CN110077600B - Deicing device is prevented to hydrodynamic cavitation wing - Google Patents
Deicing device is prevented to hydrodynamic cavitation wing Download PDFInfo
- Publication number
- CN110077600B CN110077600B CN201910406649.6A CN201910406649A CN110077600B CN 110077600 B CN110077600 B CN 110077600B CN 201910406649 A CN201910406649 A CN 201910406649A CN 110077600 B CN110077600 B CN 110077600B
- Authority
- CN
- China
- Prior art keywords
- wing
- cavitation
- liquid
- hydrodynamic cavitation
- skin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/06—Liquid application
- B64D15/10—Liquid application sprayed over surface
Abstract
The invention discloses a hydrodynamic cavitation wing ice prevention and removal device which comprises a hydrodynamic cavitation system arranged in a wing skin, wherein the hydrodynamic cavitation system comprises a spraying part capable of cavitating liquid, the spraying part is arranged in a circulating pipeline, the circulating pipeline is communicated with a liquid inner cavity tightly attached to the wing skin, and bubbles generated in the cavitated liquid can enter the liquid inner cavity to act on the wing skin so as to realize the deicing of a wing. The invention simplifies the complexity of the device, has high feasibility and is suitable for deicing wings of various types.
Description
Technical Field
The invention relates to the field of airplane wing deicing, in particular to a hydrodynamic cavitation wing deicing device.
Background
The icing on the surface of the airplane wing can seriously affect the flight performance, the weight of the airplane is increased, the shape of the wing is changed, the flight resistance is increased, the lift force of the airplane is reduced, the airplane can rapidly descend in serious conditions, even the airplane is out of control and other consequences can be caused, and huge loss can be caused, so that the design of an airplane wing anti-icing and deicing device is needed, the airplane wing anti-icing and deicing efficiency is improved, and the airplane wing anti-icing and deicing energy consumption is reduced.
The reason why the surface of the wing of the airplane is frozen is that supercooled water drops in the cloud or supercooled rain in the falling water collide with the wing of the airplane and then are frozen, or water vapor is formed by direct desublimation on the surface of the wing. It is well known that aircraft flying in clouds for too long a time tend to accumulate ice. Therefore, the reason for icing the wings of the airplane is mainly the external reason, and most of the existing deicing devices are additionally arranged inside the wings.
The existing airplane deicing and deicing devices mostly adopt electrothermal deicing and hot air deicing technologies, and in recent years, ultrasonic deicing and deicing technologies are widely researched due to high deicing and deicing efficiency. However, the ultrasonic deicing technology has large onboard energy consumption, complicated device and large onboard weight, and thus is not widely applied in practice. Therefore, the present inventors have considered that, in view of the demand for high-energy release in the field of deicing, development of a novel high-energy release deicing technology is urgently required.
Disclosure of Invention
Aiming at the defects of the existing airplane wing deicing device, the invention aims to provide a hydrodynamic cavitation wing deicing device which can improve the existing wing deicing device, and can achieve the aim of rotor wing deicing by controlling hydrodynamic cavitation energy release and applying the hydrodynamic cavitation release heat energy and impact vibration energy in the airplane deicing technology and comprehensively utilizing and controlling the hydrodynamic cavitation release heat energy and the impact vibration energy.
The invention aims to provide a hydrodynamic cavitation wing anti-icing device.
In order to realize the purpose, the invention discloses the following technical scheme:
the hydrodynamic cavitation device for preventing and removing ice of the wing comprises a hydrodynamic cavitation system arranged inside a wing skin, wherein the hydrodynamic cavitation system comprises a spraying part capable of cavitating liquid, the spraying part is arranged in a circulating pipeline, the circulating pipeline is communicated with a liquid inner cavity tightly attached to the wing skin, and bubbles generated in the cavitated liquid can enter the liquid inner cavity to act on the wing skin, so that the deicing of the wing is realized.
Furthermore, the hydrodynamic cavitation system also comprises a circulating work station, the circulating pipeline is communicated with the circulating work station, the spraying part is communicated with the circulating pipeline, and the spraying part is simultaneously communicated with the liquid inner cavity.
Further, the spraying parts extend to the inner part of the liquid cavity, and the spraying parts are uniformly arranged in the liquid cavity along the unfolding direction of the wing.
Further, the injection part is a spray head, and the spray head is provided with a pipe wall with the diameter smaller than that of the circulating pipeline.
Furthermore, the spray head comprises a cavitation pipe wall, and the diameter of the cavitation pipe wall is gradually reduced from two ends to the middle part.
Furthermore, a heating part is further arranged in the wing skin, and the heating part can heat liquid in the circulating pipeline.
Furthermore, the circulating pipeline is also communicated with a cavitation nucleus releaser, and the cavitation nucleus releaser improves the effect of preventing and removing ice by hydrodynamic cavitation through releasing cavitation solid particles.
Further, the liquid inner cavity is formed by surrounding an inner cavity skin and a wing skin, wherein the inner cavity skin covers the inner side of the wing skin.
Further, the spraying part is connected with the inner cavity skin in a sealing mode.
Further, the circulating pipeline is also connected with a temperature sensor and a pressure control valve.
The principle of the invention can be summarized as follows: when the liquid flows, the liquid passes through the spraying part, so that according to the principle of hydrodynamics, when the pressure of the liquid is less than the saturated vapor pressure, bubbles in the liquid can be expanded, and when the bubbles reach an area with high pressure and low flow rate, the bubbles can be collapsed, burst and collapse.
Compared with the prior art, the invention has the following beneficial effects:
1. the airplane wing deicing device used by the invention is based on the hydrodynamic cavitation principle, can use bubble collapse generated by hydrodynamic cavitation to perform beating and high-temperature thermal effect on the wing, so that the wing skin vibrates, and the device has the advantages of simple principle and relatively uncomplicated parts, can be arranged on the inner side of the wing skin without influencing the wing, thereby simplifying the complexity of the device, having high practicability and being suitable for the wing deicing of various types; the invention adopts a hydrodynamic cavitation system and can release heat energy so as to assist the wings to prevent and remove ice.
2. The spraying part is communicated with the circulating pipeline and the liquid inner cavity, so that water in the liquid inner cavity can be communicated with water in the circulating pipeline, and the liquid is recycled. The hydrodynamic cavitation system used by the invention circulates liquid through the circulating pipeline, thereby reducing the use of media and prolonging the service life of products.
3. In the invention, in order to make the vibration range of the wing skin wide, a plurality of spraying parts are arranged along the extending direction of the wing, thereby effectively improving the deicing efficiency of the whole wing skin.
4. The invention can also detect and control the pressure and temperature of the cavitation fluid, control the content of cavitation nuclei and improve the hydrodynamic cavitation effect.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
FIG. 1 is a schematic view of the overall structure of embodiment 1.
FIG. 2 is a system configuration diagram of embodiment 1.
Fig. 3 is a system configuration diagram of embodiment 1 with more modules added.
FIG. 4 is a schematic view of a head according to example 1.
In the figure, 1, a covering, 2, a spray head, 3, a liquid cavity, 4, a hydraulic pump, 5, a circulating pipeline, 6, an airfoil, 7, a liquid cavity outlet, 8, a liquid cavity outlet conduit, 9, a temperature sensor, 10, a pressure control valve, 11, a heating part and 12, a cavitation nucleus releaser.
Detailed Description
It is to be understood that the following detailed description is exemplary and is intended to provide further explanation of the invention as claimed. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
As the background art shows, the existing airplane wing deicing device has the defects, the invention aims to provide the hydrodynamic cavitation wing deicing device which can improve the existing wing deicing device, and the aim of preventing and removing the ice of the rotor wing is achieved by controlling hydrodynamic cavitation energy release, applying the hydrodynamic cavitation energy release to the airplane deicing technology and comprehensively utilizing and controlling the hydrodynamic cavitation release heat energy and impact vibration energy. The invention will now be further described with reference to the accompanying drawings and detailed description.
Example 1
A hydrodynamic cavitation wing ice preventing and removing device comprises a hydrodynamic cavitation system arranged inside a wing skin 1, wherein the hydrodynamic cavitation system comprises a spraying part capable of cavitating liquid, the spraying part is arranged on a circulating pipeline 5, the circulating pipeline 5 is communicated with a liquid inner cavity 3 tightly attached to the wing skin 1, and bubbles generated in the cavitated liquid can enter the liquid inner cavity 3 to act on the wing skin 1, so that the deicing of wings is realized. In the embodiment, the hydrodynamic cavitation system is designed for liquid water, and the liquid water passes through the spraying part when flowing, so that according to the principle of hydrodynamics, when the pressure of the liquid is smaller than the saturated vapor pressure, bubbles in the liquid can be expanded, and when the bubbles reach an area with high pressure and low flow rate, the bubbles can be collapsed and burst, and the series of changes of the bubbles can effectively play a beating role on the aircraft skin 1, so that the aircraft skin 1 can vibrate, and the aim of deicing is finally fulfilled.
More in detail, the hydrodynamic cavitation system further comprises a circulating work station, the circulating pipeline 5 is communicated with the circulating work station, the spraying part is communicated with the circulating pipeline 5, and the spraying part is simultaneously communicated with the liquid inner cavity 3. Since the hydrodynamic cavitation system in this embodiment is based on the circulation of liquid, the spraying portion actually also serves to connect the circulation line 5 and the liquid cavity 3, so that the circulation line 5 can obtain the water from the liquid cavity 3 for recycling.
Further perfecting this embodiment, the jets extend inside the liquid chamber 3 and are uniformly arranged in the liquid chamber 3 in the direction of wing deployment. The plurality of injection parts can work simultaneously, and the deicing effect is perfected.
Furthermore, the injection part is a nozzle 2, the nozzle 2 comprises a cavitation pipe wall, and the diameter of the cavitation pipe wall is gradually reduced from two ends to the middle part. Thereby, the water passing through the spraying part can reach a state of low pressure and high flow speed.
The interior of the wing skin 1 is also provided with a heating part 11, and the heating part 11 can heat the liquid in the circulating pipeline 5 so as to use part of the heat to heat the skin 1 to remove ice.
The circulating pipeline 5 is also communicated with a cavitation nucleus releaser 12, and the cavitation nucleus releaser 12 improves the effect of the hydrodynamic cavitation anti-icing through releasing cavitation solid particles.
The liquid inner cavity 3 is formed by surrounding an inner cavity skin covering the inner side of the wing skin 1 and the wing skin 1. And sealing is performed.
In more detail, the spraying part is connected with the inner cavity skin in a sealing mode.
The circulating pipeline 5 is also connected with a temperature sensor 9 and a pressure control valve 10, so that the hydrodynamic cavitation anti-icing effect is improved.
The following is presented by way of a specific modification example:
the carrier 9 is a current in-service transport plane in China, a fuselage adopts a light metal semi-hard shell type thin-wall pressurizing structure, a vertical tail wing, a horizontal tail wing and an outer wing of a wing adopt a light metal skin 1 and a stringer riveting structure, and a central wing and a middle and outer wing of the wing adopt an integral wall plate screw connection structure. Thus, it is relatively easy to modify the wing skin 1 of the carrier 9.
Firstly, the method needs to be arranged inside a wing skin 1, and comprises the following specific steps:
1) the method comprises the following steps of (1) completely covering the inner side of the wing skin 1 by using a light metal skin or a light high polymer material skin as an inner cavity skin, and sealing the joint between the light metal skin or the light high polymer material skin and the wing skin 1 by using rivets and adhesives;
2) perforating the light metal skin or the light high polymer material skin;
3) assembling a circulation pipeline 5 and a circulation workstation, and arranging the circulation pipeline 5 and the circulation workstation between the wing skin 1 and the wing body; in this embodiment, the circulation pipeline 5 is an aviation pipeline made of aluminum alloy or titanium alloy or stainless steel, the circulation workstation is a hydraulic pump 4, and the specific type of the hydraulic pump 4 can be selected by a person skilled in the art according to specific needs;
4) further assembling the circulation pipeline 5, referring to fig. 1, the circulation pipeline 5 includes a plurality of branch pipes arranged in parallel, and a main pipe (not shown) connected to the branch pipes; the circulating pipeline 5 is also provided with a pressure valve;
5) in the embodiment, considering that the temperature of the transport plane is lowered to-23 ℃ when the transport plane flies to a stratosphere with the height of 10000 meters, the temperature of the transport plane is lowered to-23 ℃, so that the heating area and the power of the transport plane are reduced on the basis of the existing electrothermal ice preventing and removing device, and the temperature of the liquid in the circulating pipeline 5 can be kept;
6) a temperature detector and a controller are installed, which are all possessed by the existing electrothermal ice preventing and removing device, and the temperature detector is installed on the outer wall of the circulating pipeline 5 in the application;
7) a cavitation nucleus releaser 12, which is a member for injecting gas into the circulation line 5, such as a gas pump, is installed in the circulation line 5, cavitation nuclei, which are bubble particles in the liquid in the circulation line 5, and the cavitation nucleus releaser 12.
Referring to fig. 4, fig. 4 shows the positional relationship of the temperature sensor 9, the hydraulic pump 4, the pressure control valve 10, the heating part, and the cavitation nucleus releaser 12 on the main pipe, i.e., the heating part, the cavitation nucleus releaser 12, the pressure control valve 10, the hydraulic pump 4, and the temperature sensor 9 are sequentially disposed on the main pipe of the circulation line 5, and the specific installation method thereof is well known to those skilled in the art and will not be described herein.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A hydrodynamic cavitation wing anti-icing device is characterized by comprising a hydrodynamic cavitation system arranged inside a wing skin, wherein the hydrodynamic cavitation system comprises a spraying part capable of cavitating liquid, the spraying part is arranged on a circulating pipeline, the circulating pipeline is communicated with a liquid inner cavity tightly attached to the wing skin, and bubbles generated in the cavitated liquid can enter the liquid inner cavity to act on the wing skin so as to realize deicing of the wing;
the hydraulic cavitation system also comprises a circulating work station, a circulating pipeline is communicated with the circulating work station, the spraying part is communicated with the circulating pipeline, and the spraying part is simultaneously communicated with the liquid inner cavity; the spraying part extends to the inner part of the liquid cavity; the spraying part is a spray head;
the circulating pipeline is also communicated with a cavitation nucleus releaser, and the cavitation nucleus releaser improves the effect of preventing and removing ice by hydrodynamic cavitation through releasing cavitation solid particles;
the interior of the wing skin is also provided with a heating part; the circulating pipeline is also connected with a temperature sensor and a pressure control valve; the aim of preventing and removing ice by the rotor wing is achieved by utilizing and controlling the hydraulic cavitation to release heat energy and impact vibration energy.
2. The hydrodynamic cavitation airfoil anti-icing device of claim 1 wherein the jets are uniformly disposed in the liquid cavity in the direction of airfoil deployment.
3. The hydrodynamic cavitation airfoil anti-icing device of claim 1, wherein the nozzle has a wall diameter less than a diameter of the circulation line.
4. The hydrodynamic cavitation airfoil anti-icing device of claim 3, wherein the nozzle includes a cavitation tube wall, the cavitation tube wall gradually decreasing in diameter from the ends to the middle.
5. The hydrodynamic cavitation airfoil anti-icing device of claim 1, wherein the heater is capable of heating the liquid in the circulation line.
6. The hydrodynamic cavitation airfoil anti-icing device as defined in claim 1, wherein the liquid cavity is surrounded by a cavity skin covering the inner side of the airfoil skin and the airfoil skin.
7. The hydrodynamic cavitation airfoil anti-icing device of claim 6 wherein the nozzle portion is sealingly connected to the inner skin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910406649.6A CN110077600B (en) | 2019-05-16 | 2019-05-16 | Deicing device is prevented to hydrodynamic cavitation wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910406649.6A CN110077600B (en) | 2019-05-16 | 2019-05-16 | Deicing device is prevented to hydrodynamic cavitation wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110077600A CN110077600A (en) | 2019-08-02 |
| CN110077600B true CN110077600B (en) | 2021-04-09 |
Family
ID=67420386
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910406649.6A Active CN110077600B (en) | 2019-05-16 | 2019-05-16 | Deicing device is prevented to hydrodynamic cavitation wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110077600B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110654551B (en) * | 2019-09-30 | 2021-01-26 | 山东大学 | Aircraft deicing device and aircraft wing are prevented to aircraft based on hydrodynamic cavitation principle |
| CN111794862B (en) * | 2020-07-15 | 2021-10-22 | 山东大学 | Deicing device and deicing method for air inlet lip of aircraft engine |
| CN112193420A (en) * | 2020-08-31 | 2021-01-08 | 中电科芜湖通用航空产业技术研究院有限公司 | Micropore seepage liquid structure, aircraft anti-icing system and aircraft |
| CN114162328A (en) * | 2022-02-10 | 2022-03-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Airplane deicing method and deicing device |
| CN116176843B (en) * | 2023-04-27 | 2023-06-23 | 成都流体动力创新中心 | Aircraft deicing system based on ultrasonic cavitation |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4434045A1 (en) * | 1994-09-23 | 1996-03-28 | Daimler Benz Aerospace Ag | Deicing arrangement for leading edges of aircraft wings |
| CN202449211U (en) * | 2011-12-27 | 2012-09-26 | 东南大学 | Novel anti-icing and de-icing device for airplane airfoil |
| CN203937843U (en) * | 2014-06-25 | 2014-11-12 | 哈尔滨对俄高端技术转移孵化中心 | hydrodynamic cavitation generator nozzle |
| CN104857904A (en) * | 2015-05-19 | 2015-08-26 | 金海能国际机电设备(北京)有限公司 | Cavitation reactor |
| CN106348502A (en) * | 2016-09-21 | 2017-01-25 | 江苏科技大学 | Water hammer impact wave pulsation system applied to ship ballast water treatment |
-
2019
- 2019-05-16 CN CN201910406649.6A patent/CN110077600B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4434045A1 (en) * | 1994-09-23 | 1996-03-28 | Daimler Benz Aerospace Ag | Deicing arrangement for leading edges of aircraft wings |
| CN202449211U (en) * | 2011-12-27 | 2012-09-26 | 东南大学 | Novel anti-icing and de-icing device for airplane airfoil |
| CN203937843U (en) * | 2014-06-25 | 2014-11-12 | 哈尔滨对俄高端技术转移孵化中心 | hydrodynamic cavitation generator nozzle |
| CN104857904A (en) * | 2015-05-19 | 2015-08-26 | 金海能国际机电设备(北京)有限公司 | Cavitation reactor |
| CN106348502A (en) * | 2016-09-21 | 2017-01-25 | 江苏科技大学 | Water hammer impact wave pulsation system applied to ship ballast water treatment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110077600A (en) | 2019-08-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110077600B (en) | Deicing device is prevented to hydrodynamic cavitation wing | |
| EP3257756B1 (en) | Thermal protection and drag reduction method and system for ultra high-speed aircraft | |
| CN105691620B (en) | Utilize the ultrasonic combined anti-icing and de-icing device of the heat pipe of aircraft engine waste heat and method | |
| US10125683B2 (en) | De-icing and conditioning device for an aircraft | |
| US10737792B2 (en) | Turbofan engine fluid ice protection delivery system | |
| JP2011516344A (en) | Aircraft deicing system | |
| JP7370134B2 (en) | Combined fluid deicing and electronic cooling system | |
| EP1935783B1 (en) | Ice protection system including a plurality of segmented sub-areas and a cyclic diverter valve | |
| CN103192978B (en) | Laminate type sweating and reverse-jetting combined cooling nose cone | |
| CN108058832B (en) | Combined type anti-icing liquid-air bag anti-icing and deicing system | |
| CN110450961B (en) | Wing and flying device for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation | |
| CN105508054B (en) | A kind of engine inlets anti-icing system and aero-engine | |
| CN208571450U (en) | A kind of multi-angle flame removes the cold-resistant unmanned plane of power transmission line foreign matter | |
| CN110654551B (en) | Aircraft deicing device and aircraft wing are prevented to aircraft based on hydrodynamic cavitation principle | |
| CN110963045B (en) | Automatic deicing device for fuel wing of quoted aircraft and working method of automatic deicing device | |
| CN106005431B (en) | A kind of injecting type lifting airscrew prevents/deicer | |
| EP2995553B1 (en) | Air generation unit for an aircraft and method for its operation | |
| CN113525694A (en) | Deicing system is prevented to wing | |
| CN110525663A (en) | A kind of moisture film cavitation combines anti-deicing radome fairing with deicing liquid | |
| CN109720582A (en) | A kind of combined type electric heating-anti-deicing system of anti-freeze fluid | |
| CN205203404U (en) | Auxiliary power device exhaust cabin ventilating and cooling structure | |
| EP3296208B1 (en) | Aircraft incorporating a cabin air recovery system | |
| CN113636085A (en) | Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle | |
| CN109850160A (en) | A kind of frequency trailing type electrothermal deicing system for unmanned plane | |
| CN217515375U (en) | Aircraft wing heating device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |