GB725125A - Improvements in or relating to electrically heated protective coverings - Google Patents

Improvements in or relating to electrically heated protective coverings

Info

Publication number
GB725125A
GB725125A GB31839/53A GB3183953A GB725125A GB 725125 A GB725125 A GB 725125A GB 31839/53 A GB31839/53 A GB 31839/53A GB 3183953 A GB3183953 A GB 3183953A GB 725125 A GB725125 A GB 725125A
Authority
GB
United Kingdom
Prior art keywords
conductors
wires
heaters
sheet
severed
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
Application number
GB31839/53A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Goodrich Corp
Original Assignee
BF Goodrich Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by BF Goodrich Corp filed Critical BF Goodrich Corp
Publication of GB725125A publication Critical patent/GB725125A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12De-icing or preventing icing on exterior surfaces of aircraft by electric heating

Abstract

725,125. Electric heating resistances. GOODRICH CO., B. F. Nov. 17, 1953, [Nov. 26, 1952], No. 31839/53. Class 39 (3). [Also in Group XXII] An electrically heated flexible covering especially for de-icing aeroplanes comprises rectangular or trapezoidal sheets 41-43, 45 of natural or synthetic rubber or neoprene or the like superposed to enclose resistance wires 64 extending in parallel in groups to opposite margins where they are connected to flexible conductors 62, 63 so arranged that the heating elements consist of wires in parallel in groups, and the groups are connected in series to give equal heat in each unit. The resistance wires 64 are placed between woven glass sheets 59, 60 with a rubber sheet 61 and are covered by a woven or knitted textile fabric 44 of cotton, silk or glass fibres and embedded in the covering, which is cemented together and to the aeroplane. Thus a wing is protected by several electric heaters 46-48 insulated from one another, the leading edge section 47 being rectangular and preferably heated more than the outer sections 46, 48 which are tapered. In order to ensure unbroken heating at the meeting surfaces of the sections, the outer edges of the heaters are folded downwards and inwards at 54, 55 as in Figs. 3, 16, the dielectric sheets 42, 43 being of such size as to allow space for the inwardly turned parts with their braided supply conductors 62, 63. To make the heaters, a glass fabric sheet 59 is held by tabs 83 on a rotatable drum 75 and the conductors 62, 63 are laid in pairs on strips 85 of Holland cloth thereon (Fig. 7). The resistance wire 64 is then wound on helically from a spool and soldered to the conductors 62, 63. The wires are severed between each pair of conductors 62, 63 along the line 90. A second layer 60 of glass fabric is cemented over the wires to the glass cloth 59, and the layers 59, 60 are severed also between each pair of conductors 62, 63. The heaters may be of tapered form and are then removed from the drum. The ends of the wires 64 are trimmed, the edge of the top sheet 60 being folded back as a flap 60b (Fig. 14). The lower sheet 59 is cut back as shown and a layer 61 of neoprene is adhered thereto. A woven tape 66 is secured at the lower edge of the layer 61 adjacent a polythene strip 95. The conductors 62, 63 are severed and rendered discontinuous by fillers 96 of neoprene between the severed ends, so that groups of parallel wires 64 are connected in series. The tape 66 is then bent forward to the conductor 63 and the flap 60b of the sheet 60 is folded over and cemented to the conductor 63 and tape 66. The polythene strip 95 is removed and the edge of the heater is folded back over itself as shown in Figs. 3, 16. The heaters are then vulcanized to dielectric sheets 41-43 and 45.
GB31839/53A 1952-11-26 1953-11-17 Improvements in or relating to electrically heated protective coverings Expired GB725125A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US725125XA 1952-11-26 1952-11-26

Publications (1)

Publication Number Publication Date
GB725125A true GB725125A (en) 1955-03-02

Family

ID=22108076

Family Applications (1)

Application Number Title Priority Date Filing Date
GB31839/53A Expired GB725125A (en) 1952-11-26 1953-11-17 Improvements in or relating to electrically heated protective coverings

Country Status (1)

Country Link
GB (1) GB725125A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2853589A (en) * 1953-11-26 1958-09-23 Napier & Son Ltd Electrical de-icing equipment
GB2243412A (en) * 1990-03-30 1991-10-30 United Technologies Corp Aircraft engine propulsor blade deicing
US10184235B2 (en) 2013-05-28 2019-01-22 Falcon Waterfree Technologies, Llc Directional fluid inlet
US10182688B2 (en) 2013-05-28 2019-01-22 Falcon Waterfree Technologies, Llc Splash-reducing and velocity-increasing cartridge exit
US10197430B2 (en) 2014-01-20 2019-02-05 Falcon Waterfree Technologies, Llc Visual indicator
US10273675B2 (en) 2013-04-26 2019-04-30 Falcon Waterfree Technologies, Llc Hybrid trap with water injection

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2853589A (en) * 1953-11-26 1958-09-23 Napier & Son Ltd Electrical de-icing equipment
GB2243412A (en) * 1990-03-30 1991-10-30 United Technologies Corp Aircraft engine propulsor blade deicing
GB2243412B (en) * 1990-03-30 1994-11-23 United Technologies Corp Aircraft engine propulsor blade deicing
US10273675B2 (en) 2013-04-26 2019-04-30 Falcon Waterfree Technologies, Llc Hybrid trap with water injection
US10975560B2 (en) 2013-04-26 2021-04-13 Falcon Water Technologies, LLC Hybrid trap with water injection
US10184235B2 (en) 2013-05-28 2019-01-22 Falcon Waterfree Technologies, Llc Directional fluid inlet
US10182688B2 (en) 2013-05-28 2019-01-22 Falcon Waterfree Technologies, Llc Splash-reducing and velocity-increasing cartridge exit
US10197430B2 (en) 2014-01-20 2019-02-05 Falcon Waterfree Technologies, Llc Visual indicator

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