CN110606208B - Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof - Google Patents
Giant magnetostrictive material aircraft wing ice preventing and removing device and control system and application thereof Download PDFInfo
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- CN110606208B CN110606208B CN201910918783.4A CN201910918783A CN110606208B CN 110606208 B CN110606208 B CN 110606208B CN 201910918783 A CN201910918783 A CN 201910918783A CN 110606208 B CN110606208 B CN 110606208B
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- giant magnetostrictive
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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
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
Abstract
The invention relates to the technical field of aircraft wing deicing and preventing devices, in particular to a giant magnetostrictive material aircraft wing deicing and preventing device and a control system and application thereof. The device comprises: a first magnetic coil is wound on the upper giant magnetostrictive stretch block, and an upper covering covers the first magnetic coil; a second magnetic coil is wound on the lower giant magnetic extension block, a lower covering is covered on the second magnetic coil, and two ends of the upper giant magnetic extension block and the lower giant magnetic extension block are respectively fixed on respective supporting plates; the upper skin and the lower skin are connected through the middle flexible skin, the upper skin and the middle flexible skin are connected, and the lower skin and the middle flexible skin are connected through the connecting sheets, so that a V-shaped structure is formed; an interior lining is disposed on an interior side surface of the central flexible skin. The invention comprehensively performs deicing prevention and deicer through controlling the giant magneto material to perform micro-amplitude driving deformation and coil electrification heat generation, thereby achieving the purpose of quick low-energy consumption deicing prevention and deicer prevention of the wings.
Description
Technical Field
The invention relates to the technical field of aircraft wing deicing and preventing devices, in particular to a giant magnetostrictive material aircraft wing deicing and preventing device and a control system and application thereof.
Background
The information disclosed in this background of the invention is only for enhancement of understanding of the general background of the invention and is not necessarily to be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
The icing on the windward surfaces of the airplane wings and the like can seriously affect the flight performance, reduce the flight lift force, destroy the overall flight performance of the airplane, even cause the consequences of out-of-control of the airplane and the like, so that the novel anti-icing and deicing device for the airplane wings is required to be designed, the anti-icing and deicing efficiency of the airplane wings is improved, and the energy consumption of the airplane for preventing and deicing the airplane wings is reduced. For example, patent document CN201410032752.6 discloses an anti-icing system applied to an airplane wing, which includes components such as an exhaust gas treatment device, an air pump, a housing, an evaporator, a condenser, a steam line, and a liquid line; the waste gas of the piston engine is treated and then heated for the evaporator, so that the deicing system can work normally, and the problem of source of a heat source of the aircraft deicing system is solved.
However, the inventor researches and discovers that: the hot air deicing and ultrasonic deicing preventing and removing technology has the defects of huge airborne energy consumption, complex device and large thermal inertia, and has limitation in the application of actual wing deicing. Therefore, there is a strong need for the development of a novel, energy-efficient and mobile anti-icing technology based on the demand for a rapid anti-icing response and low energy consumption in the field of anti-icing.
Disclosure of Invention
Aiming at the problems, the invention provides a giant magnetostrictive material aircraft wing deicing and preventing device, a control system and application thereof. The invention utilizes the rapid deformation response of the giant magneto-induced material and the energization heating of the upper and lower semi-skin magneto-induced coils to perform the deicing function of the wings, can effectively reduce the airborne energy consumption and improve the deicing efficiency.
In order to achieve the purpose, the invention discloses the following technical scheme:
a giant magnetostrictive material aircraft wing deicing and ice protection device comprising: the device comprises an upper giant magnetostrictive extension block, a first magnetostrictive coil, an upper skin, a lower giant magnetostrictive extension block, a second magnetostrictive coil, a lower skin, a support plate, a middle flexible skin and an inner lining plate; wherein:
a first magnetic coil is wound on the upper giant magnetostrictive stretch block, and the upper skin covers the first magnetic coil; a second magnetic coil is wound on the lower giant magnetic extension block, the lower skin covers the second magnetic coil, and two ends of the upper giant magnetic extension block and the lower giant magnetic extension block are fixed on the supporting plate; the upper skin and the lower skin are connected through a middle flexible skin, so that a V-shaped structure is formed; the inner lining plate is a rigid plate and is arranged on the inner side of the middle flexible skin; the supporting plates are positioned at openings at two ends of the V-shaped structure.
