Method for calibrating spatial errors, and method and system for estimating the attitude of a vehicle

Patent metadata

Field	Value
Publication number	US-9846243-B2
Application number	US-201314388806-A
Country	US
Kind code	B2
Filing date	Mar 28, 2013
Priority date	Mar 29, 2012
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

Abstract

A method for calibrating spatial errors induced by phase biases having a detrimental effect on the measurements of phase differences of radio signals received by three unaligned receiving antennas of a vehicle. An inter-satellite angular deviation of a pair of satellites is estimated in two different ways: on the basis of the respective positions of the vehicle and of the satellites to obtain a theoretical inter-satellite angular deviation; and on the basis of the respective directions of incidence of the satellites relative to the vehicle, which are determined from phase measurements, to obtain an estimated inter-satellite angular deviation. The space errors are estimated on the basis of said theoretical and estimated inter-satellite angular deviations. Also, a method and system for estimating the attitude of a vehicle, in particular a spacecraft.

First claim

The invention claimed is:

1. A method for of estimating attitude of a craft as a function of measurements of phase differences of radio-electric signals received by at least three non-aligned reception antennas of the craft, comprising steps of:
calibrating spatial errors induced by phase biases affecting measurements of the phase differences of the radio-electric signals received by said at least three non-aligned reception antennas of the craft, said phase biases depending on a direction of incidence of the radio-electric signals with respect to the craft, comprising steps of:
obtaining respective positions of the craft and a pair of satellites situated at a given instant in a radio-electric field of view of the craft;
calculating by at least one processor, an inter-satellite angular distance of said pair of satellites as a function of the respective positions of the craft and said pair of satellites to obtain a theoretical inter-satellite angular distance;
calculating by said at least one processor, respective directions of incidence of said pair of satellites with respect to the craft as a function of phase measurements of radio-electric signals received from said pair of satellites by the three non-aligned reception antennas of the craft;
calculating by said at least one processor, the inter-satellite angular distance of said pair of satellites as a function of the respective directions of incidence of said pair of satellites with respect to the craft to obtain an estimated inter-satellite angular distance; and
calculating by said at least one processor, the spatial errors for the respective directions of incidence of the said pair of satellites with respect to the craft as a function of the theoretical inter-satellite angular distance and of the estimated inter-satellite angular distance determined for said pair of satellites; and

compensating the spatial errors calculated during a calculation of the attitude of the craft.

2. The method as claimed in claim 1 , further comprising the step of calculating the spatial errors in a form of a parametric model whose parameters are estimated as a function of theoretical inter-satellite angular distances and of estimated inter-satellite angular distances determined for pairs of satellites.

3. The method as claimed in claim 2 , further comprising the step of pre-partitioning the radio-electric field of view of the craft into a plurality of distinct cones of incidence of radio-electric signals with respect to the craft; and wherein the spatial errors are considered to be the same for any direction of incidence inside same incidence cone.

4. The method as claimed in claim 3 , wherein the cones of incidence of low elevation with respect to a plane determined by phase centers of the three non-aligned reception antennas of the craft are of smaller respective solid angles than those of cones of incidence of high elevation with respect to said plane.

5. The method as claimed in claim 2 , further comprising the step of calculating the spatial errors in a form of a parametric model whose basis functions are spherical harmonics.

6. The method as claimed in claim 1 , wherein the satellites belong to a global satellite navigation system and the three non-aligned reception antennas are antennas of receivers of said global satellite navigation system; and further comprising the step of determining the respective positions of the satellites and of the craft in accordance with navigation information included in the radio-electric signals received from said satellites.

7. The method as claimed in claim 1 , further comprising the step of calculating the spatial errors in a recursive manner, a pair of satellites by a pair of satellites or a group of pairs of satellites by a group of pairs of satellites.

8. The method as claimed in claim 1 , wherein Ns satellites organized into Np pairs being situated simultaneously in a radio-electric field of view of the craft; and further comprising the step of calculating the spatial errors for each of the respective directions of incidence of the Ns satellites with respect to the craft simultaneously as a function of the theoretical inter-satellite angular distances and of the estimated inter-satellite angular distances determined for said Np pairs of satellites.

9. The method as claimed in claim 1 , further comprising the step of utilizing at least one of: new pairs of satellites entering the radio-electric field of view of the craft in a course of time or a same pair of satellites several times in the course of time.

10. A non-transitory computer readable medium comprising a set of program code instructions, when executed by said at least one processor, implement the steps of calculating attitude of the craft in accordance with the method as claimed in claim 1 .

