CN106644352A - Double-fuselage double-wing layout aircraft wind tunnel testing method - Google Patents
Double-fuselage double-wing layout aircraft wind tunnel testing method Download PDFInfo
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- CN106644352A CN106644352A CN201610848950.9A CN201610848950A CN106644352A CN 106644352 A CN106644352 A CN 106644352A CN 201610848950 A CN201610848950 A CN 201610848950A CN 106644352 A CN106644352 A CN 106644352A
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- aircraft
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- shipper
- wing
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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
- G01M9/02—Wind tunnels
Abstract
The invention discloses a double-fuselage double-wing layout aircraft wind tunnel testing method, which belongs to the technical field of wind testing. The method comprises the following steps: dividing a double-fuselage double-wing aircraft model from the symmetrical surface and moving the model horizontally towards two sides; placing a rod type force measurement scale to the symmetrical surface of the model wherein the left section of the model and the right section of the model are connected with the force measurement ends of the scale; the scale is connected with a support rod. A fairing is installed on the scale and at the outer side of the connection component so as to prevent the influence of the scale on the flow field and the interference of the air flows on the scale. The front wing fairing and the back-wing faring are fixedly connected with the support rod but not in contact with the model to avoid the transmission of force. The two sides of the fairing are provided with an air separation plate to prevent the interference of the middle scale installation area with the air flow of the model. The method of the invention solves the problems in the wind testing scheme designing process for a double-fuselage double-wing special aircraft that the scale is difficult to install and the model is hard to support.
Description
Technical field
The invention belongs to wind-tunnel technique field, is related to a kind of wind tunnel test methods of particular configuration aircraft, specifically
Design a kind of wind tunnel test methods of twin fuselage two-shipper wing layout aircraft.
Background technology
HAE unmanned vehicle and rise floating one aircraft and adopt high aspect ratio wing lift-drag ratio more to improve, greatly
It is big that aspect ratio wing faces structural flexibility, and the problems such as deform serious during flight, twin fuselage two-shipper wing distribution form can effectively solving
Problem above.
Wind tunnel test is the primary hand for providing excellent aerodynamic arrangement and air dynamic behaviour data for Flight Vehicle Design
Section, twin fuselage two-shipper rotor aircraft is a kind of new layout aircraft, at present to the also no mature and reliable of aircraft of this layout
Wind tunnel test scheme.Because such aircraft configurations is special, wing is located at aircraft middle part, and fuselage is located at wing both sides, right
There is no fuselage at title face, therefore force balance is installed and model support faces serious problems.According to conventional full mould wind-tunnel examination
Proved recipe case, then need, with Y shape strut support twin fuselage, day to be flat on into two fuselage interiors, and Y shape pole is to mould in this scheme
Type aerodynamic interference is larger, and later stage amendment is difficult, and double balance measurement data processing difficulties are big；According to half module wind tunnel test side
Case, then the gap between sidewall layer and model and hole wall can have a strong impact on the aerodynamic characteristic of model wing, cause measurement knot
It is really inaccurate.Therefore design a kind of interference little, measure accurate, the high force test in wind tunnel scheme of feasibility is an important section
Grind problem.
The content of the invention
To solve the problems, such as above-mentioned twin fuselage two-shipper wing layout aircraft force test in wind tunnel, the present invention proposes a kind of twin fuselage
The wind tunnel test methods of two-shipper wing layout aircraft, effectively improve the accuracy of test.
The wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention, are completed by following step：
Step 1：Twin fuselage two-shipper rotor aircraft wind-tunnel scale model is separated from the plane of symmetry, symmetrical flying is formed
Row device left side and aircraft right-hand part.
Step 2：The aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft right-hand part it
Between arrange rod-type force balance；And the aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft is right
Front tip extension in half portion is connected by balance connector with the dynamometry end of rod-type force balance, while the twin fuselage two-shipper wing is flown
The aircraft left side of row device wind-tunnel scale model is connected between the rear tip extension in aircraft right-hand part by connector.
Step 3：Pole is installed in the tail end centrum end of rod-type force balance；Pole end is installed on the regulation of the wind-tunnel angle of attack
In mechanism.
Step 4：Install front wing radome fairing additional, cover rod-type force balance and balance connector.
