U.S. patent application number 12/912501 was filed with the patent office on 2012-05-03 for gimbaled mount system for satellites.
Invention is credited to Calvin H. Woosnam.
Application Number | 20120105289 12/912501 |
Document ID | / |
Family ID | 39644067 |
Filed Date | 2012-05-03 |
United States Patent
Application |
20120105289 |
Kind Code |
A1 |
Woosnam; Calvin H. |
May 3, 2012 |
GIMBALED MOUNT SYSTEM FOR SATELLITES
Abstract
Described herein is a method and system for gimbaled mounting of
satellite dishes. The gimbaled mount for satellite systems
overcomes some of the most common negative events affecting
satellite communications. The system is a cost effective solution
that amortizes the cost of the additional equipment to well over
the customary three to five years for satellite use and extends its
working life expectancy to 20 years or more. Utilization of
stainless steel rather than normal steel or lighter duty aluminum
further extends the mounting systems longevity. The inclusion of an
environmental feedback system for both snow and ice damage, wind
damage, and earthquake damage increases the projected useful life
of the mounting system.
Inventors: |
Woosnam; Calvin H.;
(Coquitlam, CA) |
Family ID: |
39644067 |
Appl. No.: |
12/912501 |
Filed: |
October 26, 2010 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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12020269 |
Jan 25, 2008 |
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12912501 |
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60886905 |
Jan 26, 2007 |
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Current U.S.
Class: |
343/704 ;
248/295.11; 248/636; 267/136 |
Current CPC
Class: |
H01Q 1/125 20130101;
H05K 7/2039 20130101; H04H 20/02 20130101; H01B 11/22 20130101;
H04B 7/1851 20130101; H04H 20/59 20130101; H04W 28/04 20130101;
H05K 7/1015 20130101; H01B 7/17 20130101; G08B 13/19636 20130101;
F16F 15/121 20130101; H01Q 1/005 20130101; G08B 13/1966 20130101;
H04H 20/61 20130101; H04B 1/38 20130101; F16M 13/022 20130101; H04H
40/90 20130101 |
Class at
Publication: |
343/704 ;
248/295.11; 248/636; 267/136 |
International
Class: |
H01Q 1/12 20060101
H01Q001/12; H01Q 1/02 20060101 H01Q001/02; F16M 13/00 20060101
F16M013/00 |
Claims
1. A gimbaled mount system for satellites, the system comprising:
environmentally exposed components, which are made of heavy gauge
marine grade stainless steel; and four legs with screw adjustable
feet.
2. The system according to claim 1, wherein: the heavy gauge
stainless steel is at least 0.025 inches thick.
3. The system according to claim 1, further comprising: a system of
non-motorized wind damping.
4. The system according to claim 1, further comprising: a system of
motorized wind damping.
5. The system according to claim 4, further comprising: an electric
stepper motor, mounted on a slide on sleeve and a bracket assembly
on one of four legs, wherein the stepper motor is connected by a
common control cable assembly that is shared by an aerometer unit
and is routed back to a controller, wherein the aerometer unit is
electrically connected by a common control cable along with the
stepper motor assembly back to the controller, and together the
stepper motor and aerometer provide an electric automatic wind
dampening system.
6. The system according to claim 5, further comprising: aerometer
cups, wherein an action of wind turning the aerometer cups causes a
signal voltage relative to current wind speed to be fed back to the
controller for controlling the stepper motor.
7. The system according to claim 1, further comprising: a system of
non-motorized wind damping; and a system of motorized wind
damping.
8. A method of non-motorized wind damping on a gimbaled mount
system for satellites, the method comprising: rotating of a
dampening spool to cause all tension springs to be equally tension
loaded.
9. A gimbaled mounting system for satellites, the system
comprising: a satellite dish; a low noise amplifier module; pivot
points; a thermal heating cord along the backside of the satellite
dish, along an underside of the low noise amplifier module, and
along crucial pivot points of the gimbaled mounting system; and a
thermostat set which regulates the thermal heating cord.
Description
CROSS-REFERENCES TO RELATED APPLICATIONS
[0001] This application is a Continuation of U.S. application Ser.
No. 12/020,269, filed Jan. 25, 2008, which claims priority of U.S.
Provisional Patent Application No. 60/886,905, filed Jan. 26, 2007,
all of which are incorporated by reference in their entirety.
