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| United States Patent
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7,168,524 |
| Bemis |
January 30, 2007 |
Aircraft fluid drip pan system
Abstract
A system for improved collection and containment of fluids such
as oils that commonly drip from an aircraft during service
maintenance operations and during normal periods of storage. The
system comprises a ground-supported drip pan incorporating a
peripheral cutout adapted to accommodate a landing wheel of the
aircraft to permit effective positioning under the engine. An
embodiment for exterior use utilizing the weight of the aircraft to
prevent movement of the system is also disclosed.
| Inventors: |
Bemis; Christopher L.
(Glendale, AZ) |
| Appl. No.:
|
10/382,753 |
| Filed: |
March 5, 2003 |
| Current U.S.
Class: |
184/106 ;
180/69.1; 220/573; 296/38; 428/137 |
| Current
International Class: |
F16N
31/00 (20060101) |
| Field of
Search: |
184/106 180/69.1
296/38 220/573 428/137 |
References Cited
[Referenced By]
U.S. Patent
Documents
Primary Examiner: Kim; Chong H.
Attorney, Agent or Firm:
Stoneman Law Offices, Ltd. Stoneman; Martin L.
Claims
What is claimed is:
1. A fluid capture system, for collecting the discharge of fluids
from the vicinity of an aircraft landing wheel, comprising in
combination: a) fluid retaining means for retaining the fluids
discharged from the aircraft; b) wherein said fluid retaining means
comprises, i) fluid damming means for containing the fluids within
said fluid retaining means, and ii) contour means for permitting
placement of said fluid retaining means in position below the
aircraft adjacent the landing wheel of the aircraft; c) wherein said
contour means permits the landing wheel to remain outside said fluid
damming means while in position below the aircraft; and d) wherein
the landing wheel is partially surrounded by said fluid damming
means.
2. The system according to claim 1 further comprising: a) movement
restricting means for restricting movement of said fluid capture
system by utilizing the weight of the aircraft; b) wherein said
movement restricting means permits the landing wheel of the aircraft
to be moved over a portion of said fluid capture system.
3. The system according to claim 2 wherein said movement restricting
means is integral to said fluid retaining means.
4. The system according to claim 1 further comprising stiffening
means for stiffening said fluid retaining means against deflection.
5. The system according to claim 1 wherein said fluid retaining
means comprises indicia means for conveying information to a user of
said system.
6. The system according to claim 1 wherein said fluid damming means
comprises pour-assisting means for assisting in pouring and removal
of the fluids collected within said fluid retaining means.
7. The system according to claim 1 wherein said fluid capture system
comprises a fluid impermeable plastic.
8. A fluid capture system, for collecting the discharge of fluids
from the vicinity of an aircraft landing wheel, comprising in
combination: a) at least one fluid retainer structured and arranged
to retain the fluids discharged from the aircraft; b) wherein said
at least one fluid retainer comprises, i) at least one fluid dam
structured and arranged to contain the fluids within said at least
one fluid retainer, and ii) at least one contour structured and
arranged to permit placement of said at least one fluid retainer in
position below the aircraft adjacent the landing wheel of the
aircraft; c) wherein said at least one contour permits the landing
wheel to remain outside said at least one fluid dam while in
position below the aircraft; and d) wherein the landing wheel is
partially surrounded by said at least one fluid dam.
9. The system according to claim 8 further comprising: a) at least
one movement restrictor structured and arranged to restrict movement
of said fluid capture system by utilizing the weight of the
aircraft; b) wherein said at least one movement restrictor is
structured and arranged to permit the landing wheel of the aircraft
to be moved over at least one portion of said fluid capture system.
10. The system according to claim 9 wherein said at least one
movement restrictor is integral to said at least one fluid retainer.
11. The system according to claim 8 further comprising at least one
stiffener structured and arranged to stiffen said at least one fluid
retainer against deflection.
12. The system according to claim 8 wherein said at least one fluid
retainer comprises indicia structured and arranged to convey
information to a user.
13. The system according to claim 8 wherein said at least one fluid
dam comprises at least one pour assister structured and arranged to
assist in pouring and removal of the fluids collected within said at
least one fluid retainer.
14. The system according to claim 8 wherein said fluid capture
system comprises a fluid impermeable plastic.
