CN205642790U - Aircraft strutting arrangement - Google Patents
Aircraft strutting arrangement Download PDFInfo
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- CN205642790U CN205642790U CN201521009686.7U CN201521009686U CN205642790U CN 205642790 U CN205642790 U CN 205642790U CN 201521009686 U CN201521009686 U CN 201521009686U CN 205642790 U CN205642790 U CN 205642790U
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- aircraft
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- bracing cable
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Abstract
The utility model relates to a wind -tunnel testing equipment designs field, in particular to aircraft strutting arrangement to it is not high to solve current strutting arrangement stability, influences the problem of measuring accuracy easily. Aircraft strutting arrangement includes: tumbler disc, the support arm, one end fixed connection to tumbler disc upper surface, the bearing diagonal arm, the one end of keeping away from tumbler disc on one end and the support arm is articulated, the other end and a wing tip fixed connection who tests the aircraft, flexible arm, one end hinges on the support arm, and the other end hinges and is lieing in same side on the bearing diagonal arm, the bracing cable supporting mechanism, with the aircraft nose fixed connection of test aircraft. The utility model discloses an among the aircraft strutting arrangement, through the wing tip fixed connection of rigid supporting mechanism with the test aircraft, still adopt the bracing cable supporting mechanism and the aircraft nose of test aircraft to be connected simultaneously for aircraft strutting arrangement has had the bracing cable concurrently and has supported the little advantage of aerodynamical interference, and rigid braced system stability is good, the advantage of technology maturation.
Description
Technical field
This utility model relates to wind tunnel test equipment design field, props up particularly to a kind of aircraft
Support arrangement.
Background technology
Wind tunnel test be unable to do without wind tunnel model support system, and existing wind tunnel model support system is main
There are rigid support system and bracing cable support system etc..When carrying out aircraft full machine wind Tunnel Measuring Pressure Tests,
Model support is generally used to be fixed in test chamber by whole dummy vehicle, support pattern
Mainly have: tail support, abdomen support, side wall support, wing tip support, bracing cable support etc..
Generally, model can be streamed generation interference by support system, makes model test result with true
Aircraft aerodynamic characteristic creates a difference, and this difference is referred to as support interference.How to reduce or revise and prop up
Support interference problem is an important content of test aerodynamic studies, and it can be effectively improved
The accuracy of wind tunnel test data.Therefore, for support system, except requiring that it is to wind-tunnel stream
Interference is little and do not affect outside model aerodynamic configuration, also require its have simple in construction, volume little,
Dynamic property is good, applied range and low cost and other advantages.But reducing the gas of support system
While dynamic interference, the vibration of the support system that aerodynamic force is caused is also difficult to avoid that, thus makes
The contradiction that must increase between support stiffness and the aerodynamic interference reducing support system becomes more to dash forward
Going out, what this showed in rigid support system is especially apparent.
Bracing cable support system but exists significantly in the entire pressure test in airplane of some type
Limitation；The such as unmanned plane of all-wing aircraft form, owing to the body of model aircraft is little, afterbody and wing
The thinnest, arrange bracing cable support system time, it tends to be difficult to find intensity suitable
Position the strong point is set；If the wing edge the highest in its intensity arranges the bracing cable strong point,
It is easy in wind tunnel test destroy wing, and is also difficult to arrange in the position that wing is the thinnest
The mechanisms such as force balance；And if the bracing cable strong point being concentrated on the thicker parts such as fuselage, then
Bracing cable support system will excessively be concentrated due to the strong point and expose this support system stability not
High inherent shortcoming, easily waves in wind tunnel test, affects measuring accuracy.
Summary of the invention
The purpose of this utility model there is provided a kind of aircraft support device, to solve existing
Support arrangement stability is the highest, the problem easily affecting measuring accuracy.
The technical solution of the utility model is:
A kind of aircraft support device, is used for carrying out the test aircraft in wind1 tunnel laboratory propping up
Support, described aircraft support device includes:
Rotate disk；
Support arm, one end is fixedly attached to described rotation disk upper surface；
Bearing diagonal arm, one end is hinged, separately away from one end of described rotation disk with on described support arm
One end is fixing with a wing tip of described test aircraft to be connected；
Telescopic arm, one end is hinged on described support arm, and the other end is hinged on the institute being positioned at the same side
State on bearing diagonal arm；
Bracing cable supporting mechanism, one end is fixedly attached to precalculated position in described wind1 tunnel laboratory, separately
One end is connected by bracing cable is fixing with the head of described test aircraft.
