CN108106814A - A kind of four hair propeller aeroplane model in wind tunnel based on air motor - Google Patents
A kind of four hair propeller aeroplane model in wind tunnel based on air motor Download PDFInfo
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- CN108106814A CN108106814A CN201711053498.8A CN201711053498A CN108106814A CN 108106814 A CN108106814 A CN 108106814A CN 201711053498 A CN201711053498 A CN 201711053498A CN 108106814 A CN108106814 A CN 108106814A
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention discloses a kind of model in wind tunnel of the four hair propeller aeroplanes based on air motor, supporting item one end is connected with wind-tunnel balance rack, and the other end is mounted on by pole support connector, air bridges on main balance；Empennage, wing components are mounted on fuselage, and middle fuselage is connected on balance connector, and the balance connector other end is mounted on main balance, and full machine active force is transmitted to by balance connector on main balance；Wing flap and aileron are connected by each becoming cornual plate with wing stabilization；Measure the power and torque of propeller during wind tunnel test in real time by rotation axis balance；Volume control device is mounted on fuselage interior, and the output power of air motor is controlled by controlling gas flow.The present invention proposes the model in wind tunnel design method that propeller power simulation is carried out using air motor, improves flow field similarity degree in propeller dynamic simulation trial, effectively increases wind tunnel test the data precision.
Description
Technical field
The present invention relates to airplane aerodynamic design fields more particularly to propeller aeroplane model dynamic effect wind tunnel test to lead
Domain.
Background technology
It is domestic newly to grind or plan the new whirlpool paddle aircraft developed as aeronautical technology both domestic and external develops, generally employ
High-power whirlpool paddle dynamical system, whirlpool paddle dynamic effect significantly increase；Meanwhile it is limited by some particular service requirements, part spiral shell
It is smaller to revolve the takeoff speed of paddle aircraft, further increases dynamic effect amount；These factors greatly improved in wind tunnel test
The requirement of model propeller power-driven system analog capability (i.e. driving power), the conventional motor driving used domestic at present
Drive test method cannot meet the dynamic simulation trial requirement of tension coefficient and test Mach number simultaneously, and be subject to by material
Material manages the restriction of inherent characteristic, under conditions of motor volume is severely limited, it is difficult to continue to improve the output work of motor
Rate, therefore continue to be difficult to meet model propeller power-driven system analog capability requirement using motor drive mode.It is prominent
The insufficient bottleneck of broken model propeller drive system output power, new power analogue technique employ compressed air-driven whirlpool paddle
Dynamic simulator driving experiment model propeller, rotation is converted into using whirlpool paddle dynamic simulator by pressure-air potential energy (and thermal energy)
Turn mechanical energy, under the limitation of same motor volume size, substantially increase output power, meet high-power whirlpool paddle aircraft and move
The wind tunnel test simulation that power influences needs；Simultaneously because employing air driving, serious electromagnetism is done when avoiding electric current driving
Disturb problem；In addition, to further improve the test accuracy of power simulation, trebuchet is installed in each engine nacelle, in real time
Measuring the direct force of engine influences, and realizes engine direct relay and the separation of slip-stream influence amount.But inevitably, based on reality
Existing function above, by each component of aircraft, the intake and exhaust pipeline of air motor and air flow control unit, the main balance measurement of interior formula
In system and engine nacelle the compositions such as auxiliary measurement system of rotary balance complex model construct so that model design,
The difficulty of processing greatly improves.
The content of the invention
Goal of the invention
It proposes a kind of model in wind tunnel of four hairs propeller aeroplane, can solve the problems, such as present in technical background.It should
Invention provides a kind of design method of test model of the type aircraft, solves in four hair propeller aeroplane dynamic simulation trials
To tension coefficient and mach-number simulation problem, improving its experimental technique ability and wind tunnel test slip-stream influences the accurate of data
Degree.
Technical solution
A kind of four hair propeller aeroplane model in wind tunnel based on air motor realize the accurate mould of propeller power
Fit the accurate measurement of slip-stream influence, it is characterised in that：Before oblique dorsal ventral support main strut 17 and 115, connector 114, fuselage
Section 11, middle fuselage 113, fuselage endpiece 116, vertical fin 18, horizontal tail 19, wing components 16, propeller component 22, discharge hoses road
24th, air bridges 15, main balance 112 and volume control device 12；One end of the oblique front support main strut 115 of model is supported mounted on wind-tunnel
On rack, the other end is connected by pole support connector 114 and air bridges 15, and air bridges 15 are connected with one end of main balance 112, main
The other end of balance 112 is mounted on connector 111, and connector 111 is connected on middle fuselage 113.Inside middle fuselage 113
Main balance 112, air bridges 15 are installed, middle fuselage 113 is fixedly connected with wing components 16 by pin hole；Wing components 16
It is made of wing stabilization, wing body radome fairing, float component, wing flap, aileron；Horizontal tail 19 is installed on vertical fin 18 by link block
On, vertical fin 18 is mounted on by positioning pin on fuselage endpiece 116；Discharge hoses road 24 by oblique dorsal ventral support main strut 17 and 115,
Discharge hoses road 24 forms continuous supply and exhaust system inside connector 114, air bridges 15, volume control device 12 and wing
System.
The discharge hoses road 24, using copper pipe, the connection mode of pipe joint is aided with block and pressure using welding form
Plate is fixed, for ensureing air-tightness, security and pressure requirements.
17 and 115 section of main strut of support device use symmetrical airfoil section, indoor design inlet and outlet venthole, with
The connection of main balance 112 and wind-tunnel supporting mechanism is fastened using positioning pin and screw.One side implementation model supports and ventilation work(
Can, the interference to wind tunnel test data is on the other hand reduced as far as possible.
Fuselage uses digital control processing after ZL205A aluminum castings, and average wall thickness is not less than 15mm, local location distribution reinforcing rib.
Respectively design a circle reinforcing rib before and after middle fuselage 113, to ensure to be reliably connected with nosing 11, fuselage endpiece 116, two
Four beams of genesis analysis between circle reinforcing rib, strengthen fuselage ring, realize the connection with wing components 16.Before middle fuselage 113
End design 30CrMnSiA structural alloy steel fuselage balances connector 114, to connect main balance 112.Pass of the fuselage as model
Key member while full machine stress is passed to main balance, both ensure that the intensity of model, while also reduce model as far as possible
Weight.
Main balance 112 is connected with air bridges 15, and temperature, the pressure influence that gases at high pressure are brought by air bridges 15 carry out
It eliminates, improves the measurement accuracy of main balance 112.
22 model of propeller component includes engine nacelle shell 14, connector 47, air motor 46, rotation axis balance
44th, propeller hub 43, blade 41 and spinner 42.Blade 41 uses carbon fiber+30CrMnSiA composite materials, and connector 47, propeller hub 43 are adopted
With 30CrMnSiA, engine nacelle shell 14, spinner 42 use 7050 aluminium digital control processings.Pass through rotation axis balance 44 and paddle
Leaf 41 is direct-connected, directly measures the direct force of propeller blade and influences, the measurement accuracy that making propellerslip influences greatly improves.
114 floor design of pole support connector has 10 Φ, 17 millimeters of through holes, uses sunk screw and oblique front support main strut 115
It is close to be connected, be additionally provided with 50 millimeters of through holes of 4 elliptical apertures and a Φ, facilitate control system electric wire and vent line conduit into
Go out.
Advantageous effect
The advantageous effect of the embodiment of the present invention is that the power simulation wind-tunnel technique of air motor driving may be employed,
It is identical that similar parameter crucial in power simulation has been effectively ensured, has improved the accuracy that drive tests slip-stream simulation；Simultaneously
Test Mach number is similar to actual airplane, obtains the test data closer to actual aerodynamic characteristic, and employs rotation axis
Balance measures propeller direct force, further improves the accuracy of test data, to measure the slip-stream of four hair propeller aeroplanes
Influence provides a kind of accurately and effectively mode.
Description of the drawings
Fig. 1 is one embodiment of the four hair propeller aeroplane model in wind tunnel provided by the invention based on air motor
Structural side view.And
Fig. 2 is one embodiment of the four hair propeller aeroplane model in wind tunnel provided by the invention based on air motor
Structure top view.
Fig. 3 is the structure diagram of the one embodiment on discharge hoses road inside wing.
Fig. 4 is the structure diagram of one embodiment of propeller component.
11 be nosing in Fig. 1, and 12 be volume control device, and 13 be supply air line, and 14 be engine nacelle, and 15 be sky
Air bridge, 16 be wing components, and 17 be oblique back up main strut, and 18 be vertical fin, and 19 be horizontal tail, 110 be undercarriage, 111 is balance company
Fitting, 112 be main balance, and 113 be middle fuselage, and 114 be pole support connector, and 115 be oblique front support main strut, and 116 be fuselage tail
Section.
21 be float component in Fig. 2, and 22 be propeller component, and 23 be aileron, and 24 be the discharge hoses road of air motor, 25
For wing flap.
31 be air motor intake interface in Fig. 3, and 32 be air motor supply air line, and 33 be air diverter, and 34 be stream
Amount control device exhaust pipe, 35 air motor exhaust pipes.
41 be blade in Fig. 4, and 42 be spinner, and 43 be propeller hub, and 44 be rotation axis balance, and 45 engine nacelle shells, 46 are
Air motor, 47 are connector.
Specific embodiment
With reference to Fig. 1-Fig. 4 in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.It is based on
Embodiment in invention, the every other reality that those of ordinary skill in the art are obtained without making creative work
Example is applied, belongs to the scope of protection of the invention.
Refering to Figure 1, embodiments of the present invention are：One end of the oblique front support main strut 115 of model is mounted on wind-tunnel
On support stand, the other end is connected by pole support connector 114 and air bridges 15, and air bridges 15 and one end of main balance 112 connect
It connects, the other end of main balance 112 is mounted on connector 111, and connector 111 is connected on middle fuselage 113.Wind tunnel test
When, the aerodynamic force suffered by aircraft is all transferred to by fuselage on connector 111, is then measured by main balance 112.
The air bridges mainly eliminate temperature, intake and exhaust pipeline influences the measurement accuracy of main balance.
The floor design of the connector 114 has 10 Φ, 17 millimeters of through holes, uses sunk screw and oblique front support main strut
115 is close connected, is additionally provided with 50 millimeters of through holes of 4 elliptical apertures and a Φ, facilitates control system electric wire and vent line conduit
Disengaging；The back side of the connector 114 is tightened together by 2 pin holes and 8 M16 screws with oblique back up main strut 17.
The oblique predominantly support interferences experiment of back up main strut 17 uses, and connection mode is identical with oblique front support main strut 115.Wind
Hole is subtracted by the result of the test of the oblique back up main strut 17 of same fashionable dress and oblique front support main strut 115 under oblique back up mode when testing
Result of the test obtains the support interferences amount of the oblique front support main strut 115 of model.
The wing components 16 are mounted on by pin on middle fuselage 113, and propeller component 114 is connected by nacelle
Part is mounted on wing.
The horizontal tail 19 is mounted on by horizontal tail connector on the vertical fin 18, and the vertical fin 18 passes through pin hole
It is mounted on after positioning on the fuselage endpiece 116.
The 12 extension set status of frame assembly be 116 3 sections of nosing 11, middle fuselage 113 and fuselage endpiece,
Using digital control processing after ZL205A aluminum castings, average wall thickness is not less than 15mm, local location distribution reinforcing rib.
Wing components 16, horizontal tail 19 and the vertical fin 18 uses aluminum alloy materials, pole support connector 114, day flushconnection
Part 111 is using superior alloy steel 30CrMnSiA.
To avoid generating aerodynamic balance measuring interference, supply source of the gas enters from oblique front support main strut 115, is connected by the strut
Fitting 114 enters air bridges 15, after the influences such as pressure, temperature are eliminated, into volume control device 12.
Particularly, the 12 design specialized suspender of frame assembly, by model integral hoisting into wind-tunnel and mounted on strut
On.
The float component 21 is mounted below wing.
The propeller component 22 shares 4 sets, and 2 sets of the installation respectively of the wing left and right sides is symmetrical.
The vent line 31~34 uses copper pipe, and for pipeline arrangement using being welded and fixed, the connection of conduit everywhere is similary
Air-tightness is ensured using welding manner.
For air motor to be driven to use, each nacelle has supply air line all the way and is vented all the way the supply air line 31
Pipeline, supply air line are connected with the gas exhaust piping of volume control device, and exhaust pipe is mixed at one at the nacelle of inside and is connected to
Evacuating air bridge.
During propeller-driven power wind tunnel test, compressed air enters from the oblique front support main strut 115, through the company
Fitting 114 enters the air bridges 15, then through the volume control device 12, is finally divided into 4 tunnels respectively through left and right
Supply air line 32 described in wing enters inside 4 engine nacelles, reaches the air motor 46, carries out energy conversion
Afterwards, from air motor 46 exclude gas through the gas exhaust piping 35, by the air bridges 15, pole support connector 114
It is discharged to oblique belly stay main strut 115 outside model.
The model takes into account unpowered and drive wind tunnel test, and the surface that section components can be met through simple refit is surveyed
The demand of pressure, hinge moment and power-boosting experiment.
The model and attachment are full machine dynamometer check model.
