GB840509A - Improvements relating to aircraft de-icing installations - Google Patents
Improvements relating to aircraft de-icing installationsInfo
- Publication number
- GB840509A GB840509A GB12261/57A GB1226157A GB840509A GB 840509 A GB840509 A GB 840509A GB 12261/57 A GB12261/57 A GB 12261/57A GB 1226157 A GB1226157 A GB 1226157A GB 840509 A GB840509 A GB 840509A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- icing
- lamp
- representation
- relay
- 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
- 238000009434 installation Methods 0.000 title 1
- 238000010438 heat treatment Methods 0.000 abstract 3
- 238000013021 overheating Methods 0.000 abstract 2
- 230000015572 biosynthetic process Effects 0.000 abstract 1
- 230000001351 cycling effect Effects 0.000 abstract 1
- 239000005338 frosted glass 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
- B64D15/20—Means for detecting icing or initiating de-icing
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Resistance Heating (AREA)
Abstract
840,509. Aircraft icing and de-icing indicators. FAIREY CO. Ltd., July 15, 1958 [April 15, 1957], No. 12261/57. Class 4. An aircraft indicator includes a number of tell tale indicators operated automatically by external means sensing the onset of critical climatic conditions leading to icing, and/or sensing ice formation, and a dial bearing a pictorial representation of the aircraft and with several tell tale lamps located in various parts of the representation corresponding to the parts of the aircraft associated with various de-icing circuits to which the lamps are connected, each lamp being lit up as long as its associated de-icing circuit is energized. In Fig. 1, detector 20 is sensitive to ambient temperature and humidity, and when either of these conditions becomes critical, energizes a control system 21 which lights up the appropriate lamp T or H on the face of an indicator 23. When both conditions are critical, indicating impending icing, a further lamp I is lit up, and a signal passes on line 25 to a relay 26, provided a dynamic pressure responsive switch 32 is closed, which is the case when the flight speed is sufficient to prevent overheating of the deicing elements. Relay 26 when actuated operates a set of contactor devices 12 fed from the aircraft three phase power circuit 14 through an integrator device 13, and feeding three phase lines 11 supplying heating mats 10 located in various parts of the aircraft. Overheating of any one mat 10 sends a signal on one line 18 to operate cut-out relays 17 and light a warning lamp O. When the heating circuits are switched on, the integrator 13 operates a relay 33 to light a green lamp P. If a fault develops in one of the mats, the resulting lack of balance in the load transmitted by integrator 13 is arranged to operate relay 33 to switch off lamp P and light a red lamp L. The instrument 23 shown in part cross-section in Fig. 3, comprises a frosted glass or translucent plastic face 41, and an apertured backing plate 43, each aperture containing a lamp 45, and being shaped to conform to one of the areas into which the pictorial representation of the aircraft is divided. Each corresponding area of the actual aircraft has its own de-icing circuit. These areas on the representation are the propellers and spinner 51, 52, cowling 53, engine air intake guide vanes 55, wing leading edges 57, 58, wing main surfaces 60, 61, 62, 63, tail plane and fin leading edges 65, 66, 67, and tail plane and fin surfaces 69, 70, 71. Of these areas, the wing main surfaces 60-63, the propellers, spinner, and cowling 51-53, and the tail plane and fin main surfaces 69-71, are heated cyclically by means of switches 15 in the leads 11 controlled by a cycling motor 16 adjustable by the pilot, so that the heating cycle may be, say, 10 seconds on, 5 seconds off, or 30 seconds on, 15 seconds off. Further, the surfaces 60-63 are heated in successive order during the cycle. The other surfaces are continuously heated during deicing. The apertures in the plate 43 and the connections to the various lamps 45 are such that when any area of the aircraft is being heated, the corresponding area of the representation is illuminated from behind. For example, during de-icing, the four areas 60-63 are illuminated in sequence. In the case of continuously heated areas, the continuous flow of current may be indicated by a "flowing" illuminated chain line. In the instrument front face of Fig. 2 (not shown), the lamps L and P are situated in the centre of the aircraft representation, and the lamps H, T, I and O, one in each of the four quadrants into which the representation divide the instrument face. A switch 29 when closed manually by-passes relay 26, and provides de-icing of the propellers, spinner, cowling, and air intake at will, and a similar switch 30 provides de-icing of the remaining surfaces at will.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB12261/57A GB840509A (en) | 1957-04-15 | 1957-04-15 | Improvements relating to aircraft de-icing installations |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB12261/57A GB840509A (en) | 1957-04-15 | 1957-04-15 | Improvements relating to aircraft de-icing installations |
Publications (1)
Publication Number | Publication Date |
---|---|
GB840509A true GB840509A (en) | 1960-07-06 |
Family
ID=10001314
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB12261/57A Expired GB840509A (en) | 1957-04-15 | 1957-04-15 | Improvements relating to aircraft de-icing installations |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB840509A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1272737B (en) * | 1962-08-09 | 1968-07-11 | Napier & Son Ltd | De-icing device control, especially for helicopter rotors |
US4292502A (en) * | 1979-02-05 | 1981-09-29 | The B.F. Goodrich Company | Helicopter deicer control system |
FR2961898A1 (en) * | 2010-06-25 | 2011-12-30 | Snecma | METHOD FOR DETECTING FAILURE OF MEANS FOR DEFROSTING A PROBE FOR MEASURING A PHYSICAL PARAMETER |
CN110102530A (en) * | 2019-05-08 | 2019-08-09 | 武汉惟景三维科技有限公司 | A kind of pipeline system automatic blade three-dimensional detection system |
CN112373697A (en) * | 2020-10-30 | 2021-02-19 | 哈尔滨飞机工业集团有限责任公司 | Aircraft icing stall warning system and method |
CN113476993A (en) * | 2021-07-12 | 2021-10-08 | 中车大同电力机车有限公司 | Snow-resisting filtering device, snow-resisting method and locomotive |
-
1957
- 1957-04-15 GB GB12261/57A patent/GB840509A/en not_active Expired
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1272737B (en) * | 1962-08-09 | 1968-07-11 | Napier & Son Ltd | De-icing device control, especially for helicopter rotors |
US4292502A (en) * | 1979-02-05 | 1981-09-29 | The B.F. Goodrich Company | Helicopter deicer control system |
FR2961898A1 (en) * | 2010-06-25 | 2011-12-30 | Snecma | METHOD FOR DETECTING FAILURE OF MEANS FOR DEFROSTING A PROBE FOR MEASURING A PHYSICAL PARAMETER |
WO2011161377A3 (en) * | 2010-06-25 | 2012-03-22 | Snecma | Method of detecting a fault with the means for de-icing a probe for measuring a physical parameter |
CN102959360A (en) * | 2010-06-25 | 2013-03-06 | 斯奈克玛 | Method of detecting fault with the means for de-icing probe for measuring physical parameter |
US8994392B2 (en) | 2010-06-25 | 2015-03-31 | Snecma | Method of detecting a fault with the means for de-icing a probe for measuring a physical parameter |
CN102959360B (en) * | 2010-06-25 | 2015-04-01 | 斯奈克玛 | Method of detecting fault with the means for de-icing probe for measuring physical parameter |
CN110102530A (en) * | 2019-05-08 | 2019-08-09 | 武汉惟景三维科技有限公司 | A kind of pipeline system automatic blade three-dimensional detection system |
CN112373697A (en) * | 2020-10-30 | 2021-02-19 | 哈尔滨飞机工业集团有限责任公司 | Aircraft icing stall warning system and method |
CN112373697B (en) * | 2020-10-30 | 2022-11-18 | 哈尔滨飞机工业集团有限责任公司 | Aircraft icing stall warning system and method |
CN113476993A (en) * | 2021-07-12 | 2021-10-08 | 中车大同电力机车有限公司 | Snow-resisting filtering device, snow-resisting method and locomotive |
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