embodiments of the invention provide a self contained lightweight , collapsible and rugged antenna positioner for use in receiving and transmitting to low earth orbit , geosynchronous and geostationary satellites . in the following exemplary description numerous specific details are set forth in order to provide a more thorough understanding of embodiments of the invention . it will be apparent , however , to an artisan of ordinary skill that the present invention may be practiced without incorporating all aspects of the specific details described herein . any mathematical references made herein are approximations that can in some instances be varied to any degree that enables the invention to accomplish the function for which it is designed . in other instances , specific features , quantities , or measurements well - known to those of ordinary skill in the art have not been described in detail so as not to obscure the invention . readers should note that although examples of the invention are set forth herein , the claims , and the full scope of any equivalents , are what define the metes and bounds of the invention . fig1 shows a top perspective view of an embodiment of the invention in the deployed position . positioner base 100 may be coupled to the ground or any structure that can adequately support the apparatus . an embodiment with stabilizer leg 117 extended as well as adjustable leg 115 extended is shown in fig1 . the legs are optional and if an embodiment comprises legs , they are not required for use but may be used individually as required to provide stability based on the exact geography at the deployment site . positioner base 100 and positioner support frame 101 may be any geometrical shape although they are roughly shown as rectangular in fig1 . positioner support frame 101 is rotationally mounted on positioner base 100 . this rotational mounting allows for altering the azimuth setting of the apparatus . keypad port 114 and gps sensor port 116 allow for access to the respective elements housed internal to the positioner base during shipping . optional or combined use of and control of the apparatus may be accomplished via a pc ( not shown ). collapsible antenna positioner 103 is further described below and in fig4 . the collapsible antenna positioner allows for altering the elevation of antenna 102 mounted on antenna mounting plate 222 ( as shown in fig2 ). beneath antenna mounting plate 222 lies waveguide 104 and lnb 105 . tilt sensor and magnetometer 106 is also coupled with the bottom of antenna mounting plate 222 . tilt sensor and magnetometer 106 is used in order to measure the angle that antenna mounting plate 222 is pointing and determine the direction of north . pinch paddles 107 and 108 , release knobs 112 and 113 are used in order to disengage the positioning arms from antenna mounting plate 222 and elevation motor as will be explained in relation to fig4 . any method of disengagement may be substituted with regards to pinch paddles 107 and 108 and release knobs 112 and 113 . fig2 shows a bottom perspective view of an embodiment of the invention in the deployed position . stabilizer leg 200 is visible in this figure . the deployment of stabilizer leg 200 is optional as well as is the deployment of stabilizer leg 117 and adjustable leg 115 as shown in fig1 . optional battery compartment 201 allows for battery removal and replacement without disturbing the internal components of positioner base 100 . pinch paddle port 206 allows for operation of the pinch paddles when the apparatus is in the collapsed position . collapse grooves 203 , 204 and 205 allow for the collapsing of collapsible antenna positioner 103 as shown in fig1 by allowing for the disengaging of the respective axles in the associated positioning arms as will be further described in relation for fig4 . fig3 shows a perspective view of an embodiment of the positioner base with cover removed to expose internal elements . normally , positioner base 100 is closed to the external elements so that dust and water are not able to readily enter the apparatus . microcontroller 300 hosts the control program which reads inputs from keypad 320 and commands azimuth motor 330 to rotate via motor controller 303 to a desired azimuth based on various inputs . optional motor controller 302 may run the elevation motor in the positioner support frame , or motor controller 303 may comprise a two port motor controller capable of running both motors independently . gps receiver 324 provides time and position information to microcontroller 300 . drive hub 331 rotates positioner support frame 101 in order to point antenna 102 mounted to antenna mounting plate 222 in the desired azimuth . optional location for battery 301 may be as shown in fig3 , or as was shown in fig2 may lie between motor controller 303 and gps receiver 324 . optionally , if motor controller 303 comprises two independent ports , then motor controller 302 may be replaced by an optional wireless transceiver to eliminate the need to physically connect to a pc . any other unused space within positioner base 100 may also be used for external communications such as wireless transceivers . fig4 shows a close up of collapsible antenna positioner 103 as is partially shown in fig1 and 2 . plate mounts 402 , 403 and 404 act to couple antenna mounting plate 222 as shown in fig1 and 2 to positioner arms 110 , 111 and 109 respectively . positioner arms 109 and 110 are not directly coupled to one another . pinch paddles 107 and 108 act to disengage positioner arms 110 and 111 from associated antenna mounting plate 222 in order to collapse the apparatus . when pinch paddles 107 and 108 are forced together , the common axle is disengaged and slides freely along collapse grooves 204 and 205 . similarly , when