Source: http://www.google.com/patents/US6400319?dq=5,973,252
Timestamp: 2017-05-28 07:00:49
Document Index: 633489479

Matched Legal Cases: ['Application No. 60', 'Application No. 60', 'Application No. 60', '§119', 'arth 21', 'arth 21', 'arth 21', 'arth 21', 'arth 21', 'arth 21', 'arth 21']

Patent US6400319 - Communication network intialization apparatus and method for fast GPS-based ... - Google PatentsSearch Images Maps Play YouTube News Gmail Drive More »Sign inPatentsAn apparatus and method is disclosed, utilizing a communications network (in this particular design, it is a GEM (Geo-Mobile) satellite system) to initialize a Global Positioning System (GPS) receiver (such one integrated into a handheld user terminal, or phone used within the communication network)...http://www.google.com/patents/US6400319?utm_source=gb-gplus-sharePatent US6400319 - Communication network intialization apparatus and method for fast GPS-based positioningAdvanced Patent SearchTry the new Google Patents, with machine-classified Google Scholar results, and Japanese and South Korean patents.Publication numberUS6400319 B1Publication typeGrantApplication numberUS 09/538,050Publication dateJun 4, 2002Filing dateMar 29, 2000Priority dateSep 1, 1998Fee statusPaidAlso published asUS6067045Publication number09538050, 538050, US 6400319 B1, US 6400319B1, US-B1-6400319, US6400319 B1, US6400319B1InventorsMichael Castelloe, Allan Lamkin, Anthony Noerpel, Dave RoosOriginal AssigneeHughes Eelctronics CorporationExport CitationBiBTeX, EndNote, RefManPatent Citations (12), Non-Patent Citations (1), Referenced by (39), Classifications (18), Legal Events (3) External Links: USPTO, USPTO Assignment, EspacenetCommunication network intialization apparatus and method for fast GPS-based positioning
Priority of U.S. Provisional Patent Application No. 60/109,963, filed on Nov. 25, 1998, U.S. Provisional Patent Application No. 60/098,664, filed on Sep. 1, 1998, and U.S. Provisional Patent Application No. 60/098,686, filed on Sep. 1, 1998, is hereby claimed under 35 USC §119 (e).
Typically, a GPS receiver relies on GPS satellite trajectory parameters stored in memory during recent operation, a time estimate from a running clock or user input, and a position estimate from memory or user input to perform a startup faster than a “cold start”. If any of this information is missing, a cold start will be necessary and the time to first fix (TTFF) may be 1-3 minutes.
There are technologies emerging in communication networks, primarily for Emergency-911 systems, such as those developed by Navsys, Inc. and Snaptrack, Inc., that use wholly integrated approaches to determination of terminal positions, meaning that the position determination requires substantial handshaking and cooperation between remote terminals and the network infrastructure. (As used herein, the term “terminal” describes a mobile unit within a communication network, such as a cellular phone.)
μ = 3.986 × 1014 m3/sec2 WGS 84 value of the Earth's
For each received GPS satellite signal, a “code phase offset” at time t must be computed:
Each spot beam 22 in a GEM system has the shape of a cone emitted from the GEM satellite 12. The projection of this cone on the surface of the Earth 21 forms the area served by the spot beam 22. From the satellite perspective, all spot beams 22 are about 0.695° in diameter, i.e., about 0.695° apart if the GEM satellite 12 was in a zero-inclination orbit. Because the GEM satellite 12 moves from about 6° and −6° latitude through the day due to inclined orbit operation, the beamwidth from the satellite perspective will vary to maintain a constant beam “footprint” on the ground. Because of the curvature of the Earth 21, spot beams on the ground have diameters that increase as a function of distance from the subsatellite point. Spot beam diameters can vary between 450 km to more than 1200 km at the far edge of the coverage on the Earth 21. This is shown in FIG. 5.
In the GEM system, the GEM satellite 21 is in a nominal geostationary orbit and consequently appears almost stationary relative to the Earth 21 as compared to a low earth-orbit system. In fact, in the GEM system, the GEM satellite 12 moves between about −6 and 6° latitude through the day due to inclined orbit operation. The GEM satellite 12 is located at approximately 35787 km from the surface of the earth 21. At that altitude, it is permissible to assume a spherical earth with a radius of 6378 km and ignore the altitude of the terminal 18 on the Earth 21. Two possible methods are proposed for user terminal position determination.
The coordinates of the point along axis2 with relative power (diff_power2) equivalent to the measured relative power (max2—power_level) are denoted yu2 and zu2. Similarly, the coordinates of the point along axis3 with relative power (diff_power3) equivalent to the measured relative power (max3—power_level) are denoted yu3 and zu3.
The minimum power level, used to first guess the location of the terminal 18 within the selected spot beam, can vary depending on the satellite inclined orbit. Beam center positions do not change on the ground. The satellite beamwidth is modified to keep the beam center positions fixed on the ground. Consequently, the angle between the center of a beam and the edge of the same beam is not fixed but depends on the satellite position. To calculate the minimum_power_level2 and minimum_power_level3, we first need to calculate the angle between beam1 and beam2 and beam1 and beam3 respectively. Once we get these angles, we can calculate, via the antenna pattern approximation equation, the powers at these angles. The   algorithm   shall   be   perfomed   twice   for   i = 2 , and   i = 3. 1 )   Initialize   the   different   variables  : •   increment = 0.0 ; •   increment 1 = 0.0 ; •   minimum —  power —  level 2 , minimum —  power —  level 3 ; / *  Use   to   first   guess   terminal   location   within  selected   spot   beam .  See   FIG .  8  * / •   maximum —  power —  level = 0.0   dB ; •   diff —  power 2 = diff —  power 3 = 100.0 ;  / *  Temporary  value  * / •   if   ( minimum —  power —  level i < max i —  power —  level <  maximum —  power —  level )  y ui ′″ = y i ′″ / 2 ;  z ui ′″ = z i ′″ / 2 ; else  y ui ′″ = - y i ′″ / 2 ;  z ui ′″ = - z i ′″ / 2 ; 2 )   Perform   position   determination while   ( max i—  power —  level  != diff —  power i ) {  y ui ′″ = y ui ′″ + y i ′″ * increment 1 ;  z ui ′″ = z ui ′″ + z i ′″ * increment 1 ;  H fixed = x sat ′″2 + ( y sat ′″ - y ui ′″ ) 2 + ( z sat ′″ - z ui ′″ ) 2 ;  H 1 = x sat ′″2 + y sat ′″ + z sat ′″ ;  Δ 1 = y ui ′″2 + z ui ′″2 ;  Δϕ 1 = a   cos  ( H 1 2 + H fixed 2 - Δ 1 2 2 * H 1 * H fixed ) ;  H i = x sat ′″2 + ( y sat ′″ - y i ′″ ) 2 + ( z sat ′″ - z i ′″ ) 2 ;  Δ i = ( y i ′″ - y ui ′″ ) 2 + ( z i ′″ - z ui ′″ ) 2 ;  Δϕ i = a   cos  ( H i 2 + H fixed 2 - Δ i 2 2 * H i * H fixed ) ;  Δ   D 1 = 10 * log  [ ( sin  ( 2  π * ap λ  sin  ( Δϕ 1 ) ) 2  π * ap λ  sin  ( Δϕ 1 ) ) 2 ] ;  / *  ap   is   the  aperture = 4.5  m  * /  Δ   D i = 10 * log  [ ( sin  ( 2  π * ap λ  sin  ( Δϕ i ) ) 2  π * ap λ  sin  ( Δϕ i ) ) 2 ] ;  / *  Power   in   dB  * /  diff —  power i = Δ   D 1 - Δ   D i ;  / *  Calculated   relative  power   in   dB  * /  if   ( diff —  power i > max i—  power —  level )  increment 1 = - 1 4 * increment ;  else  increment 1 = 1 4 * increment ;  increment = 2 * increment ; } if   ( ( y u2 ′″  0.0 ) && ( y u3 ′″  0.0 ) ) {  y new ′″ = 0.0 ;  z new ′″ = ( z u2 ′″ + z u3 ′″ ) 2.0 ; else   if   ( ( y u2 ′″  y u3 ′″ ) && ( z u2 ′″  z u3 ′″ ) ) {  y new ′″ = ( y u2 ′″ + y u3 ′″ ) 2.0 ;  z new ′″ = ( z u2 ′″ + z u3 ′″ ) 2.0 } else {  y new ′″ =  ( z 2 ′″ * y 3 ′″ * y u3 ′″ + z u3 ′″ * z 2 ′″ * z 3 ′″ -  y 2 ′″ * z 3 ′″ * y u2 ′″ - z u2 ′″ * z 2 ′″ * z 3 ′″ ) /  ( z 2 ′″ * y 3 ′″ - y 2 ′″ * z 3 ′″ ) ;  z new ′″ = ( ( y 2 ′″ / z 2 ′″ ) * ( y u2 ′″ - y new ′″ ) ) + z u2 ′″ ; } Where ap=4.5 m is the aperture of the satellite, λ≈0.2 m is the wavelength, and H1, Hi, Hfixed, Δ1, Δi, Δφ1, and Δφi are graphically represented in FIG. 9.
2) Map the coordinates from the 2-D plane 100 back to the surface of the earth 21: x new ′ = - B ± B 2 - 4 * A * C 2 * A   where A = 1 + ( y new ″ H ) 2 * ( 1 + ( z new ″ y new ″ ) 2 ) ; B = - 2 * ( R + H ) * ( y new ″ H ) 2 * ( 1 + ( z new ″ y new ″ ) 2 ) ; C = ( R + H ) 2 * ( y new ″ H ) 2 * ( 1 + ( z new ″ y new ″ ) 2 ) - R 2 ; y new ′ = ( R + H - x new ′ ) * ( y new ″ H ) ; z new ′ = ( z new ″ y new ″ ) * y new ′ ; with R=6378 km and H=35787 km.
By performing these transformations, the position search problem was reduced from a 3-D problem to a 2-D problem with y, and z as unknowns. Once these transformation are completed, the user terminal 18 shall first identify the limits of the region where it shall search for its location to further reduce the amount of computations. The user terminal 18 can then start scanning this region. For each y, and z possible combination within that region, the user terminal 18 calculates the relative power from the three strongest spot beams excluding the selected spot beam. If at a certain location y and z, each relative power matches each corresponding relative power measured by the user terminal, a position estimate is found. The relative power between spot beam1 and spot beam2, spot beam3, and spot beam4 is calculated for a certain user terminal position (yu, zu) as follows: H fixed = x sat u ′′′ 2 + ( y sat u ′′′ - y u ′′′ ) 2 + ( z sat u ′′′ - z u ′′′ ) 2 ; H i = x sat i ′″2 + ( y sat i ′″ - y i ″ ) 2 + ( z sat i ′″ - z i ″ ) 2 ; / *  For   i = 1 , 2 , 3 , 4  * / Δ i = ( y i ′″ - y u ′″ ) 2 + ( z i ′″ - z u ′″ ) 2 ; Δϕ = a   cos  ( H i 2 + H fixed 2 - Δ i 2 2 * H i * H fixed ) ; Δ   D i = ( sin ( 2  π * ap λ  sin  ( Δϕ i ) 2  π * ap λ  sin  ( Δϕ i ) ) 2 ; / *  ap = aperature = 4.5   m , λ = wavelength .  Power   in   Watts  * / diff —  power i = Δ   D i Δ   D 1 ;   / *  for   i = 2 , 3 , 4.   Relative power   in   Watts  * / where H1, Hi, Hfixed, Δ1, Δi, Δφ1 and Δφi are graphically represented in FIG. 9.
