CN114655443B

CN114655443B - Deicing device, system and method for airplane

Info

Publication number: CN114655443B
Application number: CN202210150237.2A
Authority: CN
Inventors: 柳庆林; 倪章松; 刘森云; 王梓旭; 薛明; 张颖; 于馨凝
Original assignee: Chengdu Fluid Power Innovation Center
Current assignee: Chengdu Fluid Power Innovation Center
Priority date: 2021-12-30
Filing date: 2022-02-18
Publication date: 2023-06-23
Anticipated expiration: 2042-02-18
Also published as: CN114655443A

Abstract

The invention relates to an active-passive combined deicing system for an aircraft, comprising: the ice-repellent layer is arranged on the outer surface of the front edge skin of the aircraft ice-accumulating area; a mechanical deicing module, the mechanical deicing module comprising: the impact force generators are respectively arranged in a plurality of deicing partitions of the ice accumulation area; the control module is connected with the mechanical deicing module and used for controlling the working state of the mechanical deicing module, and when deicing is needed to be carried out on the ice accumulation area, the control module sends a first trigger signal to the mechanical deicing module so as to control at least one impact force generator in the mechanical deicing module to start working, so that the ice accumulation on the ice accumulation area is broken; the deicing partition is divided in advance based on the ice accumulation characteristic of the ice accumulation area. Based on the system, the invention also provides a deicing method and device, and the deicing device, system and method have high deicing efficiency and lower energy consumption.

Description

Deicing device, system and method for airplane

Technical Field

The invention relates to the technical field of aircraft deicing, in particular to a deicing device, a deicing system and a deicing method for an aircraft.

Background

When an aircraft flies in a cloud layer containing supercooled water drops, the windward surfaces of wings, tail wings, rotors and the like of the aircraft can be frozen, the aeronautical appearance of the aircraft can be greatly influenced by the icing of the aircraft, the flight safety of the aircraft is seriously influenced, particularly, the icing of the wings can directly lead to insufficient lift force, so that the aircraft cannot take off, climb and even cannot keep flying, and serious flight accidents are caused.

In order to avoid the damage caused by aircraft icing, the icing phenomenon needs to be dealt with by adopting a special deicing device or method, and the existing wing deicing technology mainly comprises hot air deicing, electric heating deicing, airbag deicing, antifreeze liquid deicing, mechanical deicing and the like by taking a wing as an example. The mechanical deicing periodically removes a small amount of accumulated ice on the front edge of the wing in a vibration mode, achieves the aim of maintaining flight safety with extremely low electricity consumption energy cost, and is a deicing mode with extremely low energy consumption.

However, the existing vibration deicing has the defect of incomplete deicing like airbag deicing, and the phenomenon of residual ice is encountered, namely, partial accumulated ice still adheres closely to the skin of the airfoil under the condition of vibration crushing, so that the aerodynamic performance of the aircraft is affected; meanwhile, if the acting force and the acting area of vibration are too large, the airfoil (for example, the airfoil of a wing, a tail wing or a rotor wing) may be excessively deformed, so that the airfoil material is damaged, but the vibration acting force is too small and the expected deicing effect is difficult to achieve, so that the vibration deicing has a problem in practical application engineering.

Therefore, in practical application, the deicing is generally performed by adopting a mode of combining thermal energy and mechanical energy, but on one hand, the energy consumption is too high, on the other hand, overflow water is generated during deicing due to thermal energy, and overflow ice is generated when the overflow water flows outside the ice accumulation area, so that the deicing effect is not ideal.

For example, see application publication number CN104627369a, an apparatus, method and profile body for deicing and/or avoiding icing and an aircraft are disclosed. The device has a heat-dissipating device for dissipating heat to a surface region of the aircraft, wherein the heat-dissipating device (12) is designed to dissipate heat in a linear manner in order to produce a break or a break line (32) or a parting line in the ice accumulated on the surface region. And the device is configured as a hybrid device for deicing and/or avoiding icing by means of thermal and mechanical energy. The deicing device disclosed in this patent application, although capable of achieving better deicing and/or deicing effects, has at least the following drawbacks, since it is still necessary to rely mainly on thermal energy for deicing:

on the one hand, because the electric power resources which the aircraft can carry in the middle of flight are limited, higher energy consumption will cause a certain electric power burden to the aircraft, especially the electric power burden caused by deicing will increase when the aircraft flies for a long distance or passes through a low-temperature zone; on the other hand, too high energy consumption would only increase the economic cost of the flight.

Therefore, there is a need for a deicing method that is low in energy consumption and does not affect flight safety.

Disclosure of Invention

In order to partially solve or partially alleviate the technical problems, and solve the problems of 'overflow ice' and higher energy consumption existing in the traditional vibration deicing method, a novel active and passive combined deicing method and device are provided, an ice-dispersing interface is utilized to reduce adhesion between accumulated ice and the surface of a skin, and the effectiveness of the vibration deicing method and device is improved.

The first aspect of the present invention provides an active-passive combined deicing system for an aircraft, comprising:

the ice-repellent layer is arranged on the outer surface of the front edge skin of the aircraft wing surface;

a mechanical deicing module, the mechanical deicing module comprising: a plurality of impact force generators respectively arranged on each deicing partition on the inner surface of the skin of the airplane airfoil;

the control module is connected with the mechanical deicing module and is used for judging whether deicing is needed to be performed on the skin at present according to the icing condition of the skin, and sending a first trigger signal to the mechanical deicing module when the deicing is needed to be performed on the skin, so as to control the mechanical deicing module to start deicing work, and the deicing work comprises at least one deicing work period, wherein the deicing work period comprises: at least two striking force generators strike the corresponding skin areas in sequence based on a preset sequence;

The deicing partition is obtained by dividing the deicing partition on the basis of the ice accumulation characteristic of the skin in advance, the deicing partition comprises a first partition and a second partition, at least two impact force generators for removing ice accumulation on the surface of the skin are arranged in the second partition correspondingly, at least two impact force generators for removing overflow ice are arranged in the first partition, impact points of the impact force generators arranged in the second partition have a heating function, and/or an electric heating film is arranged on the second partition.

Further, in some embodiments, the spacing between adjacent impact force generators disposed within the first zone is greater than the spacing between adjacent impact force generators disposed within the second zone, and/or the impact force of the impact force generators disposed within the second zone is less than the impact force of the impact force generators disposed within the first zone, and/or the width of the deicing zone at the wing root of the aircraft is less than the width of the deicing zone at the wing tip of the aircraft (or the width of the aircraft deicing zone gradually increases in the direction of the wing root to the wing tip of the aircraft).

Further, in some embodiments, further comprising: the ice accumulation monitoring module is connected with the control module and is used for monitoring the ice accumulation condition of the skin and uploading a first data signal containing the ice accumulation condition to the control module, wherein the ice accumulation condition comprises: the distribution characteristic of the ice accumulation, and/or the first trigger signal comprises: the working start time, the working end time, the beating force and the beating frequency of each beating force generator.

Further, in some embodiments, at least two impact force generators are disposed within the deicing partition, wherein at least one of the impact force generators is disposed above the deicing partition and at least one of the impact force generators is disposed below the deicing partition; and/or the number of the groups of groups,

the deicing partition has a spanwise length of between about 0.25m and about 1.0 m.

Further, in some embodiments, the system further comprises: a pulsed power supply for powering the mechanical deicing module.

Further, in some embodiments, the number of impact force generators located within a deicing zone at the wing root of the aircraft is greater than the number of impact force generators located within a deicing zone at the wing tip of the aircraft (or, the number of impact force generators for each deicing zone on the aircraft gradually decreases in the root-to-tip direction).

Further, in some embodiments, the strike point area on the interior surface of the skin is coated with a lubricating material, optionally: polytetrafluoroethylene, or graphite, or boron nitride, or polyoxymethylene.

The second aspect of the present invention also provides an active-passive combined de-icing assembly for an aircraft, comprising:

a mechanical deicing module, the mechanical deicing module comprising: the plurality of impact force generators are respectively arranged on each deicing partition of the skin of the aircraft;

the deicing partition is divided in advance based on the ice accumulation characteristics of the ice accumulation area;

at least two impact force generators are optionally arranged in the deicing partition, at least one impact force generator is arranged above the deicing partition, and at least one impact force generator is arranged below the deicing partition.

Further, in some embodiments, further comprising: a pulsed power supply for powering the mechanical deicing module.

In a third aspect of the present invention, there is also provided a deicing method based on the deicing system described above,

the method comprises the following steps:

monitoring the ice accumulation condition of the ice accumulation area through an ice accumulation monitoring module of the deicing system, and uploading a first data signal containing the ice accumulation condition to the control module;

The control module judges whether to start the mechanical deicing module based on the received first data signal, and when judging that the mechanical deicing module needs to be started, the control module sends a first trigger signal to the mechanical deicing module;

and starting deicing operation in response to the received first trigger signal in the mechanical deicing module, wherein the deicing operation comprises at least one deicing operation period, and the deicing operation period comprises: and (3) a process that at least two impact force generators impact the corresponding skin areas in sequence.

The beneficial effects are that:

according to the active-passive combined deicing system for the aircraft, accumulated ice around the front edge of the wing and overflow ice on the rear side of the front edge of the wing are removed through the combined action of the ice-thinning layer and the mechanical deicing device (such as a pulse force exciter), further growth of the accumulated ice is avoided within the range of the allowable envelope of the wing icing, and the safe flight limit of the aircraft is maintained.

The system mainly depends on the periodic work of the mechanical deicing device of each deicing partition to carry out deicing, and the impact force generators of different deicing partitions sequentially start to impact the corresponding skin areas, so that the corresponding skin areas deform, the skins of the deicing partitions adjacent to the corresponding skin areas do not deform (or deform slightly), therefore, the accumulated ice will generate cracks at the joints of the deicing partitions, and meanwhile, the interior of the accumulated ice covered on the skin areas is broken due to the deformation of the corresponding skin areas. Therefore, the crushing of the accumulated ice can be realized by selecting a smaller vibration action area or acting force, namely the deicing efficiency is improved, and the energy consumption in the deicing process is reduced.

Further, because the area of action of the single impact force generator is limited, when the accumulated ice of one or more deicing subareas is thicker, the impact force in the deicing subareas can be increased, so that the accumulated ice of the deicing subareas can be completely crushed, and the impact on the whole airfoil surface is smaller because the impact force of only a local area is larger.

Furthermore, the working sequence, the beating force and the beating frequency of the beating force generator of the system in the system can be adaptively adjusted based on the ice accumulation situation measured or predicted in real time, so that the system can be flexibly applied to various ice removal situations.

Compared with the traditional electric deicing system, the electric deicing system reduces the dependence on the action of heat energy, reduces the adhesion force of accumulated ice and breaks the accumulated ice in a passive and active mode, reduces the energy consumption of deicing the system, and achieves good deicing effect.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. Like elements or portions are generally identified by like reference numerals throughout the several figures. In the drawings, elements or portions thereof are not necessarily drawn to scale. It will be apparent to those of ordinary skill in the art that the drawings in the following description are of some embodiments of the invention and that other drawings may be derived from these drawings without inventive faculty.

FIG. 1 is a schematic view of a leading edge skin structure of an exemplary embodiment of the present invention;

FIG. 2 is a schematic view of the installation location of a impact force generator according to an exemplary embodiment of the present invention;

FIG. 3 is a schematic diagram of the connection between a pulsed power supply and a impact force generator according to an exemplary embodiment of the present invention;

FIG. 4a is a graph showing a test of deicing effect of a comparative experiment of a deicing system according to still another exemplary embodiment of the present invention with a prior art electrothermal deicing apparatus;

FIG. 4b is a test result of a comparative experiment of a deicing system according to yet another exemplary embodiment of the present invention with a electrothermal ice detachment apparatus according to the prior art;

FIG. 5 is a schematic diagram of a partition of a deicing partition in an exemplary embodiment of the present invention;

FIG. 6 is a schematic illustration of the location of the impact force generator on a cross-section of an airfoil in an exemplary embodiment of the invention;

FIG. 7 is a schematic cross-sectional view of an airfoil in an exemplary embodiment of the invention;

FIG. 8 is a schematic view of an airfoil configuration of an aircraft;

FIG. 9a is a schematic diagram of a stroke force generator according to an exemplary embodiment of the present invention;

FIG. 9b is a schematic structural view of a wing section;

fig. 10 is a physical view of a striking force generator according to yet another exemplary embodiment of the present invention.

Wherein 1 is the skin, 2 is the ice-repellent layer, 3 hits the force generator, 31 is the hit point, 4 is the base, 5 is deicing subregion, 51a is first upper subregion, 51b is first lower subregion, 52a is second upper subregion, 52b is second lower subregion, 53a is third upper subregion, 53b is third lower subregion, 6 is pulse power, 20 is wing box, and 22 is the accumulated ice.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

In this document, suffixes such as "module", "component", or "unit" used to represent elements are used only for facilitating the description of the present invention, and have no particular meaning in themselves. Thus, "module," "component," or "unit" may be used in combination.

The terms "upper," "lower," "inner," "outer," "front," "rear," "both ends," "one end," "the other end," and the like herein refer to an orientation or positional relationship based on that shown in the drawings, merely for convenience of description and to simplify the description, rather than to indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

The terms "mounted," "configured," "connected," "coupled," and the like, herein, are to be construed broadly as, for example, "connected," either permanently connected, detachably connected, or integrally connected, unless otherwise specifically indicated and defined; can be mechanically or electrically connected; the wireless communication connection can be adopted; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.

The terms "about" and "approximately" herein mean values that are understood by those of skill in the art to include a range of errors that are conventional in the art.

As used herein, "spanwise" refers to the direction from the root to the tip and "chordwise" refers to the reversal of the line from the leading edge point to the trailing edge point of the airfoil, i.e., along the length of the fuselage.

As used herein, "identical" or "similar" refers to differences between two or more items having an absolute value of zero or near zero such that the difference between two or more items has a negligible effect on the actual engineering application.

Herein, "deicing partition at the wing root of an aircraft" refers to one deicing partition near the wing root of an aircraft (e.g., one deicing partition furthest from the wing tip), or two deicing partitions or more deicing partitions, "deicing partition at the wing tip of an aircraft" refers to one deicing partition near the wing tip of an aircraft (e.g., one deicing partition furthest from the wing root), or two deicing partitions or more deicing partitions.

The ice deposition and the adhesion force of the surface of the skin are reduced by utilizing the ice-dispersing layer on the outer surface of the skin; the impact force generator arranged in the skin is utilized to impact the skin from inside to outside, so that the skin is forced to vibrate and deform, ice accumulation on the surface of the skin is driven to vibrate and deform, the ice accumulation is broken, and even the ice accumulation is directly separated from the surface of the skin; the ice deposit is directly separated from the surface of the skin or is blown away from the surface of the skin by airflow under the dual actions of the icephobic layer and the impact force generator. Specifically, the ice-repellent layer is arranged in the icing area (namely the icing area) of the front edge of the wing, and the ice-repellent layer cooperates with the impact force generator to remove the ice on the surface of the skin. The number and location of impact force generators can be redesigned according to the wing structure and icing area, typically one on each of the upper and lower surfaces of the leading edge of the chordwise upper wing, with the spanwise direction being arranged according to the spanwise zoning situation.

Example 1

A first aspect of the present invention provides an active-passive combined deicing system for an aircraft, the system comprising:

an icephobic layer disposed on an outer surface of a front edge skin (a structure of the front edge skin is shown in fig. 1) of the aircraft, wherein the icephobic layer 2 is used for reducing adhesion between ice deposition and the skin;

a mechanical deicing module, the mechanical deicing module comprising: a plurality of impact force generators 3 (wherein the impact force generators may be electromagnetic impact force generators, pneumatic impact force generators, thermal impact force generators, or other types of impact force generators, of course), and the plurality of impact force generators are respectively disposed in a plurality of deicing partitions of the ice accumulation region, wherein the impact force generators are used for impacting corresponding skin regions, so that the corresponding skin regions are deformed to different degrees;

the control module is connected with the mechanical deicing module and is used for judging whether deicing is needed to be performed on the skin at present according to the icing condition of the skin (namely, the control module is used for controlling the working state of the mechanical deicing module), and when the deicing is needed to be performed on the skin, a first trigger signal is sent to the mechanical deicing module so as to control the mechanical deicing module to start deicing operation, and the deicing operation comprises at least one deicing working period, wherein the deicing working period comprises: sequentially striking the corresponding skin region by at least two striking force generators based on a preset sequence;

The deicing partition is divided in advance based on the ice accumulation characteristic of the ice accumulation area.

In this embodiment, the mechanical deicing module is disposed inside the aircraft skin, that is, inside the wing, and compared with the technical scheme that the mechanical deicing module (for example, the piezoelectric fiber film) is disposed on the outer surface of the skin in the prior art, the mechanical deicing module is disposed inside the skin, so that the working stability of the mechanical deicing module can be ensured. In some prior art, since the mechanical deicing module, such as a film, is disposed between the surface of the wing skin and the icephobic layer, and is attached to the icephobic layer by an adhesive, the adhesive effect between the film and the icephobic layer may be reduced under the action of long-term vibration deformation, so that the vibration deformation of the film acting between the icephobic layers is gradually weakened, and it is difficult to monitor the state of the film (for example, whether the film falls off from the icephobic layer).

Further, in some embodiments, the system further comprises: the working monitoring module is connected with each impact force generator in the mechanical deicing module and used for monitoring and obtaining working parameters (including but not limited to working start time, working end time, impact force and impact frequency of the impact force generator) of each impact force generator, comparing the obtained working parameters with a first trigger signal sent by the control module, judging whether each impact force generator in the mechanical deicing module is in a normal working state (when the difference value between the actual working parameters of the impact force generator and the working parameters in the first trigger signal is smaller than or equal to a preset value, judging that the impact force generator is in the normal working state), and when at least one impact force generator is judged to be in an abnormal working state, giving a corresponding alarm by the system so as to remind a worker to overhaul.

Specifically, in some embodiments, the system further comprises: a pulsed power supply 6 for powering the individual impact force generators in the mechanical deicing module. Wherein the connection relation of the pulse power supply 6 and each of the impact force generators 3 is shown in fig. 3.

Preferably, in some embodiments, referring to fig. 2, each deicing partition includes: at least two impact force generators 3, wherein at least one impact force generator is disposed at a position corresponding to the upper surface (inner side) of the airfoil, so that when the impact force generator is activated to start working (i.e., impact the corresponding skin region), the impact force generator can act on the corresponding upper surface skin (inner side) and deform the corresponding upper surface skin, thereby causing the ice accretion outside the upper surface skin (i.e., the side in contact with the external air) to crack or even break and separate from the skin; accordingly, at least one impact force generator is disposed at a position corresponding to the lower surface of the airfoil, so that when the impact force generator is activated to start working, the impact force generator can act on the corresponding lower surface skin (inner side), so that the corresponding lower surface skin is deformed, and thus, the accumulated ice outside the lower surface skin is cracked or even broken, and separated from the skin. The upper surface of the wing, namely the surface of the wing facing upwards when the aircraft normally flies or stops, and the lower surface of the wing, namely the surface facing to the ground.

In some embodiments, the deicing partition is uniformly partitioned in the spanwise direction of the airfoil (i.e., on the windward side, as indicated by arrow L2 in fig. 8), e.g., several deicing partitions are partitioned in the spanwise direction of the airfoil, and the several deicing partitions have the same width in the spanwise direction.

