CN104443396A - Surface ice protection system for composite airfoils - Google Patents
Surface ice protection system for composite airfoils Download PDFInfo
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- CN104443396A CN104443396A CN201410752695.9A CN201410752695A CN104443396A CN 104443396 A CN104443396 A CN 104443396A CN 201410752695 A CN201410752695 A CN 201410752695A CN 104443396 A CN104443396 A CN 104443396A
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- temperature
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- empennage
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Abstract
The invention relates to a surface ice protection system for composite airfoils and a temperature control method thereof. A small aircraft or an unmanned aerial vehicle has low load, hot gas guided from an engine is insufficient, and carrying the existing ice control and removal system is difficult for the small aircraft or the unmanned aerial vehicle. According to the surface ice protection system, graphite foil electrothermal material is used to make a heating part of the system, electricity is used, no gas entrainment is required, and power consumption is low. According to signals generated by a peripheral temperature control sensor and an ice sensor, the heating power of the novel surface ice protecting part based on a flexible graphite foil is controlled area by area, and thus, ice on an empennage is adaptively removed at low power consumption.
Description
Technical field
The present invention relates to a kind of novel surface formula being applied to composite wing to freeze protective system, be applicable to the wing of SUAV (small unmanned aerial vehicle) and helicopter and the anti-icing of empennage and deicing.
Background technology
The aircraft protective system that freezes comprises the large class of anti icing system and ice removal system two, is mainly used in aircraft key position, as wing, empennage, engine inlets leading edge, radom etc.Anti icing system is evaporated by most shock water and keeps surface temperature always higher than the system that freezing point is frozen to prevent aircraft components surface; Ice removal system refer to periodically by parts surface freeze remove system, allow parts surface tie a small amount of ice.Energy required for the relative ice removal system of anti icing system is high a lot, is applied to the parts of particular importance more.The protective device that freezes at present has a variety of, and what have reaches ripe application, have at design study, their Applicable scope and energy ezpenditure have very large difference.Conventional anti-de-icing method mainly comprises mechanical deicing, the anti-deicing of chemical liquid, the anti-icing and hot anti-deicing of super hydrophobic surface.These anti-de-icing methods have application on various aircraft, various icing parts, and wherein maximum are the anti-ice removal systems of hot gas and electric heating.But along with the development of aircraft industry, the increasing weight using composite material to reduce aircraft on aircraft, the poor feature of composite material permeability of heat has carried out new problem to anti-deicing system band.Moreover for blimp or unmanned plane, because load own is less, and do not have the hot gas that sufficient driving engine attracts, such aircraft is difficult to carry existing anti-ice removal system.
Because graphite foil elasticity is good, its extra-thin laminar texture makes it lightweight, and is easily installed on unconventional machine side, and in addition, owing to heating up instantaneously, the heating power of requirement is little.This invention to be frozen proposing protective system based on the novel surface formula of graphite foil, and is mainly used in and adopts the unmanned plane of composite material and the wing anti-ice of helicopter and empennage deicing.But because the present invention is towards the anti-deicing of composite wing, its temperature control method will exist different as follows from the metal skin wing of routine:
(1) composite material poor thermal conductivity, must be installed on outside wing by the system of preventing and kill off;
(2) composite material poor thermal conductivity, must be placed in wing outer rim as far as possible by temperature-control senser, with correct perceptron wing surface heating-up temperature;
(3) due to the complexity of meteorological conditions, for the unknown feature of surperficial wing deicing amount, novel subregion temperature control method must be set up.
Due to the problems referred to above, the present invention proposes a kind of novel surface formula being applied to composite wing and to freeze protective system and temperature control method thereof, for realizing adopting the unmanned plane of composite material and the wing anti-ice of helicopter and empennage deicing.
Summary of the invention
According to an aspect of the present invention, use graphite foil electric heating material to adhere to composite wing, form the novel surface-type towards composite wing and to freeze protective system.This novel surface-type towards composite wing freezes protective system owing to employing graphite foil as surface heating part, there is good, the ultra-thin laminar texture of elasticity, be easy to adhere to irregular outside face, lightweight feature, in addition, the heating power can heat up instantaneously, required is little.
According to an aspect of the present invention, the protective system subregion that frozen by a kind of surface-type towards composite wing of proposition is arranged and zoned temperature control method.Set up novel subregion to arrange and temperature control method, solve IFR conditions lower surface wing deicing amount unknown problem, according to outside wall temperature sensor or freezing sensor signal adaptive ground heating region and add heat.
According to an aspect of the present invention, provide a kind of novel surface formula being applied to composite wing and to freeze protective system and temperature control method thereof, be applicable to wing anti-ice and empennage deicing that unmanned plane and helicopter adopt composite material.The invention is characterized in and comprise:
Novel surface formula based on soft graphite paper tinsel is frozen protecting component, for unmanned plane and helicopter composite material wing anti-ice and the deicing of composite material empennage;
Outer rim temperature-control senser, due to composite wing or empennage poor thermal conductivity, this temperature-control senser must be positioned at wing outer rim, for experiencing wing or empennage hull-skin temperature best;
Freezing sensor, for experiencing aircraft wing or whether empennage outside face freezes;
Self adaptation heating controller, according to outer rim temperature-control senser and freezing sensor signal, controls to freeze protecting component heating power based on the novel surface formula of soft graphite paper tinsel according to control law.
Accompanying drawing explanation
Fig. 1 is that the aircraft electric pulse of prior art prevents and kill off ice principle schematic,
Fig. 2, for illustration of according to one embodiment of present invention, illustrates the principle of a kind of novel surface formula composite wing anti icing system and temperature control thereof, for unmanned plane and helicopter composite material wing anti-ice,
Fig. 3, for illustration of according to one embodiment of present invention, illustrates the principle of a kind of novel surface formula composite material empennage ice removal system and temperature control thereof, for unmanned plane and the deicing of helicopter composite material empennage,
Fig. 4, for illustration of according to one embodiment of present invention, illustrates a kind of novel surface formula composite material empennage ice removal system intermittent-heating temperature control method.
Detailed description of the invention
An object of the present invention is to set up a kind of novel surface formula being applied to composite wing to freeze protective system, good, the ultra-thin laminar texture of elasticity can be realized, be easy to adhere to irregular outside face, lightweight surface-type freezes fail-safe structure, and heat up instantaneously, low energy consumption object that heating power is little.
A kind of novel surface formula being applied to composite wing protective system that freezes that the present invention sets up includes two type systematics, i.e. a kind of novel surface formula composite wing anti icing system and a kind of novel surface formula composite material empennage ice removal system.For novel surface formula composite material empennage ice removal system, set up novel subregion to arrange and temperature control method, according to outside wall temperature sensor or freezing sensor signal adaptive ground heating region and add heat, solve IFR conditions lower surface wing deicing amount unknown problem.
The electro heat that currently available technology is mentioned freezes protective system, be that electric pulse freezes protective system as shown in Figure 1, form primarily of aircraft skin 301, coil 1 (302), intensifier 303, coil 2 (304), coil support 305, cond 306, binary pair 307, silicon control 308.The electro heat that prior art the is mentioned main Problems existing of protective system that freezes is: (1) is for composite wing or empennage, permeability of heat is poor, the heat transfer that electric energy conversion cannot become by the built-in anti-ice removal system of electric arteries and veins, to wing outer rim, carrys out new problem therefore to anti-deicing system band; (2) for blimp or unmanned plane, because load own is less, and do not have the hot gas that sufficient driving engine attracts, such aircraft is difficult to carry existing hot gas or the anti-ice removal system of electric pulse.
The present invention proposes a kind of novel surface formula being applied to composite wing and to freeze protective system and temperature control method thereof, is mainly used in and adopts the unmanned plane of composite material and the wing anti-ice of helicopter and empennage deicing object.Present invention comprises two kinds System, a kind of novel surface formula composite wing anti icing system and a kind of novel surface formula composite material empennage ice removal system.
According to a specific embodiment of the present invention, provide a kind of novel surface formula composite wing anti icing system and temperature control method thereof, as shown in Figure 2.Novel surface formula composite wing anti icing system according to an embodiment of the invention comprises: composite wing 102, for the formation of the good air current composition of airplane ascensional force; Novel surface formula based on soft graphite paper tinsel is frozen protecting component 101, for being heat energy by electric energy conversion, improves composite wing surface temperature, thus the ice that anti-stagnant ice produces or removing produces; Outer rim temperature-control senser 103, this temperature-control senser is positioned at wing outer rim, for experiencing airfoil outer surface temperature; Whether freezing sensor 107, freeze for experiencing aircraft wing outside face; Self adaptation heating controller 106, the temperature signal 104 produced according to outer rim temperature-control senser 103 and freezing sensor 107 and icing signal 108, produce according to control law and add heat control signal 105, control to freeze protecting component heating power based on the novel surface formula of soft graphite paper tinsel.
According to a specific embodiment of the present invention, provide a kind of novel surface formula composite material empennage ice removal system and temperature control method thereof, as shown in Figure 3.Novel surface formula composite wing ice removal system according to an embodiment of the invention comprises: composite material empennage 201, for keeping the good lift air-flow of aircraft, novel surface formula subregion based on soft graphite paper tinsel freezes protecting component 2021 ~ 2025, for being heat energy by electric energy conversion, improve composite material stabilizing surfaces temperature, thus remove the ice of stabilizing surfaces generation discontinuously, because fin area is larger, as large area heating stabilizing surfaces, to consume energy very much, for the unknown feature of surperficial empennage deicing amount, novel surface formula based on the soft graphite paper tinsel protecting component 2021 ~ 2025 that freezes have employed subregion arrangement, according to temperature signal 205 and icing signal 207, by intermittent-heating temperature control method (Fig. 4), control in subregional to freeze protecting component heating power based on the novel surface formula of soft graphite paper tinsel, outer rim temperature-control senser 2031 ~ 2035, is positioned at wing outer rim, and every block surface-type protecting component that freezes arranges a temperature sensor, for experiencing empennage zones of different hull-skin temperature, whether freezing sensor 204, freeze for experiencing aircraft tail outside face, self adaptation heating controller 206, the temperature signal 205 produced according to outer rim temperature-control senser 2031 ~ 2035 and freezing sensor 204 and icing signal 207, adding heat control signal 208 according to producing by intermittent-heating temperature control method (Fig. 4), controlling in subregional to freeze protecting component heating power based on the novel surface formula of soft graphite paper tinsel.
The present invention proposes a kind of novel surface formula being applied to composite wing and to freeze protective system and temperature control method thereof, freezes compared with protective device, the invention has the advantages that with existing aircraft hot gas and electric heating:
The present invention uses graphite foil electric heating material to freeze protecting component as novel surface formula, and have good, the ultra-thin laminar texture of elasticity, be easy to adhere to irregular outside face, lightweight feature, panelty is little;
The present invention uses graphite foil electric heating material to freeze protecting component as novel surface formula, and the heating power can heat up instantaneously, required is little, is more conducive to energy-conservation;
The present invention uses graphite foil electric heating material to freeze protecting component as novel surface formula, can adhere to composite wing or empennage outside face, solves the poor new problem come to anti-deicing system band of composite material permeability of heat well;
For blimp or unmanned plane, because load own is less, do not have the hot gas that sufficient driving engine attracts, such aircraft is difficult to carry existing anti-ice removal system, and the icing protective system that the present invention proposes uses electric energy, without the need to bleed, and power consumption is little;
The present invention proposes outer rim temperature-control senser to be placed in composite wing or empennage outer rim, can perceptron wing surface heating-up temperature better, prevents heating overheated;
The present invention proposes interval subregion heated for controlling temperature method, instrument meteorological condition flight environment can be adapted to well, signal is produced according to outer rim temperature-control senser and freezing sensor, control in subregional to freeze protecting component heating power based on the novel surface formula of soft graphite paper tinsel, realize low-power consumption, remove the ice that empennage produces adaptively.The present invention uses graphite foil electric heating material to freeze protecting component as novel surface formula, composite wing or empennage outside face can be adhered to, solve the poor new problem come to anti-deicing system band of composite material permeability of heat well, have good, the ultra-thin laminar texture of elasticity, be easy to adhere to irregular outside face, lightweight feature, panelty is little;
For blimp or unmanned plane, because load own is less, there is no the hot gas that sufficient driving engine attracts, such aircraft is difficult to carry existing anti-ice removal system, and the icing protective system that the present invention proposes uses electric energy, without the need to bleed, the heating power can heat up instantaneously, required is little, is more conducive to energy-conservation and power consumption is little; The present invention proposes outer rim temperature-control senser to be placed in composite wing or empennage outer rim, can perceptron wing surface heating-up temperature better, prevents heating overheated; And owing to have employed interval subregion heated for controlling temperature method, instrument meteorological condition flight environment can be adapted to well, signal is produced according to outer rim temperature-control senser and freezing sensor, control in subregional to freeze protecting component heating power based on the novel surface formula of soft graphite paper tinsel, realize low-power consumption, remove the ice that empennage produces adaptively.
Claims (2)
1. to freeze a protective system for the surface of composite wing, it is characterized in that: comprise
Novel surface formula based on soft graphite paper tinsel is frozen protecting component (101), for being heat energy by electric energy conversion, improves composite wing surface temperature, thus the ice that anti-stagnant ice produces or removing produces;
Outer rim temperature-control senser (103), this temperature-control senser is positioned at wing outer rim, for detecting airfoil outer surface temperature;
Self adaptation heating controller (106), according to the signal that outer rim temperature-control senser produces, produces according to control law and adds heat, the heating power of the protecting component that controls to freeze based on the novel surface formula of soft graphite paper tinsel.
2. for an ice removal system for composite material empennage, it is characterized in that: comprise
Outer rim temperature-control senser (2031 ~ 2035), is positioned at empennage outer rim, and every block surface-type protecting component that freezes arranges a temperature sensor, for experiencing empennage zones of different hull-skin temperature;
Self adaptation heating controller (206), adds heat control signal according to producing by intermittent-heating temperature control method, controls in subregional to freeze protecting component heating power based on the surface-type of soft graphite paper tinsel;
Surface-type subregion based on soft graphite paper tinsel freezes protecting component (2021 ~ 2025), be heat energy by electric energy conversion, improve composite material stabilizing surfaces temperature, novel surface formula based on the soft graphite paper tinsel protecting component (2021 ~ 2025) that freezes have employed subregion arrangement, according to temperature signal and icing signal, by intermittent-heating temperature control method, thus remove the ice that stabilizing surfaces produces discontinuously, control in subregional to freeze protecting component heating power based on the novel surface formula of soft graphite paper tinsel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201410752695.9A CN104443396A (en) | 2014-12-10 | 2014-12-10 | Surface ice protection system for composite airfoils |
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| CN201410752695.9A CN104443396A (en) | 2014-12-10 | 2014-12-10 | Surface ice protection system for composite airfoils |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106582129A (en) * | 2016-12-26 | 2017-04-26 | 江苏华强新能源科技有限公司 | Static air filter |
| CN107985607A (en) * | 2017-11-02 | 2018-05-04 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane icing protective device |
| CN109696290A (en) * | 2019-02-18 | 2019-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system |
| CN111452979A (en) * | 2020-04-27 | 2020-07-28 | 西北工业大学 | Deicing device and unmanned aerial vehicle |
| CN112124600A (en) * | 2020-09-30 | 2020-12-25 | 中航(成都)无人机系统股份有限公司 | Anti-icing and deicing coating of composite wing |
| CN112193421A (en) * | 2020-09-30 | 2021-01-08 | 中航(成都)无人机系统股份有限公司 | Electric heating coating for preventing and removing ice on wing |
| CN112208772A (en) * | 2020-09-08 | 2021-01-12 | 刘红光 | Full-automatic low-energy-consumption deicing control system |
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| US6237874B1 (en) * | 1997-09-22 | 2001-05-29 | Northcoast Technologies | Zoned aircraft de-icing system and method |
| GB2447374A (en) * | 2004-01-30 | 2008-09-10 | Ultra Electronics Ltd | Modular aircraft control system and method |
| US20100243811A1 (en) * | 2007-06-26 | 2010-09-30 | Stothers Ian Mcgregor | Ice protection heater system |
| US20140191084A1 (en) * | 2012-12-05 | 2014-07-10 | Mesocribe Technologies, Inc. | Ice detection and mitigation device |
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2014
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6237874B1 (en) * | 1997-09-22 | 2001-05-29 | Northcoast Technologies | Zoned aircraft de-icing system and method |
| GB2447374A (en) * | 2004-01-30 | 2008-09-10 | Ultra Electronics Ltd | Modular aircraft control system and method |
| US20100243811A1 (en) * | 2007-06-26 | 2010-09-30 | Stothers Ian Mcgregor | Ice protection heater system |
| US20140191084A1 (en) * | 2012-12-05 | 2014-07-10 | Mesocribe Technologies, Inc. | Ice detection and mitigation device |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106582129A (en) * | 2016-12-26 | 2017-04-26 | 江苏华强新能源科技有限公司 | Static air filter |
| CN107985607A (en) * | 2017-11-02 | 2018-05-04 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane icing protective device |
| CN109696290A (en) * | 2019-02-18 | 2019-04-30 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind energy conversion system wing panel Anti-icing Heat Loads demand measuring system |
| CN111452979A (en) * | 2020-04-27 | 2020-07-28 | 西北工业大学 | Deicing device and unmanned aerial vehicle |
| CN112208772A (en) * | 2020-09-08 | 2021-01-12 | 刘红光 | Full-automatic low-energy-consumption deicing control system |
| CN112124600A (en) * | 2020-09-30 | 2020-12-25 | 中航(成都)无人机系统股份有限公司 | Anti-icing and deicing coating of composite wing |
| CN112193421A (en) * | 2020-09-30 | 2021-01-08 | 中航(成都)无人机系统股份有限公司 | Electric heating coating for preventing and removing ice on wing |
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Application publication date: 20150325 |