CN111452951A - Wing deicer and wing comprising same - Google Patents
Wing deicer and wing comprising same Download PDFInfo
- Publication number
- CN111452951A CN111452951A CN202010289546.9A CN202010289546A CN111452951A CN 111452951 A CN111452951 A CN 111452951A CN 202010289546 A CN202010289546 A CN 202010289546A CN 111452951 A CN111452951 A CN 111452951A
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- wing
- vibrator
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- 239000012528 membrane Substances 0.000 claims abstract description 28
- 239000000463 material Substances 0.000 claims abstract description 15
- 239000000758 substrate Substances 0.000 claims abstract description 7
- 238000005265 energy consumption Methods 0.000 abstract description 5
- 230000009471 action Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 230000008859 change Effects 0.000 description 4
- 230000000737 periodic effect Effects 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means
Abstract
The invention discloses a wing deicing device and a wing comprising the same, wherein the device is arranged in the wing and comprises a substrate, a magnetic vibrator, an elastic film, a wing skin and a screw; the magnetic vibrator consists of a coil framework, a vibrator shell, a magnetic telescopic rod, an actuating rod, a coil and a disc spring; the wing vibration generator comprises a base body, a magnetic vibrator, a coil framework, an execution rod, an elastic membrane and a wing skin, wherein the base body is fixed inside a wing, the magnetic vibrator is perpendicular to the base body through the coil framework and is arranged in an inner cavity formed between the skin and the base body, the coil framework and the magnetic telescopic rod are arranged inside a vibrator shell, a coil is wound outside the coil framework, the top end of the magnetic telescopic rod is connected with the execution rod, the execution rod is connected with the center of the elastic membrane through a screw, the edge of the elastic membrane is. The invention utilizes the continuous deformation of the giant magneto material in the changing magnetic field to clear the accumulated ice on the wing, has high efficiency and low energy consumption, does not damage the aerodynamic appearance of the wing and does not damage the wing skin.
Description
Technical Field
The invention relates to a wing deicing device adopting a giant magnetostrictive material, and belongs to the technical field of airplane wing deicing.
Technical Field
When the aircraft body touches supercooled water drops in the air during the flight of the aircraft, the surface of the aircraft risks being frozen. When ice accretion is generated on the wings, the aerodynamic shape of the wings is changed, so that the lift force is reduced, the resistance is increased, and meanwhile, the ice accretion on the wings can also damage the manipulation performance, thereby seriously influencing the flight safety.
The conventional deicing methods include a thermal deicing method, a mechanical deicing method, a chemical deicing method and the like, wherein the mechanical deicing method is used for destroying adhesion between accumulated ice and wings by utilizing deformation of the surfaces of the wings so as to achieve the aim of deicing.
Disclosure of Invention
The invention provides a wing deicing device adopting a giant magnetostrictive material by utilizing the principle that the giant magnetostrictive material can generate telescopic deformation under the action of an external magnetic field, which is used for removing accumulated ice on a wing and has the advantages of small energy consumption, short time, no damage to a wing skin and the like.
The technical scheme adopted by the invention is as follows:
the invention provides a wing deicing device adopting a giant magnetostrictive material, which comprises a magnetostrictive vibrator, wherein the magnetostrictive vibrator consists of a coil framework, a vibrator shell, a magnetostrictive rod, an execution rod and a coil; the bottom of the vibrator shell is connected with the bottom of the coil framework, a coil is wound outside the coil framework, a magnetostrictive rod is arranged inside the coil framework, one end of the magnetostrictive rod is installed in a groove of the coil framework, the other end of the magnetostrictive rod is fixed in a groove in the lower portion of the actuating rod, the lower portion of the actuating rod is in clearance fit with the upper portion of the coil framework, and the upper portion of the actuating rod extends forwards to the upper surface of the vibrator shell.
As a further technical scheme, the top of the vibrator shell is provided with an elastic membrane, the top of the actuating rod is connected with the center of the elastic membrane, and the edge of the elastic membrane is connected with the vibrator shell.
As a further technical scheme, the vibrator shell is cylindrical, a circular opening is reserved at the upper end of the vibrator shell, and the lower end of the vibrator shell is connected with the bottom of the coil framework.
