CN104787344A - Automatic airplane surface heating device - Google Patents
Automatic airplane surface heating device Download PDFInfo
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- CN104787344A CN104787344A CN201510193615.5A CN201510193615A CN104787344A CN 104787344 A CN104787344 A CN 104787344A CN 201510193615 A CN201510193615 A CN 201510193615A CN 104787344 A CN104787344 A CN 104787344A
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- aircraft surfaces
- aircraft
- heating device
- gas valve
- surface heater
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Abstract
The invention discloses an automatic airplane surface heating device, and relates to the technology of airplane surface heating. According to the adopted technical scheme, the automatic airplane surface heating device comprises a tail gas pipeline, a gas valve, a surface heater, a temperature sensor and a valve controller, one end of the tail gas pipeline is used for collecting tail gas of an airplane, the other end of the tail gas pipeline is connected to an air inlet of the surface heater, and the gas valve is arranged inside the tail gas pipeline. The surface heater is used for heating the surface of the airplane. The temperature sensor is used for collecting the temperature of the surface of the airplane and transmitting the collected temperature information to the valve controller. The automatic airplane surface heating device has the advantages that tail gas of the airplane is used for heating the surface of the airplane, and energy consumption and cost are saved.
Description
Technical field
The present invention 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.
Summary of the invention
Technical matters to be solved by this invention is: for above-mentioned Problems existing, provides a kind of device utilizing aircraft tail gas to carry out deicing.
The technical solution used in the present invention is as follows: comprise exhaust pipe, gas valve, surface heater, temperature sensor and valve positioner.
One end of exhaust pipe is for collecting aircraft tail gas, and the other end of exhaust pipe is connected to the admission port of surface heater, and is also provided with gas valve in exhaust pipe.
Described surface heater is used for for aircraft surfaces heating.
Described temperature sensor is for gathering the temperature of aircraft surfaces and the temperature information collected being transferred to valve positioner.
Described valve positioner is used for the opening and closing controlling gas valve according to described temperature information.
Further, described surface heater comprises heat exchange cavity, and described admission port is also the admission port of heat exchange cavity, and the other end of described heat exchange cavity is provided with air extractor duct.
Further, described heat exchange cavity is snakelike heat exchange cavity.
Further, exhaust pipe is high-temperature resistant pipeline, and described gas valve is high-temperature-resistant gas valve, and described high temperature is for being more than or equal to 1000 degrees Celsius.
Further, described surface heater is fixed on aircraft surfaces, and between surface heater and aircraft surfaces, be filled with flexible heat-conducting medium.
Further, described valve positioner works in such a way:
Setting low temperature threshold and high temperature threshold value, low temperature threshold is less than high temperature threshold value;
Then judge whether described temperature information is less than described low temperature threshold at interval of certain hour, if be less than, control described gas valve and open, judge whether described temperature information is greater than high temperature threshold value simultaneously, if be greater than, control described gas valve and close.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows:
1. the present invention 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. adopt temperature sensor and valve positioner automatically to control heat process, ensure that heat stable everywhere, and improve intelligent processing ability.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the structural representation of apparatus of the present invention.
Fig. 2 is the structural representation of surface heater in the present invention.
Fig. 3 is the workflow diagram of valve positioner of the present invention.
Detailed description of the invention
All features disclosed in this specification sheets, or the step in disclosed all methods or process, except mutually exclusive feature and/or step, all can combine by any way.
Arbitrary feature disclosed in this specification sheets, unless specifically stated otherwise, all can be replaced by other equivalences or the alternative features with similar object.That is, unless specifically stated otherwise, each feature is an example in a series of equivalence or similar characteristics.
As Fig. 1, the present invention includes exhaust pipe, gas valve, surface heater, temperature sensor and valve positioner.
One end of exhaust pipe is for collecting aircraft tail gas, and the other end of exhaust pipe is connected to the admission port of surface heater, and is also provided with gas valve in exhaust pipe.
It is aircraft surfaces heating that described surface heater is installed on aircraft surfaces by screw or fixture.
Described temperature sensor is for gathering the temperature of aircraft surfaces and the temperature information collected being transferred to valve positioner.
Described valve positioner is used for the opening and closing controlling gas valve according to described temperature information.
In a specific embodiment, described surface heater comprises heat exchange cavity, can be specifically be bent to form snakelike heat exchange cavity by the metal tube such as copper or copper alloy according to sine wave shape, described admission port be also the admission port of heat exchange cavity, and the other end of described heat exchange cavity 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, can also be to form snakelike heat exchange cavity, as Fig. 3 with dividing plate staggered up and down in a coffin.Snakelike heat exchange cavity in the present invention refers to the cavity that gas can be made from admission port according to sinusoidal waveform trend in cavity to flow to air extractor duct.
Because aircraft exhaust temperature is higher, exhaust pipe and gas valve all need to have resistance to elevated temperatures, and high temperature here refers to the temperature being more than or equal to 1000 degrees Celsius.Preferably, exhaust pipe and gas valve material are pottery.
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.Preset low temperature threshold and high temperature threshold value, low temperature threshold is less than high temperature threshold value.Low temperature threshold is 0 DEG C in a specific embodiment, and high temperature threshold value is 10 DEG C.
At interval of certain hour, valve positioner then judges whether the described temperature information that temperature sensor exports is less than described low temperature threshold, if be less than, control described gas valve and open, tail gas enters the heat exchange pipeline of surface heater by exhaust pipe, interchange of heat is carried out with the external world in heat exchange pipeline, 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.The temperature information that valve positioner real-time reception temperature sensor exports also judges whether described temperature information is greater than high temperature threshold value, if be greater than, control described gas valve and closes, stop heating.As Fig. 3.Valve positioner can also receive other equipment, and as CPU, switch etc., the control command transmitted, controls the opening and closing of other valves according to control command.
The present invention is not limited to aforesaid detailed description of the invention.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.
Claims (6)
1. an aircraft surfaces automatic heating device, is characterized in that, comprises exhaust pipe, gas valve, surface heater, temperature sensor and valve positioner;
One end of exhaust pipe is for collecting aircraft tail gas, and the other end of exhaust pipe is connected to the admission port of surface heater, and is also provided with gas valve in exhaust pipe;
Described surface heater is used for for aircraft surfaces heating;
Described temperature sensor is for gathering the temperature of aircraft surfaces and the temperature information collected being transferred to valve positioner;
Described valve positioner is used for the opening and closing controlling gas valve according to described temperature information.
2. a kind of aircraft surfaces automatic heating device according to claim 1, it is characterized in that, described surface heater comprises the heat exchange cavity be bent to form by metal tube, and described admission port is also the admission port of heat exchange cavity, and the other end of described heat exchange cavity is provided with air extractor duct.
3. a kind of aircraft surfaces automatic heating device according to claim 2, is characterized in that, described heat exchange cavity is snakelike heat exchange cavity.
4. a kind of aircraft surfaces automatic heating device according to claim 1, is characterized in that, exhaust pipe is high-temperature resistant pipeline, and described gas valve is high-temperature-resistant gas valve, and described high temperature is for being more than or equal to 1000 degrees Celsius.
5. a kind of aircraft surfaces automatic heating device according to claim 1 or 2 or 3, it is characterized in that, described surface heater is fixed on aircraft surfaces, and between surface heater and aircraft surfaces, be filled with flexible heat-conducting medium.
6. a kind of aircraft surfaces automatic heating device according to claim 1, it is characterized in that, described valve positioner works in such a way:
Setting low temperature threshold and high temperature threshold value, low temperature threshold is less than high temperature threshold value;
Then judge whether described temperature information is less than described low temperature threshold at interval of certain hour, if be less than, control described gas valve and open, judge whether described temperature information is greater than high temperature threshold value simultaneously, if be greater than, control described gas valve and close.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510193615.5A CN104787344A (en) | 2015-04-23 | 2015-04-23 | Automatic airplane surface heating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510193615.5A CN104787344A (en) | 2015-04-23 | 2015-04-23 | Automatic airplane surface heating device |
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| CN104787344A true CN104787344A (en) | 2015-07-22 |
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| CN201510193615.5A Pending CN104787344A (en) | 2015-04-23 | 2015-04-23 | Automatic airplane surface heating device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691620A (en) * | 2016-01-20 | 2016-06-22 | 南京师范大学 | Heat pipe and ultrasonic wave combined ice preventing and removing device and method utilizing waste heat of aircraft engine |
| CN107499398A (en) * | 2017-06-23 | 2017-12-22 | 吉林大学 | Active variant automobile tail fin mechanism control system and method based on marmem |
| CN109850159A (en) * | 2019-02-18 | 2019-06-07 | 广西大学 | One kind is based on the recoverable unmanned plane during flying winterization system of heat |
| CN110641711A (en) * | 2019-10-30 | 2020-01-03 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle |
| CN113636085A (en) * | 2020-04-27 | 2021-11-12 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle |
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| CN204660027U (en) * | 2015-04-23 | 2015-09-23 | 四川正冠科技有限公司 | A kind of aircraft surfaces automatic heating device |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691620A (en) * | 2016-01-20 | 2016-06-22 | 南京师范大学 | Heat pipe and ultrasonic wave combined ice preventing and removing device and method utilizing waste heat of aircraft engine |
| CN105691620B (en) * | 2016-01-20 | 2018-04-24 | 南京师范大学 | Utilize the ultrasonic combined anti-icing and de-icing device of the heat pipe of aircraft engine waste heat and method |
| CN107499398A (en) * | 2017-06-23 | 2017-12-22 | 吉林大学 | Active variant automobile tail fin mechanism control system and method based on marmem |
| CN107499398B (en) * | 2017-06-23 | 2023-04-28 | 吉林大学 | Active variant automobile tail wing mechanism control system and method based on shape memory alloy |
| CN109850159A (en) * | 2019-02-18 | 2019-06-07 | 广西大学 | One kind is based on the recoverable unmanned plane during flying winterization system of heat |
| CN110641711A (en) * | 2019-10-30 | 2020-01-03 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle |
| CN110641711B (en) * | 2019-10-30 | 2021-08-03 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle |
| CN113636085A (en) * | 2020-04-27 | 2021-11-12 | 西安京东天鸿科技有限公司 | Unmanned aerial vehicle and control method of anti-icing and deicing system of unmanned aerial vehicle |
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Application publication date: 20150722 |