Patent CitationsCited PatentFiling datePublication dateApplicantTitleUS5412389 *Aug 11, 1993May 2, 1995Motorola, Inc.Multibeam position ambiguity resolutionUS5841396Dec 4, 1996Nov 24, 1998Snaptrack, Inc.GPS receiver utilizing a communication linkUS5874914Mar 8, 1996Feb 23, 1999Snaptrack, Inc.GPS receiver utilizing a communication linkUS5907809 *Sep 20, 1996May 25, 1999Ericsson Inc.Position determination using multiple base station signalsUS5945944Apr 24, 1997Aug 31, 1999Snaptrack, Inc.Method and apparatus for determining time for GPS receiversUS6006067 *Apr 28, 1997Dec 21, 1999MotorolaMethod for a selective call receiver to determine its position and to disregard certain signals from a satelliteUS6052561 *Feb 23, 1998Apr 18, 2000Rudowicz; Michael JamesLocation method for a elective call receiver operating in a satellite communication systemUS6091716 *Jul 1, 1998Jul 18, 2000Motorola, Inc.Receive signal quality estimates suitable for pagers used in satellite-based communication systemsUS6195555 *Jun 24, 1997Feb 27, 2001Ericsson Inc.Method of directing a call to a mobile telephone in a dual mode cellular satellite communication networkUS6233451 *Jul 13, 1998May 15, 2001Hughes Electronics CorporationSpot beam selection in a mobile satellite communication systemWO1997033382A1Mar 7, 1997Sep 12, 1997Snaptrack, Inc.An improved gps receiver utilizing a communication linkWO1998025157A2Nov 20, 1997Jun 11, 1998Snaptrack, Inc.An improved gps receiver utilizing a communication link* Cited by examinerNon-Patent CitationsReference198/5157Referenced byCiting PatentFiling datePublication dateApplicantTitleUS6867734May 15, 2003Mar 15, 2005Motorola, Inc.System and method for frequency management in a communications positioning deviceUS7415353 *May 25, 2004Aug 19, 2008Seiko Epson CorporationSatellite-position table messagingUS7612714Mar 28, 2006Nov 3, 2009Mediatek Inc.Satellite search methodUS7671796 *Dec 1, 2006Mar 2, 2010Mediatek Inc.Satellite search methodUS7786931Jul 12, 2004Aug 31, 2010AlcatelDetermining mobile terminal positions using assistance data transmitted on requestUS7796084Sep 18, 2009Sep 14, 2010Mediatek Inc.Cold start satellite search methodUS7839332Jan 21, 2009Nov 23, 2010Mediatek Inc.Satellite search method and receiver using the sameUS7839333Feb 5, 2009Nov 23, 2010Mediatek Inc.Satellite search method and receiver using the sameUS7920873 *Jan 25, 2005Apr 5, 2011AlcatelAssisted method of locating mobile communications terminals of a cellular network using a USSD transport channelUS8031113Apr 2, 2004Oct 4, 2011Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataUS8432312Aug 19, 2011Apr 30, 2013Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataUS8519887Aug 19, 2011Aug 27, 2013Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataUS8692711Aug 19, 2011Apr 8, 2014Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataUS8711036Aug 19, 2011Apr 29, 2014Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataUS9191913May 23, 2012Nov 17, 2015Eutelsat S AMethod for locating a terminal at the surface of a coverage area by means of a telecommunication network using a multi-beam satelliteUS20030214436 *May 15, 2003Nov 20, 2003Voor Thomas E.System and method for frequency management in a communications positioning deviceUS20050164714 *Jan 25, 2005Jul 28, 