CN206488910U - A kind of low-speed wind tunnel swears the experimental rig of rolling around speed - Google Patents
A kind of low-speed wind tunnel swears the experimental rig of rolling around speed Download PDFInfo
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- CN206488910U CN206488910U CN201720179074.5U CN201720179074U CN206488910U CN 206488910 U CN206488910 U CN 206488910U CN 201720179074 U CN201720179074 U CN 201720179074U CN 206488910 U CN206488910 U CN 206488910U
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Abstract
The utility model discloses the experimental rig that a kind of low-speed wind tunnel swears rolling around speed, including aerofoil profile pole, radome fairing, electrical feedthrough, wobble shaft, angular contact ball bearing, counterweight, lightweight pole and pitching/yaw freedom turntable；Aerofoil profile pole bottom is fixed under test chamber on hole wall or platform, and electrical feedthrough, wobble shaft and angular contact ball bearing are located inside radome fairing；Lightweight pole one end is fixedly connected with wobble shaft, and the other end is fixedly connected with pitching/yaw freedom turntable, and counterweight is movably fixed to the end of lightweight pole；Pitching/yaw freedom turntable one end is fixedly connected with lightweight pole, and the other end is fixedly connected with test model.The utility model is simple and compact for structure, it is easy to install and use, Whole Process Simulation experiment of the test model in rolling, pitching and driftage three degree of freedom motion can be realized, kinematic parameter is measured in real time, the angle of attack, the purpose of yaw angle consecutive variations are reached, and ensure that in process of the test the stability of air-flow.
Description
Technical field
The utility model belongs to a kind of flow tunnel testing device, and in particular to a kind of low-speed wind tunnel swears the experiment of rolling around speed
Device.
Background technology
Speed arrow rolling is one of most basic tactical maneuver action of modern combat aircraft, and this is motor-driven can quickly to change head
Point to, first enemy's capture Target Acquisition favorably attacks situation.Tailspin is one of most complicated, most dangerous extreme flight state of aircraft；
The maneuverability of aircraft significantly degenerates or even completely lost in tailspin, while dimensional orientation judges and riving condition becomes more multiple
It is miscellaneous, thus great threat is constituted to the safety of pilot and aircraft.Under the essence of aircraft tailspin motion is a kind of High Angle of Attack
The state of flight of rolling is sweared around speed.
When studying guided missile (aircraft), it is even more important around motor-driven moved with tailspin of speed arrow, (flies in guided missile
Machine) when being acted, want to determine the direction of the motion of guided missile (aircraft) in space, it is necessary to yaw angle, the angle of pitch and rolling
These three angles of corner.
Mainly swear that motor-driven and tailspin is moved around speed by the research of flight test means in the prior art, this means wind
Danger is higher, expense expends greatly and the cycle is longer, therefore many aircraft all do not carry out taking a flight test for tailspin so far.Skill now
Art is mainly is flown using low-speed wind tunnel simulation test device analog study aircraft around speed, but traditional low-speed wind tunnel
Rolling Balance Experimental Equipment artificial intelligence is fixed under the angle of attack and yaw angle and swears rolling movement around speed, and vertical wind tunnel tailspin is tried
Test mainly analog study stable state Tail chain, it is impossible to the characteristic that Overall Acquisition tailspin enters, changed, so, experiment now
It is difficult to which the rolling movement while when there are the angle of attack, yaw angle consecutive variations is realized in maneuver simultaneously, particularly ensureing examination
Experiment device compact conformation is simple, it is easy for installation in the case of, it is difficult to simulate when aircraft testing model carries out rolling movement
Free pitching and yawing rotation process, and the real-time measurement of each flight parameter can not be carried out, it can not more ensure to try in wind-tunnel
The stability of air-flow when testing.
Utility model content
In view of the shortcomings of the prior art, the purpose of this utility model is the experiment for proposing that a kind of low-speed wind tunnel is sweared around speed
Device, the apparatus structure is simple and compact, can effectively realize test model in rolling, pitching and driftage three degree of freedom motion
Whole Process Simulation is tested, and can carry out the real-time measurement of parameter, can reach the angle of attack, the purpose of yaw angle consecutive variations, and
The stability of wind-tunnel interior air-flow is ensure that in process of the test, it is very convenient using installing.
To achieve the above object, the technical scheme that the utility model is used is：
A kind of low-speed wind tunnel around speed swear rolling experimental rig, the device include aerofoil profile pole, radome fairing, electrical feedthrough,
Wobble shaft, angular contact ball bearing, counterweight, lightweight pole and pitching/yaw freedom turntable；
The aerofoil profile pole bottom is fixed under test chamber on hole wall or platform, and radome fairing is fixed on aerofoil profile pole top
Portion；The radome fairing is hollow-core construction, is internally provided with electrical feedthrough, wobble shaft and the angular contact ball axle for supporting wobble shaft
Hold, the electrical feedthrough is fixedly connected with wobble shaft；
The lightweight pole integrally passes through three pre-bending, and its one end is fixedly connected with wobble shaft, the other end and pitching/driftage
Free degree turntable is fixedly connected, and lightweight pole two ends are respectively positioned on the axis of wobble shaft, and the counterweight is solid by fix bar
The end that lightweight pole is connected with wobble shaft is scheduled on, counterweight is enclosed in fix bar and is flexibly connected, and counterweight is kept with lightweight pole
At grade；
The pitching/yaw freedom turntable one end is fixedly connected with lightweight pole, and the other end is fixed with test model to be connected
Connect, and pitching/center of rotation of yaw freedom turntable is overlapped with the center of gravity of test model.
It is further that the pitching/yaw freedom turntable includes axis of sideslip, turntable outer framework, turntable inner frame, list
Row angular contact ball bearing and biserial deep groove ball bearing, the pitching/yaw freedom turntable are connected by axis of sideslip and lightweight pole
Connect, turntable outer framework is installed on turntable inner frame, turntable inner frame is supported by double deep groove ball bearings, turntable outer framework is by single-row
Angular contact ball bearing is supported；Elevating movement can be realized by turntable outer framework, desire of freely going off course can be realized by turntable inner frame
Dynamic, wherein aircraft testing model is fixed on turntable outer framework.
It is further that the aerofoil profile branch bar section is in aerofoil profile；The support of aerofoil profile pole is reduced to flow field residing for model
The influence of generation.
Further that multiple bolts hole are provided with the top and bottom of the aerofoil profile pole, aerofoil profile pole and radome fairing and
Hole wall or platform are bolted under pneumatic test section.
It is further that the radome fairing head uses smooth contour；So that the air-flow more fairing for passing through radome fairing.
It is further, the electrical feedthrough and wobble shaft synchronous rotary, and wobble shaft is provided with and supplies electrical feedthrough signal wire and electricity
The hollow structure of source line arrangement；Electrical feedthrough can be used for simulated interior airborne equipment to power and the data parameters of collecting device are believed in real time
Number, use hollow structure not only can provide cabling space for the signal wire and power line of electrical feedthrough, device can also be reduced
Quality and inertia.
It is further that the head of the counterweight uses smooth contour, its afterbody uses tapering transition；So that passing through counterweight
Air-flow more fairing, the influence to air-flow is smaller.
It is further that the lightweight pole is hollow structure, and its three pre- crooks are using seamlessly transitting；Using three
Secondary pre-bending, first time pre-bending can leave enough elevating movement allowances to test model, it is to avoid produce interference, second of pre-bending can
Reduce the influence that the lightweight pole inertia is caused to model sport, third time pre-bending can increase the angle-of-attack range of model of mobile action,
And reduce interference with lightweight pole.
It is further that the device can realize that test model roll angle range of movement is -180 °~180 °, yaw angle fortune
Dynamic scope is -180 °~180 °, and pitch movement scope is 0 °~90 °.
