Ionospheric correction for single frequency GPS receivers using two satellites

• US 6,163,295 A
• Filed: 04/09/1999
• Issued: 12/19/2000
• Est. Priority Date: 04/09/1999
• Status: Expired due to Fees

• Current Assignee: Mitsubishi Electric & Electronics USA Incorporated (Mitsubishi Electric Corporation)
• Original Assignee: Vsis, Inc.
• Inventors: Usman, Mohammad, Sun, James, Nagasamy, Vijay
• Primary Examiner(s): Tarcza, Thomas H.
• Assistant Examiner(s): PHAN, DAO LINDA
• Application Number:
  US09/289,216
• Time in Patent Office: 620 Days
• Field of Search: 342/357.01, 342/357.06, 342/357.09, 342/457, 701/207, 701/213
• US Class Current: 342/357.59
• CPC Class Codes: G01S 19/40 Correcting position, velocity or attitude
• CPC Class Codes: G01S 19/426 by combining or switching between position solutions or signals derived from different modes of operation in a single system

Abstract

Systems and methods are disclosed for ionospheric correction in a system employing a single GPS frequency receiver for determining the geographic location of an object on the earth'"'"'s surface. The receiver receives signals transmitted at the GPS L₁ frequency from at least first and second GPS satellites, the first and second satellites having respective orbital positions relative to the receiver such that the total electron count (TEC) contribution to ionoshperic interference to signals transmitted by the respective satellites and received by the receiver is approximately the same. Respective measured distances of the two satellites to the receiver are determined based on the actual signal transmission times. True distances of the respective satellites are then calculated based on the assumption that the TEC contribution to the interference from each satellite is approximately the same.

Claims

1. A method using satellite signal transmission for determining the geographic location of a receiver on the earth'"'"'s surface, comprising:

receiving a first signal transmitted at a known frequency from a first satellite having a known orbital position;

receiving a second signal transmitted at the same frequency as the first signal from a second satellite having a known orbital position;

calculating measured distances λ

¹ and λ

² of the respective first and second satellites from the receiver based at least in part on the transmission times of the first and second signals; and

calculating actual distances ρ

¹ and ρ

² of the respective first and second satellites from the receiver based on the measured distances λ

¹ and λ

², according to the relationships ##EQU14## where .o slashed. is the angle formed between a first vector extending from the receiver to the first satellite and a second vector extending from the receiver to the second satellite, the respective first and second vectors determined by the measured distances λ

¹ and λ

²,

ρ

^1-2 is the distance between the first and second satellites as determined by the measured distances λ

¹ and λ

², and

where F_pp¹ and F_pp² are obliquity factors for the first and second satellites based on the respective angles φ

₁ and φ

₂ they form with a plane tangent to the earth'"'"'s surface at the geographic location of the receiver, with ##EQU15## where R_e is the radius of the earth and H_r is the height of maximum electron density in the ionosphere surrounding the earth'"'"'s surface.

2. The method of claim 1, wherein the first and second satellites are global positioning system (GPS) satellites.

3. The method of claim 2, wherein the first and second signals are transmitted at the GPS L₁ signal frequency.

4. The method of claim 1, wherein the first and second satellites have respective orbital positions relative to the receiver such that the total electron count (TEC) contribution to ionoshperic interference to the transmission of the first and second signals is approximately the same.

5. A system for determining the geographic location of objects on the earth'"'"'s surface, comprising:

a receiver configured to receive signals transmitted at a selected frequency from first and second satellites having known orbital positions, the receiver further configured to

calculate measured distances λ

¹ and λ

² of the respective first and second satellites from the receiver based at least in part on the transmission times of the received signals, and

calculate actual distances ρ

¹, and ρ

² of the respective first and second satellites from the receiver based on the measured distances λ

¹ and λ

², according to the relationships ##EQU16## where .o slashed. is the angle formed between a first vector extending from the receiver to the first satellite and a second vector extending from the receiver to the second satellite, the respective first and second vectors determined by the measured distances λ

¹ and λ

²,

ρ

^1-2 is the distance between the first and second satellites as determined by the measured distances λ

¹ and λ

², and

where F_pp¹ and F_pp² are obliquity factors for the first and second satellites based on the respective angles φ

₁ and φ

₂ they form with a plane tangent to the earth'"'"'s surface at the geographic location of the receiver, with ##EQU17## where R_e is the radius of the earth and H_r is the height of maximum electron density in the ionosphere surrounding the earth'"'"'s surface.

6. The system of claim 5, wherein the first and second satellites are global positioning system (GPS) satellites.

7. The system of claim 6, wherein the first and second signals are transmitted at the GPS L₁ signal frequency.

8. The system of claim 5, wherein the first and second satellites have respective orbital positions relative to the receiver such that the total electron count (TEC) contribution to ionoshperic interference to the transmission of the first and second signals is approximately the same.

9. A system for determining the geographic location of objects on the earth'"'"'s surface, comprising:

a single frequency global positioning system (GPS) receiver configured to receive signals transmitted at the GPS L₁ frequency from first and second GPS satellites, the receiver and first and second satellites having synchronized clocks, the first and second satellites having respective orbital positions relative to the receiver such that the total electron count (TEC) contribution to ionaspheric interference to signals transmitted by the respective satellites and received by the receiver is approximately the same, the receiver further configured to

calculate measured distances λ

_L1^GPS2 and λ

_L1^GPS2 of the respective first and second satellites from the receiver based at least in part on the transmission times of the received signals, and

calculate actual distances ρ

^GPS1 and ρ

^GPS2 of the respective first and second satellites from the receiver based on the measured distances λ

_L1^GPS1 and λ

_L1^GPS2, according to the relationships ##EQU18## where .o slashed. is the angle formed between a first vector extending from the receiver to the first satellite and a second vector extending from the receiver to the second satellite, the respective first and second vectors determined by the measured distances λ

_L1^GPS1 and λ

_L1^GPS 2,

ρ

^GPS1-2 is the distance between the first and second satellites as determined by the measured distances λ

_L1^GPS1 and λ

_L1^GPS2, and

where F_pp^GPS1 and F_pp^GPS2 are obliquity factors for the first and second satellites based on the respective angles φ

₁ and φ

₂ they form with a plane tangent to the earth'"'"'s surface at the geographic location of the receiver, with ##EQU19## where R_e is the radius of the earth and H_r is the height of maximum electron density in the ionosphere surrounding the earth'"'"'s surface.