CN204660026U - A kind of aircraft surfaces temperature booster - Google Patents
A kind of aircraft surfaces temperature booster Download PDFInfo
- Publication number
- CN204660026U CN204660026U CN201520247069.4U CN201520247069U CN204660026U CN 204660026 U CN204660026 U CN 204660026U CN 201520247069 U CN201520247069 U CN 201520247069U CN 204660026 U CN204660026 U CN 204660026U
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- heat exchange
- exchange cavity
- aircraft
- utility
- aircraft surfaces
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Abstract
The utility model discloses a kind of aircraft surfaces temperature booster, relate to aircraft surfaces heating technique.The technical solution adopted in the utility model is as follows: comprise admission port, air extractor duct and heat exchange cavity, described admission port is positioned at one end of heat exchange cavity, and air extractor duct is positioned at the other end of heat exchange cavity; Described heat exchange cavity is snakelike heat exchange cavity.The utility model has the advantages that to achieve utilizes the heat of aircraft tail gas to heat for aircraft surfaces, saves resource, more economically, environmental protection, efficient.
Description
Technical field
The utility model relates to aircraft surfaces heating technique.
Background technology
Under cold environment condition, the easy accumulated ice of aircraft surfaces.Aircraft icing is one of the most complicated flight weather, and when flying in cloud, mist, rain or snow slush, the position windward of aircraft, engine installation and special equipment exposed parts, the ice sheet built up due to droplets freeze or condensation of moisture, this phenomenon is exactly aircraft icing.When aircraft is at cloud flying, when body encounters super-cooling waterdrop, if when the temperature of body surface is lower than 0 DEG C, super-cooling waterdrop will freeze in some part of body surface and the formation that gathers together is frozen.In addition, aircraft enters warm wet low layer by the high level of cold, also there will be icing, it is formed because the aqueous vapor in warm layer of moisture occurs to condense on colder body, super-cooling waterdrop is very unstable, when it is subject to impacting, namely can become the ice of solid, all can produce aircraft when flying in lower than the sexual intercourse of 0 DEG C and freeze.
Aircraft any position accumulated ice all can make the aerodynamic performance of aircraft degenerate, and airplane ascensional force is reduced, and resistance increases, thus affects road-holding property and the stability of aircraft.The leading edge of a wing and empennage leading edge are frozen and may be caused that resistance increases, lift declines, the critical angle of attack reduces and the harm such as aircraft controllability reduction; Engine inlets freeze and engine charge effective amount may be caused to decline, and engine power reduces, and even cause parking, and the harm such as engine structure damage; Screw propeller position freezes may cause the harm such as unbalanced propeller, engine installation and aircraft vehicle vibrations so that bearing damage, engine off, passive safety; Windscreen position freezes may hinder crew's sight line; Meter probe position freezes may cause meter system malfunctioning (temperature, pressure etc.); Aircraft antenna position freezes and antenna may be caused to fracture, the harm such as thrashing.
Visible, aircraft any position accumulated ice all runs the safety and efficiently of aircraft and causes high risks, needs rationally, actv. solves airplane antifreezing and deicing problem, to ensure safety, the Effec-tive Function of aircarrier aircraft under cold environment condition.
Common anti-icing, deicing mode has three kinds: heating power is anti-icing, the anti-icing and mechanical deicing of liquid.Wherein, mechanical deicing's technology can be divided into again pneumatic band deicing and Electro-Impulse De-icing technology; The anti-icing technology of heating power respectively by thermal source and type of heating be divided into respectively again electro-thermal anti-ice, gas heat anti-icing technology, and continuously anti-icing and be interrupted clearing ice technology.
Current aircraft de-icing systems mainly adopts the anti-icing inefficiency of electrothermal forces, energy dissipation comparatively large, is only suitable for the deicing of widget; Liquid deicer is because liquid-consumed amount is large and spray system plant maintenance trouble; Mechanical deicing is only limited to aircraft leading edge and wing cover deicing.
Existing clearing ice technology, except there is high, the unhandy problem of cost, also cannot solve the demand of deicing in flight course.
Utility model content
Goal of the invention of the present utility model is: for above-mentioned Problems existing, provides a kind of surface heater that can utilize aircraft tail gas heating.
The technical solution adopted in the utility model is as follows: comprise admission port, air extractor duct and heat exchange cavity, described admission port is positioned at one end of heat exchange cavity, and air extractor duct is positioned at the other end of heat exchange cavity; Described heat exchange cavity is snakelike heat exchange cavity.
Further, the heat exchange cavity be bent to form by metal tube, one end of described metal tube is provided with admission port, and the other end of described metal tube is provided with air extractor duct.
Further, metal shell is comprised; One end of described metal shell has admission port, and the other end of metal shell has air extractor duct; Some baffle plates are provided with to form snakelike heat exchange cavity in metal shell inside in described metal shell.
Further, described metal shell is cuboid.
Further, in described metal shell, be staggeredly equipped with multiple baffle plate up and down to form described snakelike heat exchange cavity.
In sum, owing to have employed technique scheme, the beneficial effects of the utility model are:
1. the utility model utilizes high pressure, high temperature, the high speed tail gas heating aircraft surfaces temperature booster of aircraft engine emission, and then aircraft surfaces is carried out to gas heat is anti-icing, deicing, is a kind of economy, environmental protection, energy-conservation, efficient measure.
2. adopt aircraft tail gas as heating source that is anti-icing, deicing, as long as aircraft work, regardless of in ground or flight course, all can play effect that is anti-icing, deicing, improve the service requirement of aircraft.
3. heat exchange cavity is designed to snakelike, make aircraft tail gas can fully and the external world carry out heat exchange, improve the degree of utilization of heat energy.
Accompanying drawing explanation
Fig. 1 is the structural representation of surface heater first embodiment in the utility model.
Fig. 2 is the structural representation of surface heater second embodiment in the utility model.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in detail.
In order to make the purpose of this utility model, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
As Fig. 1, the utility model first embodiment comprises heat exchange cavity, can be specifically to be bent to form snakelike heat exchange cavity by the metal tube such as copper or copper alloy according to sine wave shape, and admission port is arranged on one end of metal tube, and the other end of metal tube is provided with air extractor duct.
In other embodiments, described pipeline can also be bent to form snakelike heat exchange cavity according to square-wave form.
As Fig. 2, the main body of the utility model second embodiment is a metal shell, and admission port is in one end of metal shell, and air extractor duct is at the other end of metal shell.Snakelike heat exchange cavity is formed with dividing plate staggered up and down in the space that betal can is formed.
In a preferred embodiment, described metal shell is cuboid.
Snakelike heat exchange cavity in the utility model refers to the cavity that gas can be made from admission port according to similar sinusoidal waveform trend in cavity to flow to air extractor duct.
During use, described surface heater is fixed on aircraft surfaces, and between surface heater and aircraft surfaces, is filled with flexible heat-conducting medium, as heat-conducting silica gel sheet or Graphite pad etc.When tail gas enters in the heat exchange pipeline of surface heater by exhaust pipe, in heat exchange pipeline, carry out interchange of heat with the external world, heat heats aircraft surfaces through heat-conducting medium, and tail gas is by being discharged in air by air extractor duct after heat exchange cavity.
Be only preferred embodiment of the present utility model described in upper, not in order to limit the utility model, all do within spirit of the present utility model and principle any amendment, equivalently to replace and improvement etc., all should be included within protection domain of the present utility model.
Claims (5)
1. an aircraft surfaces temperature booster, is characterized in that, comprise admission port, air extractor duct and heat exchange cavity, described admission port is positioned at one end of heat exchange cavity, and air extractor duct is positioned at the other end of heat exchange cavity; Described heat exchange cavity is snakelike heat exchange cavity.
2. a kind of aircraft surfaces temperature booster according to claim 1, is characterized in that, the heat exchange cavity be bent to form by metal tube, and one end of described metal tube is provided with admission port, and the other end of described metal tube is provided with air extractor duct.
3. a kind of aircraft surfaces temperature booster according to claim 1, is characterized in that, comprise metal shell; One end of described metal shell has admission port, and the other end of metal shell has air extractor duct; Some baffle plates are provided with to form snakelike heat exchange cavity in metal shell inside in described metal shell.
4. a kind of aircraft surfaces temperature booster according to claim 3, is characterized in that, described metal shell is cuboid.
5. a kind of aircraft surfaces temperature booster according to claim 4, is characterized in that, in described metal shell, is staggeredly equipped with multiple baffle plate up and down to form described snakelike heat exchange cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520247069.4U CN204660026U (en) | 2015-04-23 | 2015-04-23 | A kind of aircraft surfaces temperature booster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520247069.4U CN204660026U (en) | 2015-04-23 | 2015-04-23 | A kind of aircraft surfaces temperature booster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204660026U true CN204660026U (en) | 2015-09-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520247069.4U Expired - Fee Related CN204660026U (en) | 2015-04-23 | 2015-04-23 | A kind of aircraft surfaces temperature booster |
Country Status (1)
| Country | Link |
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| CN (1) | CN204660026U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787343A (en) * | 2015-04-23 | 2015-07-22 | 四川正冠科技有限公司 | Airplane surface heater |
-
2015
- 2015-04-23 CN CN201520247069.4U patent/CN204660026U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787343A (en) * | 2015-04-23 | 2015-07-22 | 四川正冠科技有限公司 | Airplane surface heater |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150923 Termination date: 20170423 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |