CN211919037U - Icing wind tunnel test device for aircraft anti-icing and deicing leading-edge slat - Google Patents
Icing wind tunnel test device for aircraft anti-icing and deicing leading-edge slat Download PDFInfo
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- CN211919037U CN211919037U CN201922374200.4U CN201922374200U CN211919037U CN 211919037 U CN211919037 U CN 211919037U CN 201922374200 U CN201922374200 U CN 201922374200U CN 211919037 U CN211919037 U CN 211919037U
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Abstract
The embodiment of the utility model discloses icing wind tunnel test device of aircraft anti-icing deicing leading-edge slat, leading-edge slat part includes: the wing joint comprises a skin, a wing component, a wing rib and a flute-shaped pipe penetrating through the wing rib, wherein a connecting lug plate used for connecting a main body component of the wing is arranged at the rear part of the wing rib; the front edge rib of the wing main body part is provided with connecting holes which are in one-to-one correspondence with the connecting lugs, the middle connecting hole is fixedly connected with the connecting lug of the middle seam wing rib through a fixed bushing arranged in the middle connecting hole, the side connecting hole is internally provided with a sliding bushing, and the side connecting hole is connected with the connecting lug of the side seam wing rib and is provided with a sliding space along the axial direction of the sliding bushing; the two butt joint side plates are respectively arranged on two sides of the wing main body component of the leading edge slat component and fixedly connected with the wing main body component, and the two butt joint side plates are respectively fixed on the wind tunnel test rotary table. The embodiment of the utility model provides a can effectively avoid the appearance of too high stress, guarantee the safe and reliable of test piece, satisfy experimental demand.
Description
Technical Field
The application relates to the technical field of aircraft structures, in particular to an icing wind tunnel test device for an anti-icing and deicing leading edge slat of an aircraft.
Background
The hot gas deicing and anti-icing system for the leading edge slat of the airplane mainly introduces high-temperature hot gas of an engine into a cavity of the slat to heat a skin, so that the aim of deicing is fulfilled. Compared with the real structure of the airplane, the test piece of the hot-gas ice prevention and removal system of the leading edge slat of the airplane is subjected to more serious thermal load besides pneumatic load and cavity pressure load, wherein the thermal load is dominant in contribution to structural stress. The safety factor of the test is required to be multiple times of that of a real structure in order to ensure the safety factor of the test.
At present, airfoil test pieces for an icing wind tunnel test of an aircraft wing anti-icing system are proposed. However, the airfoil test piece mainly aims at the contents of determining the critical section of the shell of the test piece, determining parameters of the flute tube and the like, and focuses on the appearance design of the test piece. The contents of thermal deformation release and structural force transmission optimization caused by thermal stress are not considered too much.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the embodiment of the utility model provides an icing wind tunnel test device of aircraft anti-icing deicing leading-edge slat can effectively avoid the appearance of too high stress, has guaranteed the safe and reliable of test piece, satisfies experimental demand.
The embodiment of the utility model provides an icing wind tunnel test device of aircraft anti-icing deicing leading-edge slat, include: a leading-edge slat component, a wing main component, and two abutting side plates;
the leading-edge slat component comprising: the wing comprises a skin, three seam wing beams, three seam wing ribs vertically connected to the slat beams and a flute-shaped pipe penetrating through the three seam wing ribs, wherein three groups of connecting lug plates for connecting a main body component of the wing are arranged at the rear parts of the three seam wing ribs;
three groups of connecting holes which are in one-to-one correspondence with the connecting lugs are arranged on the front edge rib of the wing main body part, the middle connecting hole is fixedly connected with the connecting lug of the middle seam wing rib through a fixed bushing arranged in the middle connecting hole, a sliding bushing is arranged in the side connecting hole, and the side connecting hole is connected with the connecting lug of the side seam wing rib and is provided with a sliding space along the axial direction of the sliding bushing;
the two butt joint side plates are respectively arranged on two sides of the wing main body component of the leading edge slat component and fixedly connected with the wing main body component, and the two butt joint side plates are respectively fixed on the wind tunnel test rotary table.
Optionally, in the icing wind tunnel testing device for an aircraft anti-icing and deicing leading edge slat as described above, the flute tube is provided with a hot air ejection hole therein, and the hot air ejection hole is configured to eject hot air to an internal cavity of the leading edge slat component by heating the flute tube.
Optionally, in the ice wind tunnel test device for an aircraft anti-icing and de-icing leading edge slat as described above, the sliding bush provided in the side connecting hole is used for enabling the connecting lug and the sliding bush to have relative sliding when the leading edge slat component is deformed by heat, so as to release the temperature deformation of the leading edge slat component.
