Method of determining a position using satellites

• US 4,987,420 A
• Filed: 01/05/1990
• Issued: 01/22/1991
• Est. Priority Date: 01/11/1989
• Status: Expired due to Fees

• Current Assignee: Mitsubishi Denki Kabushiki Kaisha (Mitsubishi Electric Corporation)
• Original Assignee: Mitsubishi Denki Kabushiki Kaisha (Mitsubishi Electric Corporation)
• Inventors: Inamiya, Kenichi
• Primary Examiner(s): Hellner, Mark
• Application Number:
  US07/461,536
• Time in Patent Office: 382 Days
• Field of Search: 342/457, 342/357, 342/352
• US Class Current: 342/457
• CPC Class Codes: G01S 5/10 Position of receiver fixed by co-ordinating a plurality of position lines defined by path-difference measurements , e.g. omega or decca systemsG01S5/12 takes precedence ; beacons and receivers cooperating therewith G01S1/306, G01S1/308

Abstract

A method of determining the position of an observation point on the earth using M satellites on a stationary orbit which has a predetermined orbit inclination angle such that N (<M) satelites are in the range of vision of the observation point. One of the N satellites generates a reference signal at a known time. This reference signal is sent directly to the observation point, sequentially relayed by the remaining satellites and transmitted from the respective satellites to the observation point. The observation point measures the differences in time of reception of the signals from the N satellites and determines the positions of the N satellites. The position of the observation point is determined as an intersecting point of the hyperboloids each placing the foci on adjacent two of the satellite positions.

Claims

1. A method of determining the position of an observation point on the earth using M satellites disposed on a predetermined orbit, comprising the steps of:

(a) transmitting a reference signal at a predetermined time from a first of N satellites of the M satellites (N<

M) to the observation point and to an adjacent subsequent N satellite, the orbit having a predetermined orbit inclination angle with respect to the equatorial plane such that the N satellites are simultaneously in the range of vision of the observation point;

(b) causing, in sequential order, the adjacent subsequent N satellite and the remaining N satellites to transmit the reference signal to the observation point and to an adjacent subsequent satellite thereto;

(c) measuring at the observation point the arrival times of the reference signals transmitted from the N satellites;

(d) calculating the orbit position of the N satellites on the basis of the arrival times obtained in said step (c) and estimated values of the orbit position of the satellites within the predetermined orbit provided by a control station on the earth; and

(e) determining at least three hyperboloids each having foci on adjacent two of the calculated orbit positions of the N satellites, whereby the position of the observation point is determined at an intersecting point of the hyperboloids.

2. A method as set forth in claim 1, wherein said step (e) includes the step of calculating the mutual distance between two adjacent satellites of the N satellites.

3. A method as set forth in claim 1, wherein the number M is four.

17. The method as recited in claim 1 wherein the predetermined orbit includes a geosynchronous orbit.

4. A method of determining the position of an observation point on the earth using five or more satellites disposed on a predetermined orbit, comprising the steps of:

(a) transmitting a reference signal at a predetermined time from a first of four satellites of the five or more satellites to the observation point and an adjacent subsequent satellite of the remaining three satellites, the predetermined orbit having the orbit inclination angle within the equatorial plane of substantially 6 degrees such that the four satellites are simultaneously in the range of vision of the observation point and the anomalies of the four satellites are separated from one another substantially at an angle of 120 degrees at the same point of time;

(b) causing, in sequential order, the adjacent subsequent satellite and the remaining two satellites to transmit the reference signal to an adjacent subsequent satellite thereto;

(c) causing, in sequential order, the respective adjacent subsequent satellite and the remaining two satellites to transmit the received reference signal to the observation point;

(d) determining at the observation point the times of reception of the reference signals transmitted from the four satellites;

(e) calculating the orbit positions of the four satellites using the reception times determined in said step (d) and estimated values of the orbit position of the four satellites within a predetermined orbit obtained from a control station on the earth; and

(f) determining three hyperboloids each having foci on adjacent two of the calculated positions of the four satellites, whereby the position of the observation point is determined as an intersecting point of the hyperboloids.

5. A method as set forth in claim 4, wherein said step (a) includes transmitting the reference signal from the first of the four satellites at a time calibrated by the control station.

6. A method as set forth in claim 5, wherein said transmitting step of step (a) includes transmitting the reference signal from the first of the four satellites at a time calibrated by the control station at an integral-second time.

7. A method as set forth in claim 6 further including the steps of calculating the mutual distance between a satellite and an adjacent subsequent satellite and transmitting the calculated results to the observation point.

8. A method as set forth in claim 5, wherein said step (a) comprises:

calibrating a clock means in the first of four satellites by a signal sent from the control station;

in response to the calibrated clock means, transmitting from the first of four satellites a reference signal to the observation point; and

transmitting from the first of four satellites the reference signal to the adjacent subsequent satellite.

18. The method as recited in claim 4 wherein the predetermined orbit includes a geosynchronous orbit.

9. A method of determining the position of an observation point on the earth using five or more satellites disposed on a predetermined orbit, comprising the steps of:

(a) transmitting a synthesized signal including a time signal designating a transmission time and a reference signal synchronized with the time signal, from a first of four adjacent satellites to the observation point and an adjacent subsequent satellite, the predetermined orbit having the orbit inclination angle with the equatorial plane of 6-10 degrees such that the four satellites are simultaneously in the range of vision of the observation point and the anomalies of the four satellites are separated from one another substantially at an angle of 120 degrees at the same point of time;

(b) allowing, in sequential order, the adjacent subsequent satellite and the remaining two satellites to transmit a new synthesized signal including the reference signal and a time signal designating a time at the respective satellite, to the observation point and an adjacent subsequent satellite thereto;

(c) determining at the observation point the times of reception of the signals transmitted from the four satellites;

(d) calculating the orbit positions of the four satellites from the reception times determined in said step (c) and estimated values of the orbit position of the four satellites within the predetermined orbit obtained from the control station on the earth; and

(e) determining three hyperboloids each having the foci on adjacent two of the calculated orbit positions of the four satellites, whereby the position of the observation point is determined as an intersecting point of the hyperboloids.

10. A method as set forth in claim 9, wherein said steps (a) and (b) comprise:

calibrating a clock means for producing a timing signal in the first of four satellites by a command signal sent from the control station;

generating a reference signal for distance measurement;

producing a synthesized signal including the timing signal and the reference signal; and

transmitting from the first of four satellites the synthesized signal to the observation point and the adjacent subsequent satellite.

11. A method as set forth in claim 10 wherein said calibrating step further includes the step of producing the command signal at the control station.

12. A method as set forth in claim 11, wherein said producing step includes the step of producing the command signal on the basis of the time signal contained in the synthesized signal received by the observation point, the calculated positions of the orbits and the estimated values of the orbit positions of the four satellites and the standard time at the control station.

19. The method as recited in claim 9 wherein the predetermined orbit includes a geosynchronous orbit.

13. A method of determining the position of an observation point on the earth using four satellites disposed on a predetermined orbit, comprising the steps of:

(a) transmitting a synthesized signal including a time signal designating a transmission time and a reference signal synchronized with the time signal, from a first of adjacent three satellites to the observation point and to an adjacent subsequent satellite, the predetermined orbit having the orbit inclination angle with the equatorial plane of substantially 6 degrees such that the three adjacent satellites are simultaneously in the range of vision of the observation point and the anomalies of the three satellites are separated from one another substantially at an angle of 120 degrees at the same point of time;

(b) allowing, in sequential order, the adjacent subsequent satellite and the remaining satellite to transmit a new synthesized signal including the synthesized signal and a time signal designating a time at the respective satellite, to the observation point and an adjacent subsequent satellite thereto;

(c) repeating said steps (a) and (b) after the lapse of a period sufficient for detecting the orbit positions of the three satellites;

(d) determining at the observation point the times of reception of the synthesizer signals transmitted from the three satellites in said steps (a) and (b);

(e) calculating the positions of the three satellites when they perform the operations in said steps (a) and (b), using the times determined in said step (d) and estimated values of the orbit position of the three satellites within the predetermined orbit obtained from a control station on the earth; and

(f) determining three hyperboloids each having the foci on adjacent two of the positions of the three satellites calculated in said step (e), whereby the position of the observation point is determined as an intersecting point of the hyperboloids.

14. A method as set forth in claim 13, wherein said steps (a) and (b) comprise:

calibrating a clock means for producing a timing signal in the first of adjacent three satellites by a command signal sent from the control station;

generating a reference signal for distance measurement;

producing a synthesized signal of the timing signal and the reference signal;

transmitting the synthesized signal to the observation point and an adjacent subsequent satellite.

15. A method as set forth in claim 14 wherein said calibrating step further includes a step of producing the command signal at the control station.

16. A method as set forth in claim 15, wherein said producing step includes the step of producing the command signal on the basis of the time signal contained in the synthesized signal received by the observation point, the calculated positions of the orbit and the estimated values of the orbit positions of the respective three N satellites and the standard time at the control station.

20. The method as recited in claim 13 wherein the predetermined orbit includes a geosynchronous orbit.