15. A fluid capture system, for collecting the discharge of fluids
from the vicinity of an aircraft landing wheel, comprising in
combination: a) at least one drip pan to retain the fluids
discharged from the aircraft; b) wherein said at least one drip pan
comprises, i) at least one perimeter rim to contain the fluids
within said at least one drip pan, ii) at least one peripheral wheel
cutout to permit placement of said at least one drip pan in a
position below the aircraft adjacent to the landing wheel of the
aircraft; c) wherein said at least one peripheral wheel cutout
permits the landing wheel to remain outside said at least one
perimeter rim while in position below the aircraft; and d) wherein
the landing wheel is partially surrounded by said at least one
perimeter rim.
16. The system according to claim 15 further comprising: a) at least
one web to restrict movement of said fluid capture system by
utilizing the weight of the aircraft; b) wherein said at least one
web permits the landing wheel of the aircraft to be moved over at
least one portion of said fluid capture system.
17. The system according to claim 16 wherein said at least one web
is integral to said at least one drip pan.
18. The system according to claim 15 further comprising at least one
stiffener rib to stiffen said at least one fluid drip pan against
deflection.
19. The system according to claim 15 wherein said at least one drip
pan comprises indicia to convey information to a user.
20. The system according to claim 15 wherein said at least one
perimeter rim comprises at least one formed spout to assist in
pouring and removal of the fluids collected within said at least one
drip pan.
21. The system according to claim 15 wherein said fluid capture
system comprises fluid impermeable plastic.
Description
CROSS-REFERENCE TO RELATED APPLICATION
The present application is related to Applicant's prior U.S.
Provisional Application No. 60/341,100, filed Nov. 29, 2001,
entitled "AIRCRAFT OIL DRIP PAN", and U.S. Utility application Ser.
No. 10/307,056, filed Nov. 29, 2002, the contents of which are
herein incorporated by reference and are not admitted to be prior
art with respect to the present invention by their mention in this
cross-reference section.
BACKGROUND
This invention relates to providing a system for improved collection
and containment of fluids, such as oils, that commonly drip from an
aircraft during service maintenance operations and during normal
periods of storage.
Typically, aircraft engines as well as other internal combustion
engines employ oil, whether natural or synthetic, and sometimes
other fluids for lubrication and cooling. When the aircraft is
parked in a hangar or tied down on a tarmac, these fluids will
commonly leak from the engine compartment, normally in small
quantities. Even in small amounts, these fluids will collect on the
parking pavement. The pavement surface, usually asphalt, absorbs
these petroleum drippings and is affected by that absorption to the
detriment and degradation of the parking surface and even of the
environment.
In addition, part of the pre-flight inspection of aircraft by the
crew before departure requires that small quantities of fuel be
drained from the tanks and inspected to assure all condensed
moisture is removed, and to confirm that the fuel is the proper
grade and octane for the engines in the aircraft. In the past, this
drained fuel has been discarded by being thrown on the pavement.
This practice is no longer acceptable in these environmentally
conscious times and is now forbidden by most airport management and
environmental authorities, or frequently illegal.
A need has arisen for a means to dispose of or collect these
residues safely and conveniently.
Since the engine compartment is normally above the nose wheel of
single engine aircraft and commonly adjacent the main landing gear
wheels of twin-engine aircraft, drip pans intended for use by
automobiles cannot be used, not having an accommodation for the
wheel.
OBJECTS OF THE INVENTION
A primary object and feature of the present invention is to provide
a system to hold an accumulation of fluids that drip from an
aircraft by the use of a drip pan placed under the engine
compartment.
It is a further object and feature of the present invention to
provide such a system that provides an effective means to dispose of
such accumulations at the convenience of the operator or maintenance
crews.
It is another object and feature of the present invention to provide
such a system that addresses the need for a place of temporary
containment of fuel contaminants.
It is a further object and feature of the present invention to
provide such a system that incorporates a cutout for a landing wheel
of the aircraft within the reservoir area of such drip pan to permit
effective positioning of such a drip pan.
It is another object and feature of the present invention to provide
such a system that has a web that fits under the aircraft wheel,
thus effectively fixing the pan in place to prevent it from being
moved by wind, weather, or theft.
It is a further object and feature of the present invention to
provide such a system that permits convenient pouring of the
collected fluids.
A further primary object and feature of the present invention is to
provide such a system that is efficient, inexpensive, and handy.
Other objects and features of this invention will become apparent
with reference to the following descriptions.
SUMMARY OF THE INVENTION
In accordance with a preferred embodiment hereof, this invention
provides a fluid capture system, for collecting the discharge of
fluids from the vicinity of an aircraft landing wheel, comprising in
combination: fluid retaining means for retaining the fluids
discharged from the aircraft; wherein such fluid retaining means
comprises, fluid damming means for containing the fluids within such
fluid retaining means, and contour means for permitting placement of
such fluid retaining means in position below the aircraft adjacent
the landing wheel of the aircraft; wherein such contour means
permits the landing wheel to remain outside such fluid damming means
while in position below the aircraft; and wherein the landing wheel
is partially surrounded by such fluid damming means.
Moreover, it provides such a system further comprising: movement
restricting means for restricting movement of such fluid capture
system by utilizing the weight of the aircraft; wherein such
movement restricting means permits the landing wheel of the aircraft
to be moved over a portion of such fluid capture system.
Additionally, it provides such a system wherein such movement
restricting means is integral to such fluid retaining means.
Also, it provides such a system further comprising stiffening means
for stiffening such fluid retaining means against deflection. In
addition, it provides such a system wherein such fluid retaining
means comprises indicia means for conveying information to a user of
such system. And, it provides such a system wherein such fluid
damming means comprises pour-assisting means for assisting in
pouring and removal of the fluids collected within such fluid
retaining means. Further, it provides such a system wherein such
fluid capture system comprises a fluid impermeable plastic.
In accordance with another preferred embodiment hereof, this
invention provides a fluid capture system, for collecting the
discharge of fluids from the vicinity of an aircraft landing wheel,
comprising in combination: at least one fluid retainer structured
and arranged to retain the fluids discharged from the aircraft;
wherein such at least one fluid retainer comprises, at least one
fluid dam structured and arranged to contain the fluids within such
at least one fluid retainer, and at least one contour structured and
arranged to permit placement of such at least one fluid retainer in
position below the aircraft adjacent the landing wheel of the
aircraft; wherein such at least one contour permits the landing
wheel to remain outside such at least one fluid dam while in
position below the aircraft; and wherein the landing wheel is
partially surrounded by such at least one fluid dam.
Even further, it provides such a system further comprising: at least
one movement restrictor structured and arranged to restrict movement
of such fluid capture system by utilizing the weight of the
aircraft; wherein such at least one movement restrictor is
structured and arranged to permit the landing wheel of the aircraft
to be moved over at least one portion of such fluid capture system.
Moreover, it provides such a system wherein such at least one
movement restrictor is integral to such at least one fluid retainer.
Additionally, it provides such a system further comprising at least
one stiffener structured and arranged to stiffen such at least one
fluid retainer against deflection. Also, it provides such a system
wherein such at least one fluid retainer comprises indicia
structured and arranged to convey information to a user. In
addition, it provides such a system wherein such at least one fluid
dam comprises at least one pour assister structured and arranged to
assist in pouring and removal of the fluids collected within such at
least one fluid retainer. And, it provides such a system wherein
such fluid capture system comprises a fluid impermeable plastic.
In accordance with another preferred embodiment hereof, this
invention provides a fluid capture system, for collecting the
discharge of fluids from the vicinity of an aircraft landing wheel,
comprising in combination: at least one drip pan to retain the
fluids discharged from the aircraft; wherein such at least one drip
pan comprises, at least one perimeter rim to contain the fluids
within such at least one drip pan, at least one peripheral wheel
cutout to permit placement of such at least one drip pan in a
position below the aircraft adjacent to the landing wheel of the
aircraft; wherein such at least one peripheral wheel cutout permits
the landing wheel to remain outside such at least one perimeter rim
while in position below the aircraft; and wherein the landing wheel
is partially surrounded by such at least one perimeter rim.
Further, it provides such a system further comprising: at least one
web to restrict movement of such fluid capture system by utilizing
the weight of the aircraft; wherein such at least one web permits
the landing wheel of the aircraft to be moved over at least one
portion of such fluid capture system. Even further, it provides such
a system wherein such at least one web is integral to such at least
one drip pan.
Moreover, it provides such a system further comprising at least one
stiffener rib to stiffen such at least one fluid drip pan against
deflection.
Additionally, it provides such a system wherein such at least one
drip pan comprises indicia to convey information to a user.
Also, it provides such a system wherein such at least one perimeter
rim comprises at least one formed spout to assist in pouring and
removal of the fluids collected within such at least one drip pan.
In addition, it provides such a system wherein such fluid capture
system comprises fluid impermeable plastic.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a perspective view of a drip pan system positioned around
the front wheel area of an aircraft according to a preferred
embodiment of the present invention.
FIG. 2 is an isometric view of the drip pan system showing the wheel
cutout, perimeter rim, fluid containment area, and stiffener ribs
according to a preferred embodiment of the present invention.
FIG. 3 is a top view of the top of the drip pan system according to
a preferred embodiment shown in FIG. 2.
FIG. 4 is a front view of the drip pan system according to the
preferred embodiment shown in FIG. 2.
FIG. 5 is a top view of the drip pan system showing the wheel
insert, perimeter rim and stiffener ribs and further showing the web
in the insert area upon which the aircraft wheel rests to secure the
pan from blowing away or being stolen according to another preferred
embodiment of the present invention.
FIG. 6 is a front view of the drip pan system according to the
preferred embodiment shown in FIG. 5.
FIG. 7 is an isometric view of the top of the drip pan system
according to the preferred embodiment shown in FIG. 5.
FIG. 8 is a partial isometric view of a corner pouring spout
configuration according to yet another preferred embodiment of the
present invention.
FIG. 9 is a perspective view of the drip pan system positioned
around an aircraft wheel according to the preferred embodiment shown
in FIG. 2.
FIG. 10 is a perspective view of the drip pan system with the web of
the drip pan system secured by the aircraft wheel.
DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT OF THE INVENTION
Reference is now made to the drawings. FIG. 1 is a perspective view
of drip pan system 100 positioned around the front wheel area 102 of
aircraft 104 according to a preferred embodiment of the present
invention. Because the engine compartments of light aircraft are
typically located above the nose wheel 106 of single engine
aircraft, as shown, and commonly adjacent to the main landing gear
wheels of twin-engine aircraft, conventional drip pans intended for
use by automobiles cannot be used, not having an accommodation for
the wheel. Preferably, drip pan system 100 is adapted to permit
effective positioning under the engine compartment 108 of aircraft
104 by incorporating peripheral wheel cutout 110, as shown in FIG.
2.
FIG. 2 is an isometric view of the drip pan system 100 (embodying
herein fluid retaining means for retaining the fluids discharged
from the aircraft; and also embodying herein at least one fluid
retainer structured and arranged to retain the fluids discharged
from the aircraft) showing peripheral wheel cutout 110 (embodying
herein contour means for permitting placement of such fluid
retaining means in a position below the aircraft adjacent the
landing wheel of the aircraft; and also embodying herein at least
one contour structured and arranged to permit placement of such at
least one fluid retainer in a position below the aircraft adjacent
the landing wheel of the aircraft), perimeter rim 112 (embodying
herein fluid damming means for containing the fluids within such
fluid retaining means; and also embodying herein at least one fluid
dam structured and arranged to contain the fluids within such at
least one fluid retainer), fluid containment area 114 and stiffener
ribs 116 (embodying herein stiffening means for stiffening such
fluid retaining means against deflection; and also embodying herein
at least one stiffener structured and arranged to stiffen such at
least one fluid retainer against deflection) according to the
preferred embodiment of the present invention. In the preferred
embodiment, the drip pan system 100 is pressure or vacuum formed
from sheet plastic, preferably, high-density polyethylene--although,
under appropriate circumstances, drip pan system 100 may be formed
from stamped sheet metal or injected-molded plastic.
FIG. 3 is a top view of the top of drip pan system 100 according to
the preferred embodiment of FIG. 2. Preferably, fluid containment
area 114 comprises an essentially rectangular, planar panel 118
having a perimeter rim 112 and a perimeter edge 120, as shown.
Preferably, perimeter rim 112 extends continuously around planar
panel 118 and between perimeter edge 120 to form a dam-like
structure surrounding fluid containment area 114, as shown.
Peripheral wheel cutout 110 comprises an essentially rectangular
shaped indentation, preferably of a size to accommodate all aircraft
wheels common to light aircraft, and is preferably formed within a
narrow end of drip pan system 100, as shown. Although, under
appropriate circumstances, drip pan system 100 may conform to any
desired size or capacity, drip pan system 100 has a preferred width
of about 25'' and a preferred length of about 45'', as shown.
Preferably, peripheral wheel cutout 110 has a clear inside width of
about 71/2'' and a clear inside length of about 18'', as shown.
Preferably, perimeter rim 112 has a height of about 5/8'' and a
width of between about 1/2'' and 5/8'', from top to bottom.
A plurality of stiffener ribs 116 are preferably molded or stamped
into the surface of planar panel 118 to add strength to drip pan
system 100 by reducing deflection within planar panel 118 under
load.
Also, as shown in FIG. 3, planar panel 118 is sufficiently sized
such that information can be communicated to the user through the
means of indicia 124. Preferably, indicia 124 provides information
about the trade name used to identify the drip pan system. However,
indicia 124 may also provide information to the user concerning the
use and care of the system.
FIG. 4 is a front view of the drip pan system 100 according to the
preferred embodiment of FIG. 2. Perimeter rim 112 preferably
comprises an integrally molded element having an inverted "U"-shaped
sectional profile as indicated within FIG. 4 by dashed lines.
Preferably, perimeter rim 112 is of a height suitable to form a
reservoir of a capacity to hold any predictable volume of fluid
accumulations. The capacity of the preferred embodiment, as shown in
FIG. 2, is about two U.S. gallons.
FIG. 5 is a top view of the drip pan system 100 showing peripheral
wheel cutout 110, perimeter rim 112, fluid containment area 114,
stiffener ribs 116 and further showing web 122 (embodying herein
movement restricting means for restricting movement of such fluid
capture system by utilizing the weight of the aircraft; and also
embodying herein at least one movement restrictor structured and
arranged to restrict movement of such fluid capture system by
utilizing the weight of the aircraft) within peripheral wheel cutout
110 upon which the aircraft wheel rests, to secure drip pan system
100 from blowing away or being stolen according to another preferred
embodiment of the present invention.
FIG. 6 is a front view of the drip pan system 100 according to the
preferred embodiment of FIG. 5.
FIG. 7 is an isometric view of the top of the drip pan system 100,
showing web 122 within peripheral wheel cutout 110, according to the
preferred embodiment of FIG. 5.
FIG. 8 is a partial isometric view of drip pan system 100
illustrating formed spout 126 (embodying herein pour-assisting means
for assisting in pouring and removal of the fluids collected within
such fluid retaining means; also embodying herein at least one pour
assister structured and arranged to assist in pouring and removal of
the fluids collected within such at least one fluid retainer)
according to yet another preferred embodiment of the present
invention. Under appropriate circumstances, it may be preferable to
have in one or more corner(s) 128 of fluid containment area 114,
formed spout 126 integrally molded within perimeter rim 112, as
shown, to facilitate pouring accumulated fluids into a container for
removal without spilling. Preferably, formed spout 126 comprises a
narrowing of the inverted "U"-shaped profile of perimeter rim 112,
as shown.
FIG. 9 is a perspective view of drip pan system 100 positioned
around an aircraft nose wheel 106 according to the preferred
embodiment of FIG. 2. Although drip pan system 100 may be used
inside or outside an enclosed hanger, the embodiment of FIG. 9 is
preferably used indoors where the potential of loss due to wind or
theft is negligible.
FIG. 10 is a perspective view of drip pan system 100 with web 122 of
drip pan system 100 secured by the weight of aircraft nose wheel
106, as shown. The embodiment of FIG. 10 is preferably used exterior
of an enclosed hanger where the potential of loss due to wind or
theft is greater.
Although applicant has described applicant's preferred embodiments
of this invention, it will be understood that the broadest scope of
this invention includes such modifications as diverse shapes and
sizes and materials. Such scope is limited only by the below claims
as read in connection with the above specification.
Further, many other advantages of applicant's invention will be
apparent to those skilled in the art from the above descriptions and
the below claims.
* * * * *
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