Step 5：Install rear wing radome fairing additional, cover the aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model
With the not dynamometry wing panel of rear tip extension in aircraft right-hand part.
Step 6：On the aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft right-hand part
Air baffle is installed, is fixed with front wing radome fairing and rear wing radome fairing respectively.
It is an advantage of the current invention that：
(1) wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention, using full mould test method, it is to avoid
Hole wall and model and impact of the Dong Bi gaps to model aerodynamic characteristic, improve test accuracy in half-modcl test；
(2) wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention, using the support side of single pole shoe
Formula, effectively reduces interference of the support system to model, and convenient arrangement angle of attack governor motion；
(3) wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention, by a high-precision rod-type dynamometry
It is flat on model inside dynamometry, and certainty of measurement is high, and Data Post is simple and reliable；
(4) wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention, using air baffle by middle balance
And radome fairing separates with dynamometry model, it is to avoid interference of the middle radome fairing to dynamometry model.
Description of the drawings
Fig. 1 is rod-type force balance installation position in the wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention
Put schematic diagram；
Fig. 2 is that in the wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention, radome fairing and air baffle are pacified
Dress schematic diagram；
Fig. 3 is that in the wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention, balance connecting-piece structure is illustrated
Figure；
Fig. 4 is the overall configuration schematic diagram of the wind tunnel test methods of twin fuselage two-shipper wing layout aircraft of the present invention.
In figure：
1- aircraft left side 2- aircraft right-hand part 3- rod-type force balances
4- front wing 5- rear wing 6- balance connectors
7- pole 8- front wing radome fairing 9- radome fairing connectors
10- rear wing radome fairing 11- air baffle 601- connectors
602- wing connecting plate 603- location holes
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
Twin fuselage two-shipper wing layout aircraft wind tunnel test methods of the present invention, are completed by following step：
Step 1：Twin fuselage two-shipper rotor aircraft wind-tunnel scale model is separated from the plane of symmetry, symmetrical flying is formed
Row device left side 1 and aircraft right-hand part 2.
Step 2：By the aircraft left side 1 of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft right-hand part 2
Respectively to the left with to the segment distance of right translation one, rod-type force balance 3 is placed at the plane of symmetry so as to axially along the longitudinal direction, such as
Shown in Fig. 1, Fig. 2；And by the aircraft left side 1 of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft right-hand part 2
In the end of front wing 4 be connected with the dynamometry end of rod-type force balance 3 by balance connector 6, while the twin fuselage two-shipper wing is flown
It is connected by connector between the aircraft left side 1 of row device wind-tunnel scale model and the end of rear wing 5 in aircraft right-hand part 2.
By the aerodynamic force of the measurable twin fuselage two-shipper rotor aircraft wind-tunnel scale model of rod-type force balance 3.
The balance connector 6 has center connector 601, and the wing connecting plate 602 of both sides, as shown in Figure 3；In
Location hole 603 is provided with heart connector, for coaxially positioning between rod-type force balance 3.The wing connecting plate 602 of both sides is distinguished
The aircraft left side 1 of twin fuselage two-shipper rotor aircraft wind-tunnel scale model is fixedly connected with the end of front wing 4 in aircraft right-hand part 2
Portion.
Step 3：Pole is installed in the tail end centrum end of rod-type force balance 3；The front end of pole 7 is coaxially connected to be fixed on bar
The tail end centrum end of formula force balance 3, as shown in Figure 1；The end of pole 7 is installed on wind-tunnel angle of attack governor motion；By propping up
Bar 7 supports twin fuselage two-shipper rotor aircraft wind-tunnel scale model.
Step 4：Install front wing radome fairing 8 additional, rod-type force balance 3 and balance connector 6 covered by front wing radome fairing 8,
Avoid and interference of the air-flow to balance, as shown in Figure 2.The front wing radome fairing 8 is designed as T-shaped cross section structure cover body, including upper
Lower two parts, fasten up and down, are fixed on the radome fairing connector 9 being socketed at the front end of pole 7 by screw respectively.Front wing rectification
The horizontal enclosure portion of cover 8 is used for covering balance connector 6, while cover twin fuselage two-shipper rotor aircraft wind-tunnel scale model flying
Row device left side 1 and the end of front wing 4 in aircraft right-hand part 2；Longitudinal enclosure portion is used for covering rod-type force balance 3 and props up
The front end of bar 7.
