CN201195594Y - Apparatus of electric heating exterior edge of ice-proof system of airplane - Google Patents
Apparatus of electric heating exterior edge of ice-proof system of airplane Download PDFInfo
- Publication number
- CN201195594Y CN201195594Y CNU2008200668376U CN200820066837U CN201195594Y CN 201195594 Y CN201195594 Y CN 201195594Y CN U2008200668376 U CNU2008200668376 U CN U2008200668376U CN 200820066837 U CN200820066837 U CN 200820066837U CN 201195594 Y CN201195594 Y CN 201195594Y
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- leading edge
- electrical warming
- electrical
- warming leading
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Abstract
The utility model relates to a device of an electric warming leading edge in an aircraft anti-icing system, which is formed by a generator, a power distribution device, a program mechanism, binding posts, a control and signal display device and an electric warming leading edge, and is characterized in that the electric warming leading edge is formed by three to thirteen detachable sections, wherein the binding posts are respectively arranged in the middle of each detachable section, and are fixed on aircraft wing beams through screws, each detachable section is a multi-layer structure which is formed by adhering an internal and an external skins, an internal insulating layer and an external insulating layer and an electric warming element. The device has the characteristics of novel design, reasonable design, standard technique, excellent preference, high reliability, energy conservation and free pollution, and industrialization scale production and the like, which can be widely applied in fields of various air freighter and bomb carrier electric warming leading edges and the like.
Description
Technical field
The utility model relates to the device of a kind of aircraft anti-icing system, particularly relates to the device of a kind of aircraft anti-icing system electrical warming leading edge.
Background technology
When the air temperature was lower than 5 ℃, cloud, mist, rainfall, snowfall etc. all may make airframe icing.Airframe icing brings harmful effect can for the airworthiness of aircraft, should give to prevent or in time remove, otherwise the entail dangers to flight safety.The effect of anti device is exactly to keep under the normal pneumatic external form prerequisite of aircraft, prevents that aircraft surfaces from freezing under the meteorological conditions that may freeze or remove the ice of having formed.
Aircraft needs anti-icing position to have: the leading edge of a wing, slat leading edge, empennage leading edge, engine inlets and stator blade and fairing, driving compartment wind are when positions such as glass.It is different to press type of heating for the anti-icing leading edge of transport plane and bomber, is divided into hot air and adds two kinds of gentle electrical warmings.Press the aircaft configuration mode during airplane design and determine, generally speaking, when engine suspension on wing, the leading edge of a wing, slat prime adopt hot air to heat, the empennage leading edge then adopts electrical warming, for example: Ilyushin-76, fortune-8 etc.; When engine suspension in fuselage afterbody, the slat leading edge adopts electrical warming, the empennage leading edge then adopts hot air to heat, as Tu-154 etc.The former Russian electrogenesis leading edge device of heating is used to prevent that aircraft surfaces from freezing or remove the ice of having formed and brought into play effect really under the meteorological conditions that may freeze, but, because this class device selects to exist certain limitation at structure design, technology assembling and material, cause after use after a while, insulating material burns out, bubbling, the faults such as element burns of coming unglued, heat take place again and again, the electrical warming leading edge lost efficacy, and can not guarantee the normal flight of aircraft.
Summary of the invention
The device of the aircraft anti-icing system electrical warming leading edge that the utility model relates to, its purpose is exactly in order to overcome the defective of prior art, through concentrating on studies for many years and repetition test, on the basis of prior art, in structure design, processes and selection, done bigger improvement and innovation, the device of a kind of novel, moisture resistivity and the aircraft anti-icing system electrical warming leading edge that insulating power are good, reliability is high is provided.
In order to realize above-mentioned purpose; the technical solution of the utility model is such: this device is by driving engine, electrical generator, central distribution equipment, cabin distribution equipment, programmer, control fender guard, binding post, and manipulation and signal display apparatus and electrical warming leading edge constitute.Electrical generator is contained on the driving engine, and the electricity that electrical generator sends flows to central distribution equipment, cabin distribution equipment, programmer, control fender guard, binding post by the lead connection successively with electricity, handles and signal display apparatus.It is characterized in that, the electrical warming leading edge of this device is made up of 3 to 13 independently detachable sections, in the middle of each independently detachable section binding post is housed, directly flow to detachable section of electrical warming leading edge from the electricity of binding post input, electrical warming element in the detachable section receives and produces calorific effect immediately behind the electricity and to the aircraft surfaces heating, realize preventing to freeze or remove the effect of having build-up ice; Each independently detachable section on the aircraft spar, is equipped with 3 to 14 ribs by screw retention on each detachable section, rib is used for keeping the aerodynamic configuration of aircraft, and rib is riveted on the spar or is glued on each detachable section.The detachable section of each of electrical warming leading edge is multiple-structure, and it is formed by connecting through glued membrane by inside panel, inner insulating layer, electrical warming element, external insulation layer and exterior skin.
The device of the aircraft anti-icing system electrical warming leading edge that the utility model is alleged is characterized in that inner insulating layer is made up of inner face insulating barrier and inside face insulating barrier; External insulation layer is made up of outer insulation layer and outside face insulating barrier.
The device of the aircraft anti-icing system electrical warming leading edge that the utility model is alleged, it is characterized in that, the electrical warming leading edge is made up of 13 independently detachable sections, wherein 5 detachable sections are fixed fin electrical warming leading edge, remaining 8 independently detachable sections are horizontal stabilizer electrical warming leading edge, balanced configuration is in the empennage left and right sides respectively, and promptly the empennage left side is 4 detachable sections, and the empennage right side is 4 detachable sections.
The device of the aircraft anti-icing system electrical warming leading edge that the utility model is alleged, its domestic animal be, the electrical warming leading edge is made up of 10 independently detachable sections, and balanced configuration is each side 5 detachable section of slat respectively.
The device of the aircraft anti-icing system electrical warming leading edge that the utility model is related, have novel, reasonable in design, selection easily, technological specification, non-environmental-pollution, be easy to form industrialized mass production.The insulating material that this device uses changes BMS8-79 into by glass fibre, and 1581 and BMS8-79,120 prepregs; Adhesion agent changes BMS5-101 into by the BK-9 glue, 10 grades of glued membranes; Composite formed method is changed into wet-formed by duse process, improved the moisture resistivity and the insulativity of product; Owing to be provided with control fender guard and programmer, be used to control the power on/off of element each several part of heating in this device, so both protected the element of heating not burnt out, realize again heating fully, the effect of saving electric energy.Practice test shows, device every functional changed at labour aircraft electrical warming leading edge fault rate height, the frequent phenomenon of outfield discharging, improve reliability, can effectively guarantee army's daily workout and the needs of executing the task, had tangible economic benefit and military benefit.This device can be widely used in fields such as various types of transport planes and bomber electrical warming leading edge.
Description of drawings
Fig. 1: the apparatus structure scheme drawing of aircraft anti-icing system electrical warming leading edge;
Fig. 2: the horizontal stabilizer electrical warming leading edge layout circle of the device of aircraft anti-icing system electrical warming leading edge as shown in Figure 1;
Fig. 3: the fixed fin electrical warming leading edge layout circle of the device of aircraft anti-icing system electrical warming leading edge as shown in Figure 1;
Fig. 4: the detachable segment structure scheme drawing of the electrical warming leading edge of the device of aircraft anti-icing system electrical warming leading edge as shown in Figure 1.
The specific embodiment
The device of the aircraft anti-icing system electrical warming leading edge that the utility model is alleged, in conjunction with the accompanying drawings 1 to 4, be described in detail as follows to its specific embodiment:
Embodiment 1: this device is handled and signal display apparatus 21 and electrical warming leading edge formation by driving engine 1, electrical generator 2, central distribution equipment 3, cabin distribution equipment 4, programmer 5, control fender guard 6, binding post 20; Electrical generator 2 is installed on the driving engine 1, and the electricity that electrical generator 2 sends flows to central distribution equipment 3, cabin distribution equipment 4, programmer 5, control fender guard 6, binding post 20, manipulation and signal display apparatus 21 successively by the lead connection.It is characterized in that, the electrical warming leading edge is made up of 13 independently detachable sections, wherein 5 independently detachable sections 7,8,9,10,11 are fixed fin electrical warming leading edge, remaining 8 independently detachable sections are horizontal stabilizer electrical warming leading edge, balanced configuration is in the aircraft tail left and right sides respectively, be that the empennage left side is 4 independently detachable sections 12,13,14,15, the empennage right side is 4 independently detachable sections 16,17,18,19; In the middle of each independently detachable section binding post 20 is installed, directly flow to each independently detachable section of electrical warming leading edge from the electricity of binding post 20 inputs, electrical warming element in the detachable section produces calorific effect immediately and to the aircraft surfaces heating, realizes anti-icing effect after receiving electricity; Each independently detachable section on the spar of aircraft, is equipped with 5 ribs 29 by screw retention on each detachable section, rib 29 plays the effect of the aerodynamic configuration that keeps aircraft, and rib 29 is riveted on the spar; The detachable section of each of electrical warming leading edge is multiple-structure, it uses BMS5-101 by inside panel 22, inner face insulating barrier 23, inside face insulating barrier 24, electrical warming element 25, outside face insulating barrier 26 and outer insulation layer 27,10 grades of glued membranes glued joint layer by layer and form, inner face insulating barrier 23 and inside face insulating barrier 24 are used BMS8-79,1581 prepregs are made, outside face insulating barrier 26 and outer insulation layer 27 are used BMS8-79, and 120 prepregs are made.When temperature is higher than-20 ℃, with the power on/off of ∏ MK-21C programmer 5 controlling level stabilators and fixed fin electrical warming leading edge; When temperature is lower than-20 ℃, with the power on/off of ∏ MK-21TB11 programmer 5 controlling level stabilators and fixed fin electrical warming leading edge.Anti-icing work only allows to connect in aircraft flight, and on ground, leading edge does not have radiating condition preferably, does not generally allow heating work.
Embodiment 2: the electrical warming leading edge of this device is made up of 10 independently detachable sections, and balanced configuration is each side 5 independently detachable section of slat 30 respectively.Other technical characterictic is identical with embodiment 1.
Claims (4)
1. one kind by driving engine (1), electrical generator (2), central authorities' distribution equipment (3), cabin distribution equipment (4), programmer (5), control fender guard (6), binding post (20), the device of the aircraft anti-icing system electrical warming leading edge that manipulation and signal display apparatus (21) and electrical warming leading edge constitute, electrical generator (2) is contained on the driving engine (1), electrical generator (2) flows to central distribution equipment (3) by the lead connection successively with electricity, cabin distribution equipment (4), programmer (5), control fender guard (6), binding post (20), handle and signal display apparatus (21), it is characterized in that, the electrical warming leading edge is made up of 3 to 13 independently detachable sections, in the middle of each independently detachable section binding post (20) is housed and by screw retention on the aircraft spar, on each detachable section 3 to 14 ribs (29) are housed, rib (29) is riveted on the spar or is glued on detachable section; The detachable section of each of electrical warming leading edge is multiple-structure, and by inside panel (22), inner insulating layer, electrical warming element (25), external insulation layer and exterior skin (28) form through splicing.
2. the device of aircraft anti-icing according to claim 1 system electrical warming leading edge is characterized in that inner insulating layer is made up of inner face insulating barrier (23) and inside face insulating barrier (24); External insulation layer is made up of outside face insulating barrier (26) and outer insulation layer (27).
3. the device of aircraft anti-icing according to claim 1 and 2 system electrical warming leading edge, it is characterized in that, the electrical warming leading edge is made up of 13 independently detachable sections, wherein 5 detachable sections (7,8,9,10,11) are fixed fin electrical warming leading edge, remaining 8 independently detachable sections are horizontal stabilizer electrical warming leading edge, balanced configuration is in the empennage left and right sides respectively, be that the empennage left side is 4 detachable sections (12,13,14,15), the empennage right side is 4 detachable sections (16,17,18,19).
4. the device of aircraft anti-icing according to claim 1 and 2 system electrical warming leading edge is characterized in that, the electrical warming leading edge is made up of 10 independently detachable sections, and balanced configuration is each side 5 detachable section of slat (30) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200668376U CN201195594Y (en) | 2008-04-30 | 2008-04-30 | Apparatus of electric heating exterior edge of ice-proof system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200668376U CN201195594Y (en) | 2008-04-30 | 2008-04-30 | Apparatus of electric heating exterior edge of ice-proof system of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201195594Y true CN201195594Y (en) | 2009-02-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008200668376U Expired - Lifetime CN201195594Y (en) | 2008-04-30 | 2008-04-30 | Apparatus of electric heating exterior edge of ice-proof system of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201195594Y (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103930346A (en) * | 2011-09-20 | 2014-07-16 | 波音公司 | Integrated surface thermal management system |
| CN105667806A (en) * | 2014-11-19 | 2016-06-15 | 中国航空工业集团公司西安飞机设计研究所 | Deicing method |
| CN110481793A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of new electrically heating ice shape regulation method and anti-freeze type aircraft |
| EP3725686A1 (en) * | 2019-04-19 | 2020-10-21 | Goodrich Corporation | Bonded structural rib for heated aircraft leading edge |
-
2008
- 2008-04-30 CN CNU2008200668376U patent/CN201195594Y/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103930346A (en) * | 2011-09-20 | 2014-07-16 | 波音公司 | Integrated surface thermal management system |
| CN103930346B (en) * | 2011-09-20 | 2017-02-08 | 波音公司 | Integrated surface thermal management system and airplane comprising same |
| CN105667806A (en) * | 2014-11-19 | 2016-06-15 | 中国航空工业集团公司西安飞机设计研究所 | Deicing method |
| EP3725686A1 (en) * | 2019-04-19 | 2020-10-21 | Goodrich Corporation | Bonded structural rib for heated aircraft leading edge |
| CN110481793A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of new electrically heating ice shape regulation method and anti-freeze type aircraft |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20090218 |
|
| CX01 | Expiry of patent term |