CN110261057A - A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system - Google Patents
A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system Download PDFInfo
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- CN110261057A CN110261057A CN201910594533.XA CN201910594533A CN110261057A CN 110261057 A CN110261057 A CN 110261057A CN 201910594533 A CN201910594533 A CN 201910594533A CN 110261057 A CN110261057 A CN 110261057A
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- 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
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- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- 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
- G01M9/08—Aerodynamic models
Abstract
The invention discloses a kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system, including airframe models, airframe models balances, main rotor, main rotor drive system, pulp distance varying mechanism, main rotor balance, torsion balance, tail-rotor, tail-rotor drive system, tail-rotor balance, support system, control system and measuring system；Pass through the posture of built-up pattern during the support system Control experiment；The control system realizes main rotor revolving speed, main rotor pitch and the tail-rotor revolving speed that wind tunnel test needs by the movement of control main rotor drive system, pulp distance varying mechanism and tail-rotor drive system；The aerodynamic loading that the measuring system is obtained the aerodynamic loading of main rotor by the gentle torsion balance in main rotor day, the aerodynamic loading of tail-rotor is obtained by tail-rotor balance, obtains airframe models by airframe models balance.The present invention is suitable for carrying out rotor/tail-rotor interference characteristic research, and improves the precision of test.
Description
Technical field
The present invention relates to a kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test systems, belong to wind tunnel test
Technical field.
Background technique
Helicopter has the characteristics that not depending on airfield runway, VTOL, hovering, all around flight can be achieved,
It is played an important role in the development of the national economy and the modernization of national defense.Especially helicopter has quick, motor-driven, ultralow
Sky flight can arrive at the outstanding features such as any shaped area and advantage, increasingly wider in the application such as military, guarantee and rescue
It is general.
Compared to fixed wing aircraft, the technical problems such as aerodynamic characteristics, aeroelasticity and noise of helicopter want complicated.
Various countries develop the experiences and lessons explanation of helicopter, as quick, accurate, economic wind tunnel test in helicopter development process
Effect that is very necessary and playing key.The wind tunnel test of helicopter includes full machine and its component test, the dress of full machine test
It sets and generally includes power drive system (power source and transmission mechanism of driving rotor), model (main rotor, fuselage)/built-up pattern
(rotor+fuselage), model manipulation control device (for the revolving speed of rotor, pitch and rotor and the gesture stability of model etc.),
Test device (for measuring aerodynamic characteristic, aeroelasticity and noise etc.), data acquisition processing system and security monitoring and report
Alert system etc..
For the characteristic of accurate simulation helicopter, the full machine test of helicopter W.T test should include tail-rotor and main rotor
Interference effect research between tail-rotor.And the size limitation of the limitation especially model inner space due to technical conditions, combination
Model only includes main rotor and fuselage, only in the transmission mechanism of model disposed outside tail-rotor, this meeting containing tail-rotor
Precision, the efficiency etc. of test are impacted.
Summary of the invention
Goal of the invention of the invention is: in view of the above problems, providing a kind of lifting airscrew, fuselage and tail-rotor
Built-up pattern wind tunnel test system, the present invention meet helicopter aerodynamic characteristic, aeroelasticity and noise etc. research.
The technical solution adopted by the invention is as follows:
A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system, including airframe models, airframe models day
It is flat, main rotor, main rotor drive system, pulp distance varying mechanism, main rotor balance, torsion balance, tail-rotor, tail-rotor drive system, tail
Paddle balance, support system, control system and measuring system；
The control system is connected with main rotor drive system, pulp distance varying mechanism, tail-rotor drive system；The measuring system
It is connected with main rotor balance, torsion balance, airframe models balance, tail-rotor balance；
Pass through the posture of built-up pattern during the support system Control experiment；
The control system by the movement of control main rotor drive system, pulp distance varying mechanism and tail-rotor drive system come
Realize main rotor revolving speed, main rotor pitch and tail-rotor revolving speed that wind tunnel test needs；
The measuring system is obtained the aerodynamic loading of main rotor by the gentle torsion balance in main rotor day, passes through tail-rotor balance
It obtains the aerodynamic loading of tail-rotor, obtain the aerodynamic loading of airframe models by airframe models balance.
Preferably, the airframe models balance, main rotor drive system, main rotor balance, torsion balance, tail-rotor driving
System and tail-rotor balance are connected by rigid member and the strut of support system.
Preferably, the first stiff baseplate, the airframe models balance, main rotor balance are arranged inside the airframe models
It being connect with the fixing end of tail-rotor balance with the first stiff baseplate, the airframe models are connect with the floating end of airframe models balance,
Main rotor is connect with the floating end of main rotor balance, and tail-rotor is connect with the floating end of tail-rotor balance.First stiff baseplate not with machine
The contact of body model.
Preferably, owner's rotor drive system is located at outside airframe models, including main rotor motor and connect with it
The retarder and main shaft connect, main rotor motor and retarder are installed on the second stiff baseplate.
Preferably, second stiff baseplate is connect by the first strut with support system, pass through the second strut and the
The connection of one stiff baseplate.
Preferably, radome fairing is arranged outside the main rotor motor and speed reducer.
Preferably, described main shaft one end passes through main rotor balance, torsion balance and pulp distance varying mechanism and main rotor
Rotation axis be connected, the other end is connected with speed reducer.
Preferably, the both ends of the torsion balance are connected with the propeller hub of main rotor and main shaft respectively.
Preferably, the mounting base of the pulp distance varying mechanism is connected with the floating end of main rotor balance.
Preferably, the tail-rotor drive system is located at airframe models tail portion cavity, including tail-rotor motor, the first tail-rotor pass
Moving axis, the first commutator, the second tail rotor driving shafts, the second commutator；The tail-rotor drive system is installed on pedestal, the base
Seat is connect with the floating end of tail-rotor balance.Tail-rotor drive system is not contacted with airframe models.
Preferably, tail-rotor motor will rotation by the first tail rotor driving shafts, the first commutator, the second tail rotor driving shafts,
Second commutator passes to tail-rotor, and tail-rotor is connected on the output shaft of the second commutator.The pitch adjustment of tail-rotor is by replacing not
With tail-rotor propeller hub realize.
Preferably, main rotor balance, torsion balance, airframe models balance, the power supply of tail-rotor balance and measurement signal line
Cable and tail-rotor motor, main rotor motor, the control of pulp distance varying mechanism motor and power cable, by edge support inside model
Substrate, the first stiff baseplate and the second stiff baseplate are drawn, and along strut respectively with external measuring system and control system phase
Even.
Preferably, further including the microphone for being arranged in the Flow Field in Wind Tunnel periphery of built-up pattern wind tunnel test system, camera shooting
Head and non-contact measurement device for measuring, and be connected with measuring system, to obtain the flow field around built-up pattern wind tunnel test system, noise
With blade deformation etc. data.
Preferably, the non-contact measurement device for measuring includes CCD camera and particle rapidity tester.
A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system of the invention, pacifies according to following sequence
Dress: the second strut is connect with the second stiff baseplate for installing main rotor motor and speed reducer, and the second stiff baseplate passes through the
One strut is connect with support system；Second strut upper end is connect with stiff baseplate, and main rotor balance, airframe models day is gentle
The fixing end of tail-rotor balance is connected on the first stiff baseplate；Main shaft is passed through into main rotor balance, torsion balance and variable pitch
Spacing mechanism is connected with the rotation axis of main rotor；The mounting base of pulp distance varying mechanism is connected with the floating end of main rotor balance；By tail
Paddle motor, the first tail rotor driving shafts, the first commutator, the second tail rotor driving shafts, the second commutator are sequentially arranged on pedestal, and
Pedestal entirety is connect with the floating end of tail-rotor balance；By tail-rotor motor, main rotor motor and pulp distance varying mechanism motor, and master
The relevant cables of the gentle tail-rotor balance in rotor balances, torsion balance, airframe models day from built-up pattern draw, along the second strut,
First strut and support system are connected with the control system on periphery and measuring system；Airframe models are mounted on the floating of fuselage balance
On moved end；Tail-rotor is mounted on the output shaft of the second commutator；Radome fairing is mounted on the second stiff baseplate.By above
Step, the installation of complete device, debugging is normal, starts relevant wind tunnel test at once.
In the present invention, support system is adjusted the posture (including yaw angle and pitch angle) of entire airframe models；It is main
The revolving speed of rotor is according to requiring to be adjusted by control system；The revolving speed of tail-rotor is according to requiring to be adjusted by control system；The paddle of main rotor
Away from according to requiring to be adjusted by control system.It can be by airframe models balance, tail-rotor balance, main rotor balance after control more than completing
The measurement for starting relevant aerodynamic loading by measuring system with torsion balance, the non-contact biography arranged additionally by model periphery
Sensor, microphone and camera etc. obtain the data such as flow field, noise and blade deformation around built-up pattern by measuring system.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are: to meet helicopter pneumatically special
Property, aeroelasticity and noise etc. research and the related wind tunnel test of development needs；Since built-up pattern periphery is not other
Extra component affecting is suitable for carrying out rotor/tail-rotor interference characteristic research, and improves the precision of test.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 is the built-up pattern structure chart of helicopter fuselage, main rotor and built-in tail-rotor mechanism.
Marked in the figure: 1- airframe models, 2- airframe models balance, 3- main rotor, 4- pulp distance varying mechanism, 5- main rotor day
Flat, 6- torsion balance, 7- tail-rotor, 8- tail-rotor balance, 9- support system, the first stiff baseplate of 11-, the second stiff baseplate of 12-,
13- pedestal, the first strut of 21-, the second strut of 22-, 31- main rotor motor, 32- retarder, 33- main shaft, 34- rectification
Cover, 71- tail-rotor motor, the first tail rotor driving shafts of 72-, the first commutator of 73-, the second tail rotor driving shafts of 74-, 75- second commutation
Device.
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.
Any feature disclosed in this specification unless specifically stated can be equivalent or with similar purpose by other
Alternative features are replaced.That is, unless specifically stated, each feature is an example in a series of equivalent or similar characteristics
?.
As shown in Figure 1, a kind of lifting airscrew of the present embodiment, fuselage and tail-rotor built-up pattern wind tunnel test system, packet
Include airframe models 1, airframe models balance 2, main rotor 3,3 drive system of main rotor, pulp distance varying mechanism 4, main rotor balance 5, torsion
Square balance 6, tail-rotor 7,7 drive system of tail-rotor, tail-rotor balance 8, support system 9, control system and measuring system.
First stiff baseplate 11, the airframe models balance 2, main rotor balance 5 and tail are set inside the airframe models 1
The fixing end of paddle balance 8 is connect with the first stiff baseplate 11, and the airframe models 1 are connect with the floating end of airframe models balance 2.
First stiff baseplate 11 is not contacted with airframe models 1.
3 drive system of owner's rotor is located at 1 lower part of airframe models, including main rotor motor 31 and connected to it subtracts
Fast device 32 and main shaft 33, main rotor motor 31 and retarder 32 are installed on the second stiff baseplate 12.
Second stiff baseplate 12 is connect by the first strut 21 with support system 9, and the second strut 22 and first is passed through
Stiff baseplate 11 connects.
Radome fairing 34 is set outside the main rotor motor 31 and speed reducer.
Turn that described 33 one end of main shaft passes through main rotor balance 5, torsion balance 6 and pulp distance varying mechanism 4 and main rotor 3
Moving axis is connected, and the other end is connected with speed reducer.
The both ends of the torsion balance 6 are connected with the propeller hub of main rotor 3 and main shaft 33 respectively.
The mounting base of the pulp distance varying mechanism 4 is connected with the floating end of main rotor balance 5.
7 drive system of tail-rotor is located at 1 tail portion cavity of airframe models, including tail-rotor motor 71, the first tail rotor driving shafts
72, the first commutator 73, the second tail rotor driving shafts 74, the second commutator 75；7 drive system of tail-rotor is installed on pedestal 13
On, the pedestal 13 is connect with the floating end of tail-rotor balance 8.7 drive system of tail-rotor is not contacted with airframe models 1.
Rotation is passed through the first tail rotor driving shafts 72, the first commutator 73, the second tail rotor driving shafts 74, the by tail-rotor motor 71
Two commutators 75 pass to tail-rotor 7, and tail-rotor 7 is connected on the output shaft of the second commutator 75.
Main rotor balance 5, torsion balance 6, airframe models balance 2, the power supply of tail-rotor balance 8 and measuring signal cable, and
Tail-rotor motor 71, main rotor motor 31, the control of 4 motor of pulp distance varying mechanism and power cable, by edge support inside model
Substrate, the first stiff baseplate 11 and the second stiff baseplate 12 are drawn, and are with external measuring system and control respectively along strut
System is connected.
It further include the microphone for being arranged in the Flow Field in Wind Tunnel periphery of built-up pattern wind tunnel test system, camera, CCD camera
With particle rapidity tester, and be connected with measuring system, with obtain the flow field around built-up pattern wind tunnel test system, noise and
The data such as blade deformation.
In the present invention, support system is adjusted the posture (including yaw angle and pitch angle) of entire airframe models；It is main
The revolving speed of rotor is according to requiring to be adjusted by control system；The revolving speed of tail-rotor is according to requiring to be adjusted by control system；The paddle of main rotor
Away from according to requiring to be adjusted by control system.It can be by airframe models balance, tail-rotor balance, main rotor balance after control more than completing
The measurement for starting relevant aerodynamic loading by measuring system with torsion balance, the non-contact biography arranged additionally by model periphery
Sensor, microphone and camera etc. obtain the data such as flow field, noise and blade deformation around built-up pattern by measuring system.
In conclusion using a kind of lifting airscrew of the invention, fuselage and tail-rotor built-up pattern wind tunnel test system, it is full
The needs of sufficient helicopter aerodynamic characteristic, aeroelasticity and noise etc. research and the related wind tunnel test of development；Due to combination die
Type periphery does not have other extra component affectings, is suitable for carrying out rotor/tail-rotor interference characteristic research, and improve the accurate of test
Degree.
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 (10)
1. a kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that: including airframe models
(1), airframe models balance (2), main rotor (3), main rotor (3) drive system, pulp distance varying mechanism (4), main rotor balance (5),
Torsion balance (6), tail-rotor (7), tail-rotor (7) drive system, tail-rotor balance (8), support system (9), control system and measurement system
System；
The control system is connected with main rotor (3) drive system, pulp distance varying mechanism (4), tail-rotor (7) drive system；The survey
Amount system is connected with main rotor balance (5), torsion balance (6), airframe models balance (2), tail-rotor balance (8)；
Pass through the posture of built-up pattern during the support system (9) Control experiment；
The control system passes through control main rotor (3) drive system, pulp distance varying mechanism (4) and tail-rotor (7) drive system
Move main rotor (3) revolving speed, main rotor (3) pitch and tail-rotor (7) revolving speed to realize wind tunnel test needs；
The measuring system obtains the aerodynamic loading of main rotor (3) by main rotor balance (5) and torsion balance (6), passes through tail
Paddle balance (8) obtains the aerodynamic loading of tail-rotor (7), obtains the aerodynamic loading of airframe models (1) by airframe models balance (2).
2. lifting airscrew as described in claim 1, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
The first stiff baseplate (11) are set inside the airframe models (1), the airframe models balance (2), main rotor balance (5) and tail
The fixing end of paddle balance (8) is connect with the first stiff baseplate (11), and the airframe models (1) are floating with airframe models balance (2)
Moved end connection.
3. lifting airscrew as claimed in claim 2, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
Owner's rotor (3) drive system is located at airframe models (1) outside, including main rotor motor (31) and deceleration connected to it
Device (32) and main shaft (33), main rotor motor (31) and retarder (32) are installed on the second stiff baseplate (12).
4. lifting airscrew as claimed in claim 3, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
Second stiff baseplate (12) is connect by the first strut (21) with support system (9), is passed through the second strut (22) and first
Stiff baseplate (11) connection.
5. lifting airscrew as claimed in claim 3, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
Radome fairing (34) are set outside the main rotor motor (31) and speed reducer.