FIELD OF THE INVENTION
[0002] The present invention was designed as primary component
within a larger communications system. This proposed communications
component addresses the need for a more robust connection between
devices that may be relied on during an emergency or security event
and cannot be allowed to fail while facilitating security and
normal communications services during normal times. The nature of
this design allows for variation in capacity and size within tight
design constraints that insure compliance with the engineering
principles that insure performance during a stressful situation
whether the actions are thermal or mechanical in nature.
[0003] More particularly, the present invention addresses the need
for a reliable weather resistant mounting system for
satellites.
BACKGROUND OF THE INVENTION
[0004] Satellite communications in the past required precision
alignment of the dish system, to comply with an aperture of 1.5 to
2.0 degrees maximum movement to be still adequately in the download
or upload beam to permit proper data or signal transfer. This
critical alignment can easily be thrown out of alignment during an
earthquake, building or ground settling condition, or severe
weather wind type calamity.
[0005] Satellite communications systems, once they are aligned, are
considered to be more robust than terrestrial communications lines,
especially when those lines are subject to events such as an
earthquake, flood, or high wind condition.
[0006] Typically satellite systems are put into operation some time
during their life span, typically 15 years for a specific
satellite. Any corrective positioning, which has occurred on
several satellites in orbit currently and in the past, requires
direct technical support and re-alignment of the earth station
equipment to take into account the positional movement.
[0007] Weather conditions are notorious for knocking out satellite
earth stations and the smaller lower cost ones are very susceptible
to weather outages. Larger network type earth stations usually or
robust enough both in diameter and construction materials to
withstand numerous weather events during their planned life span
without causing unpreventable weather outages. Excluding rain fade
which can only be addressed by larger dishes makes the smaller the
dish more susceptible to snow and ice.
[0008] Typical wind loading on a dish, and more so on the larger
the dish, can throw alignment, temporarily or permanently until a
technician can re-align the earth station dish assembly. In view of
extensive experience with conventional earth stations, it is
believed that conventional earth stations lack any self
compensating mechanism, except for those conventional stations that
are fully motorized. Furthermore the awareness or call out for
re-alignment of earth stations has been more than the norm in the
past, especially on small aperture dishes such as a Very Small
Aperture Terminal (VSAT), which is a two-way satellite ground
station with a dish antenna that is smaller than 3 meters.
Especially after a storm or serious snow fall, VSAT re-alignment
may be needed.
[0009] Construction of most earth stations is made out of standard
steel components with at the most only the primary bolts being made
of stainless steel. This leads to much needed maintenance and
painting needing to be the VSAT to be down to maintain the
appearance, to reduce corrosion, and to maintain functionality of
the typical earth station.
[0010] Snow and ice can be detrimental to proper earth station
operation. At times, on larger systems, crews may even have to go
out and sweep off the snow to stop its affect on the large dishes.
Similarly the buildup of ice from snow melting on the warm
electronics located at the feed assembly can cause serious ice
loading lower on the dish. Smaller home or commercial VSAT type
dishes are notorious for loosing satellite connectivity during
heavy snow fall till someone goes out and cleans them off.
SUMMARY OF THE INVENTION
[0011] It is an object of the present invention to obviate or
mitigate at least one or more disadvantages of previous
communications systems.
[0012] A Gimbaled Mount Satellite System in accordance with the
present invention may only need to be critically aligned once
during initial installation and all subsequent weather or
environmental factors acting upon the system may be dealt with by
the earth station facilities built into the Gimbaled Mount
Satellite System, in accordance with the present invention.
[0013] The unique design incorporated a Gimbaled Mount Satellite
system, in accordance with the present invention, uses the
principles of gimbals which like a sea compass, uses the earths
gravity pulling down perpendicularly on the suspend device to keep
it flat surfaced and viewable to the viewer.
[0014] The unique mechanical design of the Gimbaled Mount System
uses near frictionless pivotal bearings rather than typical sealed
ball or roller bearings for all pivot points. This may allow for
many years of unattended operation for a typical system.
[0015] The construction of the Gimbaled Mount System may be made
almost entirely out of high grade, heavy gauge stainless steel
construction, which may eliminate the need for painting and
preventing rust from affecting its long term continuous operation
and extending its lifespan.
[0016] The low profile, low wind resistance design and adjustable
mounting legs along with compact non-penetrating foot print makes
the Gimbaled Mount System ideal for most flat or near flat
roofs.
[0017] The incorporation of a low-power-demand-wind dampening
system within the design of the Gimbaled Mount System may improve
not only system survival following a high wind event but also the
continuous operation of the earth stations primary function during
a severe wind event.
[0018] Weather conditions vary significantly around the world, and
snow or ice can be part of that common event. A Gimbaled Mount
System, in accordance with the present invention, has an option for
fully designed de-icing or snow melting system, which may prevent
any such local weather problem from interfering with the operation
of the earth station.
[0019] A Gimbaled Mount System in accordance with the present
invention, may not need for an exterior bubble or dome type
enclosure, therefore providing the ability to support multiple
sizes of satellite dishes in both circular and elliptical designs,
with only the center balance point needing to be determined before
securing to the lower mounting plate.
[0020] Several suitable applications result from methods and
devices described herein. Those skilled in the art will further
appreciate the above-noted features and advantages of the invention
together with other important aspects thereof upon reading the
detailed description that follows in conjunction with the
drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0021] For more complete understanding of the features and
advantages of the present invention, reference is now made to a
description of the invention along with accompanying figures,
wherein:
[0022] FIG. 1 is drawing of a Gimbaled Mount Satellite System,
showing its mechanical low profile design from a side view, in
accordance with an exemplary embodiment of the present
invention;
[0023] FIGS. 2A-2E show multiple views of a Gimbaled Mount in
accordance with an exemplary embodiment of the present
invention;
[0024] FIGS. 3A-3C show details of a pivot bearing design function
to include a pivot point and v-groove in accordance with an
exemplary embodiment of the present invention;
[0025] FIG. 4 is an End view of Drop Center Pivot Point
Mounting;
[0026] FIGS. 5A-5C are drawings of legs and feet for a Gimbaled
Mount in accordance with the present invention, with several
notations as to components making up this assembly;
[0027] FIG. 6 is a drawing of the Gimbaled Mount wind dampening
system, with several notations of components within this
assembly;
[0028] FIG. 7 is a Detailed drawing of the Platform (note 12)
including anchor point pin (note 16) for stabilizer springs and
Pivot hanging points (note 13);
[0029] FIG. 8 is a Manual Wind Dampening System detail drawing,
including several notations for components within this
assembly;
[0030] FIG. 9 is The Electric Automatic Wind Dampening System, with
several notations regarding both the electric stepper motor winch
and Aerometer feedback unit; and
[0031] FIGS. 10A-10B show the path or placement of a thermal
protection system of the Gimbaled Mount, as it relates to the dish
and LNB assembly and overall Gimbaled Mount including pivot points,
in accordance with exemplary embodiments of the present
invention.
DETAILED DESCRIPTION
[0032] The Figures collectively represents actual sub sections of
the fabrication drawings for the CommPuter controllercommunications
controller, as disclosed in U.S. Provisional Patent Application No.
60/886,905, and which is incorporated herein by reference.
[0033] A Gimbaled Mount System design, in accordance with the
present invention was derived from experience with the repeated
historical failure of earth stations, that were required for
communications purposes, being made inoperable following either an
earthquake, that shifted the position of an existing structure, or
where wind damage had occurred. The present invention addresses a
design which is a component part of a much larger approach to
emergency communications previously disclosed in U.S. Provisional
Patent Application No. 60/886,905. The design and method described
herein provides a method to recreate or fabricate, a fully
functional device that significantly addresses the short falls or
failures of previous systems and provides a more robust method of
creating a earth station satellite system. The entire mechanism or
invention may be manufactured out of stainless steel further, which
may assure that this design may have a substantially longer
lifespan then a typical earth station mechanism, which is made out
aluminum and regular steel. The present invention compensates, at
least in part, for wind storm or ice or snow build up has been
taken into consideration and may ensure no outages for the this
type of earth station. The construction, in accordance with the
present invention may also benefit the building owner or manager to
which this earth station is installed as it does not require large
ballast materials to weigh down the structure nor does it require
roof penetration for any of the mounting system.
[0034] A Gimbaled Mount System, in accordance with an exemplary
embodiment of the present invention, begins with all components
being manufactured out of heavy gauge marine grade stainless steel,
typically of 0.025 inch thick material. This insures that corrosive
weather action or chemicals will not affect the longevity of this
system. The intention of this construction from the selection of
every component is designed with consideration of this earth
station remaining operable for 20 years. As satellite's in orbit
generally do not last this long, the ability to easily align to an
alternate satellite has been built into the basic design of this
system. FIG. 1 shows a side view of a Gimbaled Mount Satellite
System 100, in accordance with an exemplary embodiment of the
present invention. Its low profile design 105 is shown from this
side view, where the legs 107 are 24 inches high and the satellite
dish 115, shown in this particular embodiment, is 24.times.36
inches.
[0035] FIG. 5 is a drawing of legs and feet for a Gimbaled Mount in
accordance with the present invention, with several notations as to
components making up this assembly The legs, in accordance with an
exemplary embodiment of the present invention, as detailed in FIG.
5, are made from a 24 inches long post 2, having a 1.00 inch O.D.
stainless steel and a 0.125 wall thickness pipe. A slot 12, at
least 2.00 inches deep and 9/32 inch wide, is cut at the middle of
the top end of this pipe for sliding into a socket made on the
outer 0.250 inch by 2 inches gimbaled ring. Also shown in FIG. 5
are: 53 adjustable leg screw; 4 foot plate; 5 adjustable leg
locknut; 7 leg post top plate; 19 leg ring for tension cable
pulley; and 6 a, b, c, d respective leg alignment plates, where
only one of four is shown.
[0036] A 2 inch high by 0.250 inch thick stainless steel ring is
rolled and curved into 2 sections with overlapping and bolted ends,
forming the 48.0 inch outer ring. The bolt to hole ratio is tight
so as to not create any flex in this ring when fully assembled. At
the mid-point of each half section, or directly opposite each other
on the overall 48.0 inch ring are cut 2 "V" grooves at
approximately 45 degrees arc (see FIG. 3 note 11). FIG. 3 is a
blown up drawing detailing the pivot bearing design function, with
note 11 detailing a pivot point and V-groove relationship
detail.
[0037] Similarly, in accordance with the present invention, on the
2 inch by 0.250 inch thick stainless steel outer ring, spaced
exactly 90 degrees apart, equidistant from each other, are located
4.times.0.750 inch by 4 inch long, with a 9/32 inch slot.times.2
inches long, stainless steel pipe sections welded to outer ring,
with the 2 inch extension hanging below the outer ring. This
permits the Legs as described above to socket rigidly into the
outer ring for stable operation.
[0038] The legs, in accordance with an exemplary embodiment, all
have a 0.125 inch thick by 1 inch diameter round plate 527, with a
captured and welded 0.625 threaded diameter nut and mating 5 (see
FIG. 5 note 55). 700 hole on the plate. This permits a mating 5/8
inch threaded stock by 12 inches long rod 53 to be screwed in along
with a 2 inch diameter by 0.125 thick end plate 5 welded to one end
of the adjustable rod to act as the load bearing plate in contact
with the roof. A 5/8 inch mating locking nut is pre-loaded to each
rod during manufacturing to insure the rod does not go all the way
into the leg socket and to also lock the position of each leg once
the outer ring is made perfectly level.
[0039] The outer ring 1, as shown in FIG. 2, top view, in
accordance with an exemplary embodiment, is constructed in two
sections to ease in taking components up a standard elevator to the
rooftop installation. Once the outer ring is made perfectly level,
using either a 5 foot long bubble level or 24 inch with a straight
board, and spanning the entire outer ring diameter, the leg's lock
nuts are tightened. This ensures no movement of the outer ring and
a stable platform to build the gimbaled deck from.
[0040] The inner ring 8, in accordance with an exemplary
embodiment, is constructed similar to the outer ring 1 of 2 inch
high by 0.250 thick stainless steel, however the diameter when
assembled is 4 inches smaller than the outer ring. Mid-Point on
each arc of the Inner Ring is a welded drop type L-bracket 9. The
protruding 3 inch portion of the this L-bracket has a beveled knife
edge that will align with the two V-grooves in the Outer Ring. The
L-bracket 9 lowers the Inner ring when suspended on the Outer Ring
by 2 inches beginning the gravitational offset point. The mid-point
opposite each other is additional V-grooves for accepting the
Platform Plate.
[0041] The Platform Plate 12, in accordance with an exemplary
embodiment, (see FIG. 7 note 12) is constructed and welded in one
piece primarily with similar L-brackets 13 that rest in the
V-grooves cut in the Inner Ring. Once again, the L-brackets 13 drop
the Platform Plate approximately 4 inches from the height of the
Inner Ring. The final assembly procedure for the Platform Plate is
screw in on the underside of the Platform Plate in captured nut,
the Dampening Spring Anchor Pin (see FIG. 7 note 16). Summarizing
FIG. 2 shows: 1 Outer Gimbals Ring; 2 a, b, c, d, 24 inch leg
posts; 3 adjustable leg screw; 4 foot plate; 5 adjustable leg
locknut; 6 a,b,c,d leg alignment plates; 7 leg post top plate; 8
secondary inner ring; 9 a, b welded pivot L-brackets; 11 V groove
pivot point; 12 platform plate; 13. platform plate L-brackets; 14
tension springs; 15 Dampening cables; 16 Anchor Pin; 17 Leg post
pulley; 18 Aerometer mounting point; and 19 close-up leg ring for
tension cable pulley.
[0042] Once the 2 rings and Platform Plate have been assembled and
placed on the legs, the gimbaled operation begins. The next step is
to take the dish and its plate mount system and bolt it to the
correct holes on the Platform Plate to achieve balance when the
Dish is mounted. The bolt slots in the Platform Plate allow for
front to back movement of the Dish Mount plate and are positioned
to accommodate several different dish size configurations. Once the
Dish is properly mounted applying slight pressure to the Dish
should cause the entire Platform Plate to move. Taking pressure off
in a none windy condition should cause the Dish to return to
"Plumb" state. Gravity does all the work to this point. The Dish
although able to be roughly pointed at the correct satellite at
this point, should be avoided till the Dampening System is
installed.
[0043] Each of the 24 inch legs, and approximately 8 inches down
from the top, if each tube, is welded a 1 inch.times.% inch hook,
used for connecting or hanging a pulley with eyelet assembly for
the wind dampening system. On one leg only, and before the foot
post was fully inserted at manufacturing a spooling system is slid
over the tube. (See FIG. 8) In constant wind loading areas a manual
drum and tension system is utilized.
[0044] However, in wind conditions, a mounting system embodiment
includes a remotely operated electric drum winch mechanism which is
mounted on one of the legs pointing towards the inside of the
Gimbaled Mount assembly. This is remotely operated, by an attached
CommPuter controller system as disclosed both in U.S. Provisional
Patent Application No. 60/886,905, and as also disclosed in US.
Application No., filed concurrently herewith, both which are
incorporated herein by reference. A wind speed aerometer is
inserted into the top side of the Outer ring assembly into the leg
assembly holding the Winch assembly. A common service cable
interconnects both the lower Winch unit and the aerometer for wind
speed detection and CommPuter controller feedback which causes
either the Winch to take up slack or release slack to the dampening
cables.
[0045] The Dampening cables 15, in accordance with an exemplary
embodiment, use an eyelet formed in the end located near the center
of the Gimbaled Mount, and are attached to 4 long coil springs 14
with eyelets at each end, as shown in FIG. 6. (See FIG. 6 item 14)
One end of the Dampening springs 14 is attached to the dampening
cables 15 while their opposite ends are hooked over the Center Pin
16 of FIG. 7. Pin 16 extends down from the Center Platform 12 of
the Gimbaled Mount, as shown in FIG. 7.
[0046] The Dampening cables, when in an area with low wind
problems, may be used with a Manual Wind Dampening System, as shown
in FIG. 8. Gimbaled Mount System leg is modified to have a stop
ring 22 welded approximately 13 inches down from the top of the
post 2 (see notation #22 in FIG. 8 and in FIG. 9).
[0047] Once the Dampening cables 15 are secured to the loose end of
the Dampening Springs 14, the opposite end of the cable is routed
back to their respective Legs #1, #2, #3 through respective pulleys
17 hooked into the hook welded on 3 of 4 Legs and then the cables
are directed to the fourth Leg, spooling system. The shorter cable,
of the 4 cables is secured to Dampening Spring 14, and directed at
Leg #4, and enters the spooling system, directly. FIG. 9
[0048] All Loose ends are looped once around the Spool drum core.
The Loose ends are threaded through holes in the core of the
Dampening Spool assembly. Cables are then brought taunt and secured
without any stretching of the Dampening Springs. The stretching of
the Dampening Springs is left to the Spool drum assembly.
[0049] The Manual Wind Dampening System, in accordance with an
exemplary embodiment, and its spooling system, as shown in FIG. 8
has a 1/4 inch locking bolt in the extend hub that locks the Spool
when correct tension has been reached. The rotating of the
Dampening Spool causes all tension springs to be equally tension
loaded. This acts as a shock or wind sensitivity reducer and allows
minor breezes to buffet the dish assembly without causing the
Gimbaled Platform and subsequently the Dish from varying off the
critical alignment directed at its specific satellite. FIG. 8, a
Manual Wind Dampening spool, in accordance with the present
invention, shows: 2 a 24 inch post tube; 3 adjustable leg screw; 4
foot plate; 5 adjustable leg locknut; 6 adjustable leg guide nut; 7
adjustable leg stabilizing plate; 20 Manual Dampening spool
adjustment collar; 21 Manual Damping spool collar lock bolt; and 22
Dampening spool collar welded stops.
[0050] The Electric Automatic Wind Dampening System, in accordance
with an exemplary embodiment, as depicted in FIG. 9 is comprised of
two main devices affixed to Leg #4. The first device is an Electric
Stepper Motor driven spooling system as shown by notation #19 in
FIG. 9. This Stepper Motor is mounted on a slide on sleeve and
bracket assembly as shown in FIG. 9. The Stepper Motor is connected
by a common control cable assembly that is shared by the Aerometer
unit and routed back to the CommPuter controller as previously
disclosed in U.S. Provisional Patent Application No. 60/886,905,
and also disclosed in detail under a separate concurrent filing
U.S. Application No. TBD. FIG. 9 shows the Electric Auto Dampening
Spool, in accordance with an embodiment of the present invention.
FIG. 9 shows: 2 Dampening Spool mounting collar; 3 Adjustable leg
screw; 4 foot plate; 5 adjustable leg locknut; 6 adjustable leg
guide nut; 7 adjustable leg stabilizing plate; 19 Dampening spool
with anchor slots; 22 Dampening spool collar welded stops; 24
Aerometer assembly with cups and servo; and 25 Dampening spool
Stepper Motor.
[0051] The Second part of the Electric Automatic Wind Dampening
System is an Aerometer as depicted as note #24 in FIG. 9. The
Aerometer is electrically connected by a common control cable along
with the Stepper Motor assembly back to the CommPuter controller
System as previously disclosed in U.S. Provisional Patent
Application No. 60/886,905, and also disclosed in detail under a
separate filing under a separate concurrent filing U.S. Application
No. TBD.
[0052] The Action of wind turning the Aerometer cups (see FIG. 9
note 24) causes a signal voltage relative to current wind speed to
be fed back to the CommPuter controller Command Processor circuit
on the Segmented Addressable Communications Assembly (SACA)
Junction Box motherboard as defined previously in and as previously
disclosed in U.S. Provisional Patent Application No. 60/886,905,
and also disclosed in detail under a separate concurrent filing
U.S. Application No. TBD. This input voltage is read by the Command
Processor and either a rising or falling wind speed instructs the
Command Processor to issue a forward for increasing or reversing
for falling wind speed command to the Stepper Motor circuit and fed
back up the common control cable, where the Electric Spooling
system (see FIG. 9 note 25) either takes cable in tightening the
dampening springs or loosening to relieve tension off the dampening
springs uniformly.
[0053] The action of stretching or applying more tension to the
springs (see FIG. 6 note 14) equally in 4 diametrically different
directions causes a dampening or semi-restrictive action on the
natural externally induced wind drag motion on the dish which due
to size and angle is amplified in its reactive actions to the
Platform to which it is applied. In a conventional roof top or
larger earth station design, natural mass or the addition of
weighted blocks or bags placed on the earth station base plate
mounting system. Typically this can also cause great hardship on
the installer when having to carry these heavy ballast weights to
the roof to hopefully secure the dish and mount assembly or earth
station. The ballasts act as a restrictive force on efforts of the
wind to topple the rigid dish and mount assembly or earth station.
Ballasts are the norm for the telecommunications industry as
piercing the roof membrane to secure a dish and mount assembly or
earth station, is highly frowned upon due to liability for roof
leaks.
[0054] The primary advantage and choice point between the Manual
(see FIG. 8) and the Electric Automatic Dampening Systems (see FIG.
9) is the ability of the later to react to the unexpected. The
principles and uniqueness of the Gimbaled Mount System over
conventional choices for the same application, is that a Gimbaled
Mount System is designed to survive and not fail when
communications are most needed. Like a Public Telephone System that
is built to Telcordia.COPYRGT. Standards of 5.times.9's or 99.999
percent uptime, the Gimbaled Mount System brings this type of
unique reliability to wireless satellite communications unlike any
other system before it.
[0055] Wind is not the only threat to satellite systems, snow and
ice damage can directly affect the operations of satellite dish or
earth station. Snow laden dishes effectively change their parabolic
curve therefore becoming less or non effective for receiving the
weak satellite signals. Customary sweeping or brushing off the dish
surface takes labor and sometimes results in temporary outages
until the snow or ice is removed. By Installing a thermal heating
cord, in accordance with an exemplary embodiment, along the
backside of the Dish as detailed in attached drawings (see FIG.
10), the underside of the Low Noise Amplifier module, and crucial
pivot points on the Gimbaled Mount assembly, the dish with only the
aide of a thermostat set, for example, at 34 degrees Fahrenheit (1
degree Celsius) keeps the Dish clear of snow or ice, and the pivots
remain unclogged while the dish operation is maintained even
through a major snowfall or ice storm.
[0056] The construction of the gimbaled portion of the mount
assembly will now be disclosed in detail, in accordance with an
exemplary embodiment. Inset 2 inches in from the Outer Ring is the
Inner Ring a secondary support ring with two exactly opposite 2
inch drop offset pivot brackets made of stainless steel welded to
the secondary ring. The support portion of the L-bracket allows the
ring to sit 2 inches lower than the top surface of the outer main
ring. The L-brackets as detailed in FIG. 3, allows the 43.5 inch
diameter Secondary Ring, to pivot on these two brackets when a
blade or wedge type extension with case hardened pivot surface
point rests in matching V-grooves prepared in the Primary 48 inch
diameter outer Primary Ring. The Secondary Inner Ring also has,
directly opposite each other, 2 V-grooves cut in the top edge of
this Ring. Ordinarily this would continue to make the Inner Ring
unstable, however from these 2 V-grooves in the Secondary Ring to 4
inch high triangle type plates as detailed in FIG. 4 with similar
mating blade extensions welded onto, rest in these 2 v-grooves.
[0057] The Platform, in accordance with an exemplary embodiment is
shown in FIG. 7 in this overall assembly is a disc like 39 inch
diameter platform for the satellite dish equatorial mount to be
attached to. Various mounting holes in the Platform allow for
minute adjustment of the position of several different types of
Dishes and Equatorial Mounts to fastened and still maintain a
balance point relative to the side mounted Pivot plates. The
installer uses once again a 4 foot bubble level, to establish
actual flat position of the Platform. The actual weight of the Dish
and Mount assembly along with the weight of the Platform assembly
itself when dropped drop 3 inches below the pivot points (see FIG.
7 note 13) causes the Platform to remain stable and plum to a
gravitational point, much like a ships compass does in a rolling
sea.
[0058] At the dead center of the 39 inch diameter Platform Plate
and extending 3 inches down is the Stabilizer Spring Anchor Pin,
(see FIG. 7 note 16). This Pin along with the Wind Dampening System
and spring assemblies keeps the stability of the Platform constant
even with wind drag on the topside dish assembly. The Aerometer
(see note #23 in FIG. 9) detects the wind speed, feeds back a
proportional voltage to the CommPuter controller where the on-board
Command Processor located on the Hercules SACA Junction Box
motherboard translates the voltage to an appropriate output command
back up the same common cable to the Stepper Motor (see FIG. 9 note
25) winch system which increases or decrease the rotation of the
winch drum thereby pulling more or less on the Dampening Springs
(see FIG. 6, note 14) and thereby dampening or negating the effect
of the wind drag on the dish assembly.
[0059] While specific alternatives to steps of the invention have
been described herein, additional alternatives not specifically
disclosed but known in the art are intended to fall within the
scope of the invention. Thus, it is understood that other
applications of the present invention will be apparent to those
skilled in the art upon reading the described embodiments and after
consideration of the appended claims and drawings.
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