GB877072A - Aircraft de-icer - Google Patents
Aircraft de-icerInfo
- Publication number
- GB877072A GB877072A GB31029/59A GB3102959A GB877072A GB 877072 A GB877072 A GB 877072A GB 31029/59 A GB31029/59 A GB 31029/59A GB 3102959 A GB3102959 A GB 3102959A GB 877072 A GB877072 A GB 877072A
- Authority
- GB
- United Kingdom
- Prior art keywords
- icer
- braid
- rubber
- aircraft
- sept
- 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.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Surface Heating Bodies (AREA)
Abstract
877,072. Electrically heated de-icer for use on aircraft. GOODYEAR TIRE & RUBBER CO. Sept. 11, 1959 [Sept. 26, 1958], No. 31029/59. Class 39(3). An aircraft de-icer for use on aerodynamic surfaces includes an extensible; compressible, flat, braided electrical heating element 2 formed of uninsulated metallic conductors. As shown, the heating element 2, provided with terminals 5, 6, is arranged in serpentine fashion between two dielectric layers 3, 4 of rubber, resin, or fibre glass. If rubber layers are used these penetrate between the strands of the heater to resiliently lock the braid in place. The de-icer may be provided with an erosion resistant surface 7, e.g. of stainless steel, nickel or aluminium, or a plastic or resin. A plurality of heaters in parallel or connected in groups to separate power sources may be used where portions of the de-icer are to be supplied with different power levels or are to be cyclically heated. The watt density in any particular area may be varied by tensioning the braid to reduce its transverse section or by expanding the braid transversely. To prevent the inadvertent alteration of the braid size, the heater may be dipped in a moderate strength adhesive.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US877072XA | 1958-09-26 | 1958-09-26 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB877072A true GB877072A (en) | 1961-09-13 |
Family
ID=22206788
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB31029/59A Expired GB877072A (en) | 1958-09-26 | 1959-09-11 | Aircraft de-icer |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB877072A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2438389A (en) * | 2006-05-23 | 2007-11-28 | Gkn Aerospace Transparency Sys | Heating system for leading edge of aircraft |
| EP3866261A1 (en) * | 2019-05-27 | 2021-08-18 | Airbus Defence and Space GmbH | Method for manufacturing an electronic assembly protected against rough environmental conditions, in particular for aircrafts, electronic assembly and aircraft |
-
1959
- 1959-09-11 GB GB31029/59A patent/GB877072A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2438389A (en) * | 2006-05-23 | 2007-11-28 | Gkn Aerospace Transparency Sys | Heating system for leading edge of aircraft |
| EP3866261A1 (en) * | 2019-05-27 | 2021-08-18 | Airbus Defence and Space GmbH | Method for manufacturing an electronic assembly protected against rough environmental conditions, in particular for aircrafts, electronic assembly and aircraft |
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