CN113086211A - Mechanical deicing device and deicing method for electric heating partitioned area - Google Patents

Abstract

The invention is suitable for the technical field of deicing and provides a mechanical deicing device and a deicing method for an electric heating segmentation region, wherein the deicing device comprises: the plurality of electric heating elements are arranged in an array form; the vibration elements are arranged in one-to-one correspondence with the positions of the electric heating elements; the plurality of electric heating elements and the plurality of vibration elements are distributed on a first surface and a second surface of the airfoil model, wherein the first surface and the second surface form a leading edge area of the airfoil model, and the first surface and the second surface are separated by a leading edge line; the upper surfaces of the first surface and the second surface are provided with skins, a plurality of electric heating elements are embedded in the skins, and a plurality of vibration elements are arranged on the inner surfaces of the skins. The invention divides the whole ice into small ice blocks, and then carries out vibration deicing on each small ice block, thereby having high deicing efficiency, no residual ice and good deicing effect.

Description

Mechanical deicing device and deicing method for electric heating partitioned area

Technical Field

The invention relates to the field of deicing, in particular to a mechanical deicing device and a deicing method for an electric heating segmentation region.

Background

When the aircraft flies under icing meteorological conditions, when the outer part of the aircraft body collides with supercooled water drops, the surface can be quickly frozen, icing is accumulated to form an ice layer similar to the outline shape of the part, the optimal pneumatic appearance of the part is damaged under the condition, the flying performance of the aircraft is reduced, and a flying safety accident can be caused in serious cases. In order to avoid the harm caused by icing, effective protective measures are generally adopted in the easy-to-freeze areas of the airplane, the main ice preventing and removing means comprise hot air ice preventing and removing, electric heating ice preventing and removing, mechanical ice removing and the like, but the self-stored energy of the airplane is limited, the energy consumption for icing protection is low, icing is a very complicated process, some special situations sometimes exist, the icing problem is solved by only using a single method, and the requirement of flight protection can not be met.

For example, an airfoil component is mainly generated in a front edge section area during icing, the whole surface of the front edge of the component can be heated discontinuously by an electric heating means, so that the adhesion force of the icing to the surface of the component is reduced, the icing on the surface is removed by utilizing pneumatic external force during flight, if the ice shape of the front edge is symmetrical, the ice is subjected to more uniform external force and still continuously attached to the surface of the front edge, or the temperature of the whole surface is controlled to be above zero to perform direct anti-icing, but the energy consumption is larger by adopting long-time electrification under the condition; the inner surface of the front edge can be provided with a vibration element, the ice structure is damaged through mechanical vibration, and broken ice falls off by pneumatic external force, so that the aim of deicing is fulfilled.

Disclosure of Invention

The invention aims to provide a mechanical deicing device for an electrothermal segmentation area, which solves the technical problems of deicing in the prior art and comprises the following components:

the electric heating elements are arranged in an array manner;

the vibration elements are arranged in one-to-one correspondence with the positions of the electric heating elements;

the plurality of electric heating elements and the plurality of vibration elements are distributed on a first surface and a second surface of the airfoil model, wherein the first surface and the second surface form a leading edge region of the airfoil model, and the first surface and the second surface are separated by a leading edge line; the upper surfaces of the first surface and the second surface are provided with skins, the plurality of electric heating elements are embedded in the skins, and the plurality of vibration elements are arranged on the inner surfaces of the skins.

Further, the electric heating element is a flexible electric heating element.

Further, the electric heating element is composed of a plurality of rectangular frames.

Further, the vibration element is in contact with an inner surface of the skin.

Further, the vibration element is rectangular.

Further, the length of the vibration element in the direction of the leading edge line is greater than the length of the electric heating element.

Further, the vibrating element comprises excitation coils and insulating strips, and the excitation coils are distributed on the insulating strips at intervals.

Further, the exciting coil is located inside the rectangular frame of the electric heating element.

The invention also provides a method for deicing by adopting the mechanical deicing device for the electric heating partition region, which comprises the following steps:

step S1: electrifying the electric heating element to heat;

step S2: when the electric heating element completely melts the ice at the corresponding position on the surface of the skin, so that the whole ice is divided into a plurality of small ice blocks, stopping heating;

step S3: energizing a vibratory element that vibrates the ice cubes until the ice cubes fall off the skin surface.

The invention has the beneficial effects that:

in the prior art, an electric heating deicing mode is usually adopted when the surface of an airplane is iced, the method needs to be electrified all the time, so that the energy consumption is high, and when mechanical deicing is adopted, when large-area icing is met, more residual ice is generated; the invention combines the electric heating and mechanical deicing modes for use, firstly adopts the electric heating mode to melt the ice, and then adopts the mechanical vibration mode to separate the ice from the surface of the airplane, thereby having less energy consumption and good deicing effect.

In the prior art, when the leading edge area of the airfoil part of the airplane is iced in a large area, if the deicing is carried out only by adopting an electric heating mode, although the ice has melted away from the skin surface, since the aircraft is subjected to air resistance during flight, so that the ice remains attached to the skin surface and does not easily fall off, there is, in addition to this, a method in which a heating element is arranged on the leading edge line of the aircraft leading edge region, the whole piece of ice is divided into two parts along the leading edge line, it is then vibrated on both sides of the heating element with a vibrating element, but in this way only the ice on the leading edge line is divided into two parts, the ice away from the leading edge line is not divided, so that the time for heating is long during deicing, energy consumption is high, and the ice away from the leading edge line is easy to remain during vibration. In order to solve the problems in the prior art, the invention arranges a plurality of electric heating elements in the front edge area to heat the whole ice, so that the whole ice stops heating when being melted and divided into a plurality of small ice blocks, the electrifying time is short, the energy consumption is low, and the whole ice is quickly divided into the small ice blocks; the corresponding vibration elements are arranged below each electric heating element, the vibration elements are started at the moment, and the vibration is generated below each small ice block, so that the small ice blocks quickly fall off the surface of the skin.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic illustration of icing of the leading edge of an airfoil model in example 1 of the present invention;

FIG. 2 is a schematic cross-sectional view taken along the line A-A of FIG. 1 according to the present invention

FIG. 3 is a schematic illustration of the deicing effect in the prior art;

FIG. 4 is a schematic view of the leading edge region of the airfoil model of the present invention in an expanded configuration;

FIG. 5 is a schematic flow chart of a deicing method inembodiment 2 of the present invention;

fig. 6 is a schematic view of a state where the deicing method is employed inembodiment 2 of the present invention.

100-airfoil model, 101-leading edge region, 1011-first surface, 1012-second surface, 1013-skin, 1014-leading edge line, 200-ice, 300-deicer, 301-electric heating element, 302-vibrating element, 3021-exciting coil, 3022-insulating strip.

Detailed Description

The following description provides many different embodiments, or examples, for implementing different features of the invention. The particular examples set forth below are illustrative only and are not intended to be limiting.

Example 1:

an embodiment 1 of the present invention provides an electrothermal cutting regionmechanical deicing device 300, including:

a plurality ofelectric heating elements 301, wherein the plurality ofelectric heating elements 301 are arranged in an array;

a plurality ofvibration elements 302, wherein eachvibration element 302 is arranged in one-to-one correspondence with the position of eachelectric heating element 301;

the plurality ofelectric heating elements 301 and the plurality of vibratingelements 302 are distributed on afirst surface 1011 and asecond surface 1012 of theairfoil model 100, wherein thefirst surface 1011 and thesecond surface 1012 form a leading edge region of theairfoil model 100, and thefirst surface 1011 and thesecond surface 1012 are separated by a leadingedge line 1014; the upper surfaces of thefirst surface 1011 and thesecond surface 1012 have askin 1013, the plurality ofelectric heating elements 301 are embedded in theskin 1013, and the plurality ofvibration elements 302 are mounted on the inner surface of theskin 1013.

As shown in FIGS. 1 and 2, theicing 200 of theairfoil model 100 is mostly located at the leading edge region, and the ice layer formed by theicing 200 is similar and symmetrical to the leading edge region.

As shown in fig. 4, after the leading edge region of theairfoil model 100 is expanded, the leading edge region can be symmetrically divided into afirst surface 1011 and asecond surface 1012 along a leadingedge line 1014, wherein thefirst surface 1011 is the upper surface of theairfoil model 100, and thesecond surface 1012 is the lower surface of theairfoil model 100;

the plurality ofelectric heating elements 301 are uniformly distributed and embedded in theskins 1013 of thefirst surface 1011 and thesecond surface 1012, besides, theelectric heating elements 301 can be arranged on the upper surface and the inner surface of theskins 1013, so that the uniform arrangement aims to uniformly divide the whole ice at the same time when the large-area icing is generated in the leading edge area, and the situation that the partial ice is not divided is not generated; the specific number of theelectric heating elements 301 is not limited, and may be set to 4, 8, 12, or the like.

The distribution positions and the distribution number of thevibration elements 302 correspond to the positions and the distribution number of theelectric heating elements 301, so that when theelectric heating elements 301 heat and divide thewhole ice 200 into small ice blocks, thecorresponding vibration elements 302 are arranged below each small ice block to help the small ice blocks fall; in addition, the number of thevibration elements 302 may be larger than the number of theelectric heating elements 301 to accelerate the falling of the ice cubes.

In the prior art, when the leading edge area of the airfoil part of the airplane is iced in a large area, if the deicing is carried out only by adopting an electric heating mode, although the ice has melted away from the surface ofskin 1013, the ice remains attached to the surface ofskin 1013, is not easily shed, as shown in fig. 3, there is, in addition to this, a method of arranging a heating element on the leadingedge line 1014 of the aircraft leading edge region, dividing the ice monolith into two parts, it is then vibrated with the vibratingelement 302, but in this way only the ice on the leadingedge line 1014 is divided into two parts on the one hand, the ice far from the leadingedge line 1014 is not divided, so that heating time is long during deicing, energy consumption is high, and the ice far from the leadingedge line 1014 is easy to remain during vibration; based on the problems in the prior art, the invention arranges a plurality ofelectric heating elements 301 in the front edge area to heat thewhole ice 200, so that thewhole ice 200 stops heating when being melted and divided into a plurality of small ice blocks, the electrifying time is short, the energy consumption is low, and thewhole ice 200 is quickly divided into the small ice blocks; thecorresponding vibration elements 302 are arranged below eachelectric heating element 301, thevibration elements 302 are started at the moment, and the vibration is generated below each small ice block, so that the small ice blocks quickly fall off the surface of theskin 1013.

Further, theelectric heating element 301 is a flexibleelectric heating element 301.

Theelectric heating element 301 is preferably a flexibleelectric heating element 301 in the present invention, because the flexibleelectric heating element 301 can be bent into any shape, and only the pattern frame formed by the flexibleelectric heating element 301 is heated during heating, and the whole area where the flexible electric heating element is located is not heated like an electric heating film.

Further, theelectric heating element 301 is composed of a plurality of rectangular frames.

As shown in fig. 4, theelectric heating element 301 is formed by splicing a plurality of rectangular frames, wherein two adjacent rectangular frames share one side, in addition, theelectric heating element 301 may be configured in a honeycomb shape, a square shape, a triangular shape, etc., as long as thewhole ice 200 can be cut into small ice pieces, and the specific shape is not limited.

Further, the vibratingelement 302 is in contact with the inner surface ofskin 1013.

Thevibration element 302 can be tightly attached to the inner surface of theskin 1013 in a gluing or welding manner, so that the distance between thevibration element 302 and theice layer 200 is reduced, the loss of thevibration element 302 during vibration is reduced, and the deicing efficiency is improved.

Further, thevibration element 302 has a rectangular shape.

The shape of thevibration element 302 is the same as that of theelectric heating element 301, and may be rectangular, honeycomb, square, triangular, etc., so as to make thevibration element 302 cooperate with the ice shape divided by theelectric heating element 301, so as to better vibrate for deicing.

Further, the length of thevibration element 302 in the direction of the leadingedge line 1014 is greater than the length of theelectric heating element 301.

Further, the vibratingelement 302 includes anexciting coil 3021 and aninsulating strip 3022, and theexciting coil 3021 is distributed on theinsulating strip 3022 at intervals.

Further, theexciting coil 3021 is located inside the rectangular frame of theelectric heating element 301.

As shown in fig. 4, theexciting coil 3021 of thevibration element 302 is located at the center position corresponding to the rectangular frame of theelectric heating element 301, and this position is the preferred position where the vibration deicing effect is best, and besides, theexciting coil 3021 may be located on the left side or the right side of the rectangular frame.

Example 2:

the invention also provides a method for deicing by adopting the mechanical deicing device for the electric heating partitioned area, which comprises the following steps as shown in fig. 5:

step S1: theelectric heating element 301 is electrified for heating;

step S2: when theelectric heating element 301 completely melts theice 200 at the position corresponding to the surface of theskin 1013, so that thewhole ice 200 is divided into a plurality of small ice blocks, stopping heating;

step S3: thevibratory element 302 is energized and thevibratory element 302 vibrates the small ice pieces until they fall off the surface ofskin 1013.

In the above solution, when the aircraft needs to be deiced, the plurality ofelectric heating elements 301 are heated simultaneously, when the ice layer on the surface of theskin 1013 corresponding to the position of theelectric heating elements 301 melts and evaporates, thewhole ice 200 is divided into a plurality of small ice blocks, thevibration element 302 is turned on, wherein theexciting coil 3021 in thevibration element 302 starts to vibrate, and since theexciting coil 3021 is located at the center position of theelectric heating elements 301, the center position of the small ice blocks on theskin 1013 starts to vibrate until the small ice blocks fall off, as shown in fig. 6. If the front edge area of the airplane is only partially frozen, theelectric heating element 301 and thevibration element 302 in the area can be electrified separately, the ice in the area is divided into small ice blocks, and then vibration deicing is performed on each small ice block, so that the operation is simple, and the practicability is high.

Compared with the prior art, the invention has the advantages that one heating element is not arranged into a plurality of heating elements, the number of the heating elements is simply changed, the number of theelectric heating elements 301 is arranged into a plurality of heating elements, thewhole ice 200 is divided into small ice blocks, and then each small ice block is vibrated to perform deicing.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.

Claims (9)

1. An electrothermal split-area mechanical de-icing apparatus (300), comprising:

a plurality of electrical heating elements (301), the plurality of electrical heating elements (301) arranged in an array;

a plurality of vibration elements (302), wherein each vibration element (302) is arranged in one-to-one correspondence with the position of each electric heating element (301);

the plurality of electric heating elements (301) and the plurality of vibrating elements (302) are distributed on a first surface (1011) and a second surface (1012) of an airfoil model (100), wherein the first surface (1011) and the second surface (1012) constitute a leading edge region (101) of the airfoil model (100), and the first surface (1011) and the second surface (1012) are separated by a leading edge line (1014); the upper surfaces of the first surface (1011) and the second surface (1012) have a skin (1013), the plurality of electric heating elements (301) are embedded inside the skin (1013), and the plurality of vibration elements (302) are mounted on the inner surface of the skin (1013).

2. An electrothermal split-area mechanical de-icing apparatus (300) according to claim 1, wherein the electrical heating element (301) is a flexible electrical heating element.

3. An electrothermal split-area mechanical de-icing apparatus (300) according to claim 2, wherein the electrothermal element (301) is comprised of a plurality of rectangular frames.

4. An electrothermal split-area mechanical de-icing apparatus (300) according to claim 1, wherein the vibrating element (302) is in contact with an inner surface of the skin (1013).

5. An electrothermal split-area mechanical de-icing apparatus (300) according to claim 4, wherein the vibrating element (302) is rectangular.

6. An electrothermal split-area mechanical de-icing apparatus (300) according to claim 5, wherein the length of the vibrating element (302) in the direction of the leading edge line (1014) is greater than the length of the electrothermal element (301).

7. An electrothermal split-area mechanical de-icing apparatus (300) according to claim 6, wherein the vibrating element (302) comprises excitation coils (3021) and insulating strips (3022), the excitation coils (3021) being spaced apart on the insulating strips (3022).

8. An electrothermal split-area mechanical de-icing apparatus (300) according to claim 7, wherein the excitation coil (3021) is located within a rectangular frame of the electrothermal element (301).

9. A method of deicing using an electrothermal segmented area mechanical deicing apparatus (300) as claimed in any one of claims 1-8, comprising the steps of:

step S1: electrifying the electric heating element (301) for heating;

step S2: stopping heating when the electric heating element (301) completely melts the ice (200) at the position corresponding to the surface of the skin (1013) so that the whole ice (200) is divided into a plurality of small ice blocks;

step S3: energizing the vibratory element (302), the vibratory element (302) vibrating the small ice pieces until the small ice pieces fall off the skin (1013) surface.

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