.
Preferably, the gap b between the inner wall of the recess of the fixing base and the side of the torsion spring plate should not be less than 0.5 cm.
Preferably, the distance between the model protection column and the torsion spring piece is between 3mm and 10 mm.
Preferably, both ends of the model main shaft are rectangular sections, and the middle section of the model main shaft is a circular section; the bearing is fixed with the torsion spring plate through a rectangular section, and the circular section of the middle section is used for mounting the bearing; the rectangular section part connected by the flange plate is used for simulating the bending rigidity of the control surface model.
Preferably, the length of the rectangular section part of the model main shaft connected with the flange plate is not less than 2 cm.
Preferably, the inner diameter of the bearing is consistent with the outer diameter of the model main shaft, and the deviation is allowed to be within 0.3 mm.
Preferably, the torsional stiffness is simulated by the material and the dimensions of the free ends of the torsion spring plate.
Compared with the prior art, the invention has the beneficial effects that:
1) in the field of aerospace engineering, flight accidents caused by control surface gaps occur occasionally, and the root is that the control system inevitably has structural nonlinearity such as gaps. The influence of clearance is not considered in the traditional control surface flutter wind tunnel test, so that the aeroelasticity characteristic of the actual control surface is difficult to simulate/examine. In recent years, the requirement of nonlinear aeroelasticity wind tunnel test of the control surface clearance is increasing day by day, and urgent need is provided for a wind tunnel test device for effectively simulating the clearance control surface. The invention designs a wind tunnel test device capable of effectively simulating the control surface clearance, and the wind tunnel test device has the advantages of simple and controllable structural form and small systematic error; the method has the advantages over other complex implementation mechanisms. The same mechanism can realize the simulation of linear and nonlinear conditions, and is favorable for the comparative analysis of test results.
2) In a traditional control surface flutter wind tunnel test, the bending rigidity and the torsional rigidity of a model are simulated by using the same main beam, the design work is difficult to avoid the condition of coupling two data volumes, and the difficulty of main beam design is increased. The invention adopts the mode that the bending and torsion of the boundary condition of the model are separately and independently simulated by using the rectangular beam of the model main shaft and the torsion spring piece, so that the boundary condition simulation is more accurate and is easier to realize.
3) The invention uses the clearance control bolt to control the boundary condition of the end part of the model, the control can reach the clearance size to be simulated, each module is relatively independent, the modification and the control are easier for the actual engineering, and the nonlinear or linear boundary condition of the clearance can be effectively simulated.
4) Compared with the model protection measures/devices of the traditional wind tunnel flutter test, the invention adopts a mode that a group of model protection columns and emergency limit nails are additionally arranged on two sides of a torsion spring piece, and adopts double insurance measures (the emergency limit nails are used for model protection mechanisms (increasing torsional rigidity) when a gapless control surface is close to a flutter boundary, and the mechanisms are not started under normal conditions. The protection column is used for preventing the control surface from generating static divergence or flutter to protect the model from being damaged aiming at the control surface with a gap, and is favorable for protecting the model when the model vibrates violently and avoiding the occurrence of test accidents.
Description of the drawings:
FIG. 1 is a schematic diagram of a prior art wind tunnel control surface model fixing device;
FIG. 2 is a schematic diagram of a wind tunnel test simulation device for control surface clearance according to the present invention;
FIG. 3 is a partial schematic view of a fixed position of the control surface clearance wind tunnel test simulation device according to the present invention;
FIG. 4 is a partial front view of a fixed position of the control surface clearance wind tunnel test simulation device according to the present invention;
the model comprises a model 1, a model 2 fixed flange, a model 3 main shaft, a model 4 fixed sleeve, a bearing 5, a torsion spring plate 6, an emergency limit nail 7, a model 8 protection column, a gap control screw 9 and a fixed base 10.
Detailed Description
As shown in fig. 2, 3, and 4, the present invention includes: model 1, model 2 fixed flange, model 3 main shaft, model 4 fixed sleeve, bearing 5, torsion spring plate 6, emergency limit nail 7, model 8 guard post, clearance control screw/bolt 9, and fixed base 10
One end of the model fixed flange 2 is fixedly connected with the model 1, and the other end is fixedly connected with the model main shaft 3. The middle section of the model main shaft 3 is a circular section, two ends of the model main shaft are rectangular sections, the rectangular section beam connected with the torsion spring plate is used for fixing, the rectangular section beam connected with the flange plate is used for simulating the bending rigidity of the model, and the control of the torsional rigidity of the model is realized through the bending of the torsion spring plate 6. The bearing 5 is arranged inside the model fixing sleeve 4, and the model main shaft 3 passes through the two bearings 5. The inner diameter of the bearing is consistent with the outer diameter of the model main shaft, and the deviation is allowed to be within 0.3 mm.
The model guard post 8 and the emergency stop pin 7 are respectively located on both sides of the torsion spring plate 6 for fixing the model in an emergency. The gap control screw/bolt 9 clamps and fixes the model at the root of the model 1, and the nonlinear condition is simulated by adjusting the size of the gap. The length of the rectangular section part connected with the flange plate by the model main shaft is not less than 2 cm. The distance between the model protection column 8 and the torsion spring piece 6 is preferably 3 mm-10 mm.
During installation, the bearing 5 is installed inside the model fixing sleeve 4, one end of the fixed flange 2 is fixedly connected with the model 1, and the other end of the fixed flange is fixedly connected with the model main shaft 3. The model spindle 3 is passed through the bearing 5 and fixed. A torsion spring plate 6 is arranged on a fixed base 10, and model protection columns 8 and emergency limit nails 7 are arranged on two sides of the torsion spring plate 6. And connecting and fixing the model spindle 3 and the torsion spring plate 6.
The distance a between each group of the clearance control screws/bolts 9 is not less than 1 cm; the gap control screws/bolts are in one group located at the same longitudinal height. The torsional spring plate is positioned by the lowest group of gap control screws/bolts, or a boss is arranged on one side in the groove of the fixed base, one side of the torsional spring plate 6 is in contact with the boss, the other side of the torsional spring plate is tightly pressed and positioned by the lowest gap control screws/bolts, and the mode of tightly pressing and positioning the two groups of gap control screws/bolts at the bottom is shown in figure 4. The two groups of bolt heads are in protruding arc shapes and are symmetrically arranged by the torsional spring plate, so that the model can be clamped and fixed from two sides. The gap b between the inner wall of the recess of the fixed base 10 and the side of the torsion spring plate 6 should not be less than 0.5 cm.
The specific control mode is as follows:
before the wind tunnel starts blowing, the gap control screw 9 is adjusted to change the fixation of the torsion spring plate 6, so that the gap nonlinear boundary condition of the model is designed.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications, equivalent variations and modifications made to the above embodiment according to the technical spirit of the present invention still fall within the scope of the technical solution of the present invention.
Claims (9)
1. A wind tunnel test simulation device for a control surface clearance is characterized in that: the method comprises the following steps: the device comprises a control surface model (1), a model fixing flange plate (2), a model main shaft (3), two model fixing sleeves (4), two bearings (5), a torsion spring plate (6), an emergency limit nail (7), a group of model protection columns (8), a group of gap control screws/bolts (9) and a fixing base (10); one end of the model main shaft (3) is fixedly connected with the control surface model (1) through a model fixing flange plate (2); the other end of the model main shaft (3) is fixedly connected with a torsion spring plate (6), the free end of the torsion spring plate (6) is inserted into a groove of the fixed base (10), a gap is reserved between the free end of the torsion spring plate and the groove, the gap is adjustable through a gap control screw/bolt (9) arranged on the fixed base (10), and the control of the torsional rigidity of the model is realized through the bending of the torsion spring plate (6); the deformation of the torsion spring plate (6) is limited by a model protection column (8); the bearings (5) are arranged in the model fixing sleeve (4), the model main shaft (3) penetrates through the two bearings (5), and the model fixing sleeve (4) is used for fixing the degree of freedom of the main shaft except torsion; when the vibration of the rudder surface model (1) exceeds a threshold value in the test process, starting an emergency limit nail (7) to clamp and fix the torsion spring piece (6); the gap control screws/bolts (9) are not less than three groups in the axial direction of the torsion spring plate (6), and the distance a between each group is not less than 1 cm; the gap control screws/bolts are in one group located at the same longitudinal height.
2. The control surface clearance wind tunnel test simulation device according to claim 1, characterized in that: the torsional spring plate is positioned by the aid of the lowermost group of gap control screws/bolts, or a boss is arranged on one side inside the groove of the fixing base, one side of the torsional spring plate (6) is in contact with the boss, and the other side of the torsional spring plate is tightly jacked and positioned by the lowermost gap control screws/bolts.
3. The control surface clearance wind tunnel test simulation device according to claim 1, characterized in that: the gap control screw/bolt head is arc-shaped and symmetrically arranged relative to the torsion spring plate.
4. The control surface clearance wind tunnel test simulation device according to claim 1, characterized in that: the gap b between the inner wall of the groove of the fixed base (10) and one side of the torsion spring plate (6) is not less than 0.5 cm.
5. The control surface clearance wind tunnel test simulation device according to claim 1, characterized in that: the distance between the model protection column (8) and the torsion spring piece (6) is preferably 3 mm-10 mm.
6. The control surface clearance wind tunnel test simulation device according to claim 1, characterized in that: both ends of the model main shaft (3) are rectangular sections, and the middle section is a circular section; the bearing is fixed with the torsion spring plate through a rectangular section, and the circular section of the middle section is used for mounting the bearing; the rectangular section part connected by the flange plate is used for simulating the bending rigidity of the control surface model.
7. The control surface clearance wind tunnel test simulation device according to claim 6, characterized in that: the length of the rectangular section part connected with the model main shaft and the flange plate is not less than 2 cm.
8. The control surface clearance wind tunnel test simulation device according to claim 1, characterized in that: the inner diameter of the bearing is consistent with the outer diameter of the model main shaft, and the deviation is allowed to be within 0.3 mm.
9. The control surface clearance wind tunnel test simulation device according to claim 1, characterized in that: the torsional rigidity is simulated by the material of the torsional spring piece (6) and the size of the free end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811279446.7A CN109297668B (en) | 2018-10-30 | 2018-10-30 | Control surface clearance wind tunnel test simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811279446.7A CN109297668B (en) | 2018-10-30 | 2018-10-30 | Control surface clearance wind tunnel test simulation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109297668A CN109297668A (en) | 2019-02-01 |
| CN109297668B true CN109297668B (en) | 2020-07-14 |
Family
ID=65145160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811279446.7A Active CN109297668B (en) | 2018-10-30 | 2018-10-30 | Control surface clearance wind tunnel test simulation device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109297668B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111982460A (en) * | 2020-08-07 | 2020-11-24 | 北京航空航天大学 | Clearance simulation device of wind tunnel model |
| CN112213070B (en) * | 2020-09-21 | 2023-03-14 | 中国航空工业集团公司沈阳飞机设计研究所 | External object hangs clearance analogue means under flutter wind tunnel test wing |
| CN112432757A (en) * | 2020-12-18 | 2021-03-02 | 上海机电工程研究所 | Steering wheel clearance adjustment simulation mechanism |
| CN114018533A (en) * | 2021-10-20 | 2022-02-08 | 中国航天空气动力技术研究院 | Control surface dynamic load wind tunnel test device |
| CN114563161B (en) * | 2022-02-24 | 2023-08-01 | 中国船舶重工集团公司第七一九研究所 | Water tunnel test simulation device and method for rudder shaft system gap |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0854316A (en) * | 1994-08-12 | 1996-02-27 | Mitsubishi Heavy Ind Ltd | Flutter model for rudder |
| CN104122067A (en) * | 2013-04-24 | 2014-10-29 | 成都飞机设计研究所 | Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model |
| CN103792057B (en) * | 2014-03-10 | 2016-08-17 | 西安交通大学 | A kind of adjustable backlash nonlinearity development test platform and using method thereof |
| CN107167304B (en) * | 2017-04-20 | 2019-03-01 | 西安交通大学 | A kind of the hinge gap power characteristic development test platform and test method of Parameter adjustable |
| CN108195543A (en) * | 2017-11-29 | 2018-06-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft wind tunnel model flutter blowing test system |
| CN108344547B (en) * | 2018-02-08 | 2023-06-16 | 天津大学 | Experimental system and verification method for identifying nonlinear stiffness of gap |
-
2018
- 2018-10-30 CN CN201811279446.7A patent/CN109297668B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109297668A (en) | 2019-02-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109297668B (en) | Control surface clearance wind tunnel test simulation device | |
| CN110160758B (en) | Ground rigidity test method for cracking type rudder system | |
| CN107238457A (en) | A kind of low thrust measurement apparatus | |
| Soleimani et al. | Effect of out-of-plane defects on the postbuckling behavior of graphene sheets based on nonlocal elasticity theory | |
| CN102103056B (en) | Proportional test device for rotating bending fatigue of train wheel axle | |
| CN207600320U (en) | A kind of device of simulant missile aerodynamic loading loading | |
| CN109163626B (en) | Zero adjustment device and method for rudder wings of missile steering engine | |
| CN107796584A (en) | A kind of low velocity impact test fixture of angle of attack continuously adjustable | |
| CN105424344A (en) | Debugging device used for airplane calibration test deformation structure loading actuator | |
| CN104229145A (en) | Lead screw push rod type aircraft head deflection driving device | |
| CN106969921B (en) | A kind of test steering column is rotated up the device and method of angle variable quantity | |
| CN103616152B (en) | A kind of steel rail impact test device and method | |
| CN105606907B (en) | A kind of deformation experiment device towards smart skins antenna measurement | |
| CN209459859U (en) | T-type horizontal tail flutter model protective device | |
| CN105466768A (en) | Pretightening drop-hammer type impact testing machine plate test piece fixture with size adjustable | |
| Reichenbach et al. | Joined wing sensorcraft aeroservoelastic wind tunnel test program | |
| CN102840269B (en) | Method used for increasing wind generating set system damping and tuning quality damper | |
| CN107345536B (en) | Wind tunnel flow field start-stop damping device | |
| CN203616150U (en) | Loading test device used for vehicle body drawing device | |
| CN111982460A (en) | Clearance simulation device of wind tunnel model | |
| CN110510136A (en) | A kind of unmanned plane wing protective device | |
| CN105004236A (en) | Positioning structure and detection method for front face detection test sample frame | |
| CN114705139A (en) | Engine angular deviation and concentricity adjusting device | |
| CN103624715B (en) | Front anti-collision beam assembly assembling tool for vehicle | |
| CN211978336U (en) | Bench test tool for automobile front steering knuckle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |