CA1319666C - Pneumatic deicer - Google Patents
Pneumatic deicerInfo
- Publication number
- CA1319666C CA1319666C CA000496683A CA496683A CA1319666C CA 1319666 C CA1319666 C CA 1319666C CA 000496683 A CA000496683 A CA 000496683A CA 496683 A CA496683 A CA 496683A CA 1319666 C CA1319666 C CA 1319666C
- Authority
- CA
- Canada
- Prior art keywords
- airfoil
- passageways
- stagnation line
- pad
- deicer
- 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 - Fee Related
Links
- 238000009825 accumulation Methods 0.000 claims description 9
- 230000001681 protective effect Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 5
- 238000010276 construction Methods 0.000 description 4
- 239000004744 fabric Substances 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 2
- 230000001351 cycling effect Effects 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 239000013305 flexible fiber Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000004753 textile Substances 0.000 description 2
- 239000011800 void material Substances 0.000 description 2
- 230000002452 interceptive effect Effects 0.000 description 1
- 239000012858 resilient material Substances 0.000 description 1
- 230000000979 retarding effect Effects 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 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
- B64D15/166—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means using pneumatic boots
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- External Artificial Organs (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
- Tents Or Canopies (AREA)
Abstract
ABSTRACT
A deicer pad for use on an airfoil wherein the deicer pad is constructed to have an intermediate portion with a leading edge thereon and two spaced apart portions with inflatable passageways thereon. The pad is mounted on the airfoil with the centerline of the pad coincident with the stagnation line of the airfoil. The stagnation line is generally parallel to the leading edge of the airfoil. The passageways in the two spaced apart portions of the deicer are inflatable either simultaneously or in seriatim order and effect the breaking up of the ice over the entire deicer. The inflatable passageways are the sole means for deicing.
A deicer pad for use on an airfoil wherein the deicer pad is constructed to have an intermediate portion with a leading edge thereon and two spaced apart portions with inflatable passageways thereon. The pad is mounted on the airfoil with the centerline of the pad coincident with the stagnation line of the airfoil. The stagnation line is generally parallel to the leading edge of the airfoil. The passageways in the two spaced apart portions of the deicer are inflatable either simultaneously or in seriatim order and effect the breaking up of the ice over the entire deicer. The inflatable passageways are the sole means for deicing.
Description
1~19~6 PNEUMATIC DEICER
BACKGRO~ND OF THE INVENTION
This invention relates to aircraft deicers and more particularly to an improved inflatable deicer or boot adapted for attachment to the airfoil of an aircraft for use in retarding the accumulation of ice or to remove or break up ice accumulation.
Aircraft inflatable deicers, pads or boots are made of resilient material such as rubber and attached to the leading edge of an airfoil and extend rearwardly therefrom. The deicer has a series of inflatable passages or tubes which are distended by inflation pressure to break up ice accumulation which tends to form on the surface of the deicer. The passages or tubes are deflated by releasing the pressure medium and drawing a vacuum thereon. The normal sequence of operation is a continuous cycling of the inflation and deflation process. The present invention is an improvement on the structure and operation of prior deicers wherein the invention recognizes the need to differentiate between the stagnation line and the leading edge of an airfoil. The stagnation line of the wing of an aircraft is the line along which the air separates above and below such line on the wing whereas the leading edge of the wing is the foreward most edge of the wing. In the case of a symmetrical wing, the leading edge and the stagnation line are the same however, in the case of a non-symmetrical or asymmetrical wing, the stagnation line i8 either below or above the leading edge of the wing. The present invention locates the deicer's inflatable tubes above and below the stagnation line while leaving the area immediately adjacent the stagnation line free of inflatable tubes. The advantage of this construction is a clamshell effect which takes place on the ice when the inflatable tubes on each side of the stagnation line inflate causing the ice to break in the non-inflatable area around the stagnation line. The wind stream over the airfoil then removes the ice build-up from the airfoil's leading edge. On some asymmetrical airfoils lG wherein the deicer is constructed in a conventional manner so that the inflatable tubes are also located on or immediately adjacent the stagnation line, the ice is not broken because the inflation tube pushes the ice cap forwardly before it breaks. The ice cap is then held onto the airfoil by the airstream. This in effect does not take advantage of the clamshell type of breaking which is so effective in a symmetrical as well as a non-symmetrical type of airfoil construction. The method of de-icing the airfoil can be improved by use of a deicer as described above, employing inflatable tubes on opposite side of the stagnation line by first inflating all of the tubes, the first set, on one side of the stagnation line and thence deflating such first set of tubes and simultaneously inflating all of the tubes, the second set, on the other side of the stagnation line, and thence repeating this cycle. The above construction of the deicer is particularly economical and effective in its deicing operation while requiring a minimum of power consumption.
