WO2022010679A1 - Removable tinted window panels for aircraft cockpit windows - Google Patents
Removable tinted window panels for aircraft cockpit windows Download PDFInfo
- Publication number
- WO2022010679A1 WO2022010679A1 PCT/US2021/039350 US2021039350W WO2022010679A1 WO 2022010679 A1 WO2022010679 A1 WO 2022010679A1 US 2021039350 W US2021039350 W US 2021039350W WO 2022010679 A1 WO2022010679 A1 WO 2022010679A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- panel
- removable
- window
- tinted
- panel assembly
- Prior art date
Links
- 229920000515 polycarbonate Polymers 0.000 claims abstract description 23
- 239000004417 polycarbonate Substances 0.000 claims abstract description 21
- 230000002093 peripheral effect Effects 0.000 claims abstract description 9
- 229920000642 polymer Polymers 0.000 claims description 17
- 239000000463 material Substances 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 5
- 229920001971 elastomer Polymers 0.000 claims description 5
- 229920002943 EPDM rubber Polymers 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 3
- KKEYFWRCBNTPAC-UHFFFAOYSA-L terephthalate(2-) Chemical compound [O-]C(=O)C1=CC=C(C([O-])=O)C=C1 KKEYFWRCBNTPAC-UHFFFAOYSA-L 0.000 claims 1
- 230000004313 glare Effects 0.000 abstract description 16
- 238000003825 pressing Methods 0.000 abstract description 3
- 230000000903 blocking effect Effects 0.000 description 4
- 230000009467 reduction Effects 0.000 description 3
- 239000004425 Makrolon Substances 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 102220565919 Histatin-3_H38P_mutation Human genes 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- -1 acryl Chemical group 0.000 description 1
- NIXOWILDQLNWCW-UHFFFAOYSA-N acrylic acid group Chemical group C(C=C)(=O)O NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 description 1
- 208000003464 asthenopia Diseases 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000001143 conditioned effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 239000004800 polyvinyl chloride Substances 0.000 description 1
- 230000008707 rearrangement Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000003678 scratch resistant effect Effects 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60J—WINDOWS, WINDSCREENS, NON-FIXED ROOFS, DOORS, OR SIMILAR DEVICES FOR VEHICLES; REMOVABLE EXTERNAL PROTECTIVE COVERINGS SPECIALLY ADAPTED FOR VEHICLES
- B60J3/00—Antiglare equipment associated with windows or windscreens; Sun visors for vehicles
- B60J3/02—Antiglare equipment associated with windows or windscreens; Sun visors for vehicles adjustable in position
- B60J3/0286—Sunglare reduction by temporary translucent screens or foils removably attached to window
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60J—WINDOWS, WINDSCREENS, NON-FIXED ROOFS, DOORS, OR SIMILAR DEVICES FOR VEHICLES; REMOVABLE EXTERNAL PROTECTIVE COVERINGS SPECIALLY ADAPTED FOR VEHICLES
- B60J1/00—Windows; Windscreens; Accessories therefor
- B60J1/20—Accessories, e.g. wind deflectors, blinds
- B60J1/2011—Blinds; curtains or screens reducing heat or light intensity
- B60J1/2091—Foldable sunscreens
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/021—Sealings between relatively-stationary surfaces with elastic packing
- F16J15/022—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material
- F16J15/024—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material the packing being locally weakened in order to increase elasticity
- F16J15/027—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material the packing being locally weakened in order to increase elasticity and with a hollow profile
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/061—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with positioning means
Definitions
- the present invention relates generally to aircraft cockpit windows. More specifically, the present invention relates to removable tinted panels for installation in aircraft cockpit windows that reduce glare and heat inside the cockpit
- the present invention provides for a unique cockpit window panel that is easily installed and removed to comply with FAA regulations.
- the panel when installed, reduces glare and heat, and improves overall cockpit environment and pilot comfort.
- the panels allow the pilot to selectively block the sun when needed to remove glare and to remove the discomfort of being exposed to direct sunlight coming from the side windows.
- the panels reduce pilot fatigue, reduce eye strain, and increase pilot performance and comfort.
- the panels generally comprise a clear polycarbonate sheet which has an outer peripheral edge that is contoured to match a substantially similar same shape as the interior enclosure of the aircraft window but is slightly smaller.
- a bonding film is applied to the inner surface of the polycarbonate panel, and a tinted, anti-glare film applied to the bonding film.
- the bonding film acts as an intermediary bridging film between the polycarbonate and the tinted film as the polycarbonate material tends to off-gas when heated and does not interact well with the tinted film.
- the polycarbonate panel is bound by a flexible trim having a U-shaped channel which is frictionally received over the peripheral edge of the panel and a conformable gasket, more preferably a tubular sponge rubber gasket extends from the channel and engages the interior window ledges when the panel is in an installed position.
- a conformable gasket more preferably a tubular sponge rubber gasket extends from the channel and engages the interior window ledges when the panel is in an installed position.
- At least one pull tab is provided along the edge of the panel.
- pull tabs are provided at the bottom and top of the panel for easy removal.
- the key aspect of the window panels is that they are easily installed by simply pressing them into place within the window well, but also easily removable. When the sun is causing too much glare on the instrument panel, or discomfort to the pilot, the panels can be quickly press fit into place and secured by friction through the conformable gasket trim.
- the design and pull tabs also allow a "quick-look" feature which enables the pilot to grasp the top center pull tab and rotate the top half of the panel downwardly without fully removing the panel, allowing a view through the virgin aircraft window as needed. Afterward, the pilot can simply press fit the window panel back into place.
- the exemplary window panels provide a 36% reduction in solar energy in the cockpit, block 80% of light transmission, block 98% of UV transmission and reduce glare by 79%. Testing has revealed that use of the windows panels reduces the interior temperature of the cockpit by at least 10 degrees F as compared to a cockpit without the windows panels.
- Fig. 1 is a plan view of an exemplary embodiment of a removable cockpit window panel in accordance with the teachings of the present invention
- Fig. 2 is a cross-sectional view of the panel taken along line 2-2 of Fig. 1;
- Fig. 3 is an enlarged view of one of the pull tabs
- Fig. 4 is an image of an exemplary window panel installed in the side cockpit window next to the pilot’s station;
- Fig. 5 is another image thereof
- Fig. 6 is an image of the cockpit instrument panel showing significant glare without the present panel installed
- Fig. 7 is another image thereof showing reduced glare and better visibility of the instrument panel with the present panel installed;
- Fig. 8 is a plan view of a second exemplary embodiment of a removable cockpit window panel in accordance with the teachings of the present invention.
- Fig. 9 is a plan view of the second exemplary embodiment of Fig. 8 in a second, folded, configuration.
- the tinted window panel assembly is shown and generally illustrated at 10 in the figures.
- the tinted window panel assembly 10 generally comprises a tinted polymer panel 12 bordered by a conformable gasket trim 5.
- the polymer panel 12 comprises a flexible, clear polycarbonate sheet 2 having an outer peripheral edge that follows the same shape as and interior window well of the aircraft window into which the window panel assembly 10 is meant to be installed but is slightly smaller (See Figs. 4-5).
- Each panel must be custom shaped for a particular aircraft window.
- the panels may be used in any aircraft window such as the side windows or the main viewing windows.
- An exemplary type of polycarbonate sheet suitable for use as the clear polycarbonate sheet 2 is Makrolon® GP polycarbonate having a thickness of 0.062.
- Makrolon® GP® is a general-purpose polycarbonate material that has a polished surface. It is UV stabilized, transparent, has high impact strength, superior dimensional stability, high temperature resistance and high clarity.
- the thickness of the sheet may vary according to the overall size of the window to provide a proper amount of flexibility, i.e. a larger window panel may need to be thicker to provide a suitable level of rigidity/fl exib i 1 ity while a smaller window could potentially require a thinner sheet.
- a polyethelyne teraphthalate (PET) bonding film 3 is applied to the inner surface of the polycarbonate panel 2, and a PET tinted, anti -glare film 4 applied to the bonding film 3.
- PET polyethelyne teraphthalate
- PET bonding film 3 An exemplary type of PET bonding film 3 is Madico® Solution Series Blister Free 2 Mil film which is a clear film specifically for polycarbonate substrates that allows for solar control or decorative films to be applied. Polymeric substrates such as polycarbonate and acrylic absorb moisture on high humidity days and exude that moisture vapor on low humidity days, leading to the blistering of standard film products. Madico’ s Blister Free film offers a proprietary adhesive that is not affected by the absorption and release of this moisture and remains intact.
- An exemplary type of anti-glare film 4 is Madico® Black Pearl NR film having a at least some level of visible light blocking properties. More preferably the film has visible light blocking properties of between about 60% and 95% translating to a Visible Light Transmission (VLT) of between about 45% and 5%. More preferably film has a light blocking of about 75% at a VLT of about 25% and a more preferably the film has light blocking of about 95% at a VLT of about 5%.
- VLT Visible Light Transmission
- the outwardly facing surface of the tinted film is scratch resistant.
- the intermediate bonding film 3 is first applied to the polycarbonate and allowed to cure for 6-10 days, preferably about 7 days, in a curing environment. Thereafter, the tinted film 4 is applied over the bonding film 3 and is allowed to cure for an additional 2-4 days, preferably 3 days, in a curing environment.
- the particular films, and application methods are critical to long term durability of the panel assembly.
- the bonding film 3 acts as an intermediary bridging film between the polycarbonate panel 2 and the tinted film 4 as the polycarbonate material tends to off-gas and form bubbles between itself and a film attached thereto when heated and does not interact well with the PET tinted film 4.
- the polycarbonate panel 2 is bound by a flexible trim 5 having a channel portion 5 A which is frictionally received over the peripheral edge of the panel 12 and a conformable, compressible gasket portion 5B extending from the channel 5A which engages the interior window ledges.
- the channel portion 5 A is a flexible polyvinylchloride (PVC) material (85 Shore A Durometer) and includes an internal aluminum spring clip 5C (Aluminum 3004 H38P) to insure long term spring pressure on the facing walls of the panel 12.
- both the channel 5 A and the spring clip 5C are substantially U-shaped although any shape that is suitable to allow the gasket to be installed and retained on the edge of the panel would be considered to fall within the scope of the disclosure.
- the channel portion 5A may also include an inwardly angled blade gasket 5D on one or both internal walls of the channel.
- the width of the channel 5A is matched to the thickness of the panel 12 to provide a firm secure grip on the sides of the panel 12 without distorting the films 2, 3 when pressed over the peripheral edge.
- the gasket portion 5B is preferably a tubular shaped ethylene propylene diene monomer (EPDM) sponger rubber material which collapses to take on the shape of the window well and allows for differences in manufacturing tolerances from aircraft to aircraft.
- the sponge rubber gasket tightens around the comers of the panel which allows for air flow past the panel to reduce condensation and fogging which may occur during a descent in a humid environment.
- window panels are easily installed by simply pressing them into place within the window interior trim, but also easily removable. (See Figs. 4-5) When the sun is causing too much glare on the instrument panel, or discomfort to the pilot, the panels can be quickly press fit into place and secured by friction through the conformable gasket trim.
- At least one pull tab 6 is provided.
- two pull tabs are positioned toward the opposing bottom sides of the panel and the top middle of the panel for easy grasping and removal.
- Exemplary embodiments of the pull tabs are fabric or plastic strips which extend through slots 1 in the tinted panel.
- the design and pull tabs 6 allow a "quick-look" feature which enables the pilot to grasp the top center pull tab and rotate the top half of the panel downwardly without fully removing the panel, allowing a view through the virgin window as needed. Afterward, the pilot can simply press fit the window panel back into place.
- the outward dimensions of the window panel 12 relative to the size of the intended aircraft window well are slightly larger at the bottom of the panel and are smaller at the top of the panel. This sizing allows the gasket to compress slightly more at the bottom creating a tighter fit to keep the bottom portion of the panel in place when tilting the panel down to see through the virgin cockpit window.
- the exemplary embodiments provide a unique and novel removable cockpit window panel which meets FAA regulations and improves the comfort and environment conditions of the cockpit.
- the exemplary window panels provide a 36% reduction in solar energy in the cockpit, block 65-95% of visible light, block 98% of UV transmission and reduce glare by 79%.
- An exemplary improvement in glare is clearly seen by comparing Figs. 5 (no panel) and 6 (panel installed). Applicant testing reveals that use of the windows panels reduces the interior temperature of the cockpit by at least 10 degrees F as compared without the windows panels.
- the tinted window panel assembly 110 can be sectioned into two, or more, sections, and have at least one hinge disposed between each section.
- the sectioned window panel assembly 110 can be folded into a smaller area for increased portability. These panels can be stored in a folded conditioned in a travel case so that pilots can carry them from plane to plane as they work.
- the alternative window panel assembly 110 is substantially the same as the window panel assembly 10, thus only the sections and hinges shown herein will be discuss for brevity sake.
- the tinted window panel assembly 110 can, in general, have three distinct sections 112a, 112b, and 112c.
- Each of the three sections 112a-c can be of equal or different lengths, depending on the design of the window for which the panel assembly 110 is being used with.
- the sections 112a, 112b can be connected via two hinges 120a, 120b both disposed on a first side of the panel assembly 110 to allow the first panel 112a to rotate up and out of the page, relative to Fig. 8, towards the second panel 112b in a direction Rl.
- the two hinges 120a, 120b can be disposed on a top and bottom of the two sections 112a, 112b.
- a second set of hinges 122a, 122b can be disposed between the second and third panels 112b, 112c on a second side of the panel assembly 110.
- the second set of hinges 122a, 122b can allow the third panel 112c to rotate down and into the page, relative to Fig. 8, towards the second side of the second panel 112b in a direction R2.
- the second set of hinges 122a, 122b can be disposed on a top and bottom of the two sections 112b, 112c.
- hinges 120a, 120b and 122a, 122b are shown between the first and second panels 112a, 112b and the second and third panels 112b, 112c, any number of hinges can be used. Further while the first set of hinges 120a, 120b are shown on a first side of the panel assembly 110 and the second set of hinges 122a, 122b on the opposite side of the panel assembly 110, the two sets of hinges can be disposed on the same side. Further, in some embodiments the hinges 120a, 120b, 122a, 122b can be adhesive hook and loop material that are adhered to the respective surfaces of the panel assembly 110. When the first, second, and third panels 112a-c are folded together, as shown in Fig.
- the hook and loop material can secure the folded panels together such that the panel assembly does not unfold when not in use.
- the hinges can be any known type of hinge, and for example may comprise acryl hinges which are bonded to the panel surfaces.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US16/924,904 US20200339240A1 (en) | 2017-11-24 | 2020-07-09 | Removable tinted window panels for aircraft cockpit windows |
US16/924,904 | 2020-07-09 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2022010679A1 true WO2022010679A1 (en) | 2022-01-13 |
Family
ID=79552714
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2021/039350 WO2022010679A1 (en) | 2020-07-09 | 2021-06-28 | Removable tinted window panels for aircraft cockpit windows |
Country Status (1)
Country | Link |
---|---|
WO (1) | WO2022010679A1 (en) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1963393A (en) * | 1932-06-13 | 1934-06-19 | Woodall Industries Inc | Laminated panel |
US2730777A (en) * | 1951-05-15 | 1956-01-17 | Lockheed Aircraft Corp | Canopy mounting |
US4004388A (en) * | 1974-02-21 | 1977-01-25 | Ppg Industries, Inc. | Window panel edge construction |
GB2400882A (en) * | 2003-04-25 | 2004-10-27 | Joyce Brookes | Push fit window insert panel |
-
2021
- 2021-06-28 WO PCT/US2021/039350 patent/WO2022010679A1/en active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1963393A (en) * | 1932-06-13 | 1934-06-19 | Woodall Industries Inc | Laminated panel |
US2730777A (en) * | 1951-05-15 | 1956-01-17 | Lockheed Aircraft Corp | Canopy mounting |
US4004388A (en) * | 1974-02-21 | 1977-01-25 | Ppg Industries, Inc. | Window panel edge construction |
GB2400882A (en) * | 2003-04-25 | 2004-10-27 | Joyce Brookes | Push fit window insert panel |
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