Pneumatic deicing device for aircraft propeller

Abstract

A pneumatic deicing device for an aircraft propeller comprises a waste gas filter, a pressurization gas storage / exhaust / detection / distribution assembly and an expansion deicing pipe, and the expansion deicing pipe symmetrically arranged on the upper / lower surface of the front edge comprises a first expansion air bag used for being attached to the surface of the front edge of the propeller. A first vent hole is formed in the plane part of the first expansion airbag, a plurality of second expansion airbags are arranged on the cambered surface part of the first expansion airbag, and a corresponding second vent hole is formed in the cambered surface part covered by each second expansion airbag; a first air pipe and a second air pipe are arranged in the aircraft propeller, one end of the first air pipe and one end of the second air pipe are connected with the air supply hole of the distribution assembly, the other end of the first air pipe is connected with the first vent hole, and the other end of the second air pipe is connected with the second vent hole. The double-layer design is adopted in the expansion deicing pipe, and aiming at different icing scenes, fixed-point deicing and comprehensive deicing can be carried out, and the mode that the first expansion air bag is expanded firstly to carry out primary deicing and the second expansion air bag is expanded later to carry out secondary deicing can be achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft anti-icing and de-icing, and in particular relates to a pneumatic de-icing device for aircraft propellers. Background Art

[0002] Ice on aircraft propellers can cause serious damage to flight safety. First, ice can change the aerodynamic shape of the propeller, reduce its efficiency, lead to insufficient thrust, and affect the aircraft's climb and cruise performance; second, uneven ice can cause the propeller to lose balance and produce violent vibrations, which may damage the propeller and engine, and even affect the structure of the aircraft; third, ice can increase air resistance, change the aircraft's maneuverability, increase fuel consumption and increase engine load, which may cause engine overheating or failure; in addition, ice blocks may also hit other parts of the aircraft after falling off, causing additional damage. Therefore, to ensure flight safety, aircraft are usually equipped with anti-icing or de-icing systems. The commonly used anti-icing and de-icing systems include liquid anti-icing systems and thermal de-icing systems. The liquid anti-icing system is an aircraft anti-icing system that sprays anti-icing liquid on the surface to be protected of the component, mixes with the supercooled water droplets impacting the surface, and makes the freezing point of the liquid lower than the surface temperature without freezing. This anti-icing system consumes a huge amount of anti-icing liquid, and the spray hole is easily blocked, which makes maintenance difficult. The thermal de-icing system is a thermal de-icing system that uses thermal energy (for example, an electric heating pad bonded to the surface to be protected) to heat the anti-icing surface of the aircraft component. This de-icing system consumes a lot of energy. Summary of the invention

[0003] In view of the defects of the liquid anti-icing system and thermal de-icing system commonly used in existing aircraft, the purpose of the present invention is to provide a pneumatic de-icing device for aircraft propellers, which does not require the consumption of anti-icing liquid and additional heat energy.

[0004] The purpose of the present invention is to be achieved by adopting the following technical scheme: a pneumatic deicing device for aircraft propellers, comprising a distribution component rotatably assembled on a rotating shaft, an exhaust gas filter 1, a pressurized air storage component 2, a distribution component 4 and an expansion deicing pipe 6 connected in sequence through pipelines, a detection component 3 arranged on the leading edge surface of the propeller, and an exhaust component 5 connected to the distribution component through a pipeline; the expansion deicing pipe comprises a first expansion airbag 61 for fitting the leading edge surface of the propeller, the first expansion airbag is semi-cylindrical, a first vent hole 63 and a plurality of through-tube holes 64 spaced apart along the axial direction of the first expansion airbag are provided on a planar portion 611, and a plurality of second expansion airbags are provided on an arc portion 612 along the axial direction of the first expansion airbag 62. A corresponding second air vent 65 is provided on the arc portion covered by each second inflatable airbag; a plurality of through holes are provided on the leading edge surface of the propeller covered by the inflatable deicing tube; a first air pipe and a plurality of second air pipes are provided inside the aircraft propeller; one end of the first air pipe is connected to the air supply hole 401 of the distribution component, and the other end thereof is connected to the first air hole after passing through the corresponding through hole; one end of each second air pipe is connected to the air supply hole 401 of the distribution component, and the other end thereof is connected to the second air hole after passing through the corresponding through hole, the corresponding through-tube hole, and the inner cavity of the first inflatable airbag in sequence; the first air pipe and the second air pipe are respectively provided with solenoid valves 9; the pressurized air storage component, the detection component, the exhaust component, and the solenoid valve are all electrically connected to the controller.

[0005] In one embodiment, the pressurized air storage assembly includes a compressor 20 and an air storage chamber 21 connected by a pipeline, and the outlet end of the compressor is connected to the air inlet of the distribution assembly through a pipeline.

[0006] In one embodiment, a first one-way valve 11 is provided on the inlet pipeline of the exhaust gas filter, and a second one-way valve 22 is provided on the pipeline between the compressor and the distribution assembly.

[0007] In one embodiment, the detection assembly includes a plurality of ice sensors disposed on the leading edge surface along the length direction of the propeller.

[0008] In one embodiment, the distribution assembly includes an external cylinder body 40 and an internal cylinder body 41 that are rotatably matched, the inner wall of the external cylinder body is provided with a first boss 406 and the interior of the first boss is provided with an air supply chamber 404, the internal cylinder body is rotatably assembled on the rotating shaft 8 and a plurality of first sealing rings 403 are sandwiched between the outer wall of the internal cylinder body and the inner wall of the first boss; an air supply hole 401 is provided on the external cylinder body covering the first boss, and an air inlet duct 413 is provided inside the internal cylinder body, and the air supply hole and the air inlet duct are both connected to the air supply chamber; the compressor is connected to the air inlet duct through a pipeline.

[0009] In one embodiment, an exhaust cavity 405 is further provided inside the first boss, and an exhaust hole 402 is further provided on the outer cylinder body covering the first boss. The exhaust hole and the air inlet are both connected to the exhaust cavity; the exhaust assembly is connected to the exhaust hole through a pipeline.

[0010] In one embodiment, the air supply hole includes a first sub-air supply hole 4011, a plurality of second sub-air supply holes 4012 distributed around the first sub-air supply hole, one end of the first air pipe is connected to the first sub-air supply hole, and one end of the second air pipe is connected to the corresponding second sub-air supply hole.

[0011] In one embodiment, a second sealing ring 414 is provided at the entrance of the air inlet passage.

[0012] In one embodiment, a micro-nano protrusion structure 621 is provided on the outer wall of the second expansion airbag.

[0013] In one embodiment, the exhaust assembly includes a vacuum pump 50 connected to the distribution assembly through a pipeline, and a third one-way valve 51 is provided on the pipeline between the vacuum pump and the distribution assembly.

[0014] By means of the above technical solution, the present invention can obtain the following advantages:

[0015] (1) The pneumatic deicing device draws high-temperature exhaust gas from the engine as the air source for the device to operate, without consuming anti-icing fluid and additional heat energy;

[0016] (2) The present invention pressurizes the high-temperature gas that has passed through the exhaust gas filter and sends it into the expansion deicing pipe. The ice is removed from the leading edge surface of the propeller by the tension generated by the expansion of the expansion deicing pipe. Then, the airflow blows the ice away from the aircraft, thereby achieving a deicing effect.

[0017] (3) The inflatable deicing tube of the present invention adopts a double-layer design. According to different icing scenarios, only the second inflatable airbag in the corresponding position area can be driven to inflate to perform fixed-point deicing, thereby effectively reducing energy waste; all the second inflatable airbags can also be driven to inflate to perform comprehensive deicing; the first inflatable airbag can also be driven to inflate first to perform primary deicing, and the second inflatable airbag can be driven to inflate later to perform secondary deicing, thereby improving the deicing effect with the help of this dual mode;

[0018] (4) In the aforementioned expansion deicing process, the expansion deicing tube and the leading edge surface of the propeller are heated to a certain extent by means of heat transfer of high-temperature gas, which not only effectively reduces the icing phenomenon, but also effectively reduces the adhesion strength of the ice layer on the expansion deicing tube, making it easier to remove the ice from the deicing sleeve when the airbag is inflated; at the same time, with the help of the micro-nano protrusion structure on the outer surface of the second expansion airbag, when other deicing measures are carried out to a certain extent (such as when the ice layer is broken or melted), the melting of the ice layer can be accelerated, thereby further improving the deicing efficiency while ensuring the effectiveness of deicing.

[0019] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented according to the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the following preferred embodiments are specifically cited and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 The present invention is a schematic diagram of the principle of a pneumatic deicing device for an aircraft propeller according to an embodiment of the present invention.

[0021] Figure 2 The present invention is a schematic diagram of an air circuit control of a pneumatic deicing device for an aircraft propeller according to an embodiment of the present invention.

[0022] Figure 3 It is a schematic diagram of the assembly of the distribution component on the rotating shaft in an embodiment of the present invention.

[0023] Figure 4 Schematic diagram of the axonometric view of the external cylinder body in the embodiment of the present invention.

[0024] Figure 5A and Figure 5B It is a schematic diagram of the installation of the expansion deicing pipe in a contracted state on the upper surface and the lower surface of the leading edge of the propeller in an embodiment of the present invention.

[0025] Figure 6 Schematic diagram of an axonometric view of an expandable deicing pipe in an expanded state according to an embodiment of the present invention.

[0026] Figure 7 It is a cross-sectional schematic diagram of the expandable deicing pipe in the expanded state according to the embodiment of the present invention.

[0027] Figure 8 1 is an isometric schematic diagram of the second inflatable airbag in an inflated state according to an embodiment of the present invention.

[0028] Fig. 9 The present invention is another embodiment of a pneumatic deicing device for an aircraft propeller.

[0029] [Reference Signs]

[0030] 1-exhaust filter, 2-pressurized air storage assembly, 20-compressor, 21-air storage chamber, 22-second one-way valve, 3-detection assembly, 4-distribution assembly, 40-external cylinder, 401-air supply hole, 4011-first sub-air supply hole, 4012-second sub-air supply hole, 402-exhaust hole, 403-first sealing ring, 404-air supply chamber, 405-exhaust chamber, 406-first boss, 407-annular groove, 41-internal cylinder, 411-second boss, 412-third boss, 413-inlet Air duct, 414-second sealing ring, 42-first bearing, 43-second bearing, 5-exhaust assembly, 50-vacuum pump, 51-third one-way valve, 6-inflatable deicing pipe, 61-first inflation airbag, 611-planar portion, 612-arc portion, 62-second inflation airbag, 621-micro-nano protrusion structure, 63-first vent hole, 64-through-tube hole, 65-second vent hole, 7-propeller, 70-accommodating groove, 8-rotating shaft, 9-solenoid valve, 10-three-way solenoid valve, 11-first one-way valve. DETAILED DESCRIPTION

[0031] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by showing examples of the present invention. In the drawings and the following description, at least part of the known structures and technologies are not shown to avoid unnecessary ambiguity of the present invention; and, for clarity, the size of some structures may be exaggerated. The features, structures or characteristics described below can be combined in one or more embodiments in any suitable manner. In addition, the terms "first or I", "second or II", "third or III", etc. are used only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0032] The directional words appearing in the following description are all directions shown in the figures, and do not limit the specific structure of the present invention. In the description of the present invention, it should also be noted that, unless otherwise clearly specified and limited, the terms "setting", "installation", "connection" and "assembly" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0033] See also Figure 1 and Figure 2The present embodiment is a pneumatic deicing device for aircraft propellers, which uses engine bleed air as the air source for the device, and specifically includes an exhaust gas filter 1, a pressurized air storage component 2, a detection component 3, a distribution component 4, an exhaust component 5 and an expansion deicing pipe 6.

[0034] In this embodiment, the exhaust gas filter 1 is connected to the exhaust gas outlet of the engine through a pipeline. Since the gas source of the device is the exhaust gas produced when the aircraft engine is working, in order to avoid the pollutants in the exhaust gas clogging the pipeline and thus affecting the normal operation of the pneumatic deicing device, the exhaust gas filter is first used to filter out the pollutants in the exhaust gas discharged by the engine. Furthermore, a first one-way valve 11 is provided on the pipeline between the engine and the exhaust gas filter.

[0035] In this embodiment, the outlet end of the exhaust gas filter 1 is connected to the pressurized gas storage component 2 through a pipeline. The pressurized gas storage component should include a compressor 20 and an air storage chamber 21 connected by a pipeline. The compressor is used to pressurize the filtered gas, so that the expansion deicing tube can expand rapidly under the filling of high-pressure gas to obtain a better deicing effect; the air storage chamber is used to pre-store a certain amount of gas, so that sufficient compressed gas can be provided in a short time to meet the needs of the deicing device. At the same time, in this embodiment, a second one-way valve 22 is provided on the pipeline between the compressor and the air inlet of the distribution component, and the compressor is electrically connected to the controller.

[0036] In this embodiment, the detection component 3 includes an ice sensor, and multiple ice sensors are arranged on the leading edge surface of the aircraft propeller along the length direction of the propeller, for detecting whether the leading edge of the propeller is iced, and uploading the data of whether the propeller is iced (for example, the ice position and ice thickness) to the controller.

[0037] In this embodiment, the exhaust component 5 includes a vacuum pump 50 connected to the controller, and the vacuum pump is connected to the exhaust hole of the distribution component through a pipeline. When the deicing device stops working, the vacuum pump is turned on to extract the high-temperature and high-pressure gas in the expansion deicing pipe, so that the expansion deicing pipe is close to the leading edge surface of the propeller, thereby minimizing the impact of the expansion deicing pipe on the aerodynamic performance of the aircraft. At the same time, in this embodiment, a third one-way valve 51 is set on the pipeline between the exhaust hole of the distribution component and the vacuum pump.

[0038] See also Figure 3 In this embodiment, the distribution assembly 4 is used to deliver high-temperature and high-pressure gas to the expansion deicing pipe to achieve a fast and effective deicing effect. It specifically includes an external cylinder 40 and an internal cylinder 41. Please also refer to Figure 4The outer cylinder body is an axially hollow cylindrical part, and its inner wall is provided with a circumferentially closed first boss 406. A plurality of air supply holes 401 and a plurality of exhaust holes 402 are arranged on the outer cylinder body covering the first boss. The number of the air supply holes and the exhaust holes should be consistent with the number of propellers. Furthermore, each air supply hole includes a first sub-air supply hole 4011 and a plurality of second sub-air supply holes 4012 arranged around the first sub-air supply hole. The number of the second sub-air supply holes should be consistent with the number of the second expansion airbags on the expansion deicing tube. The inner shell is an axially hollow part with a T-shaped cross-section. The upper and lower sides of the inner wall are respectively provided with second bosses 411. During assembly, the first bearing 42, the bearing retaining ring and the second boss are matched (the bearing The retaining ring is used to limit the bearing in one axial direction, and the second boss is used to limit the bearing in another axial direction) The internal cylinder body is rotatably assembled on the outside of the rotating shaft 8 of the aircraft propeller, and the external cylinder body 40 is rotatably assembled on the outside of the internal cylinder body 41 through the cooperation of the second bearing 43, the bearing retaining ring and the first boss 406. When assembled in place, the lower end of the external cylinder body 40 is placed on the third boss 412 at the lower end of the internal cylinder body 41 (at this time, the third boss can limit the second bearing on the lower side in another axial direction). When the rotating shaft of the aircraft propeller rotates, the propeller will rotate synchronously. At this time, the external cylinder body will rotate driven by the pipeline between the external cylinder body and the propeller, but the internal cylinder body will not rotate, thereby avoiding the phenomenon of multiple pipelines being entangled.

[0039] In addition, the inner wall of the first boss 406 is provided with a plurality of annular grooves 407 for the first sealing ring 403 to be embedded in at intervals along the axis of the external cylinder body, and the upper and lower sides of the first boss 406 respectively form an annular air supply chamber 404 and an annular exhaust chamber 405. When the external cylinder body is rotated and assembled on the outer side of the internal cylinder body, the outer wall of the internal cylinder body and the plurality of first sealing rings form an extrusion fit so that the air supply chamber and the exhaust chamber form a closed space; an air inlet 413 is provided inside the internal cylinder body, and the upper part of the air inlet 413 is connected to the air supply chamber, and the lower part of the air inlet 413 is connected to the exhaust chamber, and is located on the lower end surface of the internal cylinder body. The inlet of the air inlet is connected to the outlet of the compressor 20 through pipelines and pipeline joints respectively. The first sub-air supply hole 4011 and the second sub-air supply hole 4012 are connected to the air supply cavity 404. When deicing is required, the compressor is started, and the gas filtered by the exhaust gas filter in the air storage chamber is pressurized and sent to the air supply cavity 404, and then flows to the expansion deicing pipe through the first sub-air supply hole and the second sub-air supply hole; the exhaust hole 402 is connected to the exhaust cavity 405. After deicing is completed, the vacuum pump is started, and the gas in the expansion deicing pipe is discharged through the air supply hole, the air supply cavity, part of the air inlet, the exhaust cavity, and the exhaust hole in turn. Further, a second sealing ring 414 is provided at the entrance of the air inlet 413. The first sealing ring and the second sealing ring ensure the sealing performance of the air path in the distribution component to prevent leakage of high-pressure gas.

[0040] See also Figure 5A , Figure 5B In this embodiment, an expansion deicing tube 6 is symmetrically arranged on the upper surface and the lower surface of the leading edge of the aircraft propeller. Specifically, a receiving groove 70 matching the shape of the expansion deicing tube can be symmetrically arranged on the upper surface and the lower surface of the leading edge of the aircraft propeller 7. When the expansion deicing tube is embedded in the receiving groove, the outer surface of the expansion deicing tube is flush with the outer surface of the leading edge of the aircraft propeller, so that the outer surface profile of the propeller with the expansion deicing tube is consistent with the design, and the aerodynamic performance of the propeller is not affected. In addition, the assembly method of embedding the expansion deicing tube in the receiving groove is adopted, which is convenient for maintenance and replacement of the expansion deicing tube.

[0041] For details, please refer to Figure 6 and Figure 7 In this embodiment, the expandable deicing tube includes a first expandable airbag 61 and a plurality of second expandable airbags 62 for fitting the leading edge surface of the propeller. The first expandable airbag and the second expandable airbag in the expanded state are both semi-cylindrical. A plurality of first vent holes 63 and a plurality of through-tube holes 64 spaced apart along the axial direction of the first expandable airbag are provided on the plane portion 611 of the first expandable airbag. A plurality of second expandable airbags (each second expandable airbag has a width of 10 mm, a maximum expansion height of 4.3 mm, a maximum inflation pressure of 0.2 MPa, and an inflation time of 3 s) are arranged on the arc surface portion 612 of the first expandable airbag along the axial direction of the first expandable airbag by bonding the arc surface portion of the first expandable airbag and the plane portion of the second expandable airbag. Each second expandable airbag has a plurality of second vent holes 63 and a plurality of through-tube holes 64 spaced apart along the axial direction of the first expandable airbag. A corresponding second air vent 65 is provided on the arc surface covered by the inflatable airbag; a plurality of through holes are provided on the upper and lower surfaces of the leading edge of the propeller covered by the inflatable deicing tube; a first air pipe and a plurality of second air pipes are provided inside the aircraft propeller; one end of the first air pipe is connected to the first sub-air supply hole through a pipe joint, and the other end thereof is connected to the first air vent after passing through the corresponding through hole; one end of each second air pipe is connected to the corresponding second sub-air supply hole through a pipe joint, and the other end thereof is connected to the second air vent after passing through the corresponding through hole, the corresponding through-tube hole, and the inner cavity of the first inflatable airbag in turn; independent solenoid valves 9 are provided on the first air pipe and the second air pipe, respectively, and the solenoid valves are electrically connected to the controller, and the pressure of each air pipe is accurately controlled by the solenoid valve. For further information, please refer to Figure 8 A micro-nano protrusion structure 621 is provided on the outer wall of the second expansion airbag. With the help of the aforementioned micro-nano protrusion structure, the outer surface of the expansion deicing tube has a hydrophobic effect, which can slow down the progress of ice formation, melt the ice or reduce the adhesion between the ice and the surface of the object, thereby promoting the descent of melted ice.

[0042] In this embodiment, the exhaust gas filter, the air storage chamber, and the compressor can be installed near the aircraft engine (for example, above the aircraft engine), which is conducive to the collection and utilization of the high-temperature exhaust gas generated when the engine is working. When the pneumatic deicing device is working, the high-temperature exhaust gas generated when the engine is working is filtered by the exhaust gas filter and pressurized by the compressor, and then the high-temperature and high-pressure gas is sent to the distribution component through the pipeline. The distribution component sends the high-temperature and high-pressure gas into the first expansion airbag through the first sub-air supply hole and the first air pipe, and sends the high-temperature and high-pressure gas into the second expansion airbag through the second sub-air supply hole and the second air pipe. The ice is removed from the leading edge surface of the propeller by the tension generated by the expansion of the expansion deicing pipe, and then the airflow blows the ice away from the aircraft. Furthermore, with the help of the double-layer design of the expansion deicing pipe in this embodiment, in the early stage of icing, the icing data detected and uploaded by the icing sensors at different positions, the controller controls the solenoid valve on the second air pipe connected to the second expansion airbag in the corresponding position to open, drive the second expansion airbag in the corresponding position area to expand, and perform fixed-point deicing, thereby effectively reducing energy waste; when icing occurs over a large area, all icing sensors exceeding the upper limit upload icing signals. At this time, the controller controls all When the solenoid valve on the second air pipe is opened, all the second expansion airbags are inflated to perform comprehensive de-icing. When ice forms rapidly and the ice layer is thick, the controller controls the solenoid valve on the first air pipe to open first and the solenoid valve on the second air pipe to open later. The first expansion airbag is inflated first to perform primary de-icing, and the second expansion airbag is inflated later to perform secondary de-icing. With the help of this dual mode, de-icing can be more effective. At the same time, in the aforementioned expansion and de-icing process, with the help of heat transfer of high-temperature gas, the expansion de-icing pipe and the leading edge surface of the propeller are heated to a certain extent, which not only effectively reduces the icing phenomenon, but also effectively reduces the adhesion strength of the ice layer on the expansion de-icing pipe. It is easier to remove the ice from the de-icing sleeve when the airbag is inflated. At the same time, with the help of the micro-nano protrusion structure on the outer surface of the second expansion airbag, the outer surface of the de-icing sleeve realizes a super-hydrophobic function. When other de-icing measures are carried out to a certain extent (such as when the ice layer is broken or melted), the melting of the ice layer can be accelerated, while ensuring the effectiveness of de-icing, the de-icing efficiency is further improved. When the pneumatic deicing device stops working, the compressor is turned off and the vacuum pump is turned on to discharge the high-temperature and high-pressure gas in the expansion deicing pipe through the first air pipe, the second air pipe, the distribution component and the exhaust hole in sequence, so that the expansion deicing pipe shrinks.

[0043] In other embodiments of the present invention, the detection component may also include other types of sensors such as a temperature sensor for detecting the temperature of the environment in which the propeller is located and uploading the detected ambient temperature data to a controller, a humidity sensor for detecting the humidity of the environment in which the propeller is located and uploading the detected ambient humidity data to a controller. By combining multiple types of sensors, more detection requirements can be met.

[0044] In other embodiments of the present invention, a gas filter may be provided on the pipeline at the outlet end of the vacuum pump, and the gas filter is used to filter the extracted gas again to make it meet the emission standards.

[0045] In other embodiments of the present invention, the internal cylinder body can be an axially hollow cylindrical part. In this case, the second bearing located on the lower side needs to be limited by a corresponding bearing retaining ring (replacing the third boss in this embodiment) so that the external cylinder body can be rotatably assembled on the outside of the internal cylinder body.

[0046] In other embodiments of the present invention, an annular groove for embedding the first sealing ring is provided on the outer wall of the inner cylinder body. When the outer cylinder body is rotated and assembled on the outer side of the inner cylinder body, the inner wall of the first boss squeezes multiple first sealing rings to seal the air supply chamber and the exhaust chamber.

[0047] In other embodiments of the present invention, a plurality of second sub-air supply holes may be disposed on the outer cylinder body on one side of the first sub-air supply hole so as not to surround the first sub-air supply hole.

[0048] In other embodiments of the present invention, the exhaust hole and the exhaust cavity may be omitted. Fig. 9 At this time, a three-way solenoid valve 10 is arranged at the entrance of the air intake duct, the second end of the three-way solenoid valve 10 is connected to the compressor 20 through a pipeline, and the third end thereof is connected to the vacuum pump 50 through a pipeline, and the three-way solenoid valve 10 is electrically connected to the controller. When the pneumatic deicing device is working, the compressor starts, the path between the first end and the second end is opened, and the path between the first end and the third end is closed, and the high-temperature and high-pressure gas is sent into the expansion deicing pipe for deicing; when the pneumatic deicing device stops working, the vacuum pump starts, the path between the first end and the second end is closed, and the path between the first end and the third end is opened, and the high-temperature and high-pressure gas is extracted from the expansion deicing pipe.

[0049] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A pneumatic deicing device for an aircraft propeller, characterized in that The invention comprises a distribution component rotatably mounted on a rotating shaft, an exhaust gas filter (1), a pressurized air storage component (2), a distribution component (4) and an expansion deicing pipe (6) connected in sequence through pipelines, a detection component (3) arranged on the leading edge surface of a propeller, and an exhaust component (5) connected to the distribution component through pipelines; the expansion deicing pipe is symmetrically arranged on the upper surface and the lower surface of the leading edge of the propeller, and the expansion deicing pipe comprises a first expansion airbag (61) for fitting the leading edge surface of the propeller, the first expansion airbag and the second expansion airbag in the expanded state are both semi-cylindrical, the plane part (611) of the first expansion airbag is provided with a first vent hole (63) and a plurality of through-tube holes (64) spaced apart along the axial direction of the first expansion airbag, and the arc surface part (612) thereof is provided with a first vent hole (63) and a plurality of through-tube holes (64) spaced apart along the axial direction of the first expansion airbag. A plurality of second inflatable air bags (62) are provided, and a corresponding second vent hole (65) is provided on the arc surface covered by each second inflatable air bag; a plurality of through holes are provided on the leading edge surface of the propeller covered by the inflatable deicing tube; a first air pipe and a plurality of second air pipes are provided inside the aircraft propeller; one end of the first air pipe is connected to the air supply hole (401) of the distribution component, and the other end thereof is connected to the first vent hole after passing through the corresponding through hole; one end of each second air pipe is connected to the air supply hole (401) of the distribution component, and the other end thereof is connected to the second vent hole after passing through the corresponding through hole, the corresponding through-tube hole, and the inner cavity of the first inflatable air bag in sequence; the first air pipe and the second air pipe are respectively provided with an electromagnetic valve (9); the pressurized air storage component, the detection component, the exhaust component, and the electromagnetic valve are all electrically connected to the controller.

2. A pneumatic deicing device for an aircraft propeller according to claim 1, characterized in that The pressurized gas storage assembly comprises a compressor (20) and a gas storage chamber (21) connected via a pipeline, and the outlet end of the compressor is connected to the air inlet of the distribution assembly via the pipeline.

3. A pneumatic deicing device for an aircraft propeller according to claim 1, characterized in that A first one-way valve (11) is provided on the inlet pipeline of the exhaust gas filter, and a second one-way valve (22) is provided on the pipeline between the compressor and the distribution component.

4. The pneumatic deicing device for an aircraft propeller according to claim 1, characterized in that The detection assembly includes a plurality of ice sensors arranged on the leading edge surface along the length direction of the propeller.

5. The pneumatic deicing device for an aircraft propeller according to claim 1, characterized in that The distribution assembly comprises an external cylinder body (40) and an internal cylinder body (41) which are rotatably matched, the inner wall of the external cylinder body is provided with a first boss (406) and the interior of the first boss is provided with an air supply chamber (404), the internal cylinder body is rotatably assembled on a rotating shaft (8) and a plurality of first sealing rings (403) are sandwiched between the outer wall of the internal cylinder body and the inner wall of the first boss; an air supply hole (401) is provided on the external cylinder body covering the first boss, and an air intake duct (413) is provided inside the internal cylinder body, and the air supply hole and the air intake duct are both connected to the air supply chamber; the compressor is connected to the air intake duct via a pipeline.

6. A pneumatic deicing device for an aircraft propeller according to claim 5, characterized in that An exhaust cavity (405) is also provided inside the first boss, and an exhaust hole (402) is also provided on the outer cylinder body covering the first boss. The exhaust hole and the air inlet are both connected to the exhaust cavity; the exhaust assembly is connected to the exhaust hole through a pipeline.

7. The pneumatic deicing device for an aircraft propeller according to claim 5, characterized in that The air supply hole comprises a first sub-air supply hole (4011), a plurality of second sub-air supply holes (4012) distributed around the first sub-air supply hole, one end of the first air pipe is connected to the first sub-air supply hole, and one end of the second air pipe is connected to the corresponding second sub-air supply hole.

8. The pneumatic deicing device for an aircraft propeller according to claim 5, characterized in that A second sealing ring (414) is provided at the entrance of the air inlet.

9. The pneumatic deicing device for an aircraft propeller according to claim 1, characterized in that A micro-nano protrusion structure (621) is provided on the outer wall of the second expansion airbag.

10. The pneumatic deicing device for an aircraft propeller according to claim 1, characterized in that The exhaust assembly comprises a vacuum pump (50) connected to the distribution assembly via a pipeline, and a third one-way valve (51) is provided on the pipeline between the vacuum pump and the distribution assembly.

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