Method for calculating instantaneous characteristics of a satellite in orbit, equipped with a GNSS receiver

• US 6,882,908 B2
• Filed: 09/14/2001
• Issued: 04/19/2005
• Est. Priority Date: 09/15/2000
• Status: Expired due to Term

• Current Assignee: Centre National D'Etudes Spatiales
• Original Assignee: Centre National D'Etudes Spatiales
• Inventors: Laurichesse, Denis
• Primary Examiner(s): Black, Thomas G.
• Assistant Examiner(s): Gibson, Eric M.
• Application Number:
  US10/363,696
• Publication Number:
  US 20040064222A1
• Time in Patent Office: 1,313 Days
• Field of Search: 701/13, 701/210, 701/213, 701/214, 701/215, 342/357.06, 342/357.12, 342/357.15, 342/357.16, 342/358
• US Class Current: 701/13
• CPC Class Codes: G01S 19/40 Correcting position, velocity or attitude
• CPC Class Codes: G01S 19/50 whereby the position solution is constrained to lie upon a particular curve or surface, e.g. for locomotives on railway tracks

Abstract

A method for calculating instantaneous characteristics of a satellite in orbit equipped with a GNSS receiver, capable of performing measurements of pseudo-distance, when fewer than four transmitters are simultaneously in visibility. This method pre-processes quantities measured by the receiver to deliver measurements of pseudo-distance, pseudo-speed and instantaneous pseudo-accelerations, mathematically processes the measured quantities, enhanced by knowledge of complementary data concerning the orbit of the satellite and the receiver, delivering plural solutions, and physically filters the solutions to deliver position and speed of the satellite and clock bias and drift of the receiver.

Claims

1. A method for calculating instantaneous characteristics of a satellite in orbit, equipped with a GNSS receiver, capable of performing measurements of pseudo-distance, when fewer than four transmitters are in simultaneous visibility, comprising:

pre-processing quantities measured by the receiver to deliver measurements of pseudo-distance, pseudo-speed, and instantaneous pseudo-accelerations, said pseudo-accelerations derived from pseudo-speeds measured close in time;

mathematically processing the measured quantities, enhanced by knowledge of complementary data concerning the orbit of the satellite and the receiver, delivering plural solutions;

physically filtering the plural solutions for delivering position and speed of the satellite and clock bias and drift of the receiver.

2. The method as claimed in claim 1, wherein, during the pre-processing, measurement of instantaneous pseudo-speed is calculated either by differentiation of two measurements of pseudo-distances close in time:

$\mathrm{Pv}=\frac{\mathrm{Pd2}-\mathrm{Pd1}}{\mathrm{\Delta <br><br>}<br><br>\text{\hspace{1em}<br><br>}<br><br>T},$

Δ

T being a time spread between two measurements Pd1 and Pd2, or by utilization of phase measurements, if available.

3. The method as claimed in claim 1, wherein, during the pre-processing, measurement of the instantaneous pseudo-acceleration is calculated by either differentiation of two instantaneous measurements of the pseudo-speeds close in time:

$P<br><br>\text{\hspace{1em}<br><br>}<br><br>a=\frac{\mathrm{Pv2}-\mathrm{Pv1}}{\mathrm{\Delta <br><br>}<br><br>\text{\hspace{1em}<br><br>}<br><br>T},$

Δ

T being a time spread between the two measurements Pv1 and Pv2, or by utilization of phase measurements, if available.

4. The method as claimed in claim 1, wherein, during the mathematically processing, the plural solutions include:

position of the satellite {right arrow over (P)},

speed of the satellite {right arrow over (v)};

clock bias of the receiver b;

clock frequency shift of the receiver $\frac{\mathrm{\Delta <br><br>}<br><br>\text{\hspace{1em}<br><br>}<br><br>f}{f}.$

5. The method as claimed in claim 1, wherein, during the physically filtering, for a satellite in low orbit meniscal axis a of the plural solutions is considered limited:

6400 Km<

a<

8400 Km.

6. The method as claimed in claim 1, wherein, during the physically filtering, absolute value of the clock frequency shift of the receiver is considered limited:

for a low-quality oscillator;

$<br><br>\frac{\mathrm{\Delta <br><br>}<br><br>\text{\hspace{1em}<br><br>}<br><br>f}{f}<br><br><<br><br>300<br><br>\text{\hspace{1em}<br><br>}<br><br>m<br><br>\text{/}<br><br>s$

for a good-quality oscillator;

$<br><br>\frac{\mathrm{\Delta <br><br>}<br><br>\text{\hspace{1em}<br><br>}<br><br>f}{f}<br><br><<br><br>10<br><br>\text{\hspace{1em}<br><br>}<br><br>m<br><br>\text{/}<br><br>s.$

7. The method as claimed in claim 1, wherein, during the physically processing, a reference inclination of the satellite is considered.

8. The method as claimed in claim 7, wherein the inclination of the satellite is the nearest to the reference inclination.

9. The method as claimed in claim 1, wherein, during the physically processing, the satellite is in radio-electric visibility of each transmitter.

10. The method as claimed in claim 1, wherein at least one transmitter is a satellite.

11. The method as claimed in claim 1, wherein at least one transmitter is a terrestrial station.