release knob 112 is activated , positioner arm 109 is disengaged from the axle associated with release know 112 allowing the axle to freely slide along collapse groove 203 as shown in fig2 . when motor release knob 113 is activated , elevation motor 401 and hence worm drive 441 are disengaged from positioner arm 111 allowing the apparatus to fully collapse . stiffness in collapsible antenna positioner 103 as shown in fig1 is added via positioner arm plate 118 . lnb cutout 400 provides space for lnb 105 when antenna mounting plate 222 collapses in to positioner support frame 101 . frame mounts 405 and 406 provide rotational mounts for positioner arms 110 and 111 . positioner arm 109 couples to another frame mount that is not shown for ease of illustration . fig5 shows a perspective view of an embodiment of the invention in the collapsed position . adjustable leg 115 is folded underneath positioner base 100 . stabilizer leg 117 is folded against the side of positioner base 100 . antenna mounting plate 222 is shown collapsed into positioner support frame 101 . the apparatus as shown in fig5 is ready for shipment . operation of embodiments of the invention comprise initial physical setup and powered acquisition of a desired satellite . initial physical setup may comprise extending one or both of stabilizer legs 117 and 200 and in addition , optionally unfolding adjustable leg 115 . as adjustable leg 115 may optionally comprise a powered stepper motor for altering the elevation of the apparatus when a satellite is near the zenith to eliminate keyholing . alternatively , adjustable leg 115 may be manually adjusted . after any desired legs are deployed , pinch paddles 107 and 108 may be asserted in order to extend the associated axle up into the locked position on positioner arms 110 and 111 . the opposing side of antenna 102 may then be lifted in order to lock the axle associated with release knob 112 in the extended position in positioner arm 109 . when the axle associated with release knob 112 travels the full length of collapse groove 203 , release knob 112 is in the locked position and must be asserted in order to release the associated axle and collapse the apparatus . with opposing sides of antenna 102 locked into position , motor release knob 113 is asserted in order to engage worm drive 441 and hence elevation motor 401 . for connection based configurations not employing wireless communications , connecting desired communications links to a pc or other communications processor is performed . for configurations dependent upon an external computer , microcontroller 300 is optional so long as motor controller 303 comprises a communications port . as long as the external pc comprises the requisite drivers and satellite orbit calculation programs it may be substituted for microcontroller 300 . after physically deploying the apparatus , keypad port 116 may be accessed in order to operate keypad 320 . operations accessible from keypad 320 comprise acquire , stop , stow and test . asserting the acquire button and selecting a satellite initiates an orbital calculation that determines the location of a satellite for the time acquired via the gps receiver . with the latitude and longitude acquired via gps receiver 324 and the direction north and tilt of the apparatus measured via tilt sensor and magnetometer 106 all of the parameters required to point antenna 102 towards a desired satellite may be achieved . positioner support frame 101 is rotated to the desired azimuth via drive hub 331 , azimuth motor 330 and motor controller 303 . antenna 102 is elevated to the desired elevation via antenna mounting plate 222 , plate mounts 402 , 403 and 404 , positioner arms 110 , 111 and 109 , worm drive 441 and elevation motor 401 . communications and control lines , not shown for ease of illustration , extend through a center hole in drive hub 331 to and from positioner base 100 and positioner support frame 101 . these communications and control lines allow for the control of elevation motor 401 and receipt of down converted satellite signal via lnb 105 and measurement data from tilt sensor and magnetometer 106 . for satellite locations near the zenith in the reference frame of the apparatus , an optional stepper motor at the end of adjustable leg 115 may be activated in order to shift the observed zenith of the apparatus away from the desired satellite near the observed zenith in order to prevent keyholing . asserting the stop button on keypad 320 stop whatever task the apparatus is currently performing . this button can be activated prior to activating the stow button . the stow button realigns positioner support frame 101 with positioner base 100 and performs a system shutdown . the test button performs internal system tests and may be activated with or without collapsible antenna positioner 103 deployed . these operations may be modified in certain embodiments or performed remotely by an attached pc or over a wireless network in other embodiments . fig6 shows an isometric view of an embodiment of the invention in the stowed position . positioner base 600 houses electronic components and mates with antenna housing 601 for compact storage . positioner base 600 provides access to power switch 602 , remote computer ethernet connector 604 , power plug a 606 , power plug b 607 , lnb rf out 608 , data ethernet connector 605 and day / night / test switch 603 . power plug a 606 and power plug b 607 are utilized for coupling with power sources , batteries and solar panels for embodiments without built in receivers . data ethernet connector 605 provides internal receiver data for embodiments comprising at least one built in receiver which allows for coupling with external network devices capable of consuming a satellite data stream . in addition , one or more embodiments of the invention may use data ethernet connector 605 for providing the apparatus with transmission data for transmission to a desired satellite . day / night / test switch 603 is utilized in order to set the display ( shown in fig8 - 10 ) to provide for day and night time visual needs while the third position is utilized in order to test the system without deploying antenna housing 601 . fig7 shows an isometric view of the bottom of an embodiment of the invention in the stowed position . carrying handle 703 may be used to physically move the apparatus . legs 700 , 701 and 702 may form a removable leg system as shown or may independently be mounted to the bottom of positioner base 600 . in addition , a stackable module may be coupled to positioner base 600 in order to provide cryptographic , power / battery , router or any other functionality to augment the capabilities of the apparatus . fig8 shows an isometric view of an embodiment of the invention in the deployed position . legs 700 and 701 are shown in the deployed position . bubble level 806 is used to level positioner base 600 in combination with the legs or by placing objects underneath an embodiment of the invention not comprising legs until positioner base 600 is roughly level . the system has no loose parts and requires no tools . since there are no parts to loose , the system is more robust . the system may include a camouflage bag that encapsulates the system and may be changed from desert to jungle to urban camouflage or black . many different types of legs may be employed on the system depending on the terrain that the system is to be used in , including but not limited to legs with rubber bottoms , spikes or any other type of bottom , and the legs themselves may be of any type including telescoping or rigid or any other type . keypad 804 and display 805 are utilized in order to control the apparatus . also shown is azimuth motor 800 that rotates positioning arm 801 and elevation motor 802 which rotates antenna housing 601 in elevation . in one or more embodiments , antenna housing 601 may be rotated on an axis orthogonal to the plane of antenna housing 601 and may optionally include a third motor , however low power embodiments of the invention allow for the operator of the system to manually rotate antenna housing 601 for linear polarized satellite signals . lnb 803 couples with the reverse side of the antenna that is located within antenna housing 601 . when opening one embodiment of the invention , positioning arm 801 locks into a vertical position as shown and after selecting a satellite to acquire an internal or external microcontroller rotates azimuth motor 800 and elevation motor 802 based on the gps position , time and compass orientation of the apparatus . one embodiment of the invention may provide a limited turning range for azimuth motor 800 for example 60 degrees , in order to limit the overall weight of the device by allowing for simpler cable routing and minimizing complexity of the mechanism . positioner base 600 comprises an indentation shown in the middle of positioner base 600 for housing positioning arm 801 , elevation motor 802 and lnb 803 when in the stowed position . the indentation may make use of a hole that allows for environmental elements such as water , dirt , mud , snow or any other objects to drain or fall through the indentation . in addition , the hole may be coupled to the electronic components in order to provide a thermal well for heat management purposes . ( see fig1 ). in one or more embodiments , thermal bonding of the electronic components to the upper and lower portions of the positioner base does not comprise a hole . electronic components internal to positioner base 600 may comprise a microcontroller or computer which hosts a control program which reads inputs from keypad 804 and commands azimuth motor 800 to rotate to a desired azimuth . positioner base 600 may also comprise a gps receiver that provides time and position information to the microcontroller . positioner base 600 and antenna housing 601 may comprise a three axis accelerometer or inclinometer , magnetometer , data receiver and relative signal strength indicator ( rssi ) receiver and reports to the microcomputer the signal strength of the signal received and that information is used for the accurate pointing of the antenna . using keypad 804 , embodiments of the invention may utilize a “ one button ” or “ no button setup ” procedure . after opening the system and deploying the antenna in antenna housing 601 and turning the power on , the system determines where it is and if pointed within a general direction of a satellite , requires no button pushes for the system to lock . the system can also perform the no button option so that after power loss and restore , the system re - acquires a satellite . this may occur with no intervention . one button operation may be utilized when the system is not rotated close enough to a satellite for example , where the system may prompt the user to rotate positioner base 600 in one direction or the other and assert the acquire button . the prompt may include an “ x ” to the left or right in display 805 ( for example an led screen ) to let the user know to turn positioner base 600 clockwise or counterclockwise for example . display 600 may also present auto satellite options . for example , the first choice and second choice satellites may be presented to the user based on the band the system is configured for . based on the location of the antenna on the planet , the user interface shows the operator the most likely satellite that is normally picked . with regards to saving power and minimizing heat dissipation , algorithms may be employed by the computer housed in positioner base 600 , that conserve power may be utilized in one or more embodiments of the invention . low power embodiments of the invention employ a limited range of motion in azimuth ( e . g ., azimuth motor 800 rotates only a portion of 360 degrees ) for the antenna positioner which allows the operator to be presented with an “ x ” in a box of the user interface is display 805 . the operator sets the system to point within 60 degrees of a satellite , not 360 degrees . the system then prompts the user with the “ x ” which is on the left of the box if the operator should rotate the positioner base to the left and the “ x ” appears on the right side of the box if the operator is to rotate the positioner base to the right . once the positioner base is within 30 degrees , the operator asserts a button and the system begins to acquire a satellite . wiring of the system is simplified by sub - 360 degree rotation and weight is lowered as well . the search algorithm utilized by the system may be optimized to search in azimuth and sparsely search in elevation . this is due to the fact that magnetic anomalies are more prevalent than gravitational anomalies . the system looks first in azimuth before elevation ( preferential azimuth searching ) since that is where the errors are likely found . for example in one embodiment , the search proceeds to do two horizontal scan lines first above the initial point before performing two horizontal scan lines below the initial point . in other words , after the signal peaks , it goes to peak then leaves the raster scan algorithm then uses a box peaking algorithm right and up to a corner , go to a left corner , down to corner and right bottom corner , e . g ., 5 measurements . then the system points to the strongest and does the four corner measurements again . when the four corners of the box have equal strength the antenna is positioned correctly and the search algorithm terminates . in order to further save power , one or more embodiment may allow for the computer to perform tracking at uneven time intervals . for example , when tracking a geosynchronous satellite , e . g ., one that move in a figure eight pattern but remains relatively in one general area of the sky , the system can stop tracking the satellite at the top and bottom of the figure eight since motion is relatively slow there . the system can switch to more rapid tracking when the satellite is scheduled to move from the upper to the lower portion of the figure eight since the satellite motion is fast during this period . conserving power as determined by two - line element ( tle ) determined re - peak schedule allows for lower power dissipation and longer battery life . the system may utilize distributed i2c thermal sensors . the sensors may be placed on the electronics boards utilized by the system for example , so the computer can self - monitor the components . in another power saving embodiment , the computer housed in positioner base 600 performs tracking of the satellites in a manner that may switch between transponder signal and the beacon tracking signal output by a satellite . for example , beacons have a different frequency and are lower power than the data signal of the satellite . the beacons are also omni - directional so the system can find the satellite even if it is not pointed at the system at the time of acquisition . for small low power antennas , the beacon may be to small to detect , so if the data signal via the satellite transponder is on , it can be used to find and lock onto the satellite even if the beacon is too weak to detect . in order to further save power and time in acquiring satellites , the age of the two line ( tles ) is taken into account in one or more embodiments of the invention by the computer housed in positioner base 600 . this is known as clarke belt fallback . for ephemeris data or two line elements ( tles as used by nasa ), fresh tle data allows the system to point to the satellite accurately . however , in a couple of weeks , the tle information is out of date , in a couple of months is actually quite inaccurate . for perfectly stationary satellites on the clarke belt , i . e ., equator , all the system has to know is the longitude to find one of these satellites . the satellites that move have a problem in that a fresh tle is more accurate than a clarke belt longitude , but after 30 days the system falls back to the clarke belt longitude since it is more accurate after about this time span . without fresh tles , acquisition takes more time and power , but by using the clarke belt fallback , the system can still function . fig9 shows an isometric view of an embodiment of the invention with the antenna housing at a first azimuth and elevation setting . antenna housing 601 in this figure is pointed at a satellite midway between the zenith and horizon . fig1 shows an isometric view of an embodiment of the invention with the antenna housing at a second azimuth and elevation setting wherein the satellite is directly above the apparatus at the zenith . one or more embodiments of the control program may search for a desired satellite by scanning along the azimuth as the elevation of the apparatus is generally fairly accurate and wherein the local magnetometer may give readings that are subject to magnetic sources that influence the magnetic field local to the apparatus . some embodiments of the invention allow for a quick disconnect for the antenna panel or antenna itself in antenna housing 601 . this allows for different satellites having entirely different frequency bands to be acquired with the system . this quick disconnect capability may be implemented by using double pins to hook the antenna or antenna housing 601 to positioning arm 801 . by releasing one antenna and attaching another antenna to the positioning arm , a different set of satellites in general may be acquired since some satellites use various frequencies . linearly polarized satellites , generally commercial satellites may be acquired using a third rotational motor that allows for the antenna to rotate about the axis pointing at a satellite . for low power configurations , this allows for the user to be prompted to rotate the antenna until the strength of the signal is maximized . low power embodiments therefore do not require a third axis motor . the system may also employ a failure contingency tree that is utilized by the computer housed in positioner base 600 . for example if any portion of the system fails , the system may prompt the user via the display and allow the user to utilize the keypad 804 an attached keyboard to respond to system requests for positioning the system , etc . for example , if the gps or tilt fails , the system allows the operator to compensate for the error , prompts for entry on keyboard , of the gps position or to acknowledge that the base is level . in short , the system is configured to ask the user for help is components break . the system may employ tilt compensation via the computer housed in positioner base 600 so that even if positioner base 600 is not level , the scan includes adjustment to elevation motor 802 so that the scan lines are parallel to the horizon as azimuth motor 800 turns so that the scan lines are not parallel to the incline on which the positioner base is situated . the three - axis accelerometer is used to provide tilt measurements in one or more embodiments of the invention . the system also is capable of manually - assisted linear polarization setting . when aligning the third axis , that is aligning the antenna in antenna housing 601 about an axis orthogonal to the antenna plane for linear polarization , the operator may be prompted for rotating the antenna manually via display 805 . this allows for the elimination of a third motor although this motor is optional and may be employed in embodiments that are not power sensitive . the linear polarization axis is the least critical of all of the axial settings , so a little error is acceptable . in addition , the system without a linear polarization axis motor is lower weight . an embodiment using a third axis motor for linear polarization may be manually moved if the motor controller for the linear polarization axis is detected as not working . the system may also be configured for bump detection and reacquisition via the computer housed in positioner base 600 . in this configuration , the system detects when the base or the antenna is bumped and reacquires the satellite . if the satellite signal is still high , then the system returns to a four corner boxing algorithm for example , otherwise the system goes back into half - scan mode where only half the elevation scan lines are checked while checking range of azimuth . with two three - axis accelerometers , one on positioner base 600 and one in antenna housing 601 or coupled with the antenna in antenna housing 601 , both may be used for bump detection . one or more embodiments of the invention allow for a sensor built into changeable antenna or changeable antenna housing 601 . for example , a three - axis accelerometer may be built into the changeable antenna or changeable antenna housing 601 . in addition , the antenna / housing may be configured with memory in the changeable antenna that is used to notify the system what band the antenna is , so the system does not have to perform third axis rotation when not acquiring a satellite that uses linear polarization . for example , if acquiring a ka band military satellite , the antenna panel is read and based on the fact that the ka band antenna is being utilized , a whole set of the correct satellites in the correct band may be presented to the user via display 805 wherein some of all of the previous satellites receivable with the previous antenna are no longer presented . an additional tilt sensor may be utilized in the positioner base for crosschecking with antenna . any redundant positioners may be placed throughout the system in order to provide redundancy and crosschecking capabilities . the system allows for updating tles over the data link acquired . this allows for fresh tles to be used in locating and tracking satellites . the broadcasters may be configured to send down tles that the system uses to automatically update the local tles . after one month , the tles are considered old and if the system is powered up , then it may automatically update the tles if the acquired satellite is configured to broadcast them . the download of ephemeris data or tles may occur before or after two months , or at any time that is convenient as determined by computer house in positioner base 600 or by the operator of the system for example . one ore more embodiments of the invention provide an integrated receiver decoder ( ird ) slot in positioner base 600 . an ird allows for set - top box functionality and may provide channel guide type functionality . the user interface to the ird may include an ird lock function that allows for feedback to the user for tracking qualification . if the ird is integrated into the positioner base , the ird can provide input to the positioner &# 39 ; s computer or a visual display to the user to qualify the satellite as being identified as the desired satellite . in one small area of the sky , there may be five 5 commercial satellites in the field of view , so the system may prompt the user to select next satellite to continue looking for the correct satellite via display 805 or the computer may automatically look to the next satellite . after physically deploying the apparatus , keypad 804 as shown in fig8 may be utilized in order to operate the apparatus . operations accessible from keypad 804 comprise acquire , stop , stow and test and may also include functions for receiving meta data regarding a channel for example a program information such as an electronic program guide for a channel or multiple channels . data received by the apparatus may comprise weather data , data files , real - time video feeds or any other type of data . data may also include tles so that the position information of the satellites is updated . data may be received on command or programmed for receipt at a later time based on the program information metadata . keypad 804 may also comprise buttons or functions that are accessed via buttons or other elements for recording a particular channel , for controlling a transmission , for updating ephemeris or tle data or for password entry , for searching utilizing an azimuth scan or for searching for any satellite within an area to better locate a desired satellite . any other control function that may be activated via keypad 804 may be executed by an onboard or external computer in order to control or receive or send data via the apparatus . asserting the acquire button and selecting a satellite initiates an orbital calculation that determines the location of a satellite for the time acquired via the gps receiver . with the latitude and longitude acquired via gps receiver and the direction north and tilt of the apparatus measured via tilt sensor and magnetometer all of the parameters required to point the antenna towards a desired satellite are achieved . antenna housing 601 is rotated to the desired azimuth via azimuth motor 800 . the antenna in antenna housing 601 is elevated to the desired elevation via elevation motor 802 . the internal rssi receiver may also be used in order to optimize the direction that the antenna is pointing to maximize the signal strength . asserting the stop button on keypad 804 stops whatever task the apparatus is currently performing . this button can be activated prior to activating the stow button . the stow button realigns positioner arm 801 with positioner base 600 and performs a system shutdown . the test button performs internal system tests and may be activated with or without antenna housing 601 deployed . these operations may be modified in certain embodiments or performed remotely by an attached pc or over a wireless network in other embodiments . fig1 shows a flowchart depicting the manufacture of one or more embodiments of the invention which starts at 1100 and comprises coupling an antenna with an elevation motor at 1101 . optionally a cover or antenna housing may be coupled with the antenna ( not shown in fig1 for ease of illustration ). at least one positioning arm is then coupled with the elevation motor at 1102 . the positioning arm is further coupled with an azimuth motor at 1103 . the azimuth motor is then coupled with a positioner base at 1104 . the computer is coupled with the positioner base at 1104 a . the computer is configured for for searching , tracking , bump detection and other functionality when coupled to positioner base , or before or after coupling with positioner base . the positioner base may comprise a hole for allowing environmental elements to fall or leak through the potential well created by the indentation in the base that houses the positioner arm when the antenna housing is closed against the positioner base . the positioner base may optionally comprise a configuration that limits the amount of azimuth travel in order to allow for a smaller or more compact azimuth motor and to cut total weight from the system . the apparatus is delivered to an individual in a configuration that allows for a single person to carry the apparatus at 1105 wherein the manufacture is complete at 1106 . fig1 shows an embodiment of the position base configured with a hole to allow for environmental elements to escape and to also manage heat dissipation of the system . the thermally conductive elements do not require use of a hole and the hole is optional in one or more embodiments of the invention . embodiments of the positioner base may make use of a hole in the base such that water and other environmental elements do not collect in the potential well in the positioner base where the antenna positioning elements are stored . in this embodiment , a thermal well may be employed wherein all of the heat - making components situated in the positioner base , i . e ., the electronics utilized by the system , dissipate heat . thermal well 2001 is shown in the middle of the positioner base . ( in this embodiment thermal well 2001 also includes a hole in the middle of it to allow environmental elements to pass through it . fig1 shows a close - up of thermal well 2001 ( the optional hole can be seen in the middle of thermal well 2001 ). fig1 shows a cross section of thermal well 2001 . when seen from the cross section it becomes clear that thermal well 2001 is actually male thermal conductor 2001 which couples with upper positioner base portion 2010 and prevents environmental contamination via o - rings 2003 a and 2003 b . female thermal conductor 2002 couples to positioner base bottom 2011 . ring 2013 couples to ground plane 2014 of electronic circuit board 2012 . ground plane 2013 is generally highly conductive both thermally and electrically . the hole in male thermal conductor 2001 is optional . heat dissipates through the composite positioner base upper and bottom portions and allows for the internal components to remain as cool as possible . thus embodiments of the invention directed to a portable antenna positioner apparatus and method have been exemplified to one of ordinary skill in the art . the claims , however , and the full scope of any equivalents are what define the metes and bounds of the invention .