Optionally, in the icing wind tunnel test device for the aircraft anti-icing and deicing leading edge slat, each group of connecting lug plates arranged at the rear of the slat rib includes two connecting lug plates located in one plane, and the connection mode between the connecting hole of the wing main body component and the connecting lug plates simulates the actual connection stress of the slat and the wing.
Optionally, in the icing wind tunnel test device for the aircraft anti-icing and deicing leading edge slat as described above, an overall aerodynamic pressure center of the wind tunnel test device is located between the connection points of each group of connection tabs.
Optionally, the icing wind tunnel testing apparatus for an aircraft anti-icing and deicing leading edge slat further includes: an ice-shaped measuring assembly;
the ice-shaped measuring assembly comprises a plurality of clamping plates and a guide frame used for fixing the clamping plates, and one end of each clamping plate is arranged to be in an inwards concave shape matched with the front end of the leading edge slat component.
Optionally, in the icing wind tunnel testing apparatus for aircraft anti-icing and deicing leading edge slat described above, the ice shape measuring component is configured to be heated and then clamped into a front end of the leading edge slat component to measure the icing shape of the leading edge.
The embodiment of the utility model provides an icing wind tunnel test device of aircraft anti-icing deicing leading-edge slat, the temperature stress release structure on the wing box section structure can effectively release the span direction temperature deformation brought by thermal stress, has avoided the appearance of too high stress, has guaranteed the safe and reliable of test piece; the force transmission route of the leading edge slat component and the wing box section connecting structure is direct, and the connection stress of a real sliding rail roller can be effectively simulated; the ice type cardboard location is effective, connects reliably, can effectively accomplish ice type and measure.
Drawings
The accompanying drawings are included to provide a further understanding of the embodiments of the present invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the embodiments of the invention and not to limit the embodiments of the invention.
Fig. 1 is a schematic structural diagram of an icing wind tunnel test device for an aircraft anti-icing and deicing leading-edge slat according to an embodiment of the present invention;
FIG. 2 is a schematic representation of the construction of a leading-edge slat component in the embodiment of FIG. 1;
FIG. 3 is a schematic view of another view of the leading-edge slat component of FIG. 2;
FIG. 4 is a schematic structural diagram of a body component of the wing in the embodiment shown in FIG. 1.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The present invention provides that several specific embodiments below may be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.
The embodiment of the utility model provides an icing wind tunnel test device of aircraft anti-icing deicing leading-edge slat to several in leading-edge slat steam anti-icing system test piece designProblems to be solved are urgently needed:(1) the test process is the most severeThe temperature difference of the structure under the harsh working condition is as high as 100 ℃, and the problem of thermal stress is obvious; in order to ensure the safety of the test, the stress safety coefficient is higher, and the requirement in actual design is difficult to meet. (2) Test piece of leading-edge slat hot gas anti-icing systemSupport must be safe and effectiveAnd to ensure that the support structure does not fail in the vicinity of the real aircraft structure. (3) The ice type cardboard needs effective location and fixed, just can effectively measure the ice type that freezes.
Fig. 1 is a schematic structural diagram of an icing wind tunnel test device for an aircraft anti-icing and deicing leading edge slat provided by an embodiment of the present invention. The icing wind tunnel test device for the aircraft anti-icing and deicing leading edge slat provided by the embodiment can comprise: a leading-edge slat component 3, a wing body component 5 and two abutting side plates 4;
FIG. 2 is a schematic representation of the leading-edge slat component of the embodiment of FIG. 1, and FIG. 3 is a schematic representation of the leading-edge slat component of FIG. 2 from another perspective. Referring to fig. 2 and 3, a leading-edge slat component 3 in an embodiment of the invention comprises: the connecting lug plate comprises a skin, three seam wing beams, three seam wing ribs vertically connected to the seam wing beams, and a flute-shaped pipe 1 penetrating through the three seam wing ribs, wherein three groups of connecting lug plates 6 used for connecting a wing main body part 5 are arranged at the rear parts of the three seam wing ribs, and each group of connecting lug plates 6 can comprise an upper lug plate and a lower lug plate, and the total number of the lug plates is 6.
FIG. 4 is a schematic structural diagram of a body component of the wing in the embodiment shown in FIG. 1. Three groups of connecting holes which are in one-to-one correspondence with the connecting lugs 6 are arranged on the front edge rib of the wing main body part 5, the middle connecting hole is fixedly connected with the connecting lugs of the middle seam wing rib through a fixing bush arranged in the middle connecting hole, a sliding bush 7 is arranged in the side connecting hole, and the side connecting hole is connected with the connecting lugs 6 of the side seam wing rib and is provided with a sliding space along the axial direction of the sliding bush 7.
