JPS61166800A - Air type deicing device - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an aircraft de-icing device, and in particular to an aircraft de-icing device installed on an aircraft wing used to prevent ice accumulation and to remove and destroy accumulated ice. An improved inflatable deicing device or boot.

[Conventional technology]

Inflatable de-icing devices, pads, or boots for airplanes are made of a resilient material, such as rubber, and are attached to and extend rearwardly from the rim of the airplane wing. This de-icing device has a series of expandable tubes that expand under pressure to break up ice build-up that forms on the surface of the de-icing device. The tube is deflated by removing the pressure medium and drawing a vacuum. The normal operating procedure is continuous cycles of expansion and deflation.

The present invention involves improvements to the construction and operation of conventional de-icing systems in which the present invention recognizes the need to differentiate between the stagnation line and the leading edge of a wing. The stagnation line on an airplane wing is the line along which the air divides into upper and lower parts of the wing, and the leading edge of the wing is the leading edge of the wing. In the case of a symmetrical wing, this leading edge and the stagnation line are the same.

However, in the case of an asymmetrical wing, this stagnation line is either below or above the leading edge of the wing.

[Summary of the invention]

According to the present invention, the inflatable tube of the deicing device is provided above and below this stagnation line, and no inflatable tube is provided in the region adjacent to the stagnation line.

The advantage of this construction is that when the tubes on either side of the stagnation line expand to break up the ice in the non-expanding area around the stagnation line,
This is due to the shell effect that occurs on the ice. The ice that has formed on the leading edge of the wing is then removed by the wind flowing over the wing.

For asymmetrical airfoils with inflatable tubes equipped with de-icing devices located directly above or to the side of the stagnation line in a conventional manner,
The tube pushes the ice head forward before the ice breaks, so
Ice cannot be destroyed. This ice head is held onto the wing by the airflow. For this reason, the advantage of shell-shaped fracture, which is effective not only for asymmetrical wing structures but also for symmetrical wing structures, cannot be obtained.

The method for deicing the wing is to provide inflatable tubes on both sides of the stagnation line, first inflate all the tubes in the first set on one side of the stagnation line, then deflate them, and at the same time This can be improved by repeating the cycle of inflating all the tubes in the two sets. The structure of the de-icing device described above requires minimal energy, yet its de-icing operation is economical and effective.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a de-icing device pad or boot that is attached to the leading edge of a wing.

Such a de-icing pad has an intermediate section along the stagnation line in which there is no inflatable tube, but above and below this intermediate section there are inflatable tubes, either sequentially or simultaneously, for effective wing de-icing. It has two separate parts that expand.

〔Example〕

Corresponding parts are provided with the same reference numerals throughout the drawings. 1 and 2, a de-icing system pad or boot 10 is shown attached to the leading edge of a wing 12 of an airplane 13. The wing 12 is attached to a fuselage 14 of an airplane 13. Although the invention has been described with respect to the wing 12,
It is also applicable to the tail of an airplane.

The de-icing device pad lO shown in FIGS. 2 and 3 is attached to the asymmetrical wing 12 and extends aft from the leading edge 15-15 over the upper and lower surfaces of the wing 12. . The de-icing pad 10 is of laminated construction with an inner layer 16 shown in FIG. 3 and is made of a resilient material such as rubber having a substantially rectangular cross-section, which, like other materials described below, reduces the aerodynamic effects of the wing. It has a taper at the edge so that it can be mounted on the wing 12 without twisting. Instead of this Theba,
The layer may have rectangular sides that fit snugly into recesses on the wing. Such pad 10 and layer 16
It has a stagnation line 17-17 separate from 5-15. The stagnation line is the line along which the air separates above and below the wing, and in the illustrated example is approximately parallel to the leading edge of the wing. layer 1
6 is a woven fabric coated with a suitable rubber composition to prevent air from passing through. The inside of this layer, which forms passages to be described later, is desirably fluffed to facilitate air flow. Such fluff prevents the opposing inner surfaces of the passageways described below from coming into direct contact and being completely occluded when the de-icing pad is deflated, but any remaining air in the passageways will fill the gaps that are drawn in by the vacuum. have. The uniform distribution of fluff ensures that the outer surface of the pad is smooth and regular when the channels are contracted and flattened.

The terms lateral and longitudinal are used herein to indicate the direction of passage within the de-icing band when oriented on the wing of an airplane. The lateral direction refers to the direction parallel to the leading edge or stagnation line of an airplane wing, and the longitudinal direction refers to the direction along a line running perpendicular to the wing's leading edge or stagnation line from the leading edge to the trailing edge of the wing. . A tricot layer 19 in FIG.
5-15 and the central portion of layer 16 along stagnation line 17-17. Layers 16 and 19 are glued along the outer edges to form an integral de-icing device.

Three parallel lateral channels 20.degree. 21.22 are formed by stitching together or suitably gluing layers 16 and 19 along parallel lines with respect to the stagnation line 17-17. Instead of sewing or gluing the layers together to form the passageway, separate tubes may be used. layer 1
The inside of layer 9 may also be fluffed, similar to layer 16, which facilitates the flow of air to ill channels 20, 21, 22.

The portion of the de-icing pad below the stagnation line 17-17 has four parallel lateral passages 25, 2 formed by stitching or gluing the layers 16, 19 along parallel lines.
6.27 and 28.

Instead of forming passageways 25-28 by stitching or gluing, separate inflatable tubes may be used. These stitched lateral passages are sealed and passage 2
0, 21.22 and are pressurized and evacuated by separate manifolds 30.31. As shown in FIG. 2, this manifold is located close to the side edge of the pad. Each manifold 30.31 may have an inner surface with fluff, such as short flexible fibers of uniform thickness, to prevent complete occlusion. Manifold 30.31 and corresponding passages 20-22.25-
In order to inflate 28, appropriate pipes connect them to a source of pressurized air and a source of vacuum.

These passages 20-22 provided above the stagnation line form a first set of passages in the upper region of the pad, while passages 25-2 provided below the stagnation line form the first set of passages in the lower region of the pad. Form a second set. There are no inflatable tubes or passageways in the area of the deicing system directly above and below the stagnation line 17-17. In the example shown in FIGS. 2 and 3, the straight line distance along the de-icing system from the stagnation line to the beginning of aisle 20 is approximately 1/2 inch, while from the stagnation line to the beginning of aisle 20.
The straight line distance to the beginning of 5 is also 1/2 inch.

These dimensions vary depending on the size of the wing.

In a variation of the invention shown in FIG.
is mounted on a symmetrical wing 36 with a stagnation line 3'1-37 coinciding with the leading edge of the wing.

As in the first embodiment, this pad 35 has an inner layer 38 made of an elastic material such as rubber and having a rectangular cross section, and this layer has tapered edges on both sides like the other layers described later. , which facilitates attachment to the leg 36. Instead of a taper, each layer may have a rectangular cross section and be made to fit snugly into a recess provided on the wing.

Such layer 38 is preferably a woven fabric coated with a suitable rubber composition so as to be impermeable to air. A tricot layer 39 covers 38 and is bonded to the wing 36 equidistantly above and below the stagnation line as shown in FIG. Layers 38 and 39 are then glued or sewn together along the upper portion, forming three parallel lateral channels 40 as in the first embodiment.
．． Form 41.42. Separate tubes can also be used to form the three passages.

The deicing pazod section below the stagnation line 37-37 consists of five parallel longitudinal passages 4 formed by sewing or suitably gluing the layers 38, 39 together along parallel lines.
5.46.47.48.49. Instead of sewing or gluing, separate tubes may be used to form the passageway. Passages 40-42, 45-49 are pressurized and evacuated via appropriate manifolds, as in the first embodiment. Passages 40-42 provided above the stagnation lines 37-37 form a first set of passages, and passages 45-49 form a second set of passages. Stagnation line 37
The distances from −37 to the upper and lower passages 40.45 are equal;
There is no inflatable passageway between them. The interior surfaces of layers 38 and 39 are fluffed with uniform short flexible fibers to prevent complete occlusion of the passageway.

The number of passages present above or below the stagnation line on each side can vary, and the numbers used in the described embodiments are merely exemplary to illustrate particular examples.

The operation of the de-icing pad shown in FIG. 4 is substantially the same as that of the first embodiment, and the cycle of expansion and contraction of the passages reduces the stagnation line (including the immediate vicinity of the stagnation line 37-37). Creates an effective shell effect that destroys ice on both sides.

Although the present invention has been described based on specific embodiments, it is clear that the present invention is not limited thereto, and that many F shapes can be made without departing from the spirit of the present invention.

[Brief explanation of drawings]

Figure 1 is a perspective view of a portion of an airplane with pneumatic de-icing installed on the leading edge of the wing; Figure 2 is a plan view of the de-icing boot with the location of the expansion passage indicated by dotted lines; Figure 4 is a cross-sectional view of a portion of a de-icing boot mounted on an asymmetric wing with tubes or passages in an inflated state; FIG. 3 is a cross-sectional view showing a portion of the attached deicing boot. 10... Deicing device or deicing boot 12... Wing 15... Leading edge 16.19... Layer 17... Stagnation line 20-22... Passage 25-28... Passage 3 Area, ゛“31...Margin below the manifold

Claims (1)

[Claims] 1. A de-icing device for preventing ice from accumulating on the leading edge of a wing, which includes a flexible elastic sheet-like protective cover having a pair of side edges and a pair of end edges. the edge is substantially parallel to the leading edge of the wing, the wing has a stagnation line oriented in the same direction as the leading edge, and the cover has a smooth non-inflated portion extending from the stagnation line to both sides. a plurality of lateral passageways are present on either side of the stagnation line and extend from one side edge to the other, the side edges of all passageways being spaced apart from the stagnation line;
The passageways on one side of the stagnation line form a first set of inflatable passageways and the remaining passageways form a second set of inflatable passageways and are operably connected thereto. A deicing device that selectively expands and contracts the first set and the second set of passages by a means that deices the wing using only the passages. 2. When the first set of passages expands, the second set contracts, and then the first set contracts and the second set expands, repeating the cycle. equipment. 3. The apparatus of claim 1, wherein the first and second sets are simultaneously inflated and then simultaneously deflated. 4. The apparatus of claim 1, wherein the first and second sets of passageways are comprised of individual tubes and are inflatably and deflatedly interconnected by a manifold. 5. A pneumatic inflatable wing de-icing pad having a stagnation line, an inwardly facing end and an outwardly facing end, the pad having an intermediate portion having a centerline overlapping the stagnation line and located on the wing; having a pair of separated parts behind the stagnation line when
a pair of trailing edges substantially parallel to the stagnation line, an inner layer attached to the wing and an upper resilient layer overlying the inner layer, each of the aft spaced portions disrupting ice buildup on the pad; A de-icing pad having a plurality of inflatable passageways that repeatedly expand for the purpose of de-icing. 6. A de-icing pad for an airplane wing having a leading edge, an inboard end, and an outboard end, the wing having a stagnation line spaced from and oriented in substantially the same direction as the leading edge; The pad has a centerline that overlaps the stagnation line and has a pair of portions spaced apart from the stagnation line, the portions being aft of the centerline and spaced apart from the stagnation line when positioned on the wing. forming a trailing edge of the wing, said centerline coinciding with a stagnation line of the wing;
The standoff portions constitute upper and lower portions, the pad having an inner layer for attachment to the wing, and an outer resilient layer overlying the inner layer, each standoff portion disrupting ice buildup on the pad. A de-icing pad having a plurality of inflatable passages for repeated expansion, wherein only said spaced portion comprises wing de-icing means. 7. The pad of claim 6, wherein said airfoil is asymmetrical and said stagnation line is spaced below the leading edge of the airfoil. 8. The pad according to claim 7, wherein when the passageway provided in one of the spaced apart parts expands, the passageway provided in the other part contracts. 9. The passageway closest to the stagnation line within the spaced portion is provided equidistant from the stagnation line.
Pads listed in section. 10. The pad of claim 9, wherein the passageway closest to the stagnation line in the isolation portion is at least 1 inch from the stagnation line.