6. lifting airscrew as claimed in claim 3, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
The main shaft (33) passes through the rotation of main rotor balance (5), torsion balance (6) and pulp distance varying mechanism (4) and main rotor (3)
Axis is connected.
7. lifting airscrew as claimed in claim 3, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
The both ends of the torsion balance (6) are connected with the propeller hub of main rotor (3) and main shaft (33) respectively.
8. lifting airscrew as described in claim 1, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
The mounting base of the pulp distance varying mechanism (4) is connected with the floating end of main rotor balance (5).
9. lifting airscrew as described in claim 1, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
Tail-rotor (7) drive system is located at airframe models (1) tail portion cavity, including tail-rotor motor (71), the first tail rotor driving shafts
(72), the first commutator (73), the second tail rotor driving shafts (74), the second commutator (75)；Tail-rotor (7) the drive system installation
In on pedestal (13), the pedestal (13) connect with the floating end of tail-rotor balance (8).
10. lifting airscrew as described in claim 1, fuselage and tail-rotor built-up pattern wind tunnel test system, it is characterised in that:
It further include microphone, the camera for being arranged in the Flow Field in Wind Tunnel periphery of built-up pattern wind tunnel test system, dedicated non-contact survey
Device is measured, to obtain the data such as the flow field around built-up pattern wind tunnel test system, noise and blade deformation.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910594533.XA CN110261057A (en) | 2019-07-03 | 2019-07-03 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN202010584908.7A CN111721493B (en) | 2019-07-03 | 2020-06-24 | Helicopter combined model wind tunnel test device with independent tail rotor device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910594533.XA CN110261057A (en) | 2019-07-03 | 2019-07-03 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
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| CN110261057A true CN110261057A (en) | 2019-09-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910594533.XA Pending CN110261057A (en) | 2019-07-03 | 2019-07-03 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN202010584908.7A Active CN111721493B (en) | 2019-07-03 | 2020-06-24 | Helicopter combined model wind tunnel test device with independent tail rotor device |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010584908.7A Active CN111721493B (en) | 2019-07-03 | 2020-06-24 | Helicopter combined model wind tunnel test device with independent tail rotor device |
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| CN110901951A (en) * | 2019-11-15 | 2020-03-24 | 哈尔滨飞机工业集团有限责任公司 | Multifunctional tail rotor test system |
| CN111537185A (en) * | 2020-04-03 | 2020-08-14 | 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 system for tail boom type helicopter rotor model |
| CN111649907A (en) * | 2020-05-14 | 2020-09-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Rib strip type micro-axial force annular two-component strain balance |
| 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 |
| CN113567083A (en) * | 2021-09-22 | 2021-10-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Multi-component aerodynamic interference characteristic test simulation method for full-motion horizontal tail helicopter |
| CN113567083B (en) * | 2021-09-22 | 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 | Multi-component aerodynamic interference characteristic test simulation method for full-motion horizontal tail helicopter |
| CN113670560B (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 | Pneumatic load measuring device of horizontal tail |
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| 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 |
| CN113753261B (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 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
| CN113884268A (en) * | 2021-12-08 | 2022-01-04 | 中国空气动力研究与发展中心低速空气动力研究所 | Longitudinal aerodynamic characteristic test and analysis method for full-dynamic horizontal tail helicopter body |
| CN113884268B (en) * | 2021-12-08 | 2022-02-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Longitudinal aerodynamic characteristic test and analysis method for full-dynamic horizontal tail helicopter body |
| CN116754174A (en) * | 2023-08-16 | 2023-09-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Layout conversion method for thrust-tension type tail rotor of helicopter wind tunnel test |
| CN116754174B (en) * | 2023-08-16 | 2023-10-31 | 中国空气动力研究与发展中心低速空气动力研究所 | Layout conversion method for thrust-tension type tail rotor of helicopter wind tunnel test |
| CN117782508A (en) * | 2024-02-23 | 2024-03-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter tail rotor mechanism for wind tunnel test and tail rotor variable pitch control method |
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| CN111721493B (en) | 2021-02-02 |
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