CN208109379U - A kind of helicopter built-up pattern experimental rig - Google Patents
A kind of helicopter built-up pattern experimental rig Download PDFInfo
- Publication number
- CN208109379U CN208109379U CN201820578725.2U CN201820578725U CN208109379U CN 208109379 U CN208109379 U CN 208109379U CN 201820578725 U CN201820578725 U CN 201820578725U CN 208109379 U CN208109379 U CN 208109379U
- Authority
- CN
- China
- Prior art keywords
- rotor
- tail
- helicopter
- experimental rig
- testing stand
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of helicopter built-up pattern experimental rigs, including rotor model.test system and tail-rotor testing stand, the rotor model.test system bottom is provided with rotary turntable, pitch angle driving mechanism is provided on the rotor model.test system, the top of the rotor model.test system is used to connect the rotor of helicopter, the top of the tail-rotor testing stand is used to connect the tail-rotor of helicopter, and the bottom of tail-rotor testing stand is connected on four-dimensional Transfer rack.The present invention can real simulation lifting airscrew, fuselage, the triangular movement of tail-rotor, and then study three between aerodynamic interference；Simultaneously, increase horizontal tail, vertical fin, short limb, carry object etc. on airframe models, and mating corresponding measuring device, the aerodynamic interference of the other components such as horizontal tail, vertical fin, short limb, carry object can further be studied, and then the deficiency of aerodynamic interference Research Ability between each component of domestic helicopter is made up, and improve China's helicopter W.T test research system.
Description
Technical field
The present invention relates to helicopter W.T test technical field, more particularly to research single-rotor helicopter aerodynamic interference and
A kind of helicopter built-up pattern experimental rig of layout optimization.
Background technique
The aerodynamic interference of helicopter is that the aerodynamic arrangement of helicopter designs the basic technology problem faced, how to dissolve and goes straight up to
Negative effect caused by the aerodynamic interference of machine is always helicopter aerodynamic arrangement focus of attention.
Currently, foreign well-known Helicopter Corporation and research institution put into great effort to helicopter aerodynamic interference problem into
Gone system basic theory and verification experimental verification research, form aerodynamic arrangement's technology with their own characteristics, make the synthesis of helicopter
Performance is significantly improved.And China also lacks comprehensive in-depth study in helicopter aerodynamic arrangement field, not yet slaps completely
The flow mechanism in helicopter aerodynamic interference phenomenon is held, the theory analysis side of effective prediction helicopter aerodynamic interference is also lacked
Method more can be directly used for design of aerodynamic configuration for the helicopter without enough aerodynamic interference test datas, it is straight seriously to constrain China
The autonomous Design ability of the machine of liter.
Wind tunnel test is to understand, grasp the economical and efficient means of helicopter each component aerodynamic interference characteristic and mechanism, is passed through
Wind tunnel test can study the aerodynamic interference situation between different each components of distribution form helicopter, grasp helicopter flight characteristic
With the changing rule of aerodynamic arrangement, helicopter aerodynamic interference database is constructed, it is theoretical and square to establish helicopter layout optimization design
Method.Therefore, research and develop it is a kind of can effective helicopter simulating each component built-up pattern experimental rig, mating corresponding test method,
Research cost and research risk are reduced, just seems necessary, it is also very urgent.
Summary of the invention
It is each portion of helicopter the technical problem to be solved in the present invention is that providing a kind of helicopter built-up pattern experimental rig
Aerodynamic interference research provides a kind of efficient means between part.
To achieve the goals above, the present invention adopts the following technical scheme that：
A kind of helicopter built-up pattern experimental rig, including rotor model.test system and tail-rotor testing stand, the rotor model.test system
Bottom is provided with rotary turntable, and pitch angle driving mechanism, the rotor model.test system are provided on the rotor model.test system
Top be used to connect the rotor of helicopter, the top of the tail-rotor testing stand is used to connect the tail-rotor of helicopter, tail-rotor test
The bottom of platform is connected on four-dimensional Transfer rack.
In the above-mentioned technical solutions, lower half, rotor balances and the rotor of the airframe models package rotor control mechanism
Torsion balance, the rotor control mechanism are fixedly connected with the upper flat plate of rotor balances, and the lower plate extension of rotor balances connects
Connect airframe models balance.
In the above-mentioned technical solutions, the upper flat plate of airframe models balance and airframe models are connected by truss structure.
In the above-mentioned technical solutions, airframe models are not any with other in addition to connecting with the upper flat plate of airframe models balance
Component contact.
In the above-mentioned technical solutions, the two sides of the rotor torque balance are respectively mounted elastic coupling.
In the above-mentioned technical solutions, the dimension Transfer rack translation mechanism includes the cross lead screw for providing transverse shifting, provides
The tail-rotor examination that the longitudinal screw mandrel of longitudinal movement, the tail-rotor height adjustment driver for providing height change and offer slightly axially rotate
Test platform column.
In the above-mentioned technical solutions, during model test, rotor model.test system follows turntable to rotate together to change
Be connected the yaw angles of airframe models on it, and pitch angle driving mechanism drives bowing for rotor and airframe models by moving up and down
Elevation angle variation, four-dimensional Transfer rack changes position according to the variation of fuselage yaw angle, pitch angle, to guarantee tail-rotor with respect to fuselage mould
The relative position of type is constant.
In the above-mentioned technical solutions, the tail-rotor testing stand column of the four-dimensional Transfer rack can be realized drives along tail-rotor height adjustment
The axial slightly rotation of dynamic device, to guarantee that the Plane of rotation of tail-rotor is parallel with the longitudinal cross-section of airframe models or at certain angle
Degree.
In the above-mentioned technical solutions, mountable horizontal tail, vertical fin, short limb, carry object etc. on airframe models, and it is mating corresponding
Measuring device can further measure the aerodynamic force of the other components such as horizontal tail, vertical fin, short limb, carry object.
In the above-mentioned technical solutions, pressure tap, mating corresponding survey are provided on airframe models and all parts thereon
Device is measured, corresponding pressure measurement is carried out.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
Can real simulation lifting airscrew, fuselage, the triangular movement of tail-rotor, and then study three between it is pneumatic do
It disturbs；Meanwhile increasing horizontal tail, vertical fin, short limb, carry object etc. on airframe models, and mating corresponding measuring device, it can be further
The aerodynamic interference of horizontal tail, vertical fin, short limb, the other components such as carry object is studied, and then is made up pneumatic between each component of domestic helicopter
The deficiency of the Study of Interference ability, and improve China's helicopter W.T test research system.Moreover, the overall structure of the device is opposite
Simply, implementation cost is relatively low；Wind-tunnel blockage percentage is small, and test data precision is reliable.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is a kind of D structure figure of helicopter built-up pattern experimental rig of the present invention；
Wherein：1 is rotor, and 2 be rotor control mechanism, and 3 be rotor balances, and 4 be airframe models, and 5 be rotor torque balance,
6 be COMBINATION MODEL tapered pole, and 7 be movable retarder, and 8 be wind tunnel floor, and 9 be that wind-tunnel is servo-actuated turntable, and 10 be turntable, 11
It is COMBINATION MODEL pedestal, 12 be rotor motor, and 13 be rotor pitch angle driving mechanism, and 14 be tail-rotor motor support frame,
15 be airframe models balance, and 16 be tail-rotor operating mechanism, and 17 be tail-rotor torsion balance, and 18 be tail-rotor, and 19 be angle retarder, and 20 are
Tail-rotor motor, 21 be tail-rotor balance, and 22 be tail-rotor height adjustment driver, and 23 be tail-rotor testing stand column, and 24 be longitudinal screw mandrel,
25 be cross lead screw.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
As shown in Fig. 1, built-up pattern experimental rig of the invention includes：Rotor, rotor control mechanism, airframe models, machine
Body model balance, turntable, and by rotor balances, COMBINATION MODEL tapered pole, movable retarder, COMBINATION MODEL
Pedestal, rotor motor, the COMBINATION MODEL of rotor pitch angle driving mechanism composition, by tail-rotor operating mechanism, tail-rotor torque
The tail-rotor testing stand that balance, tail-rotor, angle retarder, tail-rotor motor, tail-rotor motor support frame, tail-rotor balance form, and by tail
The four-dimensional Transfer rack that paddle height adjustment driver, tail-rotor testing stand column, longitudinal screw mandrel, cross lead screw form.
COMBINATION MODEL is mounted on turntable, and rotor control mechanism is fixedly mounted on rotor balances upper flat plate, fuselage
The lower plate of model balance is fixedly connected on the lower plate extension of rotor balances, the upper flat plate and fuselage mould of airframe models balance
Type is connected by truss structure, and airframe models do not connect in addition to connecting with the upper flat plate of airframe models balance with other any parts
Touching；Tail-rotor testing stand is mounted on wind tunnel floor by four-dimensional Transfer rack, the four-dimension Transfer rack can according to fuselage yaw angle, bow
The variation at the elevation angle changes the position of tail-rotor, to guarantee that tail-rotor is constant with respect to the relative position of airframe models, under tail-rotor balance
Plate is fixedly connected on tail-rotor height adjustment driver, and tail-rotor motor is fixedly connected on tail-rotor day by tail-rotor motor support frame
Output power is transferred to tail-rotor by angle retarder by flat upper flat plate, tail-rotor motor, and the tail-rotor testing stand column can be realized
Tail-rotor testing stand along axial slightly rotation, thus guarantee the Plane of rotation of tail-rotor it is parallel with the longitudinal cross-section of airframe models or at
Certain angle.
Generally, the yaw angle of airframe models realizes that the pitch angle of airframe models is bowed by rotor by the rotation of turntable
The promotion COMBINATION MODEL tapered pole of elevation angle driving mechanism leans forward realization, and airframe models are changing yaw angle and pitch angle
When, tail-rotor is accordingly changed position, and is led to by the longitudinal screw mandrel of four-dimensional Transfer rack, cross lead screw, tail-rotor height adjustment driver
The tail-rotor testing stand column for crossing four-dimensional Transfer rack changes the Plane of rotation of tail-rotor.The aerodynamic loading of rotor passes through rotor balances and rotation
Wing torsion balance measures, and the aerodynamic loading of airframe models is measured by airframe models balance, the aerodynamic loading of tail-rotor
It is measured by the gentle tail-rotor torsion balance in tail-rotor day.During test, rotor balances, the gentle airframe models in rotor torque day
Balance is wrapped up by fuselage, and not by interference in air flow, and the gentle tail-rotor torsion balance in tail-rotor day should install corresponding windshield device, is avoided
Air-flow enters inside balance, interference test measurement result accuracy.
Replace various forms of airframe models, rotor（2 blades or more）, tail-rotor（Seesaw type, scissor etc.）,
Experimental study can be carried out as above.Mountable horizontal tail, vertical fin, short limb, carry object etc. on the airframe models, and mating phase
The measuring device answered can further measure the aerodynamic force of the other components such as horizontal tail, vertical fin, short limb, carry object.The airframe models
With can increase pressure tap on each component, mating corresponding measuring device, the pressure that can be carried out on airframe models and each component is surveyed
Amount.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (6)
1. a kind of helicopter built-up pattern experimental rig, including rotor model.test system and tail-rotor testing stand, it is characterised in that the rotation
Airfoil test platform bottom is provided with rotary turntable, and pitch angle driving mechanism, the rotation are provided on the rotor model.test system
The top of airfoil test platform is used to connect the rotor of helicopter, and the top of the tail-rotor testing stand is used to connect the tail-rotor of helicopter,
The bottom of tail-rotor testing stand is connected on four-dimensional Transfer rack.
2. a kind of helicopter built-up pattern experimental rig according to claim 1, it is characterised in that airframe models package rotation
Lower half, rotor balances and the rotor torque balance of wing operating mechanism, the upper flat plate of the rotor control mechanism and rotor balances
It is fixedly connected, the lower plate extension of rotor balances connects airframe models balance.
3. a kind of helicopter built-up pattern experimental rig according to claim 2, it is characterised in that airframe models balance
Upper flat plate and airframe models are connected by truss structure.
4. a kind of helicopter built-up pattern experimental rig according to claim 3, it is characterised in that airframe models remove and machine
The upper flat plate connection of body model balance is outer, does not contact with other any parts.
5. a kind of helicopter built-up pattern experimental rig according to claim 2, it is characterised in that the rotor torque day
Flat two sides are respectively mounted elastic coupling.
6. a kind of helicopter built-up pattern experimental rig according to claim 1, it is characterised in that the four-dimension Transfer rack
Including providing the cross lead screw of transverse shifting, the longitudinal screw mandrel for providing longitudinal movement, providing the tail-rotor height adjustment of height change
The tail-rotor testing stand column that driver and offer slightly axially rotate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820578725.2U CN208109379U (en) | 2018-04-23 | 2018-04-23 | A kind of helicopter built-up pattern experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820578725.2U CN208109379U (en) | 2018-04-23 | 2018-04-23 | A kind of helicopter built-up pattern experimental rig |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208109379U true CN208109379U (en) | 2018-11-16 |
Family
ID=64116020
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820578725.2U Expired - Fee Related CN208109379U (en) | 2018-04-23 | 2018-04-23 | A kind of helicopter built-up pattern experimental rig |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208109379U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108593243A (en) * | 2018-04-23 | 2018-09-28 | 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 helicopter built-up pattern experimental rig |
| CN110261057A (en) * | 2019-07-03 | 2019-09-20 | 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 lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN110844113A (en) * | 2019-10-12 | 2020-02-28 | 中国直升机设计研究所 | Rigid coaxial dual-rotor test bed capable of simultaneously measuring upper and lower rotor loads |
| CN111175014A (en) * | 2020-02-28 | 2020-05-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Balance system and method for accurately measuring rotor wing pneumatic load |
| CN112798220A (en) * | 2021-04-13 | 2021-05-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device for tail boom type helicopter rotor wing model |
| CN113670561A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test simulation method for obtaining aerodynamic interference characteristic of helicopter tail rotor |
| CN113753261A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN113753262A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Device and method for measuring flow field speed of horizontal tail area of helicopter |
| CN114919772A (en) * | 2022-06-02 | 2022-08-19 | 燕山大学 | Rotating mechanical fault simulation experiment table for single-rotor unmanned helicopter with tail rotor |
-
2018
- 2018-04-23 CN CN201820578725.2U patent/CN208109379U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108593243B (en) * | 2018-04-23 | 2024-02-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter combined model test device |
| CN108593243A (en) * | 2018-04-23 | 2018-09-28 | 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 helicopter built-up pattern experimental rig |
| CN110261057A (en) * | 2019-07-03 | 2019-09-20 | 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 lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN110844113A (en) * | 2019-10-12 | 2020-02-28 | 中国直升机设计研究所 | Rigid coaxial dual-rotor test bed capable of simultaneously measuring upper and lower rotor loads |
| CN111175014A (en) * | 2020-02-28 | 2020-05-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Balance system and method for accurately measuring rotor wing pneumatic load |
| CN112798220A (en) * | 2021-04-13 | 2021-05-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device for tail boom type helicopter rotor wing model |
| CN112798220B (en) * | 2021-04-13 | 2021-06-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device for tail boom type helicopter rotor wing model |
| CN113670561A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test simulation method for obtaining aerodynamic interference characteristic of helicopter tail rotor |
| CN113670561B (en) * | 2021-10-21 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test simulation method for obtaining aerodynamic interference characteristic of helicopter tail rotor |
| CN113753262A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Device and method for measuring flow field speed of horizontal tail area of helicopter |
| CN113753262B (en) * | 2021-11-09 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Device and method for measuring flow field speed of horizontal tail area of helicopter |
| CN113753261A (en) * | 2021-11-09 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN114919772A (en) * | 2022-06-02 | 2022-08-19 | 燕山大学 | Rotating mechanical fault simulation experiment table for single-rotor unmanned helicopter with tail rotor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN208109379U (en) | A kind of helicopter built-up pattern experimental rig | |
| CN108593243A (en) | A kind of helicopter built-up pattern experimental rig | |
| CN102157089B (en) | Simulation device for steering wheel of airplane flight simulator | |
| CN103837322B (en) | A kind of water surface flying device hydrodynamic performance test method | |
| CN103954426B (en) | A kind of rotor dynamic testing equipment | |
| CN101726401B (en) | Scale measuring device for pitching dynamic derivative experiment | |
| CN205642791U (en) | Wind -tunnel is with toper motion simulation device of rotatory guided missile | |
| CN102305699A (en) | Wind tunnel experiment system for free flight model | |
| CN108454882B (en) | Control surface driving and control surface angle measuring mechanism | |
| CN203811349U (en) | Rotor dynamic test device | |
| CN105547676A (en) | Multifunctional swing-arm type rotor wing test stand | |
| CN102175420A (en) | Two-degrees-of-freedom supporting system for wind tunnel test of airplane | |
| CN102494865A (en) | Simulation apparatus of pitching/jawing/rolling over three-freedom degree forced movement of aircraft | |
| CN106564617A (en) | FLAP control plane loading device and function testing method | |
| CN106679930A (en) | Vehicle-mounted aerodynamic force and power test-measurement method and device of small unmanned aerial vehicle (UAV) | |
| CN102879171A (en) | Support system for entire pressure test in airplane | |
| CN105151280A (en) | Aircraft empennage regulation mechanism with pitching and yawing completely decoupled | |
| CN107021222A (en) | From the flapping wing capacitation device of active flaps | |
| CN208070050U (en) | A kind of driving of rudder face and rudder face angle measuring mechanism | |
| CN205209729U (en) | Wing section strutting arrangement | |
| CN104655417B (en) | Device for testing high and low temperature performance of certain indexing mechanism of space station | |
| CN206648802U (en) | A kind of pitching dynamic derivative experimental provision of tail vibration | |
| CN206140958U (en) | Crossbeam formula polar coordinates 3D printer | |
| CN106965953A (en) | A kind of Retracting Or Lowering Aerodynamic Loads On Landing Gear analogue means and its loading method | |
| CN209264241U (en) | For improving the device of the thrust test accuracy of ducted fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181116 Termination date: 20210423 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |