Title: Retractable panel interface cable device and method
Abstract: A device and method for mounting and wiring avionic equipment such as modules and display units in an aircraft is provided. The novel configuration utilizes a flexible guide that routes communication lines from a device such as a display unit to other devices such as avionic modules. Because the flexible guide is only allowed motion in substantially a two dimensional plane, the communication lines routed by the flexible guide are held securely in place before, during, and after any access procedure. Damage or failure of communication lines is prevented by the structural support of the flexible guide, while at the same time, the display unit may be easily removed to allow access to devices such as modules located behind.
Patent Number: 7,008,233 Issued on 03/07/2006 to Ruff, et al.
| Inventors:
|
Ruff; Brian F. (Lee's Summit, MO);
Rolston; Walter J. (Overland Park, KS);
Wheaton; Sheldon T. (Olathe, KS)
|
| Assignee:
|
Garmin, Ltd. (George Town, KY)
|
| Appl. No.:
|
086590 |
| Filed:
|
February 28, 2002 |
| Current U.S. Class: |
439/34; 244/118.5 |
| Current Intern'l Class: |
H01R 33/00 (20060101) |
| Field of Search: |
244/1 R,118.5
108/500.2
312/223.6
174/521,48-49,50,59-60
211/26
439/34,595,660
307/101,91
361/600,601,825
|
References Cited [Referenced By]
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| 4815984 | Mar., 1989 | Sugiyama et al.
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| 4830235 | May., 1989 | Miller.
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| 4871134 | Oct., 1989 | Oikawa.
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| 5010642 | Apr., 1991 | Takahashi et al.
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| 5106033 | Apr., 1992 | Phan.
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| 5501605 | Mar., 1996 | Ozaki et al.
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| 5534665 | Jul., 1996 | Long.
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| 5739470 | Apr., 1998 | Takeda.
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| 5800208 | Sep., 1998 | Ishizuka et al.
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| 5885107 | Mar., 1999 | Sluss et al.
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| 5947753 | Sep., 1999 | Chapman et al.
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| 5993247 | Nov., 1999 | Kidd.
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| 6102501 | Aug., 2000 | Chen et al.
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| 6159030 | Dec., 2000 | Gawron et al.
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| 6257897 | Jul., 2001 | Kubota.
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| 6272016 | Aug., 2001 | Matonis et al.
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| 6535397 | Mar., 2003 | Clark et al.
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| 6592387 | Jul., 2003 | Komenda et al.
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| 6654253 | Nov., 2003 | DiMarco.
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| 6695520 | Feb., 2004 | Sarno et al.
| |
| Foreign Patent Documents |
| 2001/-190010 | Oct., 2001 | JP.
| |
Primary Examiner: Dinh; Tien
Attorney, Agent or Firm: Terrell; David L.
Claims
What is claimed is:
1. An avionics instrument mounting system, comprising:
a mounting frame attached to a mounting surface;
an electronic module attached to the mounting frame;
a display unit coupled to the electronic module by at least one communication line;
a flexible guide coupled between the electronic module and the display unit,
wherein the flexible guide limits communication line movement to substantially
a two dimensional plane;
a stop coupled to the mounting frame, the stop limiting the flexible guide to
a depth within the mounting frame; and
a flexible guide frame attached to the mounting frame along a range of mounting
locations with respect to the mounting frame.
2. The avionics instrument mounting system of claim 1, wherein the range of mounting
locations includes a horizontal range of mounting locations.
3. The avionics instrument mounting system of claim 1, wherein the stop is attached
to the flexible guide frame.
4. The avionics instrument mounting system of claim 1, further including an electrical
connector located on an end of the flexible guide and adjacent to the display unit,
the electrical connector being accessible when the display unit is in an unmounted
state and the flexible guide is in an extended state.
5. The avionics instrument mounting system of claim 1, wherein the mounting surface
includes a cockpit instrument panel.
6. The avionics instrument mounting system of claim 1, further including a motherboard
coupled between the electronic module and the flexible guide.
7. A method of mounting an avionics instrument system, comprising:
attaching an electronic module to a mounting surface;
coupling a display unit to the electronic module using at least one communication line;
routing the communication line along a flexible guide coupled between the electronic
module and the display unit, wherein the flexible guide limits communication line
movement to substantially a two dimensional plane;
directly connecting the display unit while the flexible guide is extended; and
retracting the flexible guide to a position where the display unit is to be mounted.
8. The method of claim 7, wherein routing the communication line along the flexible
guide includes routing the communication line along a flexible guide limiting communication
line movement substantially to a vertical two dimensional plane.
9. The method of claim 7, wherein coupling a display unit to the electronic module
includes coupling a flat panel screen to the electronic module.
10. The method of claim 7, wherein routing the communication line along the flexible
guide includes routing along a jointed segmented flexible guide.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
This application is related to the following co-pending, commonly assigned U.S.
patent applications: "Slide-in Connector Plate for Avionic Unit Rack," Ser. No.
10/086,568, "Electronic Equipment Module Mounting Apparatus and Method," Ser. No.
10/086,482, "System and Method for Mounting Units for an Avionic Display," Ser.
No. 10/086,483, "Electronic Equipment Module Apparatus and Method," each of which
the disclosure is herein incorporated by reference in its entirety.
FIELD OF THE INVENTION
The invention relates to mounting devices and methods routing communication lines
between devices. Specifically, this invention relates to mounting devices and methods
of routing communication lines for avionic equipment in an aircraft.
BACKGROUND OF THE INVENTION
In aviation, there is an increasing presence of computerized and electronic equipment
for applications such as instrumentation and navigation. The term avionics refers
generally to electronics in an aviation setting. In aviation, electronic sensors
are used to monitor airspeed, electronic transmitters are used for communications,
and newer applications such as use of global positioning systems (GPS) are being
utilized in aircraft of all sizes.
Pricing of equipment for aircraft is competitive, and not all aircraft require
the same combination of instrumentation options. To lower costs and to increase
the number of end user options, more flexibility in avionic equipment is needed
In response to the need for flexibility, the electronic instrumentation industry
has evolved to a largely modular system. For example, a communication system, a
transponder, and a navigation system are each manufactured in a module. Modules
are individually selected for an aircraft based on cost and need for a particular
application. The modules are also individually replaceable, which allows aftermarket
upgrades, and inexpensive replacement should a single module become damaged.
For convenience, modules are typically mounted near each other in a stack or
similar configuration. In many cases, a frame is first mounted to the aircraft,
and a number of modules are mounted to the frame. In this configuration, communication
lines or wiring are connected directly to each module. In large aircraft, the frame
and modules can be located in a more open space, making installation and maintenance
easier. However, in small aircraft, and even in large aircraft, space is at a premium.
Increasingly, the frame with modules are mounted in less accessible locations to
save space. Reduced access locations for modules are increasing the difficultly
in installation and maintenance.
To reduce the difficulty in replacing individual modules, some frames that the
modules mount to are configured in a mounting system. A typical system includes
a number of slots for the modules to slide into. A back plate is usually located
at the back of the slots, each back plate typically including a number of electrical
sockets such as pin connectors. The modules are installed into the system by sliding
them into the slots, where they make contact with the electrical sockets. In this
way, once the frame, slots and backplates are installed in an aircraft, replacing
individual modules is simply a matter of disengaging any locking mechanism, and
pulling them out along the slots, thereby disengaging the modules from the sockets
on the backplates.
In addition to the basic mechanical mounting of the modules to a surface or an
instrument panel, the modules typically require connection of wiring to transmit
data between the module outputs and user interface displays and controls. Because
an electrical failure during flight places the aircraft and lives of its passengers
at serious risk, extra safety precautions are necessary to protect against electrical
failure. In particular, vibration of aircraft during flight gives rise to a significant
risk to damage or failure of aircraft wiring. Any configuration of wiring used
must design for a level of vibration, and ensure that wiring is well protected
against damage or failure. With this goal in mind, the Federal Aviation Administration
(FAA) has regulations in place that require all wiring to be securely fastened
against vibration.
One current approach to preventing wiring damage has been to utilize numerous
cable ties, as are commonly known in the art, every few inches along a wiring group
or harness to secure wires together. This configuration helps keep wires from rubbing
against each other. In addition, the wires or wire harnesses have been secured
to brackets or fixed structures in the aircraft along their path from one device
to another. Typically this securement is also accomplished with cable ties.
One problem with this approach has been that any re-wiring work required the
cutting of numerous cable ties, and the re-fastening of the cable ties after work
is completed. Even if new wires are not required, certain devices such as avionic
display or control units sometimes need to be removed from their attached surface
for access to other devices that may be located nearby behind, for example, a crowded
cockpit instrument panel. In this case, the associated wiring for the display needs
to be loosened from at least some of its secured locations by cutting cable ties
and re-securing the wires when the display is re-attached.
What is needed is a device for wiring and an associated method that allows easy
access to wiring without the need for cutting and re-installing cable ties. What
is also needed is a device and an associated method that allows easy replacement
of communication lines such as wires. What is also needed is a device and an associated
method that holds wires securely and protects them to prevent damage or failure
of communication lines or a their associated fixtures such as pin connectors or
the like.
SUMMARY OF THE INVENTION
The above mentioned problems with access and repair or replacement of avionic
equipment are addressed by the present invention and will be understood by reading
and studying the following specification. Systems, devices and methods are provided
for mounting various configurations of avionic equipment. The systems, devices,
and methods of the present invention offer easier access to equipment while at
the same time maintaining secure mounting to prevent damage or failure of communication lines.
An avionic wiring system is provided. The wiring system includes a flexible guide
adapted for connection between a first device and a second device, wherein the
flexible guide limits communication line movement to substantially a two dimensional plane.
A method of mounting an avionics instrument system is also provided. The method
includes attaching an electronic module to a mounting surface, and coupling a display
unit to the electronic module using at least one communication line. The method
also includes routing the communication line along a flexible guide coupled between
the electronic module and the display unit, wherein the flexible guide limits communication
line movement to substantially a two dimensional plane.
A method of manufacturing an avionics instrument system is also provided. The
method
of manufacture includes forming an electronic module adapted for attachment to
a mounting surface and forming a display unit. The method further includes coupling
the display unit to the electronic module using at least one communication line.
The method also includes forming a flexible guide and coupling the flexible guide
between the electronic module and the display unit, wherein the flexible guide
limits communication line movement to substantially a two dimensional plane.
These and other embodiments, aspects, advantages, and features of the present
invention will be set forth in part in the description which follows, and in part
will become apparent to those skilled in the art by reference to the following
description of the invention and referenced drawings or by practice of the invention.
The aspects, advantages, and features of the invention are realized and attained
by means of the instrumentalities, procedures, and combinations particularly pointed
out in the appended claims.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 shows a front view of a cockpit instrument panel.
FIG. 2A shows a perspective view of a mounting frame according to the invention.
FIG. 2B shows a top view of an embodiment of a mounting system according to
the invention.
FIG. 3A shows a perspective view of an embodiment of a mounting system according
to the invention.
FIG. 3B shows a side view of a portion of one embodiment of a flexible guide
according to the invention.
FIG. 3C shows a perspective view of multiple components of an embodiment of
a mounting system according to the invention.
FIG. 3D shows a perspective view of another embodiment of multiple components
of a mounting system according to the invention.
FIG. 4 shows a perspective view of an extended embodiment of a mounting system
according to the invention.
FIG. 5 shows a top view of an embodiment of a mounting system according to the invention.
FIG. 6 shows a top view of another embodiment of a mounting system according
to the invention.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
In the following detailed description of the invention, reference is made to
the
accompanying drawings which form a part hereof, and in which is shown, by way of
illustration, specific embodiments in which the invention may be practiced. In
the drawings, like numerals describe substantially similar components throughout
the several views. These embodiments are described in sufficient detail to enable
those skilled in the art to practice the invention. Other embodiments may be utilized
and structural, logical, and electrical changes may be made without departing from
the scope of the present invention.
References to directions, such as up, down, above, or below, etc. will
have their normal meaning with the ground being downward when referring to embodiments
not used in aircraft. When referring to embodiments mounted to an aircraft, downwards
will refer to the direction towards a bottom surface of the airplane, regardless
of the orientation of the airplane during flight. When referring to embodiments
of the invention that are mounted adjacent to a mounting surface, such as an airplane
instrument panel, references to in front of the panel will refer to a side of the
panel that is operator accessible, while behind the panel will refer to the opposite
side of the panel facing away from the operator, or that is normally towards the
nose of the aircraft, and not easily accessible to an aircraft operator.
In the following disclosure, for ease of description, the term wiring will be
used to describe communication lines themselves, or the act of installing communication
lines. One skilled in the art will recognize that wiring includes electrical communication
lines and any of a number of alternative communication lines such as fiber optic lines.
In one embodiment, the following device and method for mounting an avionic instrument
system is used in an aircraft, and is attached to a mounting surface within the
aircraft. Although this setting is used as an example, the mounting system described
can be used in other settings as well without departing from the scope of the invention.
FIG. 1 shows a typical aircraft cockpit
100. A yoke
130 is shown,
attached to an instrument panel surface
102. Also located on the instrument
panel surface
102 is an avionic display
110. In one embodiment, the
avionic display
110 includes a screen
112 and a number of controls
114 that relate to the data being displayed on the screen
112. Other
instrumentation
120 may also be located on the instrument panel surface
102. Following Figures are related to a mounting system that is adapted
for use with electronic modules that provide information to displays such as display
110 shown in FIG. 1.
FIG. 2A shows a mounting frame
200. The mounting frame includes a pair
of first mounting surfaces
202, each with a first plurality of mounting
options
204. The mounting frame
200 also includes a pair of second
mounting surfaces
206, each with a second plurality of mounting options
208. In one embodiment, the first and second plurality of mounting options
204 and
208 include an array of openings adapted to accept screws.
Other fastening devices such as rivets are also contemplated. One skilled in the
art will recognize that slots or holes are alternate options for mounting openings.
While in one embodiment, pairs of mounting surfaces are shown on opposing sides
of the mounting frame
200, it is understood that other configurations of
mounting surfaces are contemplated, such as one mounting surface, more than a pair
of mounting surfaces, or mounting surfaces that are not on opposing sides. Likewise,
the first and second plurality of mounting options
204 and
208 are
only necessary with certain fastener configurations. One skilled in the art will
also recognize that instead of screws, alternate fasteners such adhesives could
also be used without departing from the scope of the invention.
FIG. 2B shows a number of unit frames
210. Each unit frame includes a
back plate
220 that is secured to the unit frame
210 by a fastener
222. The back plate
220 in one embodiment further includes an electrical
connector
224 such as a pin connector. The unit frames
210 are attached
to the second mounting surface
206 of the mounting frame
200. In
one embodiment, the unit frames
210 are attached in a vertical orientation
to provide horizontal flexibility of installation space. Electronic modules
230
are shown as insertable along arrow
231 into the unit frames
210.
Electronic modules may include, but are not limited to examples such as a communication
device, a transponder, or a global positioning system (GPS). In one embodiment,
each unit frame
210 is specifically sized for a corresponding electronic
module
230.
FIG. 3A shows a wiring device
300. The wiring device
300 includes
a guide frame
310 with mounts
314. In one embodiment, each mount
314 includes holes for screws
316, however as discussed above, other
fasteners or attachment methods may be used in place of screws. Also shown is a
flexible guide
350. The flexible guide
350 is adapted to accept a
number of communication lines (not shown) along a central portion
352. In
one embodiment, the flexible guide
350 is fixed to the guide frame
310
at a distal end
356, and the flexible guide is adapted for attachment to
an avionic device at a proximal end
354. Referring to the coordinate axes
305 included in the Figure, the flexible guide
350 is allowed to
flex in both the "y" direction and the "z" direction. The "y" and "z" directions
define a two dimensional plane of movement. In one embodiment, the flexible guide
350 is limited to two dimensional movement. In the embodiment shown in FIG.
3A, the two dimensional plane of movement includes a vertically oriented plane
defined by the "y" and "z" axes. Substantially no movement is allowed in the "x"
direction in this embodiment.
One skilled in the art will recognize that other planes of movement are included
within the scope of the invention. For example, a horizontally oriented plane is
within the scope of the invention. A horizontally oriented plane of movement allows
movement in the "x" and "y" directions, but substantially limits motion in the
"z" direction.
FIG. 3B shows one possible embodiment of a flexible guide
350 that limits
motion to a two dimensional plane. A number of articulated joint segments
352
are included, each segment
352 including a joint
354. The joints
354 allow rotation in a two dimensional plane as shown by arrow
356,
however the joints
354 substantially prohibit motion outside a rotation
plane defined by rotation
356. For illustration, the flexible guide
350
as shown in FIG. 3B, is capable of rotation in the plane of the page, but is substantially
prohibited form motion into or out of the plane of the page. A portion of a number
of communication lines
358 are also shown in the Figure, guided along the
flexible guide
350.
FIG. 3C shows the wiring device
300 attached to a mounting frame
360.
The wiring device
300 is attached to a mounting surface
362 of the
mounting frame
360 using the mounts
314 and associated holes
316
with a plurality of slots
364 on the mounting surface
362. Again,
one skilled in the art will recognize that other types of fasteners or methods
of mounting are included withing the scope of the invention. An "S" configuration
of the flexible guide
350 is shown in FIG. 3C.
Also shown in FIG. 3C is a stop
312 attached to a portion of the guide
frame
310. In one embodiment, the stop
312 is optionally included
to further limit motion of the flexible guide
350 within its associated
two dimensional plane of movement. As shown in the Figure, in one embodiment, the
flexible guide
350 forms an "S" shape. One embodiment uses the stop
312
to limit motion of the "S" shaped flexible guide
350 by configuring the
"S" to contact the stop
312 once a desired rearward amount of motion is
achieved within the plane of movement. Several configurations of stops
312
are possible within the scope of the invention. The only requirement of the stop
312 is that it limit rearward motion of a plane of movement associated with
the flexible guide
350.
FIG. 3D shows another embodiment of the wiring system
300 attached to
a mounting frame
360. The embodiment in FIG. 3D includes a flexible guide
350 that is configured in a "C" shape. One skilled in the art will recognize
that several shapes of the flexible guide
350 are possible and included
within the scope of the invention. The configurations of the "S" shown in FIG.
3C and the "C" shown in FIG. 3D are intended as two examples of possible configurations.
Acceptable configurations of the flexible guide
350 are not so limited within
the scope of the invention.
The preceding FIGS. 3A-3C have shown the flexible guide
350 in a retracted
position within its associated plane of motion. Examples of a flexible guide in
an extended or partially extended state are further shown in other embodiments
detailed in the following Figures.
FIG. 4 shows a guide frame
420 attached to a mounting frame
410.
A flexible guide
450 is shown in a partially extended state. The flexible
guide
450 shown in FIG. 4 is configured in an "S" shape when retracted.
A stop
422 is also included in the embodiment of FIG. 4, the stop
422
being positioned to limit rearward travel of the flexible guide in a retracted
state. Similar to embodiments described above, the flexible guide
450 shown
in FIG. 4 is limited to motion in a two dimensional plane. Coordinate axes
405
indicate that the flexible guide
450 in this embodiment is limited substantially
to a vertically oriented plane of motion in the "y" and "z" axes. As discussed
above, other two dimensional planes are contemplated and the invention is not limited
to vertically oriented planes of motion.
FIG. 5 further shows a display unit
570 in front of an instrument panel
560 and a mounting frame
510 with unit frames
520 located
behind the instrument panel
560. The unit frames
520 are attached
to the mounting frame
510 along a mounting surface
512. Also shown
are a number of communication lines
558 connected between the display unit
570 and the number of unit frames
520. The communication lines
558
are shown guided by a flexible guide
550 between the display unit
570
and a guide frame
540. In one embodiment, the communication lines
558
attach to a backplate
522 using a connector
524 such as a pin connector.
A number of modules
530 are also shown contained by the unit frames
520.
The guide frame
540 in one embodiment includes a guide frame wiring connector
544 located on the guide frame. In one embodiment, communication lines
558
run from the display unit
570, along the flexible guide
550 to the
guide frame wiring connector
544. The communication lines
558 are
then conventionally wired between the guide frame wiring connector
544 and
individual backplates
522. In one embodiment, the communication lines
558
are removably coupled to the display unit
570 by a display unit connector
572. In this configuration, the display unit
570 is easily disconnected
from the flexible guide
550 and the number of communication lines
558
to allow further access to devices obstructed by the display unit
570.
When access to the modules
530 is desired, the display unit
570
is removed from the instrument panel
560. The novel wiring design of the
invention allows the display unit
570 to be removed easily without cutting
any cable ties. The flexible guide
550 extends from a retracted state along
a two dimensional plane as described above. The display unit
570 can therefore
be moved out of the way of the modules
530 to allow access. The modules
can be repaired or replaced, and the display unit
570 is then returned to
place without the need to re-tie any communication lines
558 with cable
ties or similar retention devices.
Additionally, because the flexible guide
550 is only allowed
motion in substantially a two dimensional plane, the communication lines
558
guided by the flexible guide
550 are held securely in place before, during,
and after any access procedure. Damage or failure of communication lines is prevented
by the structural support of the flexible guide
550, while at the same time,
the display unit
570 may be easily removed to allow access to devices such
as modules
530 located behind.
In addition to holding the communication lines
558 securely, the flexible
guide
550 serves as a protective shield that prevents nicking or cutting
of communication lines
558 due to inadvertent contact with any sharp surfaces
that may exist in close proximity to the communication lines
558.
FIG. 6 shows another embodiment of a mounting system according to the invention.
A display unit
670 is shown in front of an instrument panel
660 and
a mounting frame
610 with modules
630 located behind the instrument
panel
660. Also shown are a number of communication lines
658 connected
between the display unit
670 and the modules
630. The communication
lines
658 are shown guided by a flexible guide
650 between the display
unit
670 and a motherboard
620. In one embodiment, the communication
lines
658 attach the motherboard
620 using one of a number of connector
622 such as a pin connector.
CONCLUSION
Thus has been shown a device and method for mounting and wiring avionic equipment
such as modules and display units in an aircraft. The novel configuration utilizes
a flexible guide that routes communication lines from a device such as a display
unit to other devices such as avionic modules. One of the devices, such as a display
unit is removable from one location to another without the need to cut any securing
devices such as cable ties. Access is therefore easily gained to any device that
a connected device is obstructing. In one example, a display unit is removable
from in front of a number of avionic modules that are located behind the display
unit, within an aircraft cockpit instrument panel.
Because the flexible guide is only allowed motion in substantially a two
dimensional plane, the communication lines routed by the flexible guide are held
securely in place before, during, and after any access procedure. Damage or failure
of communication lines is prevented by the structural support of the flexible guide,
while at the same time, the display unit may be easily removed to allow access
to devices such as modules located behind.
Although specific embodiments have been illustrated and described herein,
it will be appreciated by those of ordinary skill in the art that any arrangement
which is calculated to achieve the same purpose may be substituted for the specific
embodiment shown. This application is intended to cover any adaptations or variations
of the present invention. It is to be understood that the above description is
intended to be illustrative, and not restrictive. Combinations of the above embodiments,
and other embodiments will be apparent to those of skill in the art upon reviewing
the above description. The scope of the invention includes any other applications
in which the above structures and fabrication methods are used. The scope of the
invention should be determined with reference to the appended claims, along with
the full scope of equivalents to which such claims are entitled.
*