The beneficial effects of the utility model are：
It is apparent that test model physical significance is realized by way of wobble shaft and pitching/yaw freedom turntable are combined
Three-degree-of-freedom motion simulation, and its motion process can be recorded in real time recorded its exercise data parameter, device
Integrated level is high；
The interference of aerofoil profile pole, radome fairing, counterweight and lightweight pole to tunnel airstream is small so that the test model can be
Carry out swearing the simulated test of rolling in stable air-flow around speed, lightweight pole uses three pre-bending, stayed to aircraft testing model
There are enough elevating movement allowances, also improve the angle-of-attack range of model of mobile action, reduce the interference between lightweight pole, together
When also reduce the influence that lightweight pole inertia is caused to model sport；
Rubbed in the present apparatus smaller, influenceed smaller by air-flow, rotated very flexible, simulate true to nature；The present apparatus is installed
Convenient, compact conformation, manufacturing cost is relatively low；Simultaneously by the adjustment of counterweight height, the different equal energy of aircraft testing model can be achieved
Dynamic balancing is kept in experiment rotary course, preferably, different aircraft testing models can be in multi-form for transplantability and versatility
Tested with being realized in different size of low-speed wind tunnel.
Brief description of the drawings
Fig. 1 is experimental rig structural representation of the present utility model；
Fig. 2 is the structural representation of pitching of the present utility model/yaw freedom turntable.
In figure：1st, aerofoil profile pole；2nd, radome fairing；3rd, electrical feedthrough；4th, wobble shaft；5th, angular contact ball bearing；6th, counterweight；7th, it is light
Matter pole；8th, pitching/yaw freedom turntable；8-1 turntable outer frameworks；The single-row angular contact ball bearings of 8-2；8-3, axis of sideslip；8-
4th, turntable inner frame；8-5 biserial deep groove ball bearings；9th, fix bar.
Embodiment
In order that the purpose, technical scheme and advantage of utility model are clearer, below in conjunction with the accompanying drawings to the utility model
It is further elaborated.
In the present embodiment, as shown in Fig. 1~2, a kind of low-speed wind tunnel swears the experimental rig of rolling, the device bag around speed
Include aerofoil profile pole 1, radome fairing 2, electrical feedthrough 3, wobble shaft 4, angular contact ball bearing 5, counterweight 6, lightweight pole 7 and pitching/driftage
Free degree turntable 8；
The bottom of aerofoil profile pole 1 is fixed under test chamber on hole wall or platform, and radome fairing 1 is fixed on aerofoil profile pole
2 tops；The radome fairing 2 is hollow-core construction, is internally provided with electrical feedthrough 3, wobble shaft 4 and the corner connection for supporting wobble shaft 4
Ball bearing 5 is touched, the electrical feedthrough 3 is fixedly connected with wobble shaft 4；
The lightweight pole 7 is overall to pass through three pre-bending, and its one end is fixedly connected with wobble shaft 4, and the other end and pitching/inclined
Boat free degree turntable 8 is fixedly connected, and the two ends of lightweight pole 7 are respectively positioned on the axis of wobble shaft 4, it is ensured that aircraft testing model
Roll-over axis, pitch axis and driftage axially homogeneously meet at the center of pitching/yaw freedom turntable 8, and the counterweight 6 passes through solid
Fixed pole 9 is fixed on the end that lightweight pole 7 is connected with wobble shaft 4, and counterweight 6 is enclosed in fix bar 9 and is flexibly connected, and counterweight 6 with
Lightweight pole 7 keeps at grade, and the height of counterweight 6 can be adjusted in fix bar 9, to ensure different model aircrafts
Dynamic equilibrium state is kept in experiment rotary course；
The pitching/one end of yaw freedom turntable 8 is fixedly connected with lightweight pole 7, and the other end is fixed with test model
Connect, and pitching/center of rotation of yaw freedom turntable 8 is overlapped with the center of gravity of test model.
As a kind of prioritization scheme of the present utility model, the pitching/yaw freedom turntable 8 includes axis of sideslip 8-3, turned
Platform outer framework 8-1, turntable inner frame 8-4, single-row angular contact ball bearing 8-2 and biserial deep groove ball bearing 8-5, the pitching/partially
Boat free degree turntable 8 is connected by axis of sideslip 8-3 with lightweight pole 7, and turntable outer framework 8-1 is installed on turntable inner frame 8-4,
Turntable inner frame 8-4 supports 8-5, turntable outer framework 8-1 to be supported by single-row angular contact ball bearing 8-2 by double deep groove ball bearings；It is logical
Elevating movement can be realized by crossing turntable outer framework 8-1, can be realized freely to go off course by turntable inner frame 8-4 and be intended to, and wherein aircraft is tried
Model is tested to be fixed on turntable outer framework.
As a kind of prioritization scheme of the present utility model, the section of aerofoil profile pole 1 is in aerofoil profile；Reduce aerofoil profile pole 1
Support to residing for model flow field produce influence.
As a kind of prioritization scheme of the present utility model, the top and bottom of aerofoil profile pole 1 are provided with multiple bolts hole,
Aerofoil profile pole 1 is bolted with hole wall or platform under radome fairing 2 and pneumatic test section.
As a kind of prioritization scheme of the present utility model, the head of radome fairing 2 uses smooth contour；So that passing through rectification
The air-flow more fairing of cover 2.
As a kind of prioritization scheme of the present utility model, the electrical feedthrough 3 and the synchronous rotary of wobble shaft 4, and wobble shaft 4 sets
There is the hollow structure arranged for the signal wire of electrical feedthrough 3 and power line；Electrical feedthrough 3 is powered and real available for simulated interior airborne equipment
When collecting device data parameters signal, use hollow structure not only can provide cabling for the signal wire and power line of electrical feedthrough
Space, can also reduce the quality and inertia of device.
As a kind of prioritization scheme of the present utility model, the head of the counterweight 6 uses smooth contour, and its afterbody is using cone
Shape transition；So that by the air-flow more fairing of counterweight 6, the influence to air-flow is smaller.
As a kind of prioritization scheme of the present utility model, the lightweight pole 7 is hollow structure, and its three pre- crooks are equal
Using seamlessly transitting；Using three pre-bending, first time pre-bending can leave enough elevating movement allowances to test model, it is to avoid production
Raw interference, second of pre-bending can reduce the influence that the inertia of lightweight pole 7 is caused to model sport, and third time pre-bending can increase
The angle-of-attack range of model of mobile action, and reduce the interference with lightweight pole 7.
As a kind of prioritization scheme of the present utility model, the device can realize test model roll angle range of movement for-
180 °~180 °, driftage range of angular motion is -180 °~180 °, and pitch movement scope is 0 °~90 °.
The utility model in the specific implementation, the present apparatus is fixed under test chamber on hole wall or platform, passes through spiral shell
The aerofoil profile pole 1 of the present apparatus is fixed together by bolt with hole wall or platform under test chamber, and aircraft testing model is fixed on
On turntable outer framework 8-1, and the center of gravity of aircraft testing model is overlapped with the center of rotation of pitching/yaw freedom turntable 8；Control
Start electrical feedthrough 3, electrical feedthrough 3 and wobble shaft 4 are rotated coaxially together, wobble shaft 4, which is rotated, drives counterweight 6 and lightweight pole 7
Rotate together, the pitching/yaw freedom turntable 8 of the one end of lightweight pole 7 drives aircraft testing model to do coaxial do with wobble shaft 4
Rolling movement, while turntable outer framework 8-1 drives aircraft testing model to do elevating movement, turntable inner frame 8-4 drives aircraft examination
Test model and do yawing rotation, test model can be realized by way of wobble shaft 4 and pitching/yaw freedom turntable 8 are combined
The simulation of the apparent three-degree-of-freedom motion of physical significance, and its motion process can be recorded in real time by electrical feedthrough 3 and transported
Dynamic data parameters are recorded, by the experimental rig, and the range of movement that can realize roll angle is -180 °~180 °, driftage
- 180 ° of range of angular motion~180 °, 0 °~90 ° of pitch movement scope, it is possible to achieve swear rolling maneuver around speed, so that
Can be with the research of convenient, the efficient tailspin overall process for carrying out air maneuver；
And the structure of the aerofoil profile pole 1, radome fairing 2, counterweight 6 and lightweight pole 7 in the experimental rig can reduce pair
The interference of tunnel airstream so that the test model can carry out swearing the simulated test of rolling around speed in stable air-flow, and
Its analog angle scope is big, and counterweight 6 can be carried out in fix bar 9 above and below regulation, can effectively meet requirement for dynamic balance；
Rubbed in the present apparatus smaller, influenceed smaller by air-flow, rotated very flexible, simulate true to nature；The present apparatus is installed
Convenient, compact conformation, cost is relatively low good；And transplantability is good, versatility is good, can be in multi-form and different size of low-speed wind tunnel
It is middle to realize.