SUMMARY OF THE INVENTION
The present invention is directed to a deicer pad or boot that is mounted on the forwardly disposed edge of an airfoil. Such deicer pad has the intermediate portion along the stagnation line devoid of inflatable tubes but two spaced apart portions above and below this intermediate portion which are inflated sequentially or simultaneously to effectively deice the airfoil.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 is a perspective view of a portion of an airplane with a pneumatic deicer mounted upon the leading edge of the wing.
Figure 2 is a plan view of a deicer boot with the position of the inflation passageways being shown in dotted lines.
Figure 3 is a cross-sectional view of a portion of the deicer or deicer boot mounted on an asymmetrical airfoil with the inflation tubes or passageways in distended condition.
Figure 4 is a cross-sectional view of a portion of the deicer or deicer boot mounted on a symmetrical airfoil with all of the inflation tubes or passageways in distended condition.
DETAILED DESCRIPTION
Referring to the drawings wherein like reference numerals designate like or corresponding parts throughout the several views, there is shown in Figures 1 and 2 a deicer boot or pad 10 mounted on the leading edge of a wing 12 of an aircraft 13, only partial shown. The wing 12 is attached to the fuselage 14 of such aircraft 13. Although the invention is described with respect to a wing 12, it is equally applicable to a tail section or an airfoil of an aircraft.
The deicer pad 10, shown in Figures 2 and 3, is mounted on a non-symmetrical wing 12 and extends rearwardly from the leading edge 15-15 over 1319~
a portion of the upper and lower surface portions of the wing 12. The deicer pad 10 is a laminated structure having an inner ply 16 (Figure 3) that is essentially a rectangular section of rubber or other resilient rubber-like material that tapers as the other layers to be described at the respective side edges to facilitate the installation on the wing 12 without interfering with the aerodynamic effects of the wing design. In lieu of tapering the plies, the plies can have rectangular sides that fit snugly into recessed portions on the wing. Such deicer pad 10 and ply 16 have a stagnation line 17-17 spaced from the leading edge 15-15. Such stagnation line is ~he line along which the air separates above and below the wing and in the example shown is generally parallel to the leading edge of the wing. Such ply 16 may be a woven textile fabric which is suitably coated with a suitable rubber compound to make this ply 16 air impervious. The inside of the plies forming the passageways to be described may have a heavy nap to facilitate the flow of air thereabove. Such nap or fibers collectively prevent complete closure and direct contact between opposing internal surfaces of the passageways to be described when the deicer pad is deflated, but have interstices through which residual air in the passageways may be vented or pumped as by a vacuum. By such uniform distribution of nap or fibers, the external surface of the deicer pad is smooth and regular when the passageways are deflated and flattened. The terms spanwise and chordwise are used herein to designate the general direction of the passageways within the deicer pad as orientated on the aircraft's wing.
Spanwise is in a direction generally parallel to the leading edge or the stagnation line of the ~3~66~
aircraft's wing while chordwise is along a line extending transversely from the leading edge or stagnation line of the airfoil to the trailing edge of the airfoil. A ply 19 (Figure 3) of tricot s fabric overlays ply 16 and is adhered to the central portion of such ply 16 including along the leading edge 15-15 and stagnation line 17-17. The plies 16 and 19 are then adhered or bonded along the outer edge portions to form a unitary deicer.
Using the stagnation line 17-17 as a basis, three parallel spanwise passageways 20, 21 and 22 are formed by stitching the plies 16 and 19 together along parallel lines or by suitably bonding such plies along parallel lines to form such passageways. In lieu of stitiching or bonding such plies to form such passageways, separate tubes may be used The inside of ply 19 may be napped as ply 16 to facilitate the flow of air to and from such passageways 20, 21 and 22.