As a further technical scheme, a circular flange is arranged at the upper end of the vibrator shell, the upper surface of the flange is matched with the shape of the wing, and a threaded hole is formed in the circular flange.
As a further technical solution, the magnetostrictive rod is arranged on the axis of the vibrator housing.
As a further technical scheme, the coil is connected with an alternating current power supply.
As a further technical scheme, a flange is arranged outside the actuating rod, and a spring sleeved on an outer ring of the actuating rod is arranged between the flange and the inner wall of the top of the vibrator shell.
In a second aspect, the invention further provides a wing, which is characterized by comprising the wing deicing device and a base body, wherein the base body is fixed on the inner side of the wing, and a plurality of magnetic vibrators are arranged in an inner cavity formed between a wing skin and the base body through the bottom of a coil framework and perpendicular to the base body; the wing skin is connected with the vibrator shell through screws. The arrangement density degree of the magnetic vibrators is in direct proportion to the icing degree of the wings.
The invention has the beneficial effects that:
1. the magnetostrictive rod is made of the giant magnetostrictive material, the giant magnetostrictive material is a material capable of realizing mutual conversion of electromagnetic energy and mechanical energy, and the giant magnetostrictive rod has the advantages of high response speed, large strain and the like, can realize large-amplitude ultrasonic vibration output, when alternating current is introduced into a coil, the length of the magnetostrictive rod generates periodic change under the action of a periodic magnetic field generated by the coil, when the change is fast, the motion is transmitted to an elastic membrane through an execution rod, the motion is expressed as the vibration of the elastic membrane, the vibration generated by the elastic membrane can damage the adhesion of surrounding accumulated ice and wings, and finally the accumulated ice falls off under the action of wind force, so that the deicing purpose is achieved. Therefore, the device is used for removing the ice on the wings, and has the advantages of low energy consumption, short time, no damage to the wing skin and the like.
2. The deicing device is positioned in the wing, the upper surface of the flange of the vibrator shell is matched with the appearance of the wing, and in the deicing process, the amplitude of the elastic membrane is in a micron order, so that the influence on the aerodynamic appearance of the wing is small.
3. By utilizing the high-frequency vibration of the elastic membrane, the deicing can be completed within a short action time, the energy consumption is low, and the deicing efficiency is high.
4. The vibration of the elastic membrane is utilized to remove ice, the metal skin of the wing cannot be damaged, and the elastic membrane is connected with the magnetic vibrator through threads, so that the elastic membrane is convenient to replace.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
Fig. 1 and 2 are schematic views of installation positions of the wing deicing device.
Fig. 3 is a schematic view of a wing de-icing apparatus.
FIG. 4(a) is a cross-sectional view of a vibrator housing; fig. 4(b) is a top view of the vibrator case.
FIG. 5 is a cross-sectional view of an actuator rod.
In the figure: 1-an airfoil; 2-a substrate; 3-a magnetic vibrator; 4-wing skin; 5-a screw; 6-disc spring; 7-an elastic film; 8-a vibrator housing; 8-1 flange portion; 8-2 cylinder; 8-3 circular openings; 8-4 threaded holes; 9-an execution rod; 9-1 threaded hole; 9-2 upper part; 9-3 flanges; 9-4 lower part; 9-5 mounting holes; 10-a coil; 11-a magnetostrictive rod; 12-coil bobbin.
Detailed Description
It is to be understood that the following detailed description is exemplary and is intended to provide further explanation of the invention as claimed. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the invention. As used herein, the singular forms "a", "an", and/or "the" are intended to include the plural forms as well, unless the invention expressly state otherwise, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof;
for convenience of description, the words "up", "down", "left" and "right" in the present invention shall only be construed to mean that they correspond to the directions of the drawing itself, including up, down, left and right, without limitation to the structure, but merely to facilitate the description of the invention and to simplify the description, and shall not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore shall not be construed as limiting the invention.
The terms "mounted", "connected", "fixed", and the like in the present invention are to be understood in a broad sense, and may be, for example, fixedly connected, detachably connected, or integrated; the two components can be connected mechanically or electrically, directly or indirectly through an intermediate medium, or connected internally or in an interaction relationship, and specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
As described in the background of the invention, the prior art has shortcomings, and in order to solve the above technical problems, the present invention provides a wing deicing device using giant magnetostrictive material. The giant magnetostrictive material is a material capable of realizing mutual conversion of electromagnetic energy and mechanical energy, has the advantages of high response speed, large strain and the like, can realize large-amplitude ultrasonic vibration output, and can be used for airplane deicing.
In a typical embodiment of the present invention, as shown in fig. 1, the whole device of the magnetic vibrator 2 is installed inside the wing 1, the wing 1 includes two layers, the outer layer is a wing skin 4, and the inner layer is a substrate 2; the magnetic vibrators 2 are perpendicular to the base body 2 and are arranged in an inner cavity formed between the wing skin 4 and the base body 2; the arrangement density degree of the magnetic vibrators is in direct proportion to the icing degree of the wings; since the leading edge of the wing 1 is typically heavily iced, the placement of the magnetic vibrators 3 is more dense at the leading edge.
As shown in fig. 2, the magnetostrictive vibrator 2 is composed of a bobbin 12, a vibrator case 8, a magnetostrictive rod 11, an actuator rod 9, a coil 10, and a disc spring 6; the bottom of a vibrator shell 8 is connected with the bottom of a coil framework 12, a coil 10 is wound outside the coil framework 12, a magnetostrictive rod 11 is installed inside the coil framework, the magnetostrictive rod 11 is arranged on the axis of the vibrator shell 8, the lower end of the magnetostrictive rod 11 is placed in a groove of the coil framework 12 and used for fixing and limiting, the top end of the magnetostrictive rod is fixed in a groove at the lower part of an execution rod 9, the lower part of the execution rod 9 is in clearance fit with the upper part of the coil framework 12, a threaded hole is formed in the top of the execution rod 9 and is connected with the center of an elastic membrane 7 through a screw 5, the edge of the elastic membrane 7 is connected with the vibrator shell 8 through a screw 5, and a wing; when alternating current is conducted in the coil 10, the length of the magnetostrictive rod 11 generates periodic change under the action of a periodic magnetic field generated by the coil 10, when the change is fast, the motion is transmitted to the elastic membrane 7 through the execution rod 9 and is represented as vibration of the elastic membrane 7, the vibration generated by the elastic membrane 7 can damage the adhesion of surrounding accumulated ice and wings, and finally the accumulated ice falls off under the action of wind force, so that the aim of deicing is fulfilled.
The bobbin 12 described above
The magnetostrictive rod 11 is made of a giant magnetostrictive material, the giant magnetostrictive material is a material capable of realizing mutual conversion of electromagnetic energy and mechanical energy, and has the advantages of high response speed, large strain and the like, and can realize large-amplitude ultrasonic vibration output, so that the device is used for removing ice accumulated on wings, and has the advantages of low energy consumption, short time consumption, no damage to the wing skin and the like.
The thickness of the elastic membrane 7 is generally 0.5-3mm, 7 through holes are arranged on the elastic membrane, and the through holes on the elastic membrane respectively correspond to the threaded holes on the inner ring of the flange of the vibrator shell and the threaded holes on the execution rod.
As shown in fig. 3, 4(a) and 4(b), the vibrator housing 8 is a T-shaped structure as a whole, and includes a cylinder 8-2, the top of the cylinder extends outwards to form a circular flange 8-1 with a certain thickness, the center line of the circular flange 8-1 coincides with the center line of the cylinder, and the vibrator housing 8 is a symmetrical pattern; the interior of the cylinder is of a hollow structure, the bottom of the cylinder is open, a circular opening 8-3 is reserved in the center of the circular flange, and the upper surface of the circular flange is matched with the shape of the wing, so that the aerodynamic shape of the wing is prevented from being damaged; 12 threaded holes 8-4 are formed in a circular flange at the upper part of the vibrator shell 8, the threaded holes are divided into two groups, each group comprises 6 threaded holes, the threaded holes are respectively arranged on two concentric circles and are uniformly distributed along the circumference; the threaded holes on the inner ring correspond to the through holes on the elastic membrane 7, and the through holes on the outer ring correspond to the through holes on the wing skin 4.
Correspondingly, the wing skin is provided with 7 through holes, the shape of the middle large through hole is the same as that of the elastic membrane, and the other 6 through holes correspond to the threaded holes of the outer ring on the flange of the vibrator shell.
