Pneumatic de-icer with reduced non-inflatable area at de-icer edge

Patent metadata

Field	Value
Publication number	US-2022380056-A1
Application number	US-202117333227-A
Country	US
Kind code	A1
Filing date	May 28, 2021
Priority date	May 28, 2021
Publication date	Dec 1, 2022
Grant date	—

Abstract

A de-icer is provided and includes first and second structural layers that each include centerline and a non-inflatable edge angled with respect to the centerline, edge sealing material disposed to adhere the first and second structural layers together to form a non-inflatable edge area extending along at least the non-inflatable edge and surrounding a central area and stitching. The stitching is disposed to stitch the first and second structural layers together in the central area to form tubes. The tubes include an outermost tube which is closest to and parallel with the non-inflatable edge.

First claim

What is claimed is:

1 . A de-icer, comprising:
first and second structural layers each comprising a centerline and a non-inflatable edge angled with respect to the centerline; edge sealing material disposed to adhere the first and second structural layers together to form a non-inflatable edge area extending along at least the non-inflatable edge and surrounding a central area; and stitching disposed to stitch the first and second structural layers together in the central area to form tubes comprising an outermost tube which is closest to and parallel with the non-inflatable edge.

2 . The de-icer according to claim 1 , wherein the first and second structural layers each have a trapezoidal shape with the non-inflatable edge and an additional non-inflatable edge on opposite sides of the centerline.

3 . The de-icer according to claim 2 , wherein the tubes comprise:
multiple central tubes which are parallel with the centerline; the outermost tube; and an additional outermost tube which is closest to and parallel with the additional non-inflatable edge.

4 . The de-icer according to claim 1 , wherein the stitching has a same pattern for each of the tubes and the outermost tube.

5 . The de-icer according to claim 1 , wherein the non-inflatable edge area is about ˜0.5 to about ˜0.9375 inches (˜1.27 to about ˜2.38125 cm) wide.

6 . The de-icer according to claim 1 , wherein the non-inflatable edge area is about ˜0.75 to about ˜0.875 inches (˜1.905 to about ˜2.2225 cm) wide.

7 . The de-icer according to claim 1 , wherein the outermost tube is narrower than at least one of the other tubes.

8 . An aircraft, comprising:
an aerodynamic surface; and a de-icer according to claim 1 operably disposed on the aerodynamic surface.

9 . The aircraft according to claim 8 , wherein the de-icer remains adhered to the aerodynamic surface during inflation and deflation of the tubes.

10 . A de-icer, comprising:
first and second structural layers, each comprising wide and narrow ends, a centerline extending between the wide and narrow ends and a non-inflatable edge which extends between the wide and narrow ends and is angled with respect to the centerline; edge sealing material disposed to adhere the first and second structural layers together to form a non-inflatable edge area extending along at least the non-inflatable edge and surrounding a central area; and stitching disposed to stitch the first and second structural layers together in the central area to form tubes, the tubes being inflatable and de-inflatable for de-icing operations and comprising an outermost tube which is closest to and parallel with the non-inflatable edge.

11 . The de-icer according to claim 10 , wherein the first and second structural layers each have a trapezoidal shape with the non-inflatable edge and an additional non-inflatable edge on opposite sides of the centerline.

12 . The de-icer according to claim 11 , wherein the tubes comprise:
multiple central tubes which are parallel with the centerline; the outermost tube; and an additional outermost tube which is closest to and parallel with the additional non-inflatable edge.

13 . The de-icer according to claim 11 , wherein the non-inflatable edge area extends along the wide and narrow ends, the non-inflatable edge and the additional non-inflatable edge.

14 . The de-icer according to claim 10 , wherein the stitching has a same pattern for each of the tubes and the outermost tube.

15 . The de-icer according to claim 10 , wherein the non-inflatable edge area is about ˜0.5 to about ˜0.9375 inches (˜1.27 to about ˜2.38125 cm) wide.

16 . The de-icer according to claim 10 , wherein the non-inflatable edge area is about ˜0.75 to about ˜0.875 inches (˜1.905 to about ˜2.2225 cm) wide.

17 . The de-icer according to claim 10 , wherein the outermost tube is narrower than at least one of the other tubes.

18 . An aircraft, comprising:
an aerodynamic surface; and a de-icer according to claim 1 operably disposed on the aerodynamic surface.

19 . The aircraft according to claim 18 , wherein the de-icer remains adhered to the aerodynamic surface during inflation and deflation of the tubes.

20 . A method of assembling a de-icer, the method comprising:
forming first and second structural layers to each comprise a centerline and a non-inflatable edge angled with respect to the centerline; adhering the first and second structural layers together to form a non-inflatable edge area extending along at least the non-inflatable edge and surrounding a central area; and stitching the first and second structural layers together in the central area to form tubes comprising an outermost tube which is closest to and parallel with the non-inflatable edge.

Assignees

• Goodrich Corp

Inventors

• Fahrner Alan J

Classifications

• B64D15/166 Primary

  using pneumatic boots · CPC title