Step 5：Install rear wing radome fairing 10 additional, as shown in Fig. 2 rear wing radome fairing 10 equally includes upper and lower two parts, up and down
Fasten, aircraft left side 1 and the aircraft of twin fuselage two-shipper rotor aircraft wind-tunnel scale model are covered by rear wing radome fairing 10
The not dynamometry wing panel of the end of rear wing 5 in right-hand part 2, it is to avoid the partial pneumatic power reaches rod-type force balance 3.
Step 6：On twin fuselage two-shipper rotor aircraft wind-tunnel scale model aircraft left side 1 and aircraft right-hand part 2
Air baffle 11 is installed, as shown in Figure 2, Figure 4 shows.The overall platy structure that air baffle 11 is constituted using double dividing plate interpolations, finally
Be enclosed within the front wing 4 of aircraft left side 1 and aircraft right-hand part 2 and rear wing 5, and respectively with the horizontal cover body of front wing radome fairing 8
Part two ends and the two ends of rear wing radome fairing 10 are fixed, and then realize the positioning of air baffle 11, are avoided by air baffle 11
Interference in air flow of the installation region of middle rod-type force balance 3 to twin fuselage two-shipper rotor aircraft wind-tunnel scale model, makes rod-type
Aerodynamic force on 3 measurement both sides models of air baffle 11 of force balance.
In above-mentioned steps 4, front wing radome fairing 8 install after, need to ensure front wing radome fairing 8 not with twin fuselage two-shipper rotor aircraft
Wind-tunnel scale model and rod-type force balance 3 are contacted, it is to avoid suffered power reaches model and then reaches bar on front wing radome fairing 8
Formula force balance 3.After rear wing radome fairing 10 is installed in step 5, need to ensure rear wing radome fairing 10 not with the double airfoil flight of twin fuselage
Device wind-tunnel scale model is contacted, it is to avoid suffered power reaches model and then reaches rod-type force balance 3 on rear wing radome fairing 10.Step
In rapid 6, after air baffle 11 is installed, need to ensure that air baffle 11 does not connect with twin fuselage two-shipper rotor aircraft wind-tunnel scale model
Touch, and ensure twin fuselage two-shipper rotor aircraft wind-tunnel scale model deform under Aerodynamic force action after also not with air baffle
11 contacts, it is to avoid suffered power reaches model and then reaches balance on air baffle 11.
When carrying out the wind tunnel test of twin fuselage two-shipper rotor aircraft by the present invention, actual experimental model is air baffle 11
Two side portions, 3 measurement air baffle 11 both sides models of rod-type force balance receive aerodynamic force, and front wing radome fairing 8, rear wing is whole
Stream cover 10 is transferred to pole 7 and is not measured by rod-type force balance 3 with aerodynamic force suffered by air baffle 11.Rod-type force balance
The interference that 3 installation region produces is separated by air baffle 11, does not affect model aerodynamic characteristic, efficiently solves twin fuselage two-shipper
Wing layout aircraft wind tunnel test balance is installed and model support problem.
Claims (2)
1. a kind of wind tunnel test methods of twin fuselage two-shipper wing layout aircraft, it is characterised in that：Completed by following step：
Step 1：Twin fuselage two-shipper rotor aircraft wind-tunnel scale model is separated from the plane of symmetry, symmetrical aircraft is formed
Left side and aircraft right-hand part；
Step 2：Set between the aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft right-hand part
Put rod-type force balance；And by the aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft right-hand part
In front tip extension be connected with the dynamometry end of rod-type force balance by balance connector, while by twin fuselage two-shipper rotor aircraft
It is connected by connector between the aircraft left side of wind-tunnel scale model and the rear tip extension in aircraft right-hand part；
Step 3：Pole is installed in the tail end centrum end of rod-type force balance；Pole end is installed on wind-tunnel angle of attack governor motion
On；
Step 4：Install front wing radome fairing additional, cover rod-type force balance and balance connector；
Step 5：Install rear wing radome fairing additional, cover the aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and fly
The not dynamometry wing panel of tip extension after in row device right-hand part；
Step 6：Install on the aircraft left side of twin fuselage two-shipper rotor aircraft wind-tunnel scale model and aircraft right-hand part
Air baffle, fixes respectively with front wing radome fairing and rear wing radome fairing.
2. as claimed in claim 1 a kind of wind tunnel test methods of twin fuselage two-shipper wing layout aircraft, it is characterised in that：Front wing
Radome fairing is not contacted with twin fuselage two-shipper rotor aircraft wind-tunnel scale model and rod-type force balance；Rear wing radome fairing not with it is double
Fuselage two-shipper rotor aircraft wind-tunnel scale model is contacted；Air baffle does not connect with twin fuselage two-shipper rotor aircraft wind-tunnel scale model
Touch.
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| CN201610848950.9A CN106644352B (en) | 2016-09-23 | 2016-09-23 | A kind of wind tunnel test methods of twin fuselage two-shipper wing layout aircraft |
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| CN201610848950.9A CN106644352B (en) | 2016-09-23 | 2016-09-23 | A kind of wind tunnel test methods of twin fuselage two-shipper wing layout aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107631852A (en) * | 2017-09-01 | 2018-01-26 | 中国航空工业集团公司沈阳空气动力研究所 | Double-support mechanism under a kind of wing |
| CN108645592A (en) * | 2018-06-27 | 2018-10-12 | 空气动力学国家重点实验室 | A kind of double balance twayblade support devices for transonic wind tunnel twin-fuselage configuration aircraft |
| CN108645591A (en) * | 2018-06-27 | 2018-10-12 | 空气动力学国家重点实验室 | A kind of V-type tail support device for flat fusion aircraft in transonic wind tunnel |
| CN110160738A (en) * | 2019-03-21 | 2019-08-23 | 北京机电工程研究所 | For the fairing of aerofoil wind tunnel test, design method and blended wing-body device |
| CN110441025A (en) * | 2019-08-19 | 2019-11-12 | 中国航空工业集团公司沈阳空气动力研究所 | One kind is for the full machine dynamometric system of the modified double balances of civil aircraft support interference and method |
| CN110657940A (en) * | 2019-09-12 | 2020-01-07 | 哈尔滨飞机工业集团有限责任公司 | High-lift wing type icing wind tunnel test mixed model and design method thereof |
| CN111337211A (en) * | 2020-03-05 | 2020-06-26 | 中国航天空气动力技术研究院 | Double-body model four-point supporting and fixing device |
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| CN105258915A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Sideslip angle-varying blade belly supporting device in high-speed wind tunnel test |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107631852A (en) * | 2017-09-01 | 2018-01-26 | 中国航空工业集团公司沈阳空气动力研究所 | Double-support mechanism under a kind of wing |
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| CN108645592B (en) * | 2018-06-27 | 2024-02-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-balance double-blade supporting device for transonic wind tunnel double-fuselage layout aircraft |
| CN108645591B (en) * | 2018-06-27 | 2024-02-20 | 中国空气动力研究与发展中心高速空气动力研究所 | V-shaped tail supporting device for flat fusion aircraft in transonic wind tunnel |
| CN110160738A (en) * | 2019-03-21 | 2019-08-23 | 北京机电工程研究所 | For the fairing of aerofoil wind tunnel test, design method and blended wing-body device |
| CN110160738B (en) * | 2019-03-21 | 2020-10-23 | 北京机电工程研究所 | Rectifying device for wing surface wind tunnel test, design method and wing body fusion device |
| CN110441025A (en) * | 2019-08-19 | 2019-11-12 | 中国航空工业集团公司沈阳空气动力研究所 | One kind is for the full machine dynamometric system of the modified double balances of civil aircraft support interference and method |
| CN110657940A (en) * | 2019-09-12 | 2020-01-07 | 哈尔滨飞机工业集团有限责任公司 | High-lift wing type icing wind tunnel test mixed model and design method thereof |
| CN110657940B (en) * | 2019-09-12 | 2021-07-16 | 哈尔滨飞机工业集团有限责任公司 | High-lift wing type icing wind tunnel test mixed model and design method thereof |
| CN111337211A (en) * | 2020-03-05 | 2020-06-26 | 中国航天空气动力技术研究院 | Double-body model four-point supporting and fixing device |
| CN111337211B (en) * | 2020-03-05 | 2022-01-04 | 中国航天空气动力技术研究院 | Double-body model four-point supporting and fixing device |
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