2005AlcatelAssisted method of locating mobile communications terminals of a cellular network using a USSD transport channelUS20050278116 *May 25, 2004Dec 15, 2005Mcburney Paul WSatellite-position table messagingUS20060238418 *Jul 12, 2004Oct 26, 2006Michel MonneratDetermining mobile terminal positions using assistance data transmitted on requestUS20070229351 *Mar 28, 2006Oct 4, 2007Mediatek Inc.Cold start satellite search methodUS20070229352 *Dec 1, 2006Oct 4, 2007Mediatek Inc.Satellite search methodUS20070275734 *Apr 2, 2004Nov 29, 2007Peter GaalSystem and Method to Obtain Signal Acquisition Assistance DataUS20090135063 *Jan 21, 2009May 28, 2009Mediatek Inc.Satellite search method and receiver using the sameUS20090179796 *Feb 5, 2009Jul 16, 2009Mediatek Inc.Satellite search method and receiver using the sameUS20100007556 *Sep 18, 2009Jan 14, 2010Mediatek Inc.Cold start satellite search methodCN1833179BJul 12, 2004Jun 6, 2012阿尔卡特公司Determining mobile terminal positions using assistance data transmitted on requestCN100531007CMay 15, 2003Aug 19, 2009摩托罗拉公司(在特拉华州注册的公司)System and method for frequency management in a communications positioning deviceCN101078764BMay 21, 2007Apr 13, 2011联发科技股份有限公司Satellite search methodCN103792555B *Apr 2, 2004Jan 4, 2017高通股份有限公司获得信号捕获辅助数据的系统和方法EP1503220A2 *Jul 12, 2004Feb 2, 2005Alcatel Alsthom Compagnie Generale D'electricitePosition determination of mobile terminals by means of assistance data transmitted on requestEP1503220A3 *Jul 12, 2004Feb 9, 2005Alcatel Alsthom Compagnie Generale D'electricitePosition determination of mobile terminals by means of assistance data transmitted on requestEP1618406A2 *Apr 2, 2004Jan 25, 2006Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataEP1618406A4 *Apr 2, 2004Sep 9, 2009Qualcomm IncSystem and method to obtain signal acquisition assistance dataEP2204666A3 *Apr 2, 2004Nov 17, 2010Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataEP2527862A3 *Apr 2, 2004Jun 26, 2013Qualcomm IncorporatedSystem and method to obtain signal acquisition assistance dataWO2005022189A2 *Jul 12, 2004Mar 10, 2005AlcatelDetermining mobile terminal positions using assistance data transmitted on requestWO2005022189A3 *Jul 12, 2004May 6, 2005Cit AlcatelDetermining mobile terminal positions using assistance data transmitted on requestWO2011123846A1 *Apr 4, 2011Oct 6, 2011Skybitz, Inc.System and method for position determination using low earth orbit satellitesWO2012163744A1 *May 23, 2012Dec 6, 2012Eutelsat S AMethod for locating a terminal at the surface of a coverage area by means of a telecommunication network using a multi-beam satellite* Cited by examinerClassifications U.S. Classification342/457, 342/357.77, 342/357.45International ClassificationG01S1/00, G01S5/00Cooperative ClassificationG01S19/06, G01S19/48, G01S19/05, G01S5/02, G01S19/10, G01S5/0252, G01S2205/008European ClassificationG01S19/10, G01S5/02, G01S5/02D, G01S19/05, G01S19/06, G01S19/48Legal EventsDateCodeEventDescriptionDec 5, 2005FPAYFee paymentYear of fee payment: 4Dec 4, 2009FPAYFee paymentYear of fee payment: 8Dec 4, 2013FPAYFee paymentYear of fee payment: 12RotateOriginal ImageGoogle Home - Sitemap - USPTO Bulk Downloads - Privacy Policy - Terms of Service - About Google Patents - Send FeedbackData provided by IFI CLAIMS Patent Services