The two butt joint side plates 4 are respectively arranged on two sides of a wing main body component 5 of the leading-edge slat component 3 and fixedly connected with the wing main body component 5, the two butt joint side plates 4 are respectively fixed on the wind tunnel test rotary table, and the two butt joint side plates 4 are used for connecting a test piece with the ice wind tunnel test rotary platform. The docking sideplate may be comprised of a sideplate, and a docking pin. The two butt joint side plates 4 are kept aligned and installed in the vertical direction of the side plate surfaces, and a test cable through hole is formed in the center of the inner side plate.
In practical applications, the leading-edge slat component 3 of the embodiments of the present invention is composed of a skin, a slat spar, a slat rib, and a flute-shaped tube. The slat has 3 stiffening ribs, and a plurality of common ribs are arranged at the trailing edge of the slat to prevent the skin from being unstable. Flute venturi tube 1 passes the rib web, passes through flange joint with the rib web, be provided with the steam blowout hole in the flute venturi tube 1, its effect does: the flute-shaped pipe is heated, hot gas is sprayed out of the inner cavity of the leading edge slat component 3, and the hot gas sprayed out of the hole of the flute-shaped pipe fills the front cavity, so that the effects of ice square and deicing are achieved.
The embodiment of the utility model provides an in, the effect of the slip bush that sets up in the lateral part connecting hole does: when the slat element 3 is deformed by heat, the connecting lug 6 and the sliding bush 7 are caused to slide relative to each other, releasing the temperature deformation of the slat element 3.
Optionally, as shown in fig. 3, each set of connecting lug plates arranged at the rear of the slot rib includes two connecting lug plates (i.e. an upper set and a lower set of two lug plates) located in one plane, and the connecting holes of the wing main body part 5 and the connecting lug plates are connected in a manner of simulating the real connecting force of the slat and the wing.
In the embodiment of the present invention, the connection form of the leading-edge slat component 3 is: the slat component 3 has 6 tabs attached to the leading edge rib of the wing body component 5, and is connected to the wing body component 5 by the tabs. The upper and lower lugs and attachment holes of the slat component 3 may simulate real attachment forces. The embodiment of the utility model provides an in wind-tunnel test device's whole pneumatic pressure heart is located between two auricle tie points of every group connection auricle, and optimal design's biography power route is excellent like this, can effectively reduce concentrated power.
The embodiment of the utility model provides an in wing main part structure includes parts such as covering, strengthening rib, front beam, leading edge rib, general rib and trailing edge baffle. The skin is connected with the beam and the rib through bolts. The two end ribs are designed to be stronger because they are to collect the load. To eliminate the great temperature stresses, sliding bushings are added: because the length of the slat is long, the temperature deformation in the length direction is large, and the temperature deformation is limited by a traditional fixing mode (fastening and fixing mode without sliding redundancy), so that great temperature stress is caused, and great hidden danger exists. The sliding bushings are added to the front edge ribs on the two sides of the wing, so that temperature deformation can be released, and the safety of the test piece structure is guaranteed.
As shown in fig. 1, the wind tunnel testing apparatus in the embodiment of the present invention may further include: an ice-shaped measuring assembly;
the ice-shaped measuring assembly comprises a plurality of clamping plates 2 and a guide frame used for fixing the clamping plates, wherein one end of each clamping plate 2 is arranged to be in an inwards concave shape matched with the front end of the leading edge slat component 3. The embodiment of the utility model provides an in, ice shape measuring component's effect does: after heating, the frozen leading edge shape was measured by snapping into the front end of the slat component.
The embodiment of the utility model provides an in ice shape measuring subassembly comprises cardboard 2 and guide frame group, can set up to 3 groups, parallel rib planar arrangement for measure the frozen shape of leading edge. And the measuring clamping plate can be connected with a heat insulation handle to prevent hands from being scalded.
The embodiment of the utility model provides an icing wind tunnel test device of aircraft anti-icing deicing leading-edge slat, the temperature stress release structure on the wing box section structure can effectively release the span direction temperature deformation brought by thermal stress, has avoided the appearance of too high stress, has guaranteed the safe and reliable of test piece; the force transmission route of the leading edge slat component and the wing box section connecting structure is direct, and the connection stress of a real sliding rail roller can be effectively simulated; the ice type cardboard location is effective, connects reliably, can effectively accomplish ice type and measure.
The embodiment of the utility model provides an icing wind tunnel test device's embodiment does: the installation of a flute tube in the leading edge slat part 3 is completed with reference to fig. 2; referring to fig. 3 and 4, the tab 6 of the slat component 3 is completed to interface with the docking aperture on the rib of the wing body component 5. The installation of the ice-type pallet and the abutting side plates is completed with reference to fig. 1. In the experiment process, the whole test piece is fixed in a test icing wind tunnel through the butt joint side plate, hot gas of 200 ℃ is introduced into the flute-shaped pipe, and the slat structure is heated, so that the aim of icing prevention is fulfilled.
Although the embodiments of the present invention have been described above, the description is only for the convenience of understanding the present invention, and the present invention is not limited thereto. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (7)
1. The utility model provides an icing wind tunnel test device of aircraft anti-icing deicing leading-edge slat which characterized in that includes: a leading-edge slat component, a wing main component, and two abutting side plates;
the leading-edge slat component comprising: the wing comprises a skin, three seam wing beams, three seam wing ribs vertically connected to the slat beams and a flute-shaped pipe penetrating through the three seam wing ribs, wherein three groups of connecting lug plates for connecting a main body component of the wing are arranged at the rear parts of the three seam wing ribs;
three groups of connecting holes which are in one-to-one correspondence with the connecting lugs are arranged on the front edge rib of the wing main body part, the middle connecting hole is fixedly connected with the connecting lug of the middle seam wing rib through a fixed bushing arranged in the middle connecting hole, a sliding bushing is arranged in the side connecting hole, and the side connecting hole is connected with the connecting lug of the side seam wing rib and is provided with a sliding space along the axial direction of the sliding bushing;
the two butt joint side plates are respectively arranged on two sides of the wing main body component of the leading edge slat component and fixedly connected with the wing main body component, and the two butt joint side plates are respectively fixed on the wind tunnel test rotary table.
2. An icing wind tunnel test device for an aircraft anti-icing and deicing leading edge slat according to claim 1, wherein hot air ejection holes are formed in the flute-shaped tube and configured to eject hot air toward an internal cavity of the leading edge slat component by heating the flute-shaped tube.
3. The icing wind tunnel test device for the aircraft anti-icing and deicing leading edge slat of claim 1, wherein a sliding bush is arranged in the side connecting hole, and is used for enabling the connecting lug plate and the sliding bush to slide relatively to release temperature deformation of the leading edge slat component when the leading edge slat component is deformed by heating.
4. The icing wind tunnel test device for the aircraft anti-icing and deicing leading edge slat according to claim 1, wherein each group of connecting lug plates arranged at the rear part of the slat rib comprises two connecting lug plates positioned in one plane, and the connecting mode of the connecting hole of the main body component of the wing and the connecting lug plates simulates the real connecting stress of the slat and the wing.
5. The icing wind tunnel test device for the aircraft anti-icing and deicing leading edge slat according to claim 1, wherein the overall aerodynamic pressure center of the wind tunnel test device is located between the connection points of each group of connection lugs.
6. The icing wind tunnel test device for the aircraft anti-icing and deicing leading edge slat according to claim 1, further comprising: an ice-shaped measuring assembly;
the ice-shaped measuring assembly comprises a plurality of clamping plates and a guide frame used for fixing the clamping plates, and one end of each clamping plate is arranged to be in an inwards concave shape matched with the front end of the leading edge slat component.
7. The icing wind tunnel test device for an aircraft anti-icing and deicing leading edge slat of claim 6, wherein the ice shape measurement assembly is configured to be heated and then snapped into the front end of the leading edge slat component to measure the icing shape of the leading edge.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922374200.4U CN211919037U (en) | 2019-12-25 | 2019-12-25 | Icing wind tunnel test device for aircraft anti-icing and deicing leading-edge slat |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201922374200.4U CN211919037U (en) | 2019-12-25 | 2019-12-25 | Icing wind tunnel test device for aircraft anti-icing and deicing leading-edge slat |
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| CN211919037U true CN211919037U (en) | 2020-11-13 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498733A (en) * | 2021-02-07 | 2021-03-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Deicing device for icing wind tunnel test |
| CN112949127A (en) * | 2021-03-02 | 2021-06-11 | 西北工业大学 | Interference trailing edge structure of leading-edge slat and design method of interference amount of interference trailing edge structure |
| CN113460329A (en) * | 2021-06-28 | 2021-10-01 | 中国飞机强度研究所 | Aircraft structural strength ground test spare wing loading box section |
-
2019
- 2019-12-25 CN CN201922374200.4U patent/CN211919037U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498733A (en) * | 2021-02-07 | 2021-03-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Deicing device for icing wind tunnel test |
| CN112949127A (en) * | 2021-03-02 | 2021-06-11 | 西北工业大学 | Interference trailing edge structure of leading-edge slat and design method of interference amount of interference trailing edge structure |
| CN113460329A (en) * | 2021-06-28 | 2021-10-01 | 中国飞机强度研究所 | Aircraft structural strength ground test spare wing loading box section |
| CN113460329B (en) * | 2021-06-28 | 2023-05-16 | 中国飞机强度研究所 | Aeroplane structural strength ground test piece wing loading box section |
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