# US 2015/0146277 A1 · Aerospace protective dust cover > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2015/0146277 A1 - Document ID: US20150146277A1 - Status: Published application - Kind: A1 - Application number: 14/551,618 - Filed: 2014-11-24 - Published: 2015-05-28 - Earliest claimed: 2013-11-25 - Assignees: Gentex Corporation - Applicants: Gentex Corporation - Inventors: Kevin L. Ash - Web page: https://patentgrep.com/patent/US20150146277A1 ## CPC - B64C 1/1492: {Structure and mounting of the transparent elements in the window or windscreen} - G02B 27/0006: {with means to keep optical surfaces clean, e.g. by preventing or removing dirt, stains, contamination, condensation (G02B1/18 takes precedence; cleaning in general B08B)} - B64C: AEROPLANES; HELICOPTERS - G02B: OPTICAL ELEMENTS, SYSTEMS OR APPARATUS ## Abstract An aircraft window assembly includes a pressure pane. A bezel is proximate a periphery of the pressure pane and defines an inner opening. The bezel includes an inner wall with a channel. An electro-optic element is disposed in the inner opening and is configured for reception in the channel of the inner wall. The electro-optic element is capable of operation between a transmissive condition and a dimmed condition. A dust cover is proximate the bezel. The dust cover includes an interior substrate and an exterior substrate. The interior substrate and the exterior substrate generally define a gap therebetween. A thermally absorbent liquid is disposed in the gap. ## Claims ### Claim 1 An aircraft window assembly comprising: a pressure pane; a bezel proximate a periphery of the pressure pane and defining an inner opening, the bezel including an inner wall with a channel; an electro-optic element disposed in the inner opening and configured for reception in the channel of the inner wall, the electro-optic element being capable of operation between a transmissive condition and a dimmed condition; a dust cover proximate the bezel, the dust cover including an interior substrate and an exterior substrate, wherein the interior substrate and the exterior substrate generally define a gap therebetween; and a thermally absorbent liquid disposed in the gap. ### Claim 2 (depends on 1) The aircraft window assembly of claim 1, wherein the liquid is gelled. ### Claim 3 (depends on 1) The aircraft window assembly of claim 1, wherein the interior substrate is spaced a distance of approximately 14 mm to 45 mm from the exterior substrate. ### Claim 4 (depends on 1) The aircraft window assembly of claim 1, wherein the thermally absorbent liquid includes water. ### Claim 5 (depends on 1) The aircraft window assembly of claim 1, wherein the electro-optic element includes an electro-optic member. ### Claim 6 An aircraft window assembly comprising: a pressure pane in abutting contact with an inner surface of an exterior pressure pane frame, the pressure pane including an interior surface and an exterior surface, wherein the interior surface includes an electrophoretic deposition; a bezel proximate a periphery of the pressure pane and defining an inner opening, the bezel including an inner wall with a channel; an electro-optic element disposed in the inner opening and configured for reception in the channel of the inner wall, the electro-optic element being capable of operation between a transmissive condition and a dimmed condition; and a dust cover proximate the bezel, the dust cover including an interior substrate and an exterior substrate. ### Claim 7 (depends on 6) The aircraft window assembly of claim 6, further comprising: a thermally absorbent material disposed between the interior substrate and the exterior substrate. ### Claim 8 (depends on 7) The aircraft window assembly of claim 7, wherein the thermally absorbent material is liquid. ### Claim 9 (depends on 8) The aircraft window assembly of claim 8, wherein the liquid is gelled. ### Claim 10 (depends on 6) The aircraft window assembly of claim 6, wherein the interior substrate is spaced a distance of approximately 14 mm to 45 mm from the exterior substrate. ### Claim 11 (depends on 7) The aircraft window assembly of claim 7, wherein the thermally absorbent material is water. ### Claim 12 (depends on 6) The aircraft window assembly of claim 6, wherein the electro-optic element includes an electro-optic member. ### Claim 13 An aircraft window assembly comprising: a pressure pane in abutting contact with an inner surface of an exterior pressure pane frame; a bezel proximate a periphery of the pressure pane and defining an inner opening, the bezel including an inner wall with a channel; an electro-optic element disposed in the inner opening and configured for reception in the channel of the inner wall; and a dust cover proximate the bezel, the dust cover including an interior substrate and an exterior substrate. ### Claim 14 (depends on 13) The aircraft window assembly of claim 13, further comprising: a thermally absorbent material disposed between the interior substrate and the exterior substrate. ### Claim 15 (depends on 14) The aircraft window assembly of claim 14, wherein the thermally absorbent material is liquid. ### Claim 16 (depends on 15) The aircraft window assembly of claim 15, wherein the liquid is gelled. ### Claim 17 (depends on 13) The aircraft window assembly of claim 13, wherein the interior substrate is spaced a distance of approximately 14 mm to 45 mm from the exterior substrate. ### Claim 18 (depends on 14) The aircraft window assembly of claim 14, wherein the thermally absorbent material is water. ### Claim 19 (depends on 13) The aircraft window assembly of claim 13, wherein the electro-optic element includes an electro-optic member.