That portion of the deicer pad that lies below the stagnation line 17-17 has four parallel spanwise passageways 25, 26, 27 and 28 formed by stitching the plies 16 and 19 together along parallel lines or by suitably bonding such plies along such parallel lines to form such passageways. In lieu of forming such passageways 25 through 28 by stitching or bonding, separate inflatable tubes may be used. Such stitched spanwise passageways are sealed and together with passageways 20, 21 and 22 are pressurized and evacuated by separate manifolds 30 and 31 respectively. As seen in Figure 2, the manifolds are located closely adjacent the outer extremity of the deicer pad. Each manifold 30 and 31 may be provided with an interior napped surface as with short flexible fibers of uniform thickness to i3~9~
prevent complete closure. To inflate the manifolds 30 and 31 and their corresponding passageways 20 through 22 and 25 through 28 suitable conduits are connected thereto and to a suitable air pressure S source and a suitable vacuum source.
Those passageways 20 through 22 located above the stagnation line 17-17 define a first set of inflatable passageways in the upper deicer portion and those passageways 25 through 28 located below the stagnation line 17-17 define a second set of inflatable passageways in the lower deicer portion. The area of the deicer immediately below and above the stagnation line 17-17 is completely void of inflatable tubes or passageways. In the example shown in Figures 2 and 3, the linear distance along the deicer from the stagnation line to where the first portion of passageway 20 is located is approximately one-half (1/2) inch; while the linear distance along the deicer from the stagnation line to where the first portion of passageway 25 is located is approximately one-half (1/2) inch. These dimensions will vary in accordance with the size of the wing.
A modification o$ the described invention is shown in Figure 4 wherein a deicer pad 35 is shown as mounted on a symmetrical airfoil 36 having a stagnation line 37-37 coincident with leading edge. The deicer pad 35 is a laminated structuee substantially as described in the first embodiment having an inner ply 38 that is essentially a rectangular section of rubber or other resilient rubber-like material that tapers as the other layers to be described at the respective side edges to facilitate the installation on the airfoil 36.
In lieu of tapering the plies, the plies can have rectangular sides that fit snugly into recessed ~3~9~6 portions on the airfoil. Such ply 38 may be a woven textile fabric which is coated with a suitable rubber compound to make such ply air impervious. A ply 39 of tricot fabric overlays ply 38 and is adhered to airfoil 36 above and below the stagnation line an equal distance as shown in Fig.
4. The plies 38 and 39 are then adhered, bonded or stitched along the upper portion forming three parallel spanwise passageways 40, 41 and 42 as in the first embodiment. Separate tubes may be used to form these passageways.
That portion of the deicer pad below the stagnation line 37-37 has five parallel spanwise passageways 45, 46, 47, 48 and 49 formed by stitching the plies 38 and 39 together along parallel lines or by suitably bonding such plies along such parallel lines to form such passageways. In lieu of such stitching or bonding separate tubes may be used to form such passageways. Passageways 40 through 42, and 45 through 49 are pressurized and deflated via suitable manifolds as described in the first embodiment, The passageways 40 through 42 located above the stagnation line 37-37 define the first set of inflatable passageways while passageways 45 through 49 define the second ~et of passageways.
The distance above and below the stagnation line 37-37 to the passageways 40 and 45 are equal and are void of inflatable passageways. The respective inner surfaces of plies 38 and 3g may be napped as with short flexible fibers of uniform thickness to prevent complete closure of the passageways. The number of passageways above or beyond the stagnation line in each example rnay be varied and the number used in the examples above are only illustrative of the invention in a specific example.
1319~
~ he operation of the deicer pad as shown in Figure 4 is substantially similar to the operation as described in the first embodiment with the cycling of the inflation and deflation of the passageways effectively providing a clamshell effect in breaking up the ice on either side of the stagnation line 37-37 including that area to either immediate side of such stagnation line.
It will be apparent that, although a specific embodiment and a modification thereof has been described, the invention is not limited to the specifically illustrated and described constructions since variations may be made without departing from the principles of the invention.
BACKGRO~ND OF THE INVENTION
This invention relates to aircraft deicers and more particularly to an improved inflatable deicer or boot adapted for attachment to the airfoil of an aircraft for use in retarding the accumulation of ice or to remove or break up ice accumulation.
Aircraft inflatable deicers, pads or boots are made of resilient material such as rubber and attached to the leading edge of an airfoil and extend rearwardly therefrom. The deicer has a series of inflatable passages or tubes which are distended by inflation pressure to break up ice accumulation which tends to form on the surface of the deicer. The passages or tubes are deflated by releasing the pressure medium and drawing a vacuum thereon. The normal sequence of operation is a continuous cycling of the inflation and deflation process. The present invention is an improvement on the structure and operation of prior deicers wherein the invention recognizes the need to differentiate between the stagnation line and the leading edge of an airfoil. The stagnation line of the wing of an aircraft is the line along which the air separates above and below such line on the wing whereas the leading edge of the wing is the foreward most edge of the wing. In the case of a symmetrical wing, the leading edge and the stagnation line are the same however, in the case of a non-symmetrical or asymmetrical wing, the stagnation line i8 either below or above the leading edge of the wing. The present invention locates the deicer's inflatable tubes above and below the stagnation line while leaving the area immediately adjacent the stagnation line free of inflatable tubes. The advantage of this construction is a clamshell effect which takes place on the ice when the inflatable tubes on each side of the stagnation line inflate causing the ice to break in the non-inflatable area around the stagnation line. The wind stream over the airfoil then removes the ice build-up from the airfoil's leading edge. On some asymmetrical airfoils lG wherein the deicer is constructed in a conventional manner so that the inflatable tubes are also located on or immediately adjacent the stagnation line, the ice is not broken because the inflation tube pushes the ice cap forwardly before it breaks. The ice cap is then held onto the airfoil by the airstream. This in effect does not take advantage of the clamshell type of breaking which is so effective in a symmetrical as well as a non-symmetrical type of airfoil construction. The method of de-icing the airfoil can be improved by use of a deicer as described above, employing inflatable tubes on opposite side of the stagnation line by first inflating all of the tubes, the first set, on one side of the stagnation line and thence deflating such first set of tubes and simultaneously inflating all of the tubes, the second set, on the other side of the stagnation line, and thence repeating this cycle. The above construction of the deicer is particularly economical and effective in its deicing operation while requiring a minimum of power consumption.
SUMMARY OF THE INVENTION
The present invention is directed to a deicer pad or boot that is mounted on the forwardly disposed edge of an airfoil. Such deicer pad has the intermediate portion along the stagnation line devoid of inflatable tubes but two spaced apart portions above and below this intermediate portion which are inflated sequentially or simultaneously to effectively deice the airfoil.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 is a perspective view of a portion of an airplane with a pneumatic deicer mounted upon the leading edge of the wing.
Figure 2 is a plan view of a deicer boot with the position of the inflation passageways being shown in dotted lines.
Figure 3 is a cross-sectional view of a portion of the deicer or deicer boot mounted on an asymmetrical airfoil with the inflation tubes or passageways in distended condition.
Figure 4 is a cross-sectional view of a portion of the deicer or deicer boot mounted on a symmetrical airfoil with all of the inflation tubes or passageways in distended condition.
DETAILED DESCRIPTION
Referring to the drawings wherein like reference numerals designate like or corresponding parts throughout the several views, there is shown in Figures 1 and 2 a deicer boot or pad 10 mounted on the leading edge of a wing 12 of an aircraft 13, only partial shown. The wing 12 is attached to the fuselage 14 of such aircraft 13. Although the invention is described with respect to a wing 12, it is equally applicable to a tail section or an airfoil of an aircraft.
The deicer pad 10, shown in Figures 2 and 3, is mounted on a non-symmetrical wing 12 and extends rearwardly from the leading edge 15-15 over 1319~
a portion of the upper and lower surface portions of the wing 12. The deicer pad 10 is a laminated structure having an inner ply 16 (Figure 3) that is essentially a rectangular section of rubber or other resilient rubber-like material that tapers as the other layers to be described at the respective side edges to facilitate the installation on the wing 12 without interfering with the aerodynamic effects of the wing design. In lieu of tapering the plies, the plies can have rectangular sides that fit snugly into recessed portions on the wing. Such deicer pad 10 and ply 16 have a stagnation line 17-17 spaced from the leading edge 15-15. Such stagnation line is ~he line along which the air separates above and below the wing and in the example shown is generally parallel to the leading edge of the wing. Such ply 16 may be a woven textile fabric which is suitably coated with a suitable rubber compound to make this ply 16 air impervious. The inside of the plies forming the passageways to be described may have a heavy nap to facilitate the flow of air thereabove. Such nap or fibers collectively prevent complete closure and direct contact between opposing internal surfaces of the passageways to be described when the deicer pad is deflated, but have interstices through which residual air in the passageways may be vented or pumped as by a vacuum. By such uniform distribution of nap or fibers, the external surface of the deicer pad is smooth and regular when the passageways are deflated and flattened. The terms spanwise and chordwise are used herein to designate the general direction of the passageways within the deicer pad as orientated on the aircraft's wing.
Spanwise is in a direction generally parallel to the leading edge or the stagnation line of the ~3~66~
aircraft's wing while chordwise is along a line extending transversely from the leading edge or stagnation line of the airfoil to the trailing edge of the airfoil. A ply 19 (Figure 3) of tricot s fabric overlays ply 16 and is adhered to the central portion of such ply 16 including along the leading edge 15-15 and stagnation line 17-17. The plies 16 and 19 are then adhered or bonded along the outer edge portions to form a unitary deicer.
Using the stagnation line 17-17 as a basis, three parallel spanwise passageways 20, 21 and 22 are formed by stitching the plies 16 and 19 together along parallel lines or by suitably bonding such plies along parallel lines to form such passageways. In lieu of stitiching or bonding such plies to form such passageways, separate tubes may be used The inside of ply 19 may be napped as ply 16 to facilitate the flow of air to and from such passageways 20, 21 and 22.
That portion of the deicer pad that lies below the stagnation line 17-17 has four parallel spanwise passageways 25, 26, 27 and 28 formed by stitching the plies 16 and 19 together along parallel lines or by suitably bonding such plies along such parallel lines to form such passageways. In lieu of forming such passageways 25 through 28 by stitching or bonding, separate inflatable tubes may be used. Such stitched spanwise passageways are sealed and together with passageways 20, 21 and 22 are pressurized and evacuated by separate manifolds 30 and 31 respectively. As seen in Figure 2, the manifolds are located closely adjacent the outer extremity of the deicer pad. Each manifold 30 and 31 may be provided with an interior napped surface as with short flexible fibers of uniform thickness to i3~9~
prevent complete closure. To inflate the manifolds 30 and 31 and their corresponding passageways 20 through 22 and 25 through 28 suitable conduits are connected thereto and to a suitable air pressure S source and a suitable vacuum source.
Those passageways 20 through 22 located above the stagnation line 17-17 define a first set of inflatable passageways in the upper deicer portion and those passageways 25 through 28 located below the stagnation line 17-17 define a second set of inflatable passageways in the lower deicer portion. The area of the deicer immediately below and above the stagnation line 17-17 is completely void of inflatable tubes or passageways. In the example shown in Figures 2 and 3, the linear distance along the deicer from the stagnation line to where the first portion of passageway 20 is located is approximately one-half (1/2) inch; while the linear distance along the deicer from the stagnation line to where the first portion of passageway 25 is located is approximately one-half (1/2) inch. These dimensions will vary in accordance with the size of the wing.
A modification o$ the described invention is shown in Figure 4 wherein a deicer pad 35 is shown as mounted on a symmetrical airfoil 36 having a stagnation line 37-37 coincident with leading edge. The deicer pad 35 is a laminated structuee substantially as described in the first embodiment having an inner ply 38 that is essentially a rectangular section of rubber or other resilient rubber-like material that tapers as the other layers to be described at the respective side edges to facilitate the installation on the airfoil 36.
In lieu of tapering the plies, the plies can have rectangular sides that fit snugly into recessed ~3~9~6 portions on the airfoil. Such ply 38 may be a woven textile fabric which is coated with a suitable rubber compound to make such ply air impervious. A ply 39 of tricot fabric overlays ply 38 and is adhered to airfoil 36 above and below the stagnation line an equal distance as shown in Fig.
4. The plies 38 and 39 are then adhered, bonded or stitched along the upper portion forming three parallel spanwise passageways 40, 41 and 42 as in the first embodiment. Separate tubes may be used to form these passageways.
That portion of the deicer pad below the stagnation line 37-37 has five parallel spanwise passageways 45, 46, 47, 48 and 49 formed by stitching the plies 38 and 39 together along parallel lines or by suitably bonding such plies along such parallel lines to form such passageways. In lieu of such stitching or bonding separate tubes may be used to form such passageways. Passageways 40 through 42, and 45 through 49 are pressurized and deflated via suitable manifolds as described in the first embodiment, The passageways 40 through 42 located above the stagnation line 37-37 define the first set of inflatable passageways while passageways 45 through 49 define the second ~et of passageways.
The distance above and below the stagnation line 37-37 to the passageways 40 and 45 are equal and are void of inflatable passageways. The respective inner surfaces of plies 38 and 3g may be napped as with short flexible fibers of uniform thickness to prevent complete closure of the passageways. The number of passageways above or beyond the stagnation line in each example rnay be varied and the number used in the examples above are only illustrative of the invention in a specific example.
1319~
~ he operation of the deicer pad as shown in Figure 4 is substantially similar to the operation as described in the first embodiment with the cycling of the inflation and deflation of the passageways effectively providing a clamshell effect in breaking up the ice on either side of the stagnation line 37-37 including that area to either immediate side of such stagnation line.
It will be apparent that, although a specific embodiment and a modification thereof has been described, the invention is not limited to the specifically illustrated and described constructions since variations may be made without departing from the principles of the invention.
Claims (10)
1. A deicing apparatus for preventing the accumulation of ice upon the forwardly disposed portion of the leading edge of an airfoil, said apparatus having a flexible resilient sheet-like protective covering including a pair of side edges and a pair of outer edges, said outer edges adapted to be generally parallel to the leading edge of said airfoil, said airfoil having a stagnation line lying in the same direction as said leading edge, said covering having a smooth non-inflatable portion overlying said stagnation line and to either side thereof, a plurality of spanwise passageways in said deicer lying to either side of said stagnation line and extending from adjacent one of said side edges to closely adjacent the other one of said side edges, all of said passageways having side edges spaced from said stagnation line, said passageways lying to one side of said stagnation line defining a first set of inflatable passageways, said remaining passageways defining a second set of inflatable passageways, means operatively connected to said passageways to selectively inflate and deflate said first set and said second set of passageways, and said passageways being the sole means to deice said airfoil.
2. A deicing apparatus for preventing the accumulation of ice upon the forwardly disposed portion of the leading edge portion of an airfoil as set forth in claim 1 wherein said first set of passageways are inflated while said second set of passageways are deflated followed by inflating said second set and deflating said first set.
3. A deicing apparatus for preventing the accumulation of ice upon the forwardly disposed portion of the leading edge portion of an airfoil as set forth in claim 1 wherein said first set of passageways and said second set of passageways are inflated simultaneously and deflated simultaneously.
4. A deicing apparatus for preventing the accumulation of ice upon the forwardly disposed portion of the leading edge portion of an airfoil as set forth in claim 1 wherein said first set and said second set of passageways are individual separate tubes interconnected by manifolds for inflation and deflation thereof.
5. A pneumatic inflatable deicer pad for an airfoil having a stagnation line, an inboard end and an outboard end; said pad having an intermediate portion with a center line overlying said stagnation line; said pad having a pair of spaced apart portions spaced rearward of said stagnation line when positioned on said airfoil;
said pad having a pair of rearwardly disposed edges that are generally parallel to said stagnation line; said deicer pad having an inner ply for attachment to said airfoil and an upper extensible elastic ply overlying said inner ply; each of said rearwardly disposed spaced portion having a plurality of inflatable passageways operative upon successive distensions to break up ice accumulation on said deicer pad, and said passageways being the sole means to deice said airfoil.
said pad having a pair of rearwardly disposed edges that are generally parallel to said stagnation line; said deicer pad having an inner ply for attachment to said airfoil and an upper extensible elastic ply overlying said inner ply; each of said rearwardly disposed spaced portion having a plurality of inflatable passageways operative upon successive distensions to break up ice accumulation on said deicer pad, and said passageways being the sole means to deice said airfoil.
6. A pneumatic deicer pad for an airfoil of an aircraft having a leading edge, an inboard end and an outboard end; said airfoil having a stagnation line spaced from said leading edge and lying in the same general direction as said leading edge; said pad having an intermediate portion with a centerline overlying said stagnation line and also having a pair of spaced apart portions spaced from said stagnation line and located rearward of said centerline when positioned on said airfoil to provide a pair of rearwardly disposed edges; said centerline of said deicer pad coincides with said stagnation line of said airfoil; said spaced apart portions defining an upper portion and a lower portion; said deicer pad having an inner ply for attachment to said airfoil, and an outer extensible elastic ply overlying said inner ply; each of said spaced apart portions having a plurality of inflatable passageways operative upon successive distensions to break up ice accumulation on said deicer pad; and said spaced apart portions containing the sole deicing means for said airfoil.
7. A pneumatic deicer pad for an airfoil as set forth in claim 6 wherein said airfoil is non-symmetrical and said stagnation line is spaced below said leading edge of said airfoil.
8. A pneumatic deicer pad for an airfoil as set forth in claim 7 wherein said passageways in one of said spaced apart portions is inflated while said passageways in the other one of said spaced apart portions are deflated.
9. A pneumatic deicer pad for an airfoil as set forth in claim 8 wherein the passageway in said spaced apart portions that are nearest to said stagnation are equi-distant from said stagnation line.
10. A pneumatic deicer pad for an airfoil as set forth in claim 9 wherein said passageways that are nearest to said stagnation line are at least one inch apart.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US67727384A | 1984-12-03 | 1984-12-03 | |
| US677,273 | 1984-12-03 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1319666C true CA1319666C (en) | 1993-06-29 |
Family
ID=24718038
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000496683A Expired - Fee Related CA1319666C (en) | 1984-12-03 | 1985-12-02 | Pneumatic deicer |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPS61166800A (en) |
| CA (1) | CA1319666C (en) |
| FR (1) | FR2574048B1 (en) |
| GB (1) | GB2167723B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8245981B2 (en) * | 2008-04-30 | 2012-08-21 | General Electric Company | Ice shed reduction for leading edge structures |
| EP2623420A3 (en) * | 2012-01-31 | 2017-04-26 | Goodrich Corporation | Aircraft ice protection system |
| US20170266753A1 (en) * | 2016-03-17 | 2017-09-21 | Goodrich Corporation | Ultrasonic welding process for airfoil de-icer |
| US10780984B2 (en) | 2017-04-20 | 2020-09-22 | Goodrich Corporation | Sewn reinforcement features for prevention of stitch breakage in a pneumatic de-icer |
| US11511868B1 (en) * | 2021-05-28 | 2022-11-29 | Goodrich Corporation | Pneumatic de-icer with reduced non-inflatable area at de-icer edge |
| CA3192955A1 (en) * | 2022-03-30 | 2023-09-30 | Goodrich Corporation | Systems and methods for gas generator for pneumatic deicer |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2438693A (en) * | 1944-03-17 | 1948-03-30 | Goodrich Co B F | Ice removing covering for airfoils |
| US2440240A (en) * | 1944-12-29 | 1948-04-27 | Goodrich Co B F | Protective covering for preventing accumulation of ice on airfoils |
| US2623533A (en) * | 1948-05-29 | 1952-12-30 | Goodrich Co B F | Fluid pressure operated inflation control valve |
| US4361298A (en) * | 1978-03-09 | 1982-11-30 | The B.F. Goodrich Company | Pneumatic deicer |
| US4494715A (en) * | 1983-05-09 | 1985-01-22 | The B. F. Goodrich Company | Deicer |
| US4561613A (en) * | 1983-05-09 | 1985-12-31 | The B. F. Goodrich Company | Deicer for aircraft |
-
1985
- 1985-11-29 GB GB08529472A patent/GB2167723B/en not_active Expired
- 1985-11-29 JP JP26757085A patent/JPS61166800A/en active Granted
- 1985-12-02 FR FR8517784A patent/FR2574048B1/en not_active Expired - Fee Related
- 1985-12-02 CA CA000496683A patent/CA1319666C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0587437B2 (en) | 1993-12-16 |
| GB2167723A (en) | 1986-06-04 |
| GB8529472D0 (en) | 1986-01-08 |
| GB2167723B (en) | 1988-09-21 |
| FR2574048A1 (en) | 1986-06-06 |
| FR2574048B1 (en) | 1992-05-22 |
| JPS61166800A (en) | 1986-07-28 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |