[미국특허]
Differential position determination using satellites
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
H04B-007/185
G01S-005/02
출원번호
US-0722512
(1991-06-27)
발명자
/ 주소
Allison Michael T. (Santa Clara CA)
출원인 / 주소
Trimble Navigation (Sunnyvale CA 02)
인용정보
피인용 횟수 :
130인용 특허 :
0
초록▼
A method for accurately determining the position of a roving signal 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 ranging information, transmitted at a pair of predetermined carrier signal
A method for accurately determining the position of a roving signal 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 ranging information, transmitted at a pair of predetermined carrier signal frequencies and received from each of n satellites (n≥4). Pseudorange double differences are formed, between each of the two receivers and each of a first satellite and the other three satellites, using pseudorange information obtained from either one of the two signal frequencies. Phase correction information, in the form of estimates of integer lane wavelength ambiguities, is then obtained from the pseudorange double differences and from certain measurable phase differences. This products n-1 simultaneous equations that can be solved for the roving receiver position cordinates. The method can be adapted to provide roving receiver position when signals carried by both of the two carrier frequencies are encrypted, where a separate non-encrypted signal is available on one of the two carrier frequencies.
대표청구항▼
A method for determining the position of a radio signal receiver located on or above the Earth\s surface, the method comprising the steps of: (1) providing a roving receiver whose position is to be determined at a sequence of predetermined times; (2) providing a reference receiver whose position is
A method for determining the position of a radio signal receiver located on or above the Earth\s surface, the method comprising the steps of: (1) providing a roving receiver whose position is to be determined at a sequence of predetermined times; (2) providing a reference receiver whose position is known with sufficient accuracy at the sequence of predetermined times; (3) providing a plurality of n satellites (n≥4), numbered j=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 two carrier frequencies f=fL1 and f=fL2; (4) determining a plurality of n theoretical distance values R1,1,R2,1, . . . , Rn,1 from each of the satellites to the roving receiver at the sequence of predetermined times, where each theoretical distance value is determined from a knowledge of the position of a satellite and an approximate knowledge of the position of the roving receiver; (5) determining a plurality of n theoretical distance values R1,2,R2,2, . . . , Rn,2 from each of the satellites to the reference receiver at the sequence of predetermined times, where each theoretical distance value is determined from a knowledge of the position of a satellite and of the position of the reference receiver, where the position of the reference receiver is known with sufficient accuracy at each of the predetermined sequence of times; (6) forming theoretical range double difference values Di,i′;j,j′(i,i′=1,2; i=i′; j,j′=2,3,4; j=j′), defined by the relations Di,i′;j,j′=(Ri,j-Ri′,j)-(Ri,j′-Ri′,j′) for the pair of satellites i and i′and the pair of receivers j and j′; (7) determining a characteristic wavelength lDL1-fL2), where c is the velocity of light; (8) measuring first and second phase variables, denoted ba,b;Lk(k=1 and 2) from observations of the phase of a signal sent by transmitter number a and received by receiver number b (a=i or i′; b=j or j′) with carrier frequency f=fLk; (9) forming a third phase variable bDba,b;L1-ba,b;L2; (10) forming a fourth phase variable fDfDbDbDbDbD11) measuring a pseudorange ra,b;Lk=c(tb-ta), where ta is the uncorrected time a given signal is transmitted by satellite a,tb is the uncorrected time the given signal is received by receiver b, c is the speed of light, and the satellite transmits the given signal using the carrier frequency f=fLk(a=i,i′;b=j,j′; k=1 or 2); (12) forming unfiltered pseudorange double difference values Dri,i′;j,j′;Lk defined by the relations Dri,i′;j,j′;Lk=(ri,j; Lk-ri′,j;Lk)-(ri,j′;Lk-ri′;j′:Lk); (13) determining a fifth phase variable Ni,i′;j,j′by the relations Ni,i′;j,j′=Dri,i′;j,j′;Lk/lDfD1, j=1 and j′=2; (14) determining the values of the n-1 fifth phase variables N1,i′;1,2(i′=2, . . . , n) for a sequence of samples determined at the predetermined sequence of times; (15) filtering the sequence of samples of the fifth phase variables N1,i′;1,2 for each value of i′=2, . . . , n to determine a filtered fifth phase variable N1,i′;1,2(f), in order to remove or minimize the effects of noise on the fifth phase variable; and (16) solving the n-1 simultaneous equations given by fD=-D1,i′;1,2/lD+N1,i′;1,2(f), (i′=2, . . . , n) to obtain position coordinates (x1,y1,z1) of the roving receiver when the coordinates (x2,y2,z2) of the reference receiver are known are known with sufficient accuracy.
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