Determination of phase ambiguities in satellite ranges
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G01S-005/02
G01S-003/02
출원번호
US-0999099
(1992-12-31)
발명자
/ 주소
Allison Michael T. (Santa Clara CA) Deaver Phillip (Cupertino CA) Dreier Scott (San Francisco CA)
출원인 / 주소
Trimble Navigation Limited (Sunnyvale CA 02)
인용정보
피인용 횟수 :
94인용 특허 :
0
초록▼
A method for accurately determining the position of a roving receiver positioned on or above the Earth\s surface, relative to the position of a reference receiver whose position is known with sufficient accuracy, using measurements of signal phase transmitted at one or more carrier frequencies and r
A method for accurately determining the position of a roving receiver positioned on or above the Earth\s surface, relative to the position of a reference receiver whose position is known with sufficient accuracy, using measurements of signal phase transmitted at one or more carrier frequencies and received from each of four or more satellites in a Satellite Positioning System (SPS). Phase double differences are formed, using the reference and roving receivers and any two satellites drawn from four or more satellites, using phase information obtained from either or both of the two carrier signal frequencies. Phase correction information, in the form of estimates of integer wavelength ambiguities, is then obtained from two sets of ambiguity estimates computed with the roving receiver antenna in each of two specified positions, with the reference receiver antenna lying between and being collinear with the two roving receiver-antenna positions. If the distance between the reference receiver antenna position and the two roving receiver antenna positions is sufficiently small, a set of estimates at only one of the roving receiver positions may suffice. If an azimuth angle measuring device is incorporated in the apparatus, a set of estimates at only one roving receiver position may again suffice. The method produces a set of simultaneous equations that can be solved for the coordinates of a roving receiver located at an arbitrary position. The reference receiver antenna is positioned at a fixed location and orientation while the roving antenna is correctly positioned at each of two specified locations and orientations. A Global Positioning System (GPS) or a Global Orbiting Navigational System (GLONASS) may serve as the SPS.
대표청구항▼
A method for determining and removing the phase integer ambiguities associated with determination of position of a receiver that is part of a Satellite Positioning System, the method comprising the steps of: (1) providing a reference receiver and antenna, denoted receiver number 1, whose antenna pos
A method for determining and removing the phase integer ambiguities associated with determination of position of a receiver that is part of a Satellite Positioning System, the method comprising the steps of: (1) providing a reference receiver and antenna, denoted receiver number 1, whose antenna position r(ref) is known with predetermined accuracy, at a sequence of predetermined times; (2) providing a roving receiver and antenna, denoted receiver number 2, with a first roving receiver antenna position r(rov, +d, L) that is displaced from the reference receiver antenna position by a distance +d in a first direction along a selected line L also containing the reference receiver antenna position, where d need not be determined; (3) providing a plurality of n satellites (n≥4), numbered i=1, 2, . . . , n, at predetermined heights above the Earth\s surface, where each satellite transmits a predetermined signal at a predetermined sequence of times at each of at least two carrier signal frequencies f=fL1 and f=fL2; (4) determining an effective signal frequency fcp=a1fL1+a2fL2=c/lcp, expressed as a selected linear combination of the two carrier frequencies fL1=c/lL1 and fL2=c/lL2, for the Satellite Positioning System, where c is the velocity of light and lcp is the corresponding effective wavelength; (5) determining a phase integer estimate Ne;i,i′;j,j′(1) for the roving receiver located at a first roving receiver antenna position r(rov, +d, L), for satellites number i and i′and receivers number j and j′from the relation Ne;i,i′;j,j′(1)=Di,i′;j,j′(1)/lcp+Fi,i′;j,j′;cp(1), where Di,i′;j,j′(1) is a double difference range value defined by the relation Di,i′;j,j′(1)=(Ri,j(1)-Ri′,j(1))-(Ri,j′(1)-Ri′,j′(1) ), and Ri,j(1) is the theoretical range or distance from receiver number j to satellite number i for the first roving receiver antenna position, assuming that d�0 for this determination, and Fi,i′;j,j′;cp(1) is a phase variable determined by the relation Fi,i′;j,j′;cp(1)=[bi,j;cp(1)-bi′,j;cp(1)]-[bi,j′;cp(1)-bi′,j′;cp(1)], where bi,j;cp(1) is an effective phase, measured from satellite number i to receiver number j of a carrier signal with effective frequency fcp; (6) determining a phase integer estimate Ne;i,i′;j,j′(2) for the roving receiver located at a second roving receiver antenna position r(rov, -d, L), for satellites number i and i′and receivers number j and j′from the relation Ne;i,i′;j,j′(2)=Di,i′;j,j′(2)/lcp+Fi,i′;j,j′;cp(2), where Di,i′;j,j′(1) is a double difference range value defined by the relation Di,i′;j,j′(2)=(Ri,j(2)-Ri′,j(2))-(Ri, j′(2)-Ri′,j′(2)), and Ri,j(2) is the theoretical range or distance from receiver number j to satellite number i for the first roving receiver antenna position, assuming that d=0 for this determination, and Fi,i′;j,j′;cp(2) is a phase variable determined by the relation Fi,i′;j,j′;cp(2)=[bi,j;cp(2)-bi′,j;cp(2)]-[bi,j′;cp(2)-bi′j′;cp(2)], where bi,j;cp(2) is an effective phase, measured from satellite number i to receiver number j of a carrier signal with effective frequency fcp; and (7) determining the desired phase integers Ni,i′;j,j′for the reference and roving receiver antennas by the relations Ni,i′;j,j′=floor[(Ne;i,i′;j,j′(1)+Ne;i,i′;j,j′(2))/2+0.5].
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