Source: https://patents.google.com/patent/US20080211730A1/en
Timestamp: 2019-09-16 00:46:56
Document Index: 145214166

Matched Legal Cases: ['Application No. 60', 'Application No. 60', 'Application No. 60', 'Application No. 60', 'Application No. 60', 'Application No. 60', 'Application No. 60']

US20080211730A1 - Gimbaled Mount System for Satellites - Google Patents
Gimbaled Mount System for Satellites Download PDF
US20080211730A1
US20080211730A1 US12/020,269 US2026908A US2008211730A1 US 20080211730 A1 US20080211730 A1 US 20080211730A1 US 2026908 A US2026908 A US 2026908A US 2008211730 A1 US2008211730 A1 US 2008211730A1
US12/020,269
Calvin H. Woosnam
Woosnam Calvin H
2007-01-26 Priority to US88690507P priority Critical
2008-01-25 Application filed by Woosnam Calvin H filed Critical Woosnam Calvin H
2008-01-25 Priority to US12/020,269 priority patent/US20080211730A1/en
2008-09-04 Publication of US20080211730A1 publication Critical patent/US20080211730A1/en
2014-03-19 Assigned to Technology Mining Company, LLC reassignment Technology Mining Company, LLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WOOSNAM, CALVIN H.
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.
This application claims the benefit of U.S. Provisional Application No. 60/886,905 filed Jan. 26, 2007, the contents of which are incorporated herein by reference.
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.
More particularly, the present invention addresses the need for a reliable weather resistant mounting system for satellites.
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.
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.
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.
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.
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.
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.
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.
It is an object of the present invention to obviate or mitigate at least one or more disadvantages of previous communications systems.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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;
FIG. 2 is a detailed Gimbaled Mount Technical Drawing used for fabrication, with several notations as to the components making up this overall exemplary assembly;
FIG. 3 is Blown up drawing detailing the pivot bearing design function, with note 11 detailing a pivot point and V-groove relationship detail;
FIG. 4 is an End view of Drop Center Pivot Point Mounting;
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;
FIG. 6 is a drawing of the Gimbaled Mount wind dampening system, with several notations of components within this assembly;
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);
FIG. 8 is a Manual Wind Dampening System detail drawing, including several notations for components within this assembly;
FIG. 9 is The Electric Automatic Wind Dampening System, with several notations regarding both the electric stepper motor winch and Aerometer feedback unit; and
FIG. 10 is a Drawing showing the path or placement of The Thermal Protection System of the Gimbaled Mount, as it relates to the dish and LNB assembly and overall Gimbaled Mount including pivot points is shown.
The Figures collectively represents actual sub sections of the fabrication drawings for the CommPuter controller communications controller, as disclosed in U.S. Provisional Patent Application No. 60/886,905, and which is incorporated herein by reference.
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.
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 24×36 inches.
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.
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.
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 4×0.750 inch by 4 inch long, with a 9/32 inch slot×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.
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 ⅝ 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 ⅝ 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.
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.
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.
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.
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.
Each of the 24 inch legs, and approximately 8 inches down from the top, if each tube, is welded a 1 inch×¾ 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.
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.
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.
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).
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
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.
The Manual Wind Dampening System, in accordance with an exemplary embodiment, and its spooling system, as shown in FIG. 8 has a ¼ 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.
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.
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.
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.
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.
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© Standards of 5×9'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.
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.
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.
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.
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.
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.
the heavy gauge stainless steel is at least 0.025 inches thick.
a system of non-motorized wind damping.
a system of motorized wind damping.
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.
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.
a system of non-motorized wind damping; and
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 low noise amplifier module;
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.
US12/020,269 2007-01-26 2008-01-25 Gimbaled Mount System for Satellites Abandoned US20080211730A1 (en)
US88690507P true 2007-01-26 2007-01-26
US12/020,269 US20080211730A1 (en) 2007-01-26 2008-01-25 Gimbaled Mount System for Satellites
US12/912,501 US20120105289A1 (en) 2007-01-26 2010-10-26 Gimbaled mount system for satellites
US13/865,668 US9094089B2 (en) 2007-01-26 2013-04-18 Gimbaled mount system for satellites
US14/745,147 US20150288051A1 (en) 2007-01-26 2015-06-19 Gimbaled mount system for satellites
US12/912,501 Continuation US20120105289A1 (en) 2007-01-26 2010-10-26 Gimbaled mount system for satellites
US20080211730A1 true US20080211730A1 (en) 2008-09-04
ID=39644067
US12/020,269 Abandoned US20080211730A1 (en) 2007-01-26 2008-01-25 Gimbaled Mount System for Satellites
US12/021,076 Abandoned US20090042513A1 (en) 2007-01-26 2008-01-28 Networked Communications System and Segment Addressable Communications Assembly Box, Cable and Controller
US12/021,066 Abandoned US20080238671A1 (en) 2007-01-26 2008-01-28 Security assembly and system
US12/021,094 Abandoned US20080205324A1 (en) 2007-01-26 2008-01-28 Networked Communications and Early Warning System
US12/912,501 Abandoned US20120105289A1 (en) 2007-01-26 2010-10-26 Gimbaled mount system for satellites
US13/780,307 Active 2029-10-18 US10055955B2 (en) 2007-01-26 2013-02-28 Networked communications and early warning system
US13/865,668 Active US9094089B2 (en) 2007-01-26 2013-04-18 Gimbaled mount system for satellites
US13/903,415 Abandoned US20160321890A9 (en) 2007-01-26 2013-05-28 Perimeter security surveillance system
US13/935,232 Abandoned US20140099882A1 (en) 2007-01-26 2013-07-03 Networked communications system and segment addressable communications assembly box, cable and controller
US14/745,147 Abandoned US20150288051A1 (en) 2007-01-26 2015-06-19 Gimbaled mount system for satellites
US (10) US20080211730A1 (en)
WO (2) WO2008089575A1 (en)
CN101917693B (en) * 2010-07-03 2012-11-14 湖南航天亚卫通信电子有限公司 Emergency communication system and method
KR101622021B1 (en) * 2014-04-24 2016-05-17 주식회사 지이에스 Apparatus for detecting invasion of security fence
WO2016077496A1 (en) * 2014-11-11 2016-05-19 General Cable Technologies Corporation Heat shield for cables
US10212231B2 (en) 2015-01-07 2019-02-19 Passport Systems, Inc. Methods and systems for detecting a material source using a server and networked sensors
SG11201705509VA (en) * 2015-01-07 2017-08-30 Passport Systems Inc Intelligent server in a system of networked sensors
FR3049676B1 (en) * 2016-03-29 2018-10-19 Pelardy Jean Marc Matt Vandal camera support
US3277486A (en) * 1962-06-12 1966-10-04 Manfred F Kuebler Method and means for damping nutation in a satellite
US20080164361A1 (en) * 2007-01-09 2008-07-10 Hannay Reels, Inc. Spring retractable reel having a pneumatic retraction governor
DE2632615C3 (en) * 1976-07-20 1979-08-30 Siemens Ag, 1000 Berlin Und 8000 Muenchen
US4596989A (en) 1983-02-14 1986-06-24 Tracor Bei, Inc. Stabilized antenna system having an acceleration displaceable mass
US4598297A (en) 1983-10-21 1986-07-01 Hawkins Joel W Mounting apparatus for satellite dish antennas
US4793275A (en) * 1983-11-07 1988-12-27 David Usher Marine hazardous off-loading system
US4685649A (en) 1984-07-19 1987-08-11 Gregory Gault Vibration isolator camera mount
JPS6199111U (en) 1985-11-20 1986-06-25
FR2659512B1 (en) * 1990-03-09 1994-04-29 Cogema Communication installation hyperfrequences.
GB9005741D0 (en) 1990-03-14 1990-05-09 Smiths Industries Plc Fibre-optic cable assemblies
US5195158A (en) 1991-02-06 1993-03-16 Bottoms Jack Jr Tight buffered fiber optic groundwire cable
JPH05175716A (en) 1991-12-19 1993-07-13 Furuno Electric Co Ltd Antenna directing device for mobile object
AU654595B2 (en) 1992-01-23 1994-11-10 Andrew Corporation Parallel-conductor transmission line antenna
CA2148740C (en) 1995-05-05 2001-01-02 John Dennis Mcguire Damped one-way self-closing gate
US6015954A (en) 1996-04-24 2000-01-18 Ems-Inventa Ag Multi-layer ballistic cable protector
JP4294863B2 (en) 1998-01-05 2009-07-15 ユナイテッド ステイツ エンバイロメンタル プロテクション エージェンシー Vehicle exhaust gas during real-time running modular flowmeter and emissions reporting system
DE19958431C1 (en) * 1999-12-03 2001-07-05 Leoni Bordnetz Sys Gmbh & Co Cable sleeve as well as processes for their preparation
NL1014085C2 (en) 2000-01-17 2001-07-18 Koninkl Kpn Nv Mast for a source of electromagnetic waves provided with a stabilization device.
US7006791B2 (en) * 2001-03-16 2006-02-28 U.S. Monolithics, L.L.C. System and method for uplink power control by detecting amplifier compression point using dc current detection
EP1314813A1 (en) 2001-11-23 2003-05-28 N.V. Bekaert S.A. Cable and window elevator system using such cable
US20040026598A1 (en) * 2002-08-08 2004-02-12 Applied Materials, Inc. Adjustable support leg for semiconductor device manufacturing equipment
AU2002952248A0 (en) * 2002-10-25 2002-11-07 Goodcart Pty Ltd Multi purpose pole
GB0229700D0 (en) * 2002-12-19 2003-01-29 Koninkl Philips Electronics Nv Remote control system and authentication method
TW200537118A (en) * 2004-05-06 2005-11-16 Mitac Technology Corp A dynamic direction adjustment control device for a satellite disk antenna on a moving carrier
WO2005119841A2 (en) * 2004-06-04 2005-12-15 Radiall Antenna Technologies, Inc. Circuit component and circuit component assembly for antenna circuit
US20050281517A1 (en) 2004-06-18 2005-12-22 Wessels Robert A Jr Multi-layered buffer tube for optical fiber cable
EP2063223B1 (en) 2006-09-15 2014-06-18 Hitachi, Ltd. Angular velocity sensor
US20090226177A1 (en) 2007-01-26 2009-09-10 Woosnam Calvin H Communications Cable and Method of Making Same
JP4905574B2 (en) 2010-03-25 2012-03-28 株式会社豊田中央研究所 Laminated structure that includes a movable portion
2008-01-25 US US12/020,269 patent/US20080211730A1/en not_active Abandoned
2008-01-28 US US12/021,076 patent/US20090042513A1/en not_active Abandoned
2008-01-28 US US12/021,066 patent/US20080238671A1/en not_active Abandoned
2008-01-28 WO PCT/CA2008/000163 patent/WO2008089575A1/en active Application Filing
2008-01-28 US US12/021,094 patent/US20080205324A1/en not_active Abandoned
2008-01-28 WO PCT/CA2008/000176 patent/WO2008089584A1/en active Application Filing
2010-10-26 US US12/912,501 patent/US20120105289A1/en not_active Abandoned
2013-02-28 US US13/780,307 patent/US10055955B2/en active Active
2013-04-18 US US13/865,668 patent/US9094089B2/en active Active
2013-05-28 US US13/903,415 patent/US20160321890A9/en not_active Abandoned
2013-07-03 US US13/935,232 patent/US20140099882A1/en not_active Abandoned
2015-06-19 US US14/745,147 patent/US20150288051A1/en not_active Abandoned
US20120105289A1 (en) 2012-05-03
WO2008089584A1 (en) 2008-07-31
US20150288051A1 (en) 2015-10-08
US20160210831A1 (en) 2016-07-21
US20160321890A9 (en) 2016-11-03
US20130250848A1 (en) 2013-09-26
US20090042513A1 (en) 2009-02-12
US20130277523A1 (en) 2013-10-24
US10055955B2 (en) 2018-08-21
US20080205324A1 (en) 2008-08-28
US9094089B2 (en) 2015-07-28
US20080238671A1 (en) 2008-10-02
US20140099882A1 (en) 2014-04-10
WO2008089575A1 (en) 2008-07-31
US8692401B2 (en) 2014-04-08 Asymmetric mooring system for support of offshore wind turbines
US5398478A (en) 1995-03-21 Means and method for rigidly elevating a structure
AU2005327061B2 (en) 2012-02-02 Wind-energy power machine and it&#39;s energy-storage generation system and wind-energy power generation system
US20140008506A1 (en) 2014-01-09 Roof Mount Sealing Assembly
US20140360562A1 (en) 2014-12-11 Photovoltaic module support system
EP1472458B2 (en) 2012-11-21 Method of mounting elements in a wind turbine tower, wind tower suspension unit, system of mutually attachable members
US8609977B2 (en) 2013-12-17 Self ballasted celestial tracking apparatus
US8505863B2 (en) 2013-08-13 Camming clamp for roof seam
US7287962B2 (en) 2007-10-30 Construction apparatus and method for a wind power installation
JP4558785B2 (en) 2010-10-06 Stand 設方 method of tower
US6109197A (en) 2000-08-29 System for loading ships at sea
US20080060297A1 (en) 2008-03-13 Hold down system
DE102006033215B4 (en) 2008-11-06 Device for stable storage of facilities or structures at sea
JP4726891B2 (en) 2011-07-20 Stand 設方 method of tower
Owner name: TECHNOLOGY MINING COMPANY, LLC, TEXAS
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:WOOSNAM, CALVIN H.;REEL/FRAME:032472/0052