Leading edge anti-icing device and aircraft equipped with leading edge anti-icing device

Abstract

The invention relates to a front edge anti-icing device (1). The front edge anti-icing device comprises a pipeline assembly (2) and a front edge skin (8) wrapping the peripheral face of the pipeline assembly. The pipeline assembly comprises an air supply pipe (3) fixed to the inner circumferential surface of the pipeline assembly and extending in the length direction of the pipeline assembly; the gas distribution pipe (4) is positioned at the gas inlet end and is communicated with the gas supply pipe at the gas inlet end; the hot air channel (5) is arranged in the length direction of the pipeline assembly, the hot air channel is composed of a plurality of hot air pipelines (51), and the air inlet end of the air distributing pipe is communicated with the first end of the hot air channel; the gas collecting pipe (6) is positioned at the exhaust end and is communicated with the second end of the hot gas channel at the exhaust end; and the exhaust pipe is communicated with the gas collecting pipe at the exhaust end. The front edge anti-icing device not only can solve the problem that a front edge composite material structure is easy to lose efficacy, but also can improve the utilization efficiency of anti-icing hot gas.

Description

Technical Field

[0001] The present invention relates to a leading edge anti-icing device, and more particularly to a leading edge anti-icing device for an aircraft slat, so as to improve the utilization efficiency of anti-icing hot gas.

[0002] The present invention also relates to an aircraft equipped with the leading edge anti-icing device. Background Art

[0003] In the prior art, aircraft slats prevent icing of the slats by directly delivering anti-icing hot gas to the fixed leading edge skin through the exhaust holes. However, this will cause the composite skin in the adjacent area to fail prematurely, which greatly limits the application of composite structures. In order to solve this failure problem, technicians in this field have proposed to improve the composite skin to an aluminum skin. However, under the influence of high temperature, the strength allowable value of the aluminum skin will be reduced.

[0004] At the same time, due to the anti-icing design of the slat, the anti-icing cavity arranged in the slat is filled with hot gas, and other unrelated structures are also heated at the same time, resulting in low efficiency of hot gas utilization. Moreover, when the hot gas is discharged from the slat through the exhaust port, it is often discharged to the fixed leading edge skin behind the slat. The high-temperature gas will still have an adverse effect on the material of the fixed leading edge skin, thereby increasing the design cost. In addition, since the anti-icing cavity and / or the leading edge slat are made of metal, the discharged high-temperature gas will damage the composite parts in the vicinity thereof.

[0005] To this end, a series of improved inventions have emerged in this field, intending to completely solve the various problems and shortcomings mentioned above.

[0006] For example, in the invention patent CN205440885U entitled "Anti-icing cavity at the leading edge of a slat" filed by Commercial Aircraft Corporation of China Limited on December 17, 2015, an anti-icing cavity at the leading edge of a slat is disclosed. The anti-icing cavity is arranged along the skin of the leading edge of the slat, and includes a front cavity and a rear cavity separated by an anti-icing beam. A flute is arranged in the front cavity to heat the skin by introducing hot air, and a plurality of ventilation grooves connecting the front cavity and the rear cavity are arranged between the anti-icing beam and the skin, and these ventilation grooves are arranged to gradually reduce the cross section from the front cavity to the rear cavity. This anti-icing cavity at the leading edge of the slat is conducive to increasing the temperature of the skin on the rear cavity and improving the anti-icing capability.

[0007] However, the exhaust port of such an anti-icing cavity is usually arranged on the inner skin, and no flow guiding structure is arranged, so the problem of low efficiency of hot gas utilization still cannot be solved.

[0008] For another example, in U.S. Pat. No. 5,921,502, entitled "HYBRID ICE-PROTECTION SYSTEM FOR USE ON ROUGHNESS-SENSITIVE AIRFOILS", filed by Cox on June 19, 1996, a hybrid anti-icing leading edge structure is disclosed. The structure uses both electric heating wires and hot air to de-ice, wherein the hot air heats the front cavity, and the upper and lower skins are heated by arranging electric heating wires.

[0009] However, the above patent uses hot air to heat the front cavity without involving the diversion of hot gas exhaust, so there is still the problem of low hot gas utilization efficiency. Moreover, heating by arranging electric heating wires will also consume a lot of energy and will still have an adverse effect on the material of the fixed leading edge skin.

[0010] For another example, in Chinese invention patent application CN110001971A entitled “Leading edge structure for an airflow control system for an aircraft” filed by Airbus Operations LLC on December 27, 2018, a leading edge structure for an airflow control system for an aircraft is disclosed. The leading edge structure includes a double-walled leading edge panel, the leading edge panel includes an inner wall element and an outer wall element, wherein the outer wall element includes a plurality of micropores, and the inner wall element includes a passage, the passage forming a fluid connection between the hollow chamber and the vacuum system. The reinforcement forms a hot air duct, the hot air duct is configured to be connected to the hot air system, and the reinforcement includes a plurality of hot air openings, the plurality of hot air openings forming a fluid connection between the hot air duct and the hollow chamber, thereby providing a simple and effective anti-icing system in the leading edge structure for the airflow control system.

[0011] This leading edge structure utilizes micro-holes on the hot air duct to de-ice the outer surface of the outer wall element. Although the structure is simple, it still cannot solve the problems of low hot air utilization efficiency and impact on the skin material.

[0012] Therefore, there is an urgent need in the art to design a new leading edge anti-icing device to solve the problem that the leading edge composite structure is prone to failure and to improve the utilization efficiency of anti-icing hot gas. Summary of the invention

[0013] The object of the present invention is to provide a leading edge anti-icing device, which can not only solve the problem that the leading edge composite structure is prone to failure, but also improve the utilization efficiency of anti-icing hot gas.

[0014] Another object of the present invention is to provide an aircraft equipped with the leading edge anti-icing device.

[0015] A first aspect of the present invention relates to a leading edge anti-icing device, comprising: a pipeline assembly; and a leading edge skin covering the outer peripheral surface of the pipeline assembly, the pipeline assembly comprising: an air supply pipe fixed to the inner peripheral surface of the pipeline assembly and extending along the length direction of the pipeline assembly; an air distribution pipe located at the air inlet end, the air distribution pipe being connected to the air supply pipe at the air inlet end; a hot air duct arranged in the length direction of the pipeline assembly, the hot air duct being composed of a plurality of hot air pipelines, the air distribution pipe being connected to the first end of the hot air duct at the air inlet end; an air collecting pipe located at the exhaust end, the air collecting pipe being connected to the second end of the hot air duct at the exhaust end; and an exhaust pipe, the exhaust pipe being connected to the air collecting pipe at the exhaust end.

[0016] In the above technical solution, the term "the length direction of the pipeline assembly" refers to the arrangement direction of the pipeline assembly or the span direction along the leading edge slat. Since the main body of the pipeline assembly is a hot gas pipeline with a slender shape, when the pipeline assembly is arranged on the leading edge of the aircraft wing, the so-called "the length direction of the pipeline assembly" is actually the span direction of the aircraft.

[0017] In the above technical solution, the terms "inlet end" and "exhaust end" refer to the two ends of the pipeline assembly, wherein the end where the hot gas flows into the pipeline assembly is called the "inlet end", and the end where the hot gas flows out of the pipeline assembly is called the "exhaust end".

[0018] The term "communicating with..." indicates that there is a space between two components that is open and connected to each other, so that hot gas can flow from the inner space of one component to the inner space of the other component without hindrance. The term includes both direct communication and indirect communication with the help of other accessories.

[0019] The term "streamline shape" refers to a shape made according to aerodynamic principles, which can minimize the air resistance encountered by the aircraft slat during flight. This shape should be well known to those skilled in the art.

[0020] In the above preferred embodiment, not only the air distribution pipe can have substantially the same streamline shape as the pipeline assembly, but the air collection pipe can also have substantially the same streamline shape as the pipeline assembly. Such streamline shapes of the air distribution pipe and the air collection pipe are adapted to other components of the aircraft slat, and can effectively reduce wind resistance and minimize flight resistance.

[0021] It is not obvious that the above technical solution can be applied to the field of aircraft anti-icing for the following reasons:

[0022] (i) The present application provides a working structural member, but at the same time has the ability to conduct heat, and the circulating refrigerant can be simply selected and changed;

[0023] (ii) The internal wall panel provided by the present application not only forms a passage together with the outer skin, but also provides support and reinforcement for the outer skin, rather than simply constructing a thermal cycle; and

[0024] (iii) The present application can directly heat the main body of the structural member without the need for other media to achieve cooling of the workpiece. In a preferred embodiment, the pipeline assembly can be an elongated sheet metal member having a substantially streamlined cross section.

