JPS58156499A - Deicing device for aircraft - Google Patents
Deicing device for aircraftInfo
- Publication number
- JPS58156499A JPS58156499A JP3966782A JP3966782A JPS58156499A JP S58156499 A JPS58156499 A JP S58156499A JP 3966782 A JP3966782 A JP 3966782A JP 3966782 A JP3966782 A JP 3966782A JP S58156499 A JPS58156499 A JP S58156499A
- Authority
- JP
- Japan
- Prior art keywords
- heat
- heat pipe
- sheet
- airplane
- aircraft
- 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.)
- Pending
Links
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Abstract] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
している。加熱装置としては通常金属ヒー久一線にゴム
被俊した７ート状発熱体を用いており、電流値を加減す
ることにより、加熱温度を制御する構成を採っている。[Detailed Description of the Invention] The heating device usually uses a seven-point heating element made of a metal heater line covered with rubber, and is configured to control the heating temperature by adjusting the current value.
このようにシート状発熱体によるときは、抵抗加熱によ
るから電源が必要であり、７一ト状発熱体に対する絶縁
も必要である。In this way, when using a sheet-shaped heating element, a power source is required since resistance heating is used, and insulation for the sheet-shaped heating element is also required.
とこｂ
４シで飛行機においては、エンジンよりの排熱があり、
これは大気中に放散されている。そこで本発明はこのよ
うな排熱を利用するように、飛行機において発生する熱
源と翼前面部等加熱を要する部分をヒートパイプで接続
し、水着の防止を行うようにしたものである。Point b: In an airplane, there is exhaust heat from the engine,
This is dissipated into the atmosphere. Therefore, the present invention utilizes such waste heat by connecting a heat source generated in an airplane to a portion that requires heating, such as the front surface of a wing, using a heat pipe to prevent swimsuits from forming.
以下図面に示す実施例について説明する。The embodiments shown in the drawings will be described below.
第１図は概略的に示す本発明の一実施例であり、第２図
は翼面に取付けられる／一ト状ヒートパイプの一例を断
面で示す。FIG. 1 schematically shows an embodiment of the invention, and FIG. 2 shows, in cross section, an example of a single-piece heat pipe attached to an airfoil.
第１図において、１は飛行機エンジンその他においない
が後述のヒートパイプ６が配置されることを示している
。なお図示していないが、主翼５の前面部にもヒートパ
イプ６を配置することかできる。In FIG. 1, numeral 1 indicates that a heat pipe 6, which will be described later, is disposed in an airplane engine or the like. Although not shown, the heat pipe 6 can also be arranged on the front surface of the main wing 5.
熱源１は概念的に示したものであり、エンジンその他の
配置により別個に熱源とすることができる。The heat source 1 is shown conceptually, and can be used as a separate heat source depending on the arrangement of the engine or other components.
第２図のシート状ヒートパイプは多数のアルミまたは鋼
管６を集合してなる網状のヒートパイプであり、アルミ
または銅の被覆で、シート状に全体’ｌｔい、シート状
ヒートパイプ／−トＳとして構成される。このようにま
とめたものとしておくと取付けが便利である。The sheet-shaped heat pipe shown in FIG. Constructed as. It is convenient to install them if they are grouped together like this.
このようなヒートパイプシートＳを翼前面部の内側に密
着して固定し、前記熱源ｌとこのヒートパイプシートＳ
の間をヒートパイプ２で連結し、一体となったヒートパ
イプが形成される。Such a heat pipe sheet S is tightly fixed inside the front part of the blade, and the heat source L and this heat pipe sheet S are
The heat pipes 2 are connected to each other to form an integrated heat pipe.
熱源１とシート状ヒートパイプＳを連結するヒートパイ
プ２には熱的絶縁を施す必要がある。またヒートパイプ
２には熱源１よりシート状ヒートパイプＳの設置位置ま
でジヨイントのない構造のものが使用されることが好捷
しい。The heat pipe 2 connecting the heat source 1 and the sheet-like heat pipe S needs to be thermally insulated. Further, it is preferable that the heat pipe 2 has a structure in which there is no joint from the heat source 1 to the installation position of the sheet-like heat pipe S.
なお熱源ｌとノート状ヒートパイプＳとは、熱源ｌが下
方にあり、これに対し、ヒートパイプシートＳが上方に
あることが必要であり、これら？］ｌ−結えないが％Ｎ
”１１のように一展下刃に同くような配置ｉはＦ＠−ら
れ亀い。In addition, regarding the heat source 1 and the notebook-shaped heat pipe S, it is necessary that the heat source 1 is located below and the heat pipe sheet S is located above. ]l-I can't tie it, but %N
``A similar arrangement i on the lower blade like 11 is F@-rekamei.
以上貌明したように、本発明によれば、熱源としてエン
ジンの排熱を利用することができ、またエンジンが運転
状−にあるときＦｌ、 目動的に７１Ｌｌ熱装［會稼動
させることができる。As described above, according to the present invention, the exhaust heat of the engine can be used as a heat source, and when the engine is in operation, the Fl, can.
４、図面の簡単１に＃５を明
第１１は本発明の一実施例を示す、
第２１は本発明に用いられるシート状ヒートノ＜イブの
一例會示す。4. Figure 11 shows an embodiment of the present invention. Figure 21 shows an example of a sheet-like heat nozzle used in the present invention.
１・・・熱源、２・・・ヒートパイプ、８・・・垂匣尾
興、４・・・水平尾属、５・・・主義、６・・・シート
状ヒート・くイブ。1...Heat source, 2...Heat pipe, 8...Tarihako Oki, 4...Horizontal tail genus, 5...Issu, 6...Sheet-like heat squib.
Claims (2)
の内側にアルミまたは銅製の多数のヒートパイプを密着
配置し、前記ヒートパイプと熱源とをヒートパイプで連
結することを特徴とする飛行機の除氷装置。(1) An airplane characterized in that a large number of heat pipes made of aluminum or copper are closely arranged inside the front wing of the airplane to prevent swimsuits on the front wing of the airplane, and the heat pipes and the heat source are connected by the heat pipe. de-icing equipment.
属製の被覆で覆ったシート状ヒートパイプを用いること
を特徴とする特許請求の範囲第１項記載の飛行機の除氷
装置。(2) The aircraft de-icing device according to claim 1, characterized in that a sheet-shaped heat pipe is used in which a large number of heat pipes made of aluminum or copper are covered with a metal coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3966782A JPS58156499A (en) | 1982-03-13 | 1982-03-13 | Deicing device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3966782A JPS58156499A (en) | 1982-03-13 | 1982-03-13 | Deicing device for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58156499A true JPS58156499A (en) | 1983-09-17 |
Family
ID=12559431
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3966782A Pending JPS58156499A (en) | 1982-03-13 | 1982-03-13 | Deicing device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58156499A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8967543B2 (en) | 2010-08-30 | 2015-03-03 | Mitsubishi Heavy Industries, Ltd. | Aircraft ice protection system and aircraft provided with the same |
-
1982
- 1982-03-13 JP JP3966782A patent/JPS58156499A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8967543B2 (en) | 2010-08-30 | 2015-03-03 | Mitsubishi Heavy Industries, Ltd. | Aircraft ice protection system and aircraft provided with the same |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6279856B1 (en) | Aircraft de-icing system | |
| US3204084A (en) | Electrical deicer | |
| US6237874B1 (en) | Zoned aircraft de-icing system and method | |
| Gupta | Steady and transient free convection of an electrically conducting fluid from a vertical plate in the presence of a magnetic field | |
| GB1184354A (en) | De-icing installation for aircraft | |
| US2427972A (en) | Self-energizing airfoil | |
| US2552075A (en) | Heating device for airplanes | |
| US2330632A (en) | Means of radiating heat | |
| JPS58156499A (en) | Deicing device for aircraft | |
| US2297540A (en) | Prevention of ice formation | |
| US2391994A (en) | Electrical generating apparatus | |
| US2425088A (en) | Fan blade and mounting means therefor | |
| US5085559A (en) | Composite vane | |
| CA2375544C (en) | Aircraft de-icing system | |
| US3114524A (en) | Hypersonic velocity leading edge | |
| EP3643617B1 (en) | Heater design for carbon allotrope ice protection systems | |
| Anderson et al. | Engine-out performance characteristics | |
| GB2105520A (en) | Electro-mechanical aircraft de-icer | |
| US2375146A (en) | Protective means | |
| RU190093U1 (en) | INFRARED ELECTRICAL HEATER, INCLUDED IN SUSPENDED CEILING | |
| JPS57208703A (en) | Snow-melting device for antenna mirror surface | |
| Schoonover Jr et al. | Wind-tunnel investigation of vortex flaps on a highly swept interceptor configuration | |
| Tribus | Intermittent heating for aircraft ice protection with application to propellers and jet engines | |
| JPH03287497A (en) | Anti-icing device for airplane | |
| RU2233232C2 (en) | Method of anti-icing protection of structural members of flying vehicles |