As shown in FIG. 4, the actuating rod 9 includes an upper portion 9-2, a lower portion 9-4; the upper part 9-2 and the lower part 9-4 are cylindrical, and the middle part is provided with a flange 9-3 extending towards the outer ring; the upper part 9-2 of the actuating rod 9 extends into a circular opening 8-3 of the vibrator shell 8, the outer ring of the lower part 9-4 is in clearance fit with the inner ring of the upper part of the coil framework 12, the lower part 9-4 is also provided with a mounting hole, the top of the magnetostrictive rod 11 is mounted in the mounting hole, and the lower part 9-4 is used for fixing the magnetostrictive rod 11; and a disc spring 6 is arranged between the flange 9-3 and the inner wall of the top of the vibrator shell 8, and pre-tensions the giant magnetostrictive rod 11, and meanwhile, the execution rod 9 can be ensured to recover along with the magnetostrictive rod 11. The center position of the upper portion 9-2 is provided with a threaded hole 9-1, and the threaded hole 9-1 can be connected with the elastic membrane 7 through a screw 5, so that the motion of the magnetostrictive rod 11 can be accurately transmitted. The bottom of the flange 9-3 is supported by the top of the bobbin 12.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The wing deicing device is characterized by comprising a magnetic vibrator, wherein the magnetic vibrator is composed of a coil framework, a vibrator shell, a magnetic telescopic rod, an execution rod and a coil; the bottom of the vibrator shell is connected with the bottom of the coil framework, a coil is wound outside the coil framework, a magnetostrictive rod is arranged inside the coil framework, and the magnetostrictive rod is made of a giant magnetostrictive material; one end of the magnetostrictive rod is arranged in the groove of the coil framework, the other end of the magnetostrictive rod is fixed in the groove at the lower part of the actuating rod, the lower part of the actuating rod is in clearance fit with the upper part of the coil framework, and the upper part of the actuating rod extends forwards to the upper surface of the shell of the vibrator.
2. The wing deicing apparatus as set forth in claim 1, wherein said vibrator housing is provided at a top portion thereof with an elastic membrane, the actuator rod top portion is connected to a center of the elastic membrane, and edges of the elastic membrane are connected to the vibrator housing.
3. The wing deicing apparatus as set forth in claim 1, wherein said vibrator housing is cylindrical, has a circular opening at an upper end thereof, and has a lower end connected to the bobbin.
4. The wing deicing apparatus as set forth in claim 1, wherein said vibrator casing has a circular flange at an upper end thereof, an upper surface of said flange conforming to the shape of said wing, and said circular flange having a threaded hole.
5. A wing de-icing apparatus as defined in claim 1 wherein said magnetostrictive rod is disposed on the axis of the vibrator housing.
6. A wing de-icing apparatus as defined in claim 1, wherein said coil is connected to an ac power source.
7. The wing deicing device as set forth in claim 1, wherein said actuator rod is externally provided with a flange, and a spring fitted around an outer ring of the actuator rod is provided between the flange and an inner wall of a top portion of the vibrator casing.
8. An airfoil comprising an airfoil de-icing assembly as claimed in any one of claims 1 to 9.
9. The airfoil of claim 8, further comprising a substrate, wherein the substrate is fixed on the inner side of the airfoil, and a plurality of the magnetic vibrators are arranged in an inner cavity formed between the airfoil skin and the substrate through the coil bobbin and perpendicular to the substrate; the wing skin is connected with the vibrator shell through screws.
10. The airfoil as claimed in claim 8, wherein the arrangement density of the magnetic vibrators is proportional to the icing degree of the airfoil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010289546.9A CN111452951B (en) | 2020-04-14 | 2020-04-14 | Wing deicer and wing comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010289546.9A CN111452951B (en) | 2020-04-14 | 2020-04-14 | Wing deicer and wing comprising same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111452951A true CN111452951A (en) | 2020-07-28 |
| CN111452951B CN111452951B (en) | 2022-01-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010289546.9A Expired - Fee Related CN111452951B (en) | 2020-04-14 | 2020-04-14 | Wing deicer and wing comprising same |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550665A (en) * | 2021-02-24 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Aircraft defroster based on elastic skin |
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