[0025] In another preferred embodiment, the hot gas channel may extend continuously in the length direction of the pipeline assembly, and each hot gas pipeline may have a different arrangement density according to the leading edge icing position and / or the hot gas flow requirement.

[0026] Since the hot gas channel is composed of multiple hot gas pipelines, the arrangement density of the hot gas pipelines depends on the spacing between each hot gas pipeline and the adjacent hot gas pipelines, that is, the smaller the spacing between the hot gas pipelines, the greater the arrangement density of the hot gas pipelines.

[0027] It should be understood by those skilled in the art that if ice is formed seriously at the leading edge, the heat supply of the hot gas needs to be increased, and the arrangement density of the hot gas pipelines needs to be increased accordingly, that is, the spacing distance between the hot gas pipelines needs to be reduced. Similarly, if ice is not formed seriously at the leading edge, the heat supply of the hot gas can be reduced, and the arrangement density of the hot gas pipelines needs to be reduced accordingly, that is, the spacing distance between the hot gas pipelines needs to be increased.

[0028] In the above preferred embodiment, at least one hot gas pipeline in the hot gas channel can be arranged in a straight line or a curve. In addition, the cross section of the hot gas pipeline can also be designed to be a constant cross section or a variable cross section.

[0029] Through the above design, local heating can be easily adjusted to meet the actual demand for hot air flow.

[0030] In another preferred embodiment, the air supply pipe can be gradually thinned along the length direction of the pipeline assembly according to the pressure distribution requirements.

[0031] By changing the diameter of the air supply pipe, the rate and flow rate of hot air supplied by the air supply pipe can be controlled to meet the desired pressure distribution requirements.

[0032] In the above-mentioned embodiment, the leading edge anti-icing device is applicable to aircraft slats. However, for those skilled in the art, such a leading edge anti-icing device may also be applicable to other fields.

[0033] A second aspect of the present invention relates to an aircraft equipped with the leading edge anti-icing device according to the first aspect of the present invention.

[0034] In summary, the leading edge anti-icing device according to the present invention can achieve the following advantages:

[0035] (i) The hot gas flows on the skin surface, and the heat utilization efficiency is significantly improved;

[0036] (ii) It avoids direct exposure of other structures to the hot gas environment, significantly reducing heat loss;

[0037] (iii) Since the exhaust gas flowing through the hot gas channel is discharged centrally through the exhaust pipe, the impact of hot gas on other structures is eliminated, while also avoiding damage to composite parts in nearby areas;

[0038] (iv) The layout of the hot gas duct can be flexibly designed according to the ice formation location and anti-icing needs. The variable cross-section and curve design of the hot gas pipeline are conducive to further improving the deicing effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to further illustrate the structure and technical effects of the leading edge anti-icing device according to the present invention, the present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments, wherein:

[0040] Figure 1 is a general schematic diagram of an aircraft equipped with a leading edge anti-icing device according to the present invention;

[0041] Figure 2A is a perspective view of the leading edge anti-icing device as seen from the exterior side of the leading edge anti-icing device;

[0042] Figure 2B is a perspective view of the leading edge anti-icing device as seen from the inner side of the leading edge anti-icing device;

[0043] Figure 3 yes Figure 2A and 2B An exploded schematic diagram of a leading edge anti-icing device is shown, wherein the leading edge anti-icing device is decomposed into two parts: a pipe assembly and a leading edge skin;

[0044] Figure 4 It is an enlarged schematic diagram of the air supply pipe and the air distribution pipe that constitute the leading edge anti-icing device;

[0045] Figure 5 is an enlarged schematic diagram of the hot gas duct that constitutes the leading edge anti-icing device;

[0046] Figure 6 is an enlarged schematic diagram of the manifold and exhaust pipe that make up the leading edge anti-icing device; and

[0047] Figure 7 and Figure 5 A similar schematic diagram, in which the solid line with an arrow shows the path and direction of the hot air flow in the hot air duct.

[0048] Reference numerals

[0049] 1 Leading edge anti-icing device

[0050] 2 Pipeline components

[0051] 3 Air supply pipe

[0052] 4-way air pipe

[0053] 5 Hot air duct

[0054] 51 Hot gas pipeline

[0055] 52 Hot gas line cross section

[0056] 6 Gas collector

[0057] 7 Exhaust pipe

[0058] 8 Leading edge skin DETAILED DESCRIPTION

[0059] The structure, working principle and technical effect of the leading edge anti-icing device according to the present invention are described below with reference to the accompanying drawings.

[0060] It should be clear that the embodiments described in this specification only cover some embodiments of the present invention, not all embodiments. Based on the embodiments recorded in the specification, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0061] Unless otherwise defined, all technical and scientific terms used in the present invention have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention.

[0062] For example, the terms "including" and "having" and any variations thereof in the specification and claims of the present invention and the above-mentioned accompanying drawings are intended to cover non-exclusive inclusions. The singular forms "a", "said" and "the" used in the embodiments of the present invention and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings.

[0063] Figure 1 An aircraft equipped with a leading edge anti-icing device 1 is schematically shown. Figure 1 As shown, it can be seen that the leading edge anti-icing device 1 is arranged at the leading edge of the aircraft slat. Since the aircraft slats have a streamlined shape made according to aerodynamic principles, the leading edge anti-icing device 1 arranged at its leading edge should generally also be designed to have a corresponding streamlined shape, which will be described in detail below.

[0064] Figure 2A and Figure 2B The three-dimensional images of the leading edge anti-icing device are respectively viewed from the outer side and the inner side of the leading edge anti-icing device. Figure 2A As shown, the leading edge anti-icing device 1 has a main body with a streamlined shape. Such a shape helps to improve the lift, drag and fuel efficiency of the aircraft, which should be well known to those skilled in the art and will not be described in detail herein.

[0065] from Figure 2B It can be clearly seen that the air supply pipe 3 is fixed to the inner circumference of the streamlined body of the leading edge anti-icing device 1 and extends along the length direction of the streamlined body. In other words, the air supply pipe 3 is basically surrounded by the streamlined body of the leading edge anti-icing device 1, and is hidden in the space surrounded by the leading edge anti-icing device 1 when observed from the outside of the leading edge anti-icing device 1. The specific arrangement of the air supply pipe 3 will be described in detail below in conjunction with the structure of the leading edge anti-icing device 1.

[0066] See also Figure 3 , which is a schematic diagram of the decomposition of the leading edge anti-icing device 1. It can be seen that the leading edge anti-icing device 1 includes a pipeline assembly 2 and a leading edge skin 8 covering the outer peripheral surface of the pipeline assembly 2. Combined with the above, it can be considered that the streamlined body of the leading edge anti-icing device 1 is Figure 3 The pipeline assembly 2 in the embodiment of the present invention is a slender sheet metal part having a substantially streamlined cross section. Figures 4 to 6 The specific configuration of the pipe assembly 2 will be described.

[0067] The pipeline assembly 2 includes: an air distribution pipe 4 located at the air inlet end, which is connected to the air supply pipe 3 at the air inlet end; a hot air duct 5 arranged in the length direction of the pipeline assembly 2, the hot air duct 5 is composed of a plurality of hot air pipelines 51, and the air distribution pipe 4 is also connected to the first end of the hot air duct 5 at the air inlet end; an air collecting pipe 6 located at the exhaust end, which is connected to the second end of the hot air duct 5 at the exhaust end; and an exhaust pipe 7, which is connected to the air collecting pipe 6 at the exhaust end.

[0068] like Figure 4 As shown, the figure shows the structure of the pipeline assembly 2 at its air inlet end, which mainly includes an air supply pipe 3 and an air distribution pipe 4.

[0069] from Figure 4 It can be seen that the air supply pipe 3 extends along the length direction of the pipeline assembly 2, that is, along the wingspan direction of the aircraft, within the space bounded by the leading edge anti-icing device 1, and its end close to the air inlet end of the pipeline assembly 2 is connected to the air distribution pipe 4 to transport the hot gas from the heat source to the air distribution pipe 4 for subsequent air distribution. Preferably, the air supply pipe 3 gradually becomes thinner along the length direction of the pipeline assembly 2 according to the pressure distribution requirements.

[0070] The air distribution pipe 4 is installed at the air inlet end of the pipeline assembly 2, and has substantially the same streamline shape as the pipeline assembly 2. In this embodiment, the air supply pipe 3 is preferably connected to the inner side of the air distribution pipe 4 by means of a connecting port. Of course, for those skilled in the art, if the connecting port is eliminated and the air supply pipe 3 is directly connected to the air distribution pipe 4, or the two are made into one body, such variations should all fall within the protection scope of the present invention.

[0071] like Figure 5 As shown, the figure shows the hot gas duct 5 of the pipeline assembly 2 which constitutes the streamlined body of the leading edge anti-icing device 1.

[0072] In this figure, the left end of the pipeline assembly 2 is the air inlet end, and the right end is the exhaust end. It can be seen that the hot air duct 5 is composed of a plurality of hot air pipes 51 extending from the air inlet end to the exhaust end along the length direction of the pipeline assembly 2. The number and distribution position of these hot air pipes 51 are basically consistent with the preset interface on the air distribution pipe 4, so that the air distribution pipe 4 can be interconnected with the end of the hot air duct 5 close to the air inlet end of the pipeline assembly 2 at the air inlet end. In this embodiment, the shape of the air distribution pipe 4 is similar to a brace that can be nested on the teeth, but it is easy for those skilled in the art to understand that various modifications can be made to the shape of the air distribution pipe 4, the number and distribution position of the hot air pipes 51 within the scope of protection of the present invention, and such modifications will not exceed the scope of protection of the present invention.

[0073] Please continue to see Figure 5 The hot gas channel 5 extends continuously in the length direction of the pipeline assembly 2, and each hot gas pipeline 51 can have different arrangement densities according to the leading edge icing position and / or hot gas flow requirements.

[0074] As an example, at least one hot gas pipeline 51 in the hot gas channel 5 can be arranged in a straight line or a curve. At this time, the arrangement density of the hot gas pipelines 51 will depend on the spacing distance between each hot gas pipeline 51 and the adjacent hot gas pipelines 51, that is, the smaller the spacing distance between the hot gas pipelines, the greater the arrangement density of the hot gas pipelines, and vice versa.

[0075] As another example, the cross section 52 of the hot gas pipeline 51 can be designed to be a constant cross section or a variable cross section, such as Figure 5 Similarly, when the cross section 52 of the hot gas pipeline 51 gradually increases, the spacing between the hot gas pipelines decreases accordingly, and the arrangement density of the hot gas pipelines increases accordingly, and vice versa.

[0076] like Figure 6 As shown, the figure shows the structure of the pipeline assembly 2 at its exhaust end, which mainly includes a collecting pipe 6 and an exhaust pipe 7.

[0077] from Figure 6It can be seen that the air collecting pipe 6 is installed at the exhaust end of the pipeline assembly 2, and has a streamline shape substantially the same as that of the pipeline assembly 2 and the air distribution pipe 4. In this embodiment, the exhaust pipe 7 is preferably connected to the outside of the air collecting pipe 6 by means of a connecting port. Of course, for those skilled in the art, if the connecting port is eliminated and the exhaust pipe 7 is directly connected to the air collecting pipe 6, or the two are made into one body, such variations should all fall within the protection scope of the present invention.

[0078] Similar to the gas distribution pipe 4, the number and distribution position of the hot gas pipeline 51 are basically consistent with the preset interface on the gas collecting pipe 6, so that the gas collecting pipe 6 can be interconnected with one end of the hot gas duct 5 close to the exhaust end of the pipeline assembly 2, so that the hot gas leaving the hot gas duct 5 can enter the exhaust pipe 7 through the gas collecting pipe 6 for subsequent discharge. In this embodiment, the shape of the gas collecting pipe 6 is also similar to a brace that can be nested on the teeth. It is easy for those skilled in the art to understand that various modifications can be made to the shape of the gas collecting pipe 6 within the scope of protection of the present invention, and such modifications will not exceed the scope of protection of the present invention.

[0079] The following will be combined Figure 7 Describe in detail the hot gas flow process in the leading edge anti-icing device:

[0080] like Figure 7 As shown by the solid arrow in the figure, the hot gas from the heat source (not shown in the figure) is introduced into the air supply pipe 9. At the air inlet end of the pipeline assembly 2, the hot gas flows out from the air supply pipe 9 and is introduced into the various hot gas pipelines 51 constituting the hot gas channel 5 through the air distribution pipe 4. As the hot gas gradually fills the various hot gas pipelines 51, the hot gas begins to be transported along the length direction of the pipeline assembly 2, that is, along the wingspan direction of the aircraft toward the exhaust end of the pipeline assembly 2, and heats the leading edge skin 8 covering the pipeline assembly 2. After reaching the exhaust end of the pipeline assembly 2, the heated exhaust gas enters the exhaust pipe 7 through the air collecting pipe 6, and is finally discharged from the exhaust pipe 7 to the fuselage structure.

[0081] Compared with the traditional leading edge anti-icing device, the present invention has the following advantages:

[0082] (i) The hot gas flows on the skin surface, and the heat utilization efficiency is significantly improved;

[0083] (ii) No other structures are directly exposed to the hot gas environment, and heat loss is significantly reduced;

[0084] (iii) Since the exhaust gas flowing through the hot gas duct is discharged centrally through the exhaust pipe, the impact of hot gas on other structures is eliminated;

[0085] (iv) The layout of the hot gas duct can be flexibly designed according to the ice formation location and anti-icing needs. The variable cross-section and curve design of the hot gas pipeline are conducive to further improving the deicing effect.

[0086] Although the structure, working principle and technical effects of the leading edge anti-icing device according to the present invention are described above in combination with the preferred embodiments and the accompanying drawings, it should be recognized by those skilled in the art that the above examples are only for illustration and cannot be used as limitations of the present invention. Therefore, the present invention can be modified and varied within the spirit of the claims, and these modifications and variations will fall within the scope required by the claims of the present invention.

Claims

1. A leading edge anti-icing device (1), comprising: Pipeline assembly (2); as well as a leading edge skin (8) covering the outer peripheral surface of the pipeline assembly (2), It is characterized in that The pipeline assembly (2) comprises: an air supply pipe (3) fixed to the inner circumferential surface of the pipeline assembly (2) and extending along the length direction of the pipeline assembly (2); An air distribution pipe (4) located at the air inlet end, the air distribution pipe (4) being connected to the air supply pipe (3) at the air inlet end; A hot air channel (5) arranged in the length direction of the pipeline assembly (2), the hot air channel (5) being composed of a plurality of hot air pipelines (51), and the gas distribution pipe (4) being also connected to a first end of the hot air channel (5) at the air inlet end; an air collecting pipe (6) located at the exhaust end, the air collecting pipe (6) being connected to the second end of the hot air duct (5) at the exhaust end; and An exhaust pipe (7), wherein the exhaust pipe (7) is connected to the gas collecting pipe (6) at the exhaust end.

2. The leading edge anti-icing device (1) according to claim 1, characterized in that: The pipeline assembly (2) is an elongated sheet metal part and has a substantially streamlined cross section.

3. The leading edge anti-icing device (1) according to claim 2, characterized in that: The gas distribution pipe (4) has substantially the same streamline shape as the pipeline assembly (2).

4. The leading edge anti-icing device (1) according to claim 2, characterized in that: The air collecting pipe (6) has substantially the same streamline shape as the pipeline assembly (2).

5. The leading edge anti-icing device (1) according to claim 1, characterized in that: The hot gas channel (5) extends continuously in the length direction of the pipeline assembly (2), and each hot gas pipeline (51) has a different arrangement density according to the leading edge icing position and / or hot gas flow demand.

6. The leading edge anti-icing device (1) according to claim 5, characterized in that: At least one hot gas pipeline (51) in the hot gas channel (5) is arranged in a straight line or a curve.

7. The leading edge anti-icing device (1) according to claim 5, characterized in that: The cross section (52) of the hot gas pipeline (51) is designed to be a constant cross section or a variable cross section.

8. The leading edge anti-icing device (1) according to claim 1, characterized in that: The air supply pipe (3) gradually becomes thinner along the length direction of the pipeline assembly (2) according to pressure distribution requirements.

9. The leading edge anti-icing device (1) according to any one of claims 1 to 8, characterized in that: The leading edge anti-icing device (1) is suitable for aircraft slats.

10. An aircraft, the aircraft being equipped with the leading edge anti-icing device (1) according to claim 1.

Images