Optionally, described support arm is Collapsible structure.
Optionally, described bracing cable supporting mechanism includes two, is separately fixed at described wind tunnel test
The top of room and bottom, and two described bracing cable supporting mechanisms are fixing even by a bracing cable respectively
It is connected to the same position of head of described test aircraft.
Optionally, described support arm and described telescopic arm are hydraulic cylinder.
The utility model has the advantage of:
In aircraft support device of the present utility model, by rigid supporting mechanism and test aircraft
Wing tip fixing connect, the most also use bracing cable supporting mechanism to be connected with the head testing aircraft,
Make support means have bracing cable concurrently and support the advantage that aerodynamic interference is little, and rigid support system
Good stability, the advantage of technology maturation.
Accompanying drawing explanation
Fig. 1 is the structural representation of this utility model aircraft support device.
Detailed description of the invention
Clearer for the purpose making this utility model implement, technical scheme and advantage, below will
In conjunction with the accompanying drawing in this utility model embodiment, to the technical scheme in this utility model embodiment
It is further described in more detail.In the accompanying drawings, the most same or similar label represents phase
With or similar element or there is the element of same or like function.Described embodiment is this
The a part of embodiment of utility model rather than whole embodiments.Retouch below with reference to accompanying drawing
The embodiment stated is exemplary, it is intended to be used for explaining this utility model, and it is not intended that right
Restriction of the present utility model.Based on the embodiment in this utility model, ordinary skill people
The every other embodiment that member is obtained under not making creative work premise, broadly falls into this
The scope of utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is carried out in detail
Explanation.
In description of the present utility model, it is to be understood that term " " center ", " longitudinally ",
" laterally ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end ",
Orientation or the position relationship of the instruction such as " interior ", " outward " are based on orientation shown in the drawings or position
Relation, is for only for ease of description this utility model and simplifies description rather than instruction or hint
The device of indication or element must have specific orientation, with specific azimuth configuration and operation,
Therefore it is not intended that restriction to this utility model protection domain.
1 pair of this utility model aircraft support device does the most below in conjunction with the accompanying drawings
Bright.
This utility model provides a kind of aircraft support device, in wind1 tunnel laboratory
Test aircraft 1 is supported；Aircraft support device can include rotate disk 2, rigid
Support mechanism 3 and bracing cable supporting mechanism 4.
Rotate the base that disk 2 is whole aircraft support device, can use known multiple
The structure being suitable for, can drive corresponding test aircraft 1 around own axis, meet corresponding
Test requirements document.
Rigid supporting mechanism 3 one end is fixing with the wing tip of test aircraft 1 to be connected, and the other end is fixed
It is connected to rotate disk 2.
Bracing cable supporting mechanism 4 one end is fixedly attached to (such as sky, precalculated position in wind1 tunnel laboratory
Card, ground etc.), the other end is connected by bracing cable 41 is fixing with the head of test aircraft 1.
In aircraft support device of the present utility model, flown with test by rigid supporting mechanism 3
The wing tip of machine 1 is fixing to be connected, and the most also uses the machine of bracing cable supporting mechanism 4 and test aircraft 1
Head connects so that aircraft support device has had bracing cable concurrently and supported the advantage that aerodynamic interference is little, with
And rigid support system good stability, the advantage of technology maturation.
Rigid supporting mechanism 3 of the present utility model can use multiple applicable structure；This enforcement
In example, rigid supporting mechanism 3 includes two support bars, and two support bars are along test aircraft
One wing tip of 1 is arranged to another wing tip direction.
Further, every support bar includes a support arm 31 and a bearing diagonal arm 32；Support arm
31 is Collapsible structure, it is possible to adjust the yaw angle of model aircraft；Support arm 31 one end is fixing even
Connect (preferably welding) to rotating disk 2 upper surface；Bearing diagonal arm 32 one end and support arm 31
On away from rotate disk 2 one end hinged, the other end with test aircraft 1 a wing tip fix
Connect.
Aircraft support device of the present utility model also includes telescopic arm 33, and one end is hinged on props up
On arm 31, the other end is hinged on the bearing diagonal arm 32 being positioned at the same side, it is possible to by flexible
The flexible aircraft mould making whole aircraft support device adapt to the different size span of arm 33
Type.It addition, support arm 31 and telescopic arm 33 can use how many known stretching structure, such as
Hydraulic cylinder, cylinder etc., in the present embodiment, be all chosen for the hydraulic cylinder that stability is stronger.
Further, bracing cable supporting mechanism 4 can include two, is separately fixed at wind1 tunnel laboratory
Top and bottom, and two bracing cable supporting mechanisms 4 are fixing even by a bracing cable 41 respectively
It is connected to test the same position of head of aircraft 1.
Aircraft support device of the present utility model is to be mixed with bracing cable support system and rigid
The supporting construction of the feature of support system, is difficult to the position connected, such as at bracing cable supporting mechanism 4
Tip location have employed rigid supporting mechanism 3, and maintain bracing cable at Handpiece Location and support, from
And had bracing cable concurrently and supported the advantage that aerodynamic interference is little, and rigid stability of strutting system is good, technology
Ripe advantage.
The above, detailed description of the invention the most of the present utility model, but guarantor of the present utility model
The scope of protecting is not limited thereto, and any those familiar with the art is at this utility model
In the technical scope disclosed, the change that can readily occur in or replacement, all should contain in this practicality new
Within the protection domain of type.Therefore, protection domain of the present utility model should be with described claim
Protection domain be as the criterion.
Claims (4)
1. an aircraft support device, for the test aircraft (1) in wind1 tunnel laboratory is supported, it is characterised in that described aircraft support device includes:
Rotate disk (2)；
Support arm (31), one end is fixedly attached to described rotation disk (2) upper surface；
Bearing diagonal arm (32), one end is hinged away from one end of described rotation disk (2) with on described support arm (31), and the other end is fixing with a wing tip of described test aircraft (1) to be connected；
Telescopic arm (33), one end is hinged on described support arm (31), and the other end is hinged on the described bearing diagonal arm (32) being positioned at the same side；
Bracing cable supporting mechanism (4), one end is fixedly attached to precalculated position in described wind1 tunnel laboratory, and the other end is connected by bracing cable (41) is fixing with the head of described test aircraft (1).
Aircraft support device the most according to claim 1, it is characterised in that described support arm (31) is Collapsible structure.
Aircraft support device the most according to claim 1 and 2, it is characterized in that, described bracing cable supporting mechanism (4) includes two, it is separately fixed at top and the bottom of described wind1 tunnel laboratory, and two described bracing cable supporting mechanisms (4) are passed through a bracing cable (41) respectively and are fixedly attached to the same position of head of described test aircraft (1).
Aircraft support device the most according to claim 3, it is characterised in that described support arm (31) and described telescopic arm (33) are hydraulic cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521009686.7U CN205642790U (en) | 2015-12-08 | 2015-12-08 | Aircraft strutting arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521009686.7U CN205642790U (en) | 2015-12-08 | 2015-12-08 | Aircraft strutting arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205642790U true CN205642790U (en) | 2016-10-12 |
Family
ID=57079007
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521009686.7U Active CN205642790U (en) | 2015-12-08 | 2015-12-08 | Aircraft strutting arrangement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205642790U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860550A (en) * | 2017-10-23 | 2018-03-30 | 中国科学院力学研究所 | A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 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 aerofoil profile sideway oscillation flow tunnel testing device |
-
2015
- 2015-12-08 CN CN201521009686.7U patent/CN205642790U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860550A (en) * | 2017-10-23 | 2018-03-30 | 中国科学院力学研究所 | A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment |
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 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 aerofoil profile sideway oscillation flow tunnel testing device |
| CN108414182B (en) * | 2018-04-23 | 2023-11-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing type yaw oscillation wind tunnel test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20201028 Address after: Building B, building 28, Jiangsu information service industry base, Guangling New Town, Yangzhou City, Jiangsu Province, 225002 Patentee after: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110035 Patentee before: SHENYANG AIRCRAFT DESIGN INSTITUTE, AVIATION INDUSTRY CORPORATION OF CHINA |