JPH01149894U - - Google Patents
Info
- Publication number
- JPH01149894U JPH01149894U JP4732188U JP4732188U JPH01149894U JP H01149894 U JPH01149894 U JP H01149894U JP 4732188 U JP4732188 U JP 4732188U JP 4732188 U JP4732188 U JP 4732188U JP H01149894 U JPH01149894 U JP H01149894U
- Authority
- JP
- Japan
- Prior art keywords
- fluid
- gas
- main wing
- circulation path
- heat exchanger
- 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
- 239000012530 fluid Substances 0.000 claims description 7
- 230000005855 radiation Effects 0.000 claims 3
- 238000010586 diagram Methods 0.000 description 2
Description
第１図は本考案の一実施例を示す全体図、第２
図は第１図のルーテイング図、第３図は従来にお
ける航空機主翼前縁の防／除氷機構を示す図であ
る。
１……航空機、２……エンジン、３……エンジ
ン排気部、４……ガス／流体熱交換器、５……イ
ンテグラルチユーブ、６……ポンプ、７……制御
弁、８……温度センサ、９……氷、１０……主翼
前縁、１１……空気ダクト。
Figure 1 is an overall view showing one embodiment of the present invention;
The drawings are a routing diagram of FIG. 1, and FIG. 3 is a diagram showing a conventional anti-icing/de-icing mechanism for the leading edge of an aircraft main wing. DESCRIPTION OF SYMBOLS 1...Aircraft, 2...Engine, 3...Engine exhaust section, 4...Gas/fluid heat exchanger, 5...Integral tube, 6...Pump, 7...Control valve, 8...Temperature sensor , 9...ice, 10...main wing leading edge, 11...air duct.
Claims (1)
／流体熱交換器と、主翼前縁部に形成される放熱
用チユーブと、上記ガス／流体熱交換器と放熱用
チユーブとの間を接続する流体の循環路と、この
循環路にガス／流体熱交換器による熱交換後の流
体を循環させる手段と、上記循環路より上記放熱
用チユーブへ供給される流体の温度を制御する温
度制御手段とを具備したことを特徴とする航空機
主翼前縁の防／除氷機構。 A gas/fluid heat exchanger installed in the exhaust section of an aircraft main wing engine, a heat radiation tube formed in the leading edge of the main wing, and a fluid connecting between the gas/fluid heat exchanger and the heat radiation tube. A circulation path, a means for circulating a fluid after heat exchange by a gas/fluid heat exchanger through the circulation path, and a temperature control means for controlling the temperature of the fluid supplied from the circulation path to the heat radiation tube. An anti-icing/deicing mechanism for the leading edge of an aircraft main wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4732188U JPH01149894U (en) | 1988-04-08 | 1988-04-08 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4732188U JPH01149894U (en) | 1988-04-08 | 1988-04-08 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH01149894U true JPH01149894U (en) | 1989-10-17 |
Family
ID=31273537
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4732188U Pending JPH01149894U (en) | 1988-04-08 | 1988-04-08 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH01149894U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012029782A1 (en) * | 2010-08-30 | 2012-03-08 | 三菱重工業株式会社 | Aircraft ice protection system and aircraft provided with same |
-
1988
- 1988-04-08 JP JP4732188U patent/JPH01149894U/ja active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012029782A1 (en) * | 2010-08-30 | 2012-03-08 | 三菱重工業株式会社 | Aircraft ice protection system and aircraft provided with same |