Of course, in other embodiments, non-uniform partitions may be selected according to deicing requirements and wing structural characteristics at different positions in the wing span direction, for example, referring to fig. 8, the wing size gradually decreases from the wing root 8b (i.e. the connection between the wing and the fuselage) to the wing tip 8a, that is, the space inside the wing root 8b is relatively wider, and meanwhile, considering that the influence of ice accumulation at the wing root on the lift force of the aircraft is relatively large, more than two impact force generators may be disposed in the ice accumulation partition near the wing root 8b, and only one impact force generator may be disposed in the ice accumulation partition at the wing root. Or in other embodiments, the number of impact force generators for each deicing zone on the aircraft decreases progressively in the root-to-tip direction.

Preferably, the impact force generators in the deicing partition may be respectively disposed on the upper and lower corresponding areas inside the wing, and of course, it is understood that the impact force generators may be mounted at other positions of the wing, so long as the impact force generators can function to break ice accretions.

Preferably, in some embodiments, the icephobic layer is laid out according to icing ranges and regions obtained by wing flight envelope and icing condition envelope simulation calculation or icing wind tunnel test.

Preferably, in some embodiments, the first control signal includes, but is not limited to: the working start time, the working end time, the beating force and the beating frequency of each beating force generator.

Preferably, in some embodiments, the force of the force generator is set to a magnitude of between about 400N-600N with a frequency of about 5-8 strokes per second.

To mount and secure the impact force generator, preferably, in some embodiments, the system further comprises: a base 4 for mounting a fixed impact force generator, wherein the base 4 is disposed inside an airfoil (e.g., wing airfoil, tail airfoil), i.e., within a space enclosed by an inner surface of the airfoil, e.g., the base is disposed on a wing box 20.

Further, in some embodiments, to prevent the impact force generator from being positionally shifted after a long period of operation, the base 4 includes a recess having a certain depth for mounting the impact force generator, and the recess may restrict the displacement or deviation of the impact force generator in the horizontal direction to some extent when the impact force generator is mounted in the recess.

Preferably, in some embodiments, in order to prevent the impact force generator from generating great abrasion on the inner surface of the skin after the impact force generator strikes the skin for a long time, damage is caused to the skin material or the wing structure, and a lubricating material with a small lubrication coefficient, such as polytetrafluoroethylene, graphite, boron nitride, polyoxymethylene, etc., is coated on the impact point acting area on the inner surface of the skin (i.e., the area where the inner side of the skin is in direct contact with the impact force generator).

In a specific embodiment, the system is used for deicing an aircraft wing, wherein a plurality of deicing partitions are divided on the wing along the spanwise direction, each deicing partition comprises an upper surface and a lower surface of the wing, two impact force generators are respectively arranged in each of the plurality of deicing partitions, and the two impact force generators are respectively arranged corresponding to the upper surface and the lower surface of the wing, so that when the impact force generators start to work, the surface of the wing corresponding to the deicing partition can be impacted, the corresponding surface area of the wing vibrates to generate deformation, and further, the accumulated ice in the corresponding area generates cracks and even breaks.

For example, referring to FIG. 5, the airfoil illustrated in FIG. 5 includes at least three deicing zones: first, second, third deicing partition, wherein the first deicing partition comprises: a first upper partition 51a and a first lower partition 51b, the second deicing partition comprising: a second upper partition 52a and a second lower partition 52b; the third deicing partition includes: the third upper partition 53a and the third lower partition 53b are respectively and correspondingly provided with a hitting force generator in each of the upper partition or the lower partition, and in some application examples, the hitting force generator corresponding to the second upper partition 52a starts to hit the corresponding skin region (i.e. the skin in the region of the second upper partition 52a, and other hitting force generators do not start deicing operation at this time), so that the skin of the second upper partition 52a is deformed, and when the hitting force is high and the hitting frequency is high, the skin ice accumulation on the outer surface of the second upper partition 52a may generate cracks or even break, and is separated from the skin.

Further, since the first upper partition 51a adjacent to the second upper partition 52a is not subjected to the impact (the impact force generator in this partition does not start to operate), deformation does not occur (or even if the first upper partition 52a is subjected to the impact due to the approach to the second upper partition 52a, the impact is small, and thus deformation is small), that is, the deformation degree of the first upper partition 51a and the second upper partition 52a is different, and thus cracks are generated at the junction of the first upper partition and the second upper partition, and further, the breakage of the ice accumulation on the second upper partition 52a is promoted. Similarly, cracks may also occur at the junctions between the second lower partition, the third upper partition, and the second upper partition 52 a.

It can be understood that when the ice accumulation condition in one of the deicing partitions is very serious, or when the deicing requirement of one of the deicing partitions is more urgent, the impact force and the impact frequency of the impact force generator in the deicing partition can be increased, so that the ice accumulation in the corresponding region is crushed to a greater extent and is rapidly dropped. For example, when the outer surface ice of the skin corresponding to the first upper partition 51a is thicker, or when the deicing requirement of the first upper partition 51a is more urgent, the impact force and impact frequency of the impact force generator in the first upper partition 51a are obviously higher than those of other deicing partitions when the impact force generator works, so that the ice on the outer surface of the first upper partition 51a is obviously cracked, and then is rapidly broken and falls off, thereby realizing the deicing function. In this embodiment, the impact vibration of the impact force generator is mainly used to crush and de-ice the accumulated ice, so that the generation of overflow water is avoided to a certain extent, and the formation of overflow ice is avoided. Meanwhile, as the impact force and the impact frequency of the impact force generator in part of the deicing partitions such as the first upper partition 51a are only improved, the impact on other deicing partitions such as the second deicing partition or the third deicing partition is relatively small, and the whole airfoil is not caused to generate large vibration deformation so as to influence flight safety.

Preferably, in some embodiments, the impact force generators in different deicing zones may be set with appropriate operating parameters (e.g., with appropriate impact force, impact frequency, and impact time) based on the deicing requirements of the different deicing zones, which may reduce unnecessary energy consumption. Specifically, since the first deicing partition is close to the wing root (the influence of accumulated ice in the wing root area on the lift force of the aircraft is large), and the second deicing partition is close to the wing tip, the requirement on the deicing standard (or deicing effect) of the first deicing partition is higher than that of the third deicing partition, for example, under the condition that the beating time and the beating frequency are certain, the beating force generator of the first deicing partition needs to work for 3min to achieve the preset deicing effect, the beating force generator of the second deicing partition needs to work for 2min to achieve the preset deicing effect, the beating force generator of the third deicing partition needs to work for 1min to achieve the preset deicing effect, and if the synchronous vibration mode of each deicing partition in the prior art is selected, the preset deicing effect can be achieved only by the first, the second and the third deicing partitions, so that unnecessary workload is increased, and energy saving is not facilitated.

Further, referring to fig. 6, fig. 6 shows an airfoil section (fig. 6 is a section parallel to the fuselage direction) of one of the deicing zones, the section being divided by a dashed line L into two regions, wherein the region on the left side (the direction of the arrow is left) is the first zone and the right side is the second zone. The second sub-zone is typically the main area of the airfoil ice, and preferably at least two impact force generators are provided on the second sub-zone.

Specifically, in some embodiments, the cup, the first partition comprises: an area on the wing skin where spilled ice is easily created, the second section comprising: the leading edge of the wing skin is mainly ice accumulation area. Or the second partition is a first icing area (i.e. ice accumulation formed by supercooled water drops in the air), and the first partition is a second icing area (i.e. overflow ice icing area).

It will be appreciated that, since the wing structures of different types are different, for example, the radian of the wing of different types in the horizontal plane direction parallel to the fuselage (as shown by the arrow L1 direction in fig. 8) is different, or that is, the trend of change of the tangential slope of each point (the outermost curve) of the section of different wings is different. As shown in fig. 9b, (a), (b) and (c) in fig. 9b show schematic structural diagrams of different wing structures, and the degree of change in the tangential slope of the wing structure shown in (c) in fig. 9b is significantly greater than that of the wing structure shown in (a) or (b) in fig. 9.

During the flight of an aircraft, water melted by ice accumulation on the front edge portion (i.e. the second partition) of the wing flows reversely against the gravity of the aircraft (the flowing direction of the water is shown by an arrow in fig. 9), which is equivalent to that the air flow gives a thrust to the water, but during the flight, the highest speed of the aircraft is limited, and the maximum head-on wind speed (or the maximum airflow action) of the aircraft is limited (as can be understood, if the meteorological conditions such as wind speed are out of a safety range, the aircraft can avoid the corresponding route or stop flying), so that the thrust of the air flow to the water is limited, so that the distance that the water flows reversely along the wing against the gravity is limited, and when the gradient of the section of the wing is steeper (in other words, the gradient of each tangential line on the section of the wing changes to a greater extent), the distance that the air flow flows under the thrust of the air flow is relatively short, that is, the width of the area where the ice overflow is generated (i.e. the length along the arrow direction in fig. 9 a) is relatively small. For example, the width of the first section of the wing shown in fig. 9b (c) is smaller than the width of the first section of the wing shown in fig. 9 a.

Therefore, the first partition and the second partition of different types are also different, and the regional planning of the first partition and the second partition can be realized based on the wing structures of different types.

Since ice build-up (i.e., first ice build-up) formed by supercooled water droplets is typically located at the leading edge of the airfoil, and ice build-up (i.e., second ice build-up) formed by overflowed water is located at a position aft of the leading edge of the airfoil, preferably, in some embodiments, the boundary between the first and second partitions (i.e., the boundary between the first and second partitions) is the boundary between the first ice build-up and the second ice build-up, and the width of the first partition is the maximum distance that the overflowed water can flow outside the second partition (or the maximum distance that the overflowed water can flow upward from the boundary between the second partition and the first partition) under the driving of the airflow.

Further, in order to enhance the deicing capability of the deicing partition, a plurality of (e.g., four or six) impact force generators may be provided on the second partition, wherein the plurality of impact force generators are symmetrically provided on upper and lower surfaces inside the deicing partition.

Preferably, in other embodiments, a plurality of striking points are provided on the striking force generator (preferably, see fig. 9a, one striking force generator is provided with 4 striking points formed by outward bulge of the striking force generator, and the number of the striking points can be set adaptively according to different application scenarios).

For example, referring to FIG. 8, the 4 impact points of the impact force generator each act on a corresponding airfoil in the chordwise direction of the wing (as indicated by the arrow in FIG. 6). Of course, in other embodiments, multiple striking points of the striking force generator may also be disposed along the spanwise direction of the wing.

Preferably, in some embodiments, in order to avoid that the impact force generator generates a larger deflection during long-time working, a corresponding stress structure 7 is further arranged on the deicing partition corresponding to the impact force generator, when the impact force generator starts working, the impact point of the impact force generator acts on the stress structure 7 on the corresponding deicing partition, wherein the stress structure 7 can be made of a lubricating material, for example, a solid lubricating material, and can adapt to the impact action of the impact force generator for a long time without generating larger deformation or abrasion, meanwhile, as shown in fig. 7 (the section parallel to the machine body direction in fig. 7), the stress structure 7 is a structure with two sides bending a certain radian towards the inner side of the airfoil, so that the impact point of the impact force generator can act on the corresponding stress structure 7 even if deflection occurs during working, and the bending parts on the two sides of the stress structure can limit or prevent the impact point (or the impact head) of the impact force generator from generating further displacement to a certain extent.

Further, in some embodiments, the system further comprises: the ice accumulation monitoring module is connected with the control module and is used for monitoring the ice accumulation condition of the ice accumulation area and uploading a first data signal containing the ice accumulation condition to the control module; wherein the first data signal comprises: ice accumulation distribution in the ice accumulation area.

Specifically, in some embodiments, the ice accumulation monitoring module includes: the icing monitoring unit monitors the icing area of the airfoil in real time (or periodically) to obtain the icing condition of the airfoil, wherein the icing condition comprises: the ice accumulation distribution of the ice accumulation area, such as the ice accumulation degree and the ice accumulation type of each deicing partition. And after the ice accumulation monitoring unit acquires the ice accumulation condition, uploading the ice accumulation condition to the control module in real time (or periodically) so as to enable the control module to judge whether to start the mechanical deicing module.

Of course, in other embodiments, the ice accumulation monitoring module further includes: the ice accumulation prediction unit predicts ice accumulation growth and distribution in a future period based on the existing ice accumulation data (such as ice accumulation prediction data, reports of other pilots and meteorological conditions of a flight area), periodically (or in real time) uploads the ice accumulation condition containing the ice accumulation growth and distribution prediction to the control module, judges whether the mechanical deicing module needs to be started or not based on the information, and if the mechanical deicing module needs to be started, further analyzes and calculates the starting working time, the ending working time, the striking strength and the striking frequency of each striking force generator in the mechanical deicing module based on the information. In this embodiment, the aircraft ice accumulation is prevented, for example, the mechanical deicing device is turned on before the ice accumulation is formed or when the ice accumulation amount is small, so that the ice accumulation is difficult to continue to form.

In order to effectively control the energy consumption during deicing while improving the deicing efficiency, in some embodiments, the mechanical deicing device periodically performs deicing, i.e., the system includes a plurality of deicing cycles during deicing, wherein each of the impact force generators may operate simultaneously or sequentially in a set order during one deicing cycle, e.g., in some embodiments, the impact force generators may be individually prioritized. Specifically, the corresponding impact force generators are marked as a first priority, a second priority and a third priority … … (n+1) th priority, when the mechanical deicing device starts to work, the impact force generator marked as the first priority (namely, the 1 st group of impact force generators) starts to deicing work (namely, impact the corresponding skin region, so that the skin deforms), when the impact force generator marked as the first priority ends to deicing work, the impact force generator marked as the second priority (namely, the 2 nd group of impact force generators) starts to deicing work, until the impact force generator marked as the second priority ends to deicing work, the impact force generator marked as the third priority (namely, the 3 rd group of impact force generators) starts to work, and so on, until the impact force generator marked as the N th priority (namely, the N th group of impact force generators) ends to finish a deicing cycle; wherein the same priority comprises at least one impact force generator of at least one deicing partition. Preferably, there is a certain interval, for example, an interval of 0.5s, between the end operation time of the impact force generator marked as the nth priority and the start operation time of the impact force generator marked as the n+1th priority.

Of course, in other embodiments, different priorities may be alternately operated at intervals, e.g., dividing the impact force generators corresponding to the upper surface (inner side) of the airfoil into a first priority, dividing the impact force generators corresponding to the lower surface (inner side) of the airfoil into a second priority, and during a deicing period, the impact force generators labeled as first priority (or second priority) are first activated to begin operation, and after the impact force generators labeled as first priority (or second priority) end operation, the impact force generators labeled as second priority (or first priority) are activated to begin operation after a period of time (e.g., 0.5 s) has elapsed; after the impact force generator marked as the second priority (or the first priority) finishes the operation, the impact force generator marked as the first priority (or the second priority) is activated again to start the operation after a certain period of time (for example, 0.5 s), and thus, the operations are reciprocally performed three times each (of course, the activation times may be adaptively set based on the ice accumulation condition and the working experience of the worker, for example, the activation times may be increased, set to 4 times, 5 times or more when the ice accumulation degree is serious, and set to 2 times or 1 time when the ice accumulation degree is light), and one deicing cycle is completed.

Of course, in still other embodiments, the deicing priorities of the different deicing partitions may also be ordered, with the different deicing partitions being labeled as: first, second, third, and nth deicing priorities … …, respectively. The impact force generators in the deicing partition marked with the deicing priority can be activated sequentially according to the priority, or alternatively activated at intervals based on the setting.

It will be appreciated that the prioritization of impact force generators or de-icing zones described above may be preset (e.g., by a worker based on historical experience), or may be prioritized or adjusted in conjunction with real-time airfoil ice distribution. Likewise, the number of shots (i.e., the number of jobs) of the impact force generators, and the timing of the shot intervals of each of the impact force generators may be set and adjusted based on the real-time icing of the airfoil and the historical experience of the worker.

For example, in one embodiment, the deicing partition comprises: a plurality of deicing partitions labeled as an i deicing priority, an ii deicing priority, an iii deicing priority … …, an N deicing priority, wherein the first deicing priority includes: a hit generator labeled as priority I1 (corresponding to the inside of the upper surface of the airfoil) and a hit generator labeled as priority I2 (corresponding to the inside of the lower surface of the airfoil); wherein the second deicing priority includes: impact force generators labeled as priority ii 1 (corresponding to the inside of the upper surface of the airfoil) and impact force generators labeled as priority ii 2 (corresponding to the inside of the lower surface of the airfoil) … … wherein the nth deicing priority comprises: a hit generator labeled as the nth 1 priority (corresponding to the inside of the upper surface of the airfoil) and a hit generator labeled as the nth 2 priority (corresponding to the inside of the lower surface of the airfoil).

When the system starts deicing, the deicing partition marked as the first priority starts working first, wherein the impact force generators marked as the first priority and the second priority in the deicing partition start working alternately (interval of 0.5 s) and are respectively excited 3 times, namely the deicing partition marked as the first priority completes the corresponding deicing work, and then the deicing partition marked as the second priority starts working, wherein the impact force generators marked as the second priority in the deicing partition start working alternately (interval of 0.5 s) and are respectively excited 3 times, and so on until the impact force generators marked as the second priority complete the corresponding deicing work, namely one deicing period.

Preferably, in some embodiments, one deicing cycle is 30S.

The firing order of the impact force generators 3 may be simultaneous firing, sequential firing, or other predetermined firing order. For example, in a particular embodiment, the airfoil includes ten deicing zones, wherein the provision of the ice-repellent layer reduces ice adhesion to below 100kPa, or to below 50% of the ice cohesive stress. The impact force generators were divided into two groups on the upper and lower surfaces of the airfoil, each excited 3 times at 0.5 second intervals during deicing. And when the deicing of 1 deicing partition is finished, starting the deicing of the other 1 deicing partition. And (5) sequentially carrying out the cycle of beating, crushing and accumulating ice on each deicing partition. Assuming that the set deicing period is 30 seconds, 10 partitions complete a deicing cycle in sequence throughout 1 deicing period.

Of course, it is understood that the specific number of shots, shot intervals, and shots of the force generators in different deicing zones are not necessarily the same and may be set according to the specific ice accumulation.

Because the wing root portion has a greater effect on the lift of the aircraft, it is preferred that in some embodiments, the deicing partition located at (or near) the wing root region (or tail root region) preferably begins deicing operation, and then the deicing partition located at (or near) the wing tip region (or tail tip region) begins deicing operation again.

In this embodiment, since the airfoil skin is not heated (or the heating action on the airfoil skin is small, for example, the heating time is short or the heating temperature is low), no overflow water is generated on the airfoil (or the amount of overflow water is small even if overflow water is generated), so that overflow ice is not formed outside the icing area, and the deicing action is better. Meanwhile, the deicing mode of alternate excitation and periodic vibration is adopted, so that compared with the traditional deicing mode, the deicing mode is more energy-saving, and good deicing effect is ensured.

Further, to provide deicing efficiency of the system, the area occupied by the icephobic layer (i.e., the area provided with the icephobic layer) is greater than the area of ice accumulation.

Preferably, in some embodiments, the aircraft airfoil skin may be selected from a metallic material or a composite material, and the icephobic layer disposed on the airfoil skin may be any surface material capable of reducing ice adhesion, such as a superhydrophobic/superlubricated surface. Wherein, the icephobic layer reduces the adhesion of the accumulated ice to 100kPa or reduces the cohesive stress of the accumulated ice to below 50 percent.

Preferably, in some embodiments, the ice-repellent layer may also be adaptively arranged based on different ice removing areas, for example, an ice accumulation area where ice accumulation is easily generated is provided with a surface material with a strong capability of reducing ice adhesion.

Further, in some embodiments, the deicing partition has a spanwise length between about 0.25m and about 1.0 m.

Referring to fig. 2, the system in this embodiment includes an icephobic layer 2 disposed on the surface of the wing leading edge skin, and a striking force generator and its base under the wing skin, and a pulse power supply 6 for supplying power to the striking force generator. According to the invention, the adhesion force of the accumulated ice 22 and the skin 1 is reduced through the ice-repellent layer 2 arranged on the surface of the skin, the skin is hit by the hit force generator from inside to outside, the skin is forced to vibrate and deform by the short-time strong hit force, the accumulated ice with reduced adhesion force is crushed, and the crushed accumulated ice on the surface of the skin is separated from the skin under the blowing action of air flow. The ice accumulation on the front edge of the wing can be removed by periodically performing the above actions, and the deicing period can be adjusted as required.

In a further embodiment of the invention, a set of electrical actuators are arranged on the upper and lower airfoil surfaces of the leading edge body inboard of the skin (see FIG. 1) for generating transient forces on the leading edge skin to achieve a vibratory deicing effect. The exciter is adhered to the mounting seat (i.e. the base) extending out of the wing box 20 by using 3M VHB double sides, the upper surface of the exciter is clung to the skin, but is not connected with the skin, the exciter is driven by using an 8-channel high-voltage pulse power supply, the driving voltage is adjustable within the range of 100V-1000V, the maximum output pulse current is 800A, the pulse time is adjustable within the range of 100 mu s-1000 mu s, and the maximum pulse frequency is 4Hz. Wherein, the position and the size of the exciter can be adjusted adaptively based on practical application.

In still another embodiment of the present invention, the impact force generator is constructed as shown in fig. 10 such that the length direction of the impact force generator is parallel to the span-wise direction of the airfoil when the impact force generator is installed on the base in the corresponding deicing partition.

Unlike the above embodiment, the striking point of the striking force generator in this embodiment does not have a convex structure, and the corresponding area inside the striking point 31 is provided with a vibration structure, which can act on the striking point 31 to vibrate, and other parts of the striking force generator can vibrate under the driving of the striking point.

Example two

Based on the first embodiment, the present invention also provides another deicing system, including each device in the deicing system, but unlike the embodiment, the system further includes: the thermal deicing module, specifically, in a non-limiting embodiment, is further attached to an inner wall surface of the leading edge skin, and is used for heating the skin surface to melt surface layer icing (i.e. the thermal deicing module is composed of 2 polyimide electric heating films, a heating area of a single heating film is 470mm (spanwise direction) by 200mm (leading edge arc direction), rated power is 28V, rated power is 1.3kW, and actual heating power is controlled by a 96V adjustable direct current power supply. Or in other non-limiting embodiments, the thermal deicing module may also be implemented by a heating function of the impact force generator.

It will be appreciated that with mechanical deicing modules (e.g., a set of electrical actuators disposed within the airfoil) in combination with the icephobic layer, good deicing may already be achieved under normal conditions (e.g., micro-, light-, or medium-icing), and if extreme weather conditions are encountered, a deicing system with thermal deicing modules is preferred for achieving good deicing.

It will be appreciated that in this embodiment, the thermal energy deicing module assists, and thus the overall energy consumption of the deicing system is still low.

Preferably, in some embodiments, the heated deicing module comprises a plurality of heating units (e.g., a plurality of electrically heated films or filaments), wherein the plurality of heating units are arranged based on deicing requirements of different deicing zones, e.g., a plurality of heating units are arranged in zones that are prone to ice accumulation, fewer heating units are arranged in zones that are relatively less prone to ice accumulation, or no heating units are arranged.

Preferably, in some embodiments, the heating unit may be provided at the junction of the individual deicing zones, so that ice accretions on the skin may split along the line of the junction.

Preferably, in some embodiments, to ensure consistency of design, or to simplify structural components of the system, such that the deicing partitions may share the same heating power source, the heating power of each deicing partition remains the same, i.e., the heating power per unit area of each partition is required to be the same or similar, while since the wing tip of the airfoil is generally thinner than the wing root, the deicing partition at a location near the wing tip has a larger spanwise width, and the deicing partition at a location near the wing root has a relatively smaller spanwise width (or, the width of the aircraft deicing partition gradually increases in the direction from the wing root to the wing tip of the aircraft), thereby ensuring that the area sizes of each deicing partition are the same or similar, such that the heating power per unit area of each deicing partition remains the same or similar at the same heating power.

Preferably, in some embodiments, referring to fig. 6, at least one first impact force generator is disposed on the first partition at intervals, and a plurality of second impact force generators are disposed on the second partition closely (i.e., the distance between adjacent second impact force generators on the second partition is greater than the distance between adjacent first impact force generator partitions on the first partition), where the thermal deicing module primarily acts on the second partition (e.g., an electric heating film is disposed on the second partition).

Since the thermal deicing module is added in this embodiment, overflow ice is easily generated during deicing, and the overflow ice generally grows in a region where heating is not performed, for example, a junction between a heating region (i.e., a region where the thermal deicing module is performed, i.e., a second partition) and a non-heating region (i.e., a first partition), or in the non-heating region. It will be appreciated that the primary function of the first impact force generator on the first partition is to remove the overflow ice, which is typically thin, so that only a small number of first impact force generators may be provided on the first partition.

Preferably, the striking point of the second striking force generator (i.e. the structure of the striking force generator directly acting on the skin in the process of striking the skin) has a heating effect, and the second striking force generator adopts a working scheme with high frequency and low force during working, so that the front edge of the wing is prevented from being excessively deformed to damage the wing material while the preset deicing effect is realized, and further, when the ice accumulation on the second partition is thicker, the heating effect of the striking point of the second striking force generator is started to promote the breaking and falling of the ice accumulation. The first impact generator typically has no heating effect because there is less ice accumulation on the first partition (mainly overflow ice). It will be appreciated that in this embodiment, the thermal deicing module may alternatively be omitted, as the second impact force generator has both thermal conduction and heating.

Preferably, in some embodiments, the working time periods of the impact force generators of the first partition and the second partition are different, the impact force generator of the second partition with the heating function (or the impact force generator without the heating function and the electric heating film arranged on the second partition start working together) preferentially starts deicing, the skin is impacted and heated, so that the accumulated ice on the outer side of the skin is broken and falls off, when the impact force generator of the second partition works for a period of time, part of overflow water flows to the second partition under the action of airflow to generate overflow ice, and when the overflow ice is generated, the impact force generator of the first partition starts deicing. Because the generation amount of the overflow ice is relatively less, the impact force generator of the first deicing partition can intermittently start deicing operation, thereby meeting deicing requirements and reducing the whole deicing energy consumption.

Specifically, in some embodiments, the control module may implement the time-division operation of the first partition and the second partition, and may preset the start operation time and the end operation time of the impact force generator corresponding to the first partition and the second partition.

For example, in this embodiment, the control module sets the working parameters of the first and second partitions in advance: when the impact force generator of the second partition starts deicing operation for 30min, the impact force generator of the first partition starts deicing operation, and stops deicing operation after operation for 10min, and then the impact force generator of the first partition starts deicing operation again after continuing deicing operation for 30min, namely the impact force generator of the first partition can intermittently start deicing operation. That is, the impact force generators on the second partition may reduce periodic intermittent impacts, although the duty cycle or frequency of the impact force generators of the second partition may be set based on specific deicing requirements.

Accordingly, in some embodiments, the first trigger signal in the control module further comprises: an on or off signal for controlling a thermal deicing module (e.g., an electrically heated membrane, or a heating module on a strike force generator for heating a strike point).

In order to verify the energy-saving effect of the invention, deicing tests are respectively carried out on a deicing system (namely a first deicing system) comprising a thermal energy deicing module and a electrothermal deicing system (namely a second deicing system) in the prior art, wherein the selected test conditions are shown in a table 1:

table 1

Based on the above experiments, test results are shown in fig. 4a and 4 b.

Wherein, the graph a in fig. 4a shows the experimental graph of the deicing effect of the first deicing system, and the graph b in fig. 4a shows the experimental graph of the deicing effect of the second deicing system, and as can be seen from fig. 4a, the deicing effect of the first deicing system is obviously better than that of the second deicing system.

A in FIG. 4b represents the energy consumption per unit area (W/cm) of the second deicing system during deicing ² ) B represents the energy consumption per unit area (W/cm) of the first deicing system during deicing ² ) The ordinate of fig. 4b represents the deicing energy consumption per unit area, from fig. 4b at least the following information can be derived: under the same test environment, the deicing energy consumption of the first deicing system is obviously lower than that of the second deicing system, and referring to fig. 4a and 4b, the first deicing system provided by the invention is obviously better than electrothermal deicing in the prior art in deicing effect and energy saving. In general, the first deicing system provided by the invention achieves better deicing effect and greatly reduces deicing energy consumption under the same experimental condition.

Example III

Based on the system in the above embodiment, a second aspect of the present invention is to provide an active-passive combined deicing device for an aircraft, the device comprising:

the ice-repellent layer is arranged on the outer surface of the front edge skin of the ice accumulation area of the aircraft;

a mechanical deicing module, the mechanical deicing module comprising: the plurality of impact force generators are respectively arranged on the inner surfaces of a plurality of deicing partitions of the skin of the ice accumulation area;

Preferably, reference is made to the first and second embodiments for specific implementation of the mechanical deicing device in this embodiment.

Example IV

Based on the system in the foregoing embodiments, a third aspect of the present invention further provides a deicing method based on any one of the foregoing embodiments, including the steps of:

monitoring the ice accumulation condition of an ice accumulation area through an ice accumulation monitoring module of the deicing system, and uploading a first data signal containing the ice accumulation condition to a control module;

The mechanical deicing module begins operation in response to the received first trigger signal.

It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.

The above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention, and are intended to be included within the scope of the appended claims and description.

Claims

1. An active-passive combined deicing system for an aircraft, comprising:

a mechanical deicing module, the mechanical deicing module comprising: the aircraft comprises a plurality of impact force generators, a plurality of deicing partitions, a plurality of driving force generators and a plurality of driving force generators, wherein the impact force generators are respectively arranged on each deicing partition on the inner surface of the skin of the aircraft wing surface, a stress structure is further arranged on an action area of an impact point of each deicing partition, the stress structure is a structure with two sides bent towards the inner side of the wing surface, and the stress structure is made of a lubricating material;

the system further comprises: a base disposed inside the airfoil, the base being provided with a recess, and the impact force generator being mounted on the base through the recess;

The deicing partition is divided on the basis of the ice accumulation characteristic of the skin in advance, and comprises a first partition and a second partition, wherein at least two impact force generators for removing ice accumulation on the surface of the skin are arranged in the second partition correspondingly, and at least two impact force generators for removing overflow ice are arranged in the first partition; wherein the striking point of the striking force generator arranged in the second partition has a heating function, and/or an electric heating film is arranged on the second partition; the width of the deicing partition is gradually increased along the direction from the wing root to the wing tip of the aircraft, so that the heating power of each deicing partition in unit area is kept the same or similar;

wherein each of said impact force generators is marked with a corresponding priority during one of said deicing duty cycles, each of said impact force generators will start operating sequentially or alternately at intervals according to said priority during one deicing duty cycle; and/or each of said deicing partitions is marked with a corresponding priority during one of said deicing operation periods, each of said deicing partitions being to start operating sequentially or alternately at intervals according to said priority during one deicing operation period.

2. Active-passive combined deicing system according to claim 1, characterized in that the spacing between adjacent impact force generators arranged in the first zone is greater than the spacing between adjacent impact force generators arranged in the second zone and/or the impact force of impact force generators arranged in the second zone is smaller than the impact force of impact force generators arranged in the first zone and/or the width of a deicing zone at the wing root of the aircraft is smaller than the width of a deicing zone at the wing tip of the aircraft.

3. An actively and passively combined deicing system according to claim 1,

further comprises: the ice accumulation monitoring module is connected with the control module and is used for monitoring the ice accumulation condition of the skin and uploading a first data signal containing the ice accumulation condition to the control module, wherein the ice accumulation condition comprises: the distribution characteristics of the ice accretion,

and/or the number of the groups of groups,

the first trigger signal includes: the working start time, the working end time, the beating force and the beating frequency of each beating force generator.

4. An actively and passively combined deicing system according to claim 1,

At least two impact force generators are arranged in the deicing partition, wherein at least one impact force generator is arranged above the deicing partition, and at least one impact force generator is arranged below the deicing partition;

and/or the number of the groups of groups,

the spanwise length of the deicing partition is between 0.25m and 1.0 m.

5. The active-passive combined deicing system of claim 1, further comprising: a pulsed power supply for powering the mechanical deicing module.

6. The active-passive combined deicing system of claim 1, wherein the number of impact force generators located within a deicing zone at a wing root of said aircraft is greater than the number of impact force generators located within a deicing zone at a wing tip of said aircraft.

7. Active and passive combined deicing system according to claim 1, characterized in that the impact point active area on the inner surface of said skin is coated with a lubricating material, optionally: polytetrafluoroethylene, or graphite, or boron nitride, or polyoxymethylene.

8. A method of deicing based on a system as set forth in any one of claims 1-7,

The method comprises the following steps:

monitoring the ice accumulation condition of an ice accumulation area through an ice accumulation monitoring module of the deicing system, and uploading a first data signal containing the ice accumulation condition to the control module;

the mechanical deicing module starts deicing operation in response to the received first trigger signal, wherein the deicing operation comprises at least one deicing duty cycle, wherein the deicing duty cycle comprises: and (3) a process that at least two impact force generators impact the corresponding skin areas in sequence.