The above is the preferred embodiment of the present invention, it is noted that for those skilled in the art,
Various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also considered as this hair
Bright protection domain.
The hair propeller aeroplane model in wind tunnel of four based on air motor that the embodiment of the present invention proposes, including：Support
Device, main balance, fuselage, wing components, fin assembly, propeller component, discharge hoses road, air bridges and flow control dress
It puts.
Described support device one end is fixed on wind tunnel test supporting mechanism, and one end is fixed by connector and air bridges；
The fuselage is divided into leading portion, stage casing and endpiece three parts, and fuselage is each intersegmental to be fixed by dowel hole and screw
Connection；
The gentle air bridges in main day are installed inside the middle fuselage.
The wing components are made of wing stabilization, wing body radome fairing, float component, wing flap, aileron, pass through positioning pin
On the middle fuselage.
The fin assembly is made of vertical fin and horizontal tail, and horizontal tail is installed on by link block on vertical fin, and vertical fin passes through positioning
Pin is mounted on the fuselage endpiece.
The discharge hoses routing ventilation main strut, air connections, air bridges, volume control device and wing stabilization
Internal discharge hoses road forms continuous supply and exhaust system.
Vent line provided in an embodiment of the present invention uses for air motor for exhaust, and each nacelle has supply air line all the way
Gas exhaust piping all the way, supply air line are connected with volume control device；Exhaust pipe is merged at one at the nacelle of inside with being vented
Air bridges connect.
Support device provided in an embodiment of the present invention, using oblique abdomen/back-supported mode, main strut section uses symmetrical wing
Type profile, strut indoor design inlet and outlet venthole meet confession, exhaust requirements, the connection with the gentle wind-tunnel supporting mechanism in main day
It is fastened using positioning pin and screw.
Vent line provided in an embodiment of the present invention, it is characterised in that using copper pipe, the connection mode of pipe joint uses
Welding form, is aided with block and pressing plate is fixed.
Airframe models provided in an embodiment of the present invention, it is characterized in that using digital control processing after ZL205A aluminum castings, mean wall
Thickness is not less than 15mm, local location distribution reinforcing rib.A circle reinforcing rib is respectively designed before and after middle fuselage, to ensure with head,
Fuselage endpiece is reliably connected, and four beams of genesis analysis between two circle reinforcing ribs strengthen fuselage ring, realize the company with wing
It connects.Middle fuselage Front-end Design 30CrMnSiA structural alloy steel fuselage balance connectors, to connect main balance.
Wing provided in an embodiment of the present invention, vertical fin, horizontal tail model, feature use 7075 aluminium sheet digital control processings.
Propeller component model of the embodiment of the present invention, includes engine nacelle shell, connector, air motor, rotation axis
Balance, propeller hub, blade and spinner, it is characterized in that：Blade uses carbon fiber+30CrMnSiA composite materials, and connector, propeller hub are adopted
With 30CrMnSiA, engine nacelle shell, spinner use 7050 aluminium digital control processings.
Claims (7)
1. a kind of four hair propeller aeroplane model in wind tunnel based on air motor, it is characterised in that：It supports and leads including oblique dorsal ventral
Strut (17 and 115), connector (114), nosing (11), middle fuselage (113), fuselage endpiece (116), vertical fin (18),
Horizontal tail (19), wing components (16), propeller component (22), discharge hoses road (24), air bridges (15), main balance (112) and
Volume control device (12)；One end of the oblique front support main strut (115) of model is mounted on wind-tunnel support stand, and the other end passes through branch
Joint element for bar (114) is connected with air bridges (15), and air bridges (15) are connected with one end of main balance (112), main balance (112)
The other end is mounted on connector (111), and connector (111) is connected on middle fuselage (113)；Middle fuselage (113) is internal
Main balance (112), air bridges (15) are installed, middle fuselage (113) is fixedly connected with wing components (16) by pin hole；Machine
Wing component (16) is made of wing stabilization, wing body radome fairing, float component, wing flap, aileron；Horizontal tail (19) is pacified by link block
Loaded on vertical fin (18), vertical fin (18) is mounted on by positioning pin on fuselage endpiece (116)；Discharge hoses road (24) by tiltedly carry on the back/
Discharge hoses inside belly stay main strut (17/115), connector (114), air bridges (15), volume control device (12) and wing
Road (24) forms continuous supply and exhaust system.
2. model in wind tunnel as described in claim 1, it is characterised in that：The discharge hoses road (24), using copper pipe, pipe
The connection mode of pipeline connector use welding form, be aided with block and pressing plate be fixed, for ensure air-tightness, security and
Pressure requirements.
3. model in wind tunnel as described in claim 1, it is characterised in that：Main strut (17,115) section of support device is adopted
With symmetrical airfoil section, indoor design inlet and outlet venthole, the connection with main balance (112) and wind-tunnel supporting mechanism is using fixed
Position pin and screw fastening.
4. model in wind tunnel as described in claim 1, it is characterised in that：Numerical control adds after fuselage uses ZL205A aluminum castings
Work, average wall thickness are not less than 15mm, local location distribution reinforcing rib；A circle reinforcing rib is respectively designed before and after middle fuselage (113), is used
To ensure to be reliably connected with nosing (11), fuselage endpiece (116), two enclose genesis analysis four beams between reinforcing ribs, add
Strong fuselage ring realizes the connection with wing components (16)；Middle fuselage (113) Front-end Design 30CrMnSiA structural alloy steels
Fuselage balance connector (114), to connect main balance (112).
5. model in wind tunnel as described in claim 1, it is characterised in that：Main balance (112) is connected with air bridges (15), leads to
It crosses temperature, pressure influence that air bridges (15) bring gases at high pressure to be eliminated, improves the measurement accuracy of main balance (112).
6. model in wind tunnel as described in claim 1, it is characterised in that：Propeller component (22) model, includes engine
Nacelle shell (14), connector (47), air motor (46), rotation axis balance (44), propeller hub (43), blade (41) and spinner
(42)；Blade (41) uses carbon fiber+30CrMnSiA composite materials, and connector (47), propeller hub (43) are using 30CrMnSiA, hair
Motivation nacelle shell (14), spinner (42) use 7050 aluminium digital control processings；It is straight by rotation axis balance (44) and blade (41)
Even.
7. model in wind tunnel as described in claim 1, it is characterised in that：Pole support connector (114) floor design has 10
17 millimeters of through holes of Φ are closely connected using sunk screw and oblique front support main strut (115), are additionally provided with 4 elliptical apertures and a Φ
50 millimeters of through holes facilitate control system electric wire and vent line conduit to pass in and out.
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| CN201711053498.8A CN108106814B (en) | 2017-10-31 | 2017-10-31 | Four-engine propeller aircraft wind tunnel test model based on air motor |
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| CN201711053498.8A CN108106814B (en) | 2017-10-31 | 2017-10-31 | Four-engine propeller aircraft wind tunnel test model based on air motor |
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| CN108106814B CN108106814B (en) | 2022-06-28 |
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| CN108613792A (en) * | 2018-05-11 | 2018-10-02 | 中国商用飞机有限责任公司 | Scale model device for simulated engine rotor gyro effect |
| CN109632242A (en) * | 2018-12-17 | 2019-04-16 | 中国航天空气动力技术研究院 | Special material skin resistance measuring device in a kind of supersonic wind tunnel |
| CN109632242B (en) * | 2018-12-17 | 2020-11-20 | 中国航天空气动力技术研究院 | Material surface resistance measuring device in supersonic wind tunnel |
| CN110823506A (en) * | 2019-10-30 | 2020-02-21 | 上海理工大学 | Wing simulation test bed driven by linear motor |
| CN111591462A (en) * | 2020-07-27 | 2020-08-28 | 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 simulation system for wind tunnel test |
| CN111591462B (en) * | 2020-07-27 | 2020-10-16 | 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 simulation system for wind tunnel test |
| CN112926138A (en) * | 2021-03-23 | 2021-06-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Modeling method of control surface angle sheet applied to wind tunnel test model |
| CN112926138B (en) * | 2021-03-23 | 2022-08-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Modeling method of control surface angle sheet applied to wind tunnel test model |
| CN113029502A (en) * | 2021-04-20 | 2021-06-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle wind tunnel test method for simultaneously simulating air intake and air exhaust |
| CN113252280A (en) * | 2021-04-20 | 2021-08-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
| CN113252280B (en) * | 2021-04-20 | 2021-09-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
| CN113029502B (en) * | 2021-04-20 | 2023-03-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle wind tunnel test method for simultaneously simulating air intake and air exhaust |
| CN113525710A (en) * | 2021-07-30 | 2021-10-22 | 中国特种飞行器研究所 | Full-belt power model of amphibious aircraft |
| CN114061887A (en) * | 2021-12-01 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Amphibious aircraft power lift-increasing full-mode wind tunnel test device |
| RU216427U1 (en) * | 2022-08-19 | 2023-02-02 | Федеральное автономное учреждение "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" | Small scale aircraft model |
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