General principle of the present utility model, principal character and advantage of the present utility model has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply illustrate principle of the present utility model, on the premise of the utility model spirit and scope are not departed from, the utility model is also
Various changes and modifications are had, these changes and improvements are both fallen within the range of claimed the utility model.The utility model
Claimed scope is by appended claims and its equivalent thereof.
Claims (9)
1. a kind of low-speed wind tunnel swears the experimental rig of rolling around speed, it is characterised in that：The device includes aerofoil profile pole (1), whole
Stream cover (2), electrical feedthrough (3), wobble shaft (4), angular contact ball bearing (5), counterweight (6), lightweight pole (7) and pitching/driftage are certainly
By degree turntable (8)；
Aerofoil profile pole (1) bottom is fixed under test chamber on hole wall or platform, and radome fairing (2) is fixed on aerofoil profile pole
(1) top；The radome fairing (2) is hollow-core construction, is internally provided with electrical feedthrough (3), wobble shaft (4) and for supporting wobble shaft
(4) angular contact ball bearing (5), the electrical feedthrough (3) is fixedly connected with wobble shaft (4)；
The lightweight pole (7) integrally passes through three pre-bending, and its one end is fixedly connected with wobble shaft (4), and the other end and pitching/inclined
Boat free degree turntable (8) is fixedly connected, and lightweight pole (7) two ends are respectively positioned on the axis of wobble shaft (4), the counterweight
(6) end that lightweight pole (7) is connected with wobble shaft (4) is fixed on by fix bar (9), counterweight (6) is enclosed in fix bar (9)
It is flexibly connected, and counterweight (6) is kept at grade with lightweight pole (7)；
The pitching/yaw freedom turntable (8) one end is fixedly connected with lightweight pole (7), the other end and aircraft testing model
It is fixedly connected, and the center of rotation of pitching/yaw freedom turntable (8) is overlapped with the center of gravity of aircraft testing model.
2. a kind of low-speed wind tunnel according to claim 1 swears the experimental rig of rolling around speed, it is characterised in that：It is described to bow
Face upward/yaw freedom turntable (8) include axis of sideslip (8-3), turntable outer framework (8-1), turntable inner frame (8-4), single-row corner connection
Ball bearing (8-2) and biserial deep groove ball bearing (8-5) are touched, the pitching/yaw freedom turntable (8) passes through axis of sideslip (8-3)
It is connected with lightweight pole (7), turntable outer framework (8-1) is installed on turntable inner frame (8-4), turntable inner frame (8-4) is by double
Deep groove ball bearing (8-5) is supported, and turntable outer framework (8-1) is supported by single-row angular contact ball bearing (8-2).
3. a kind of low-speed wind tunnel according to claim 2 swears the experimental rig of rolling around speed, it is characterised in that：The wing
Type pole (1) section is in aerofoil profile.
4. a kind of low-speed wind tunnel according to claim 3 swears the experimental rig of rolling around speed, it is characterised in that：The wing
Multiple bolts hole, aerofoil profile pole (1) and hole wall under radome fairing (2) and pneumatic test section are provided with the top and bottom of type pole (1)
Or platform is bolted.
5. a kind of low-speed wind tunnel according to claim 4 swears the experimental rig of rolling around speed, it is characterised in that：It is described whole
Stream cover (2) head uses smooth contour.
6. a kind of low-speed wind tunnel according to claim 5 swears the experimental rig of rolling around speed, it is characterised in that：It is described to draw
Electrical equipment (3) and wobble shaft (4) synchronous rotary, and wobble shaft (4) be provided with for electrical feedthrough (3) signal wire and power line arrange it is hollow
Structure.
7. a kind of low-speed wind tunnel according to claim 6 swears the experimental rig of rolling around speed, it is characterised in that：It is described to match somebody with somebody
The head of weight (6) uses smooth contour, and its afterbody uses tapering transition.
8. a kind of low-speed wind tunnel according to claim 7 swears the experimental rig of rolling around speed, it is characterised in that：It is described light
Matter pole (7) is hollow structure, and its three pre- crooks are using seamlessly transitting.
9. a kind of low-speed wind tunnel according to claim 8 swears the experimental rig of rolling around speed, it is characterised in that：The device
Can realize test model roll angle range of movement be -180 °~180 °, driftage range of angular motion be -180 °~180 °, pitching
Range of angular motion is 0 °~90 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720179074.5U CN206488910U (en) | 2017-02-27 | 2017-02-27 | A kind of low-speed wind tunnel swears the experimental rig of rolling around speed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720179074.5U CN206488910U (en) | 2017-02-27 | 2017-02-27 | A kind of low-speed wind tunnel swears the experimental rig of rolling around speed |
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| Publication Number | Publication Date |
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| CN206488910U true CN206488910U (en) | 2017-09-12 |
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ID=59763106
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107796589A (en) * | 2017-12-14 | 2018-03-13 | 河北工业大学 | Automatically controlled adjustable high ferro Road quality simulation wind tunnel experiment platform |
| CN109342005A (en) * | 2018-11-26 | 2019-02-15 | 中国航空工业集团公司沈阳空气动力研究所 | Z-shaped mechanism in six degree of freedom store Combinations strut for wind-tunnel captive trajectory testing |
| CN110006616A (en) * | 2019-04-15 | 2019-07-12 | 中国空气动力研究与发展中心高速空气动力研究所 | The preparation platform and its application method and production method of high-speed wind tunnel model |
| CN111289208A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model tail boom device suitable for fighter plane wind tunnel test |
| CN112051027A (en) * | 2020-09-16 | 2020-12-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-degree-of-freedom supporting device for supersonic wind tunnel model |
| CN116046330A (en) * | 2023-03-30 | 2023-05-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | Three-degree-of-freedom virtual flight test device capable of ventilating |
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2017
- 2017-02-27 CN CN201720179074.5U patent/CN206488910U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107796589A (en) * | 2017-12-14 | 2018-03-13 | 河北工业大学 | Automatically controlled adjustable high ferro Road quality simulation wind tunnel experiment platform |
| CN107796589B (en) * | 2017-12-14 | 2024-02-20 | 河北工业大学 | Electric control adjustable high-speed railway condition simulation wind tunnel experiment table |
| CN109342005A (en) * | 2018-11-26 | 2019-02-15 | 中国航空工业集团公司沈阳空气动力研究所 | Z-shaped mechanism in six degree of freedom store Combinations strut for wind-tunnel captive trajectory testing |
| CN110006616A (en) * | 2019-04-15 | 2019-07-12 | 中国空气动力研究与发展中心高速空气动力研究所 | The preparation platform and its application method and production method of high-speed wind tunnel model |
| CN111289208A (en) * | 2020-03-06 | 2020-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Model tail boom device suitable for fighter plane wind tunnel test |
| CN112051027A (en) * | 2020-09-16 | 2020-12-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-degree-of-freedom supporting device for supersonic wind tunnel model |
| CN112051027B (en) * | 2020-09-16 | 2022-10-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-degree-of-freedom supporting device for supersonic wind tunnel model |
| CN116046330A (en) * | 2023-03-30 | 2023-05-02 | 中国航空工业集团公司哈尔滨空气动力研究所 | Three-degree-of-freedom virtual flight test device capable of ventilating |
| CN116046330B (en) * | 2023-03-30 | 2023-06-16 | 中国航空工业集团公司哈尔滨空气动力研究所 | Three-degree-of-freedom virtual flight test device capable of ventilating |
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