Compared with the prior art, the invention has the following beneficial effects:
(1) the deicing device designed by the invention is used as an airplane wing, and deicing is realized by matching the characteristics of a giant magnetostrictive material with the change of skin surface stress, so that the deicing device has the characteristics of high mechanical response speed, good deicing effect and the like.
(2) The giant magnetostrictive material aircraft wing anti-icing and deicing device designed by the invention comprehensively performs anti-icing and deicing work on the wing by directionally controlling the giant magnetostrictive material to perform micro-amplitude driving deformation and coil electrification heat generation, thereby achieving the purpose of rapid low-energy-consumption anti-icing and deicing of the wing.
(3) The invention adopts the giant magnetostrictive material to directionally control the deformation to change the stress distribution on the surface of the skin, achieves the aim of mechanical deicing prevention of the airplane wings, and is suitable for deicing prevention of various airplane wings.
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 is a schematic structural diagram of an upper skin giant magnetostrictive ice preventing and removing device in an embodiment of the invention.
FIG. 2 is a schematic structural diagram of a lower skin giant magnetostrictive ice preventing and removing device in the embodiment of the invention.
Fig. 3 is a schematic structural diagram of a flexible connection device according to an embodiment of the present invention.
FIG. 4 is a schematic view of a control system of an anti-icing apparatus according to another embodiment of the present invention.
The designations in the above figures represent respectively: 1-upper giant magnetostrictive extension block, 2-first magnetostrictive coil, 3-upper covering, 4-lower giant magnetostrictive extension block, 5-second magnetostrictive coil, 6-lower covering, 7-support plate, 8-middle flexible covering, 9-connecting sheet, 10-lining plate, 11-connecting hole, 12-spring, 13-power supply, 14-magnetic control meter, 15-ammeter and 16-rheostat.
Detailed Description
It is to be noted that, unless otherwise specified, 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 to be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, 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, unless the context clearly indicates otherwise.
For convenience of description, the words "up", "down", "left" and "right" in the present invention, if any, merely indicate that the directions of movement are consistent with those of the drawings, and do not limit the structure, but merely facilitate the description of the invention and simplify the description, rather than indicate or imply that the referenced device or element needs to have a particular orientation, be constructed and operated in a particular orientation, and thus should 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 the terms used in the present invention should be understood as having specific meanings to those skilled in the art.
As described above, there is an urgent need to develop a novel, highly energy-efficient and mobile anti-icing and deicing technology based on the demand of quick anti-icing and deicing response and low energy consumption in the anti-icing and deicing field. Therefore, the invention provides an aircraft wing deicing and anti-icing device made of the giant magnetostrictive material by utilizing the characteristics of rapid deformation response of the giant magnetostrictive material and the characteristics of energization and heating of the magneto coil, and the invention is further explained by combining the attached drawings and the specific implementation mode of the specification.
Referring to fig. 1-3, the giant magnetostrictive material aircraft wing deicing prevention device designed by the invention comprises: the flexible magnetic core comprises an upper giant magnetostrictive extension block 1, a first magnetic coil 2, an upper skin 3, a lower giant magnetostrictive extension block 4, a second magnetic coil 5, a lower skin 6, a support plate 7, a middle flexible skin 8, a connecting sheet 9 and an inner lining plate 10.
First, referring to fig. 1 and 2, a first magnetic coil 2 is wound on the upper giant magnetostrictive stretch block 1, and the upper skin 3 covers the first magnetic coil 2 (as indicated by an arrow in fig. 1); the lower giant magnetostrictive stretch block 4 is wound with a second magnetic coil 5, and the lower skin 6 covers the second magnetic coil 5 (as shown by the arrow in fig. 2). The upper giant magnetostrictive extension block 1 and the lower giant magnetostrictive extension block 4 are respectively deformed by magnetic fields generated by the first magnetic coil 2 and the second magnetic coil 5 after being electrified, so that the stress distribution on the surfaces of the upper skin and the lower skin is changed, and the ice layer and the skins are separated to achieve the aim of deicing; and the electric heat generated after the magnetic coil is electrified can be used for heating the skin, so that the aim of anti-icing is fulfilled.
The two ends of the upper giant magnetostrictive extension block 1 and the lower giant magnetostrictive extension block 4 are fixed on the supporting plate 7, and the supporting plate 7 is mainly used for fixing the upper giant magnetostrictive extension block 1, the lower giant magnetostrictive extension block 4 and the spring 12 and providing a supporting effect for the upper giant magnetostrictive extension block 1 and the lower giant magnetostrictive extension block 4.
Secondly, referring to fig. 2 and 3, the upper skin 3 and the lower skin 6 are connected through a middle flexible skin 8, so as to form a V-shaped structure, namely an airplane wing airfoil; the inner lining plate 10 is a rigid plate and is arranged on the inner side of the middle flexible skin 8, so that the effects of supporting and ensuring the integrity of wing profiles are achieved; the supporting plates are positioned at openings at two ends of the V-shaped structure.
It should be noted that, since the region where the middle flexible skin 8 is located is the leading edge of the wing, the icing of the region is more serious than that of the upper and lower skins, so that the deicing of the region is more difficult and more important; in order to overcome the problem, the flexible intermediate medium of the middle flexible skin is adopted to deform the region for deicing, and the deformation of the middle flexible skin 8 can be driven by the deformation of the upper skin 3 and the lower skin 6, so that the stress distribution on the surface of the middle flexible skin 8 is changed, and the ice layer and the skin are separated to achieve the aim of quick deicing.
Further, in some implementations, with reference to fig. 3, the connection between the upper skin 3 and the middle flexible skin 8, and between the lower skin 6 and the middle flexible skin 8, is achieved by means of connecting tabs 9; the connecting piece 9 is a metal sheet, for example, a stainless steel sheet, which mainly connects the upper and lower skins with the middle flexible skin 8.
Further, in some implementations, the upper giant magnetostrictive extension block 1 and the lower giant magnetostrictive extension block 4 are made of giant magnetostrictive materials TbFe2, DyFe2 and SmFe2 alloy, and the length and the volume of the materials can change greatly at normal temperature due to the change of the magnetization state, namely, the materials have a great magnetostrictive coefficient.
In other implementations, referring to fig. 1 and 2, the upper giant magnetostrictive stretch block 1, the upper skin 3, the lower giant magnetostrictive stretch block 4 and the lower skin 6 are all provided with connecting holes 11, the upper giant magnetostrictive stretch block 1 and the upper skin 3 are fixed together through the connecting holes 11, the lower giant magnetostrictive stretch block 4 and the lower skin 6 are fixed together, and the skins and the giant magnetostrictive stretch blocks can be conveniently detachably fixed together through the connecting holes, so that the installation and replacement of parts are facilitated.
Further, the fixing means between the upper giant magnetostrictive stretch block 1 and the upper skin 3 and between the lower giant magnetostrictive stretch block 4 and the lower skin 6 include any one or more of the connection means of screwing, riveting, bonding, welding, etc., but it should be understood that the above connection means is not limited thereto, and the skilled person can select a suitable connection method as required without departing from the inventive concept of the present invention.
In addition, in some implementations, both ends of the upper giant magnetostrictive stretch block 1 are fixed on the support plate 7 through springs 12, and both ends of the lower giant magnetostrictive stretch block 4 are also fixed on the support plate 7 through springs 12. The advantage of adopting the spring to connect is that the deformation guarantee deformation of first magnetocoil 2, second magnetocoil 5 is replied fast, improves the deformation rate of replying of first magnetocoil 2, second magnetocoil 5, prevents the emergence of the unable scheduling problem that replies of first magnetocoil 2, second magnetocoil 5.
Further, the device for preventing and removing ice on the wing of the aircraft made of the giant magneto material provided by the invention is also used in the aviation field, such as preventing and removing ice on the wing of the aircraft.
In other implementations, the invention further provides a control system for the giant magnetostrictive material aircraft wing deicing device, referring to fig. 4, the control system comprises a power supply 13, a magnetron meter 14, an ammeter 15 and a rheostat 16 which are connected in sequence, and the power supply 13 and the rheostat 16 are both connected with the first magnetocoil 2 or the second magnetocoil 5, so as to form a closed loop, and the current in the magnetocoils is controlled to change the magnetic field flux, so as to control the deformation of the upper giant magnetostrictive extension block 1 and the lower giant magnetostrictive extension block 4.
It should be noted that the above-mentioned embodiments are only preferred embodiments of the present invention, and not intended to limit the present invention, and although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and equivalents can be made in the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of them.
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. Although the embodiments of the present invention have been described with reference to the accompanying drawings, it is not intended to limit the scope of the present invention, and it should be understood by those skilled in the art that various modifications and variations can be made without inventive efforts by those skilled in the art based on the technical solution of the present invention.
Claims (13)
1. A giant magnetostrictive material aircraft wing deicing prevention device is characterized by comprising: the device comprises an upper giant magnetostrictive extension block, a first magnetostrictive coil, an upper skin, a lower giant magnetostrictive extension block, a second magnetostrictive coil, a lower skin, a support plate, a middle flexible skin, a connecting sheet and an inner lining plate; wherein:
a first magnetic coil is wound on the upper giant magnetostrictive stretch block, and the upper skin covers the first magnetic coil; a second magnetic coil is wound on the lower giant magnetic extension block, the lower skin covers the second magnetic coil, and two ends of the upper giant magnetic extension block and the lower giant magnetic extension block are fixed on the supporting plate; the upper skin and the lower skin are connected through a middle flexible skin, so that a V-shaped structure is formed; the inner lining plate is arranged on the inner side of the middle flexible skin; the supporting plates are positioned at openings at two ends of the V-shaped structure.
2. An aircraft wing deicing device as claimed in claim 1 wherein the connection between the upper skin and the middle flexible skin, and between the lower skin and the middle flexible skin, is made by connecting tabs.
3. An aircraft wing deicing device as set forth in claim 2 wherein said attachment tabs are sheet metal.
4. An aircraft wing deicing device as set forth in claim 3 wherein said web is stainless steel sheet.
5. An aircraft wing deicing device as claimed in claim 1 wherein said upper and lower blocks are made of any one of the giant magnetostrictive materials TbFe2, DyFe2, SmFe2 alloy.
6. The device for preventing and removing ice on an airplane wing made of giant magnetostrictive materials according to claim 1, wherein the upper giant magnetostrictive block, the upper skin, the lower giant magnetostrictive block and the lower skin are provided with connecting holes, and the upper giant magnetostrictive block and the upper skin and the lower giant magnetostrictive block and the lower skin are fixed together through the connecting holes.
7. An aircraft wing deicing apparatus as claimed in claim 6 wherein said upper blocks are removably secured to said upper skin.
8. An aircraft wing deicing apparatus as claimed in claim 6 wherein said lower blocks are removably secured to said lower skin.
9. An aircraft wing deicing device as claimed in claim 7 wherein the means of attachment between the upper blocks and the upper skin and between the lower blocks and the lower skin are threaded.
10. An aircraft wing deicing device as claimed in claim 6 wherein the securement between said upper blocks and said upper skin and between said lower blocks and said lower skin is by any one of riveting, bonding or welding.
11. An aircraft wing deicing device as claimed in claim 10 wherein both ends of said upper and lower blocks are secured to the support plate by springs.
12. Use of a device according to any one of claims 1 to 11 for deicing aircraft wings, in the field of aeronautics.
13. A control system for an aircraft wing deicing device using giant magnetostrictive materials according to any one of claims 1 to 11, comprising a power supply, a magnetron meter, a current meter and a varistor connected in series, wherein the power supply and the varistor are connected to the first or second magnetocoil to form a closed circuit.
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111452951B (en) * | 2020-04-14 | 2022-01-14 | 山东大学 | Wing deicer and wing comprising same |
| CN111792039A (en) * | 2020-06-29 | 2020-10-20 | 山东大学 | Deicing device, system and method for airplane wing |
| CN112977838A (en) * | 2021-02-25 | 2021-06-18 | 成都凯天电子股份有限公司 | Embedded atmospheric pressure sensor with low deicing power consumption and high reliability |
| CN114843979B (en) * | 2022-07-04 | 2022-09-06 | 中北大学 | High-voltage cable deicing device based on giant magnetostrictive effect |
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| JP6549855B2 (en) * | 2015-02-17 | 2019-07-24 | 三菱航空機株式会社 | Aircraft windshield |
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| CN208931660U (en) * | 2018-05-03 | 2019-06-04 | 中国人民解放军空军工程大学 | The device for carrying out the anti-deicing of wing is motivated using rf (discharge) plasma |
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| CN87101760A (en) * | 1986-01-27 | 1987-09-23 | B·F·古德里奇公司 | The method and apparatus of leading edge surface deicing |
| WO2013156880A3 (en) * | 2012-04-18 | 2014-07-17 | Intertechnique | De-icing systems and methods |
| CN105253305A (en) * | 2015-10-10 | 2016-01-20 | 南京航空航天大学 | Leading-edge detachable type experiment wing structure based on piezoelectric deicing system |
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