GB540711A - Improvements in and relating to de-icing apparatus for aeroplanes - Google Patents
Improvements in and relating to de-icing apparatus for aeroplanesInfo
- Publication number
- GB540711A GB540711A GB16118/40A GB1611840A GB540711A GB 540711 A GB540711 A GB 540711A GB 16118/40 A GB16118/40 A GB 16118/40A GB 1611840 A GB1611840 A GB 1611840A GB 540711 A GB540711 A GB 540711A
- Authority
- GB
- United Kingdom
- Prior art keywords
- discs
- ice
- fuselage
- rotated
- formation
- 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
- 230000015572 biosynthetic process Effects 0.000 abstract 2
- 239000004927 clay Substances 0.000 abstract 1
- 239000002245 particle Substances 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Materials Applied To Surfaces To Minimize Adherence Of Mist Or Water (AREA)
Abstract
540,711. De-icing aircraft. CLAY, W. C. Nov. 5, 1940, No. 16118. [Classes 4 and 114] To prevent the formation of ice on exposed aircraft surfaces a flexible radially expansible shield' comprising one or more discs is mounted in front of the surface and rotated so that moisture or ice particles are dislodged and thrown off by centrifugal force before they reach the surface to be protected. A screw propeller is shown in which two rubber discs 10,13, having normally closed radial slits dividing' them into separately extensible segments, are clamped on a spindle at the front of the spinner and rotate with it. The centres of the discs are thickened to form plano-convex surfaces, the convex surfaces of the two discs being juxtaposed. A single disc rotated by an electromotor at the front of a fuselage also is described. When ice formation is unlikely, the motor is stopped and the disc is caused to lie against the fuselage surface by wind pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB16118/40A GB540711A (en) | 1940-11-05 | 1940-11-05 | Improvements in and relating to de-icing apparatus for aeroplanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB16118/40A GB540711A (en) | 1940-11-05 | 1940-11-05 | Improvements in and relating to de-icing apparatus for aeroplanes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB540711A true GB540711A (en) | 1941-10-27 |
Family
ID=10071495
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB16118/40A Expired GB540711A (en) | 1940-11-05 | 1940-11-05 | Improvements in and relating to de-icing apparatus for aeroplanes |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB540711A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2116929A (en) * | 1982-03-24 | 1983-10-05 | Secr Defence | Ice prevention devices |
| FR2943726A1 (en) * | 2009-03-31 | 2010-10-01 | Snecma | ROTATING INPUT COVER FOR TURBOMACHINE, COMPRISING AN EXTREMITY BEFORE EXCENTREE |
-
1940
- 1940-11-05 GB GB16118/40A patent/GB540711A/en not_active Expired
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2116929A (en) * | 1982-03-24 | 1983-10-05 | Secr Defence | Ice prevention devices |
| FR2943726A1 (en) * | 2009-03-31 | 2010-10-01 | Snecma | ROTATING INPUT COVER FOR TURBOMACHINE, COMPRISING AN EXTREMITY BEFORE EXCENTREE |
| WO2010112453A1 (en) * | 2009-03-31 | 2010-10-07 | Snecma | Rotating inlet cowl for a turbine engine, including an eccentric front end |
| RU2529766C2 (en) * | 2009-03-31 | 2014-09-27 | Снекма | Rotary inlet cowl for turbomachine with eccentrically arranged tail |
| US8984855B2 (en) | 2009-03-31 | 2015-03-24 | Snecma | Rotating inlet cowl for a turbine engine, comprising an eccentric forward end |
| US9243562B1 (en) | 2009-03-31 | 2016-01-26 | Snecma | Rotating inlet cowl for a turbine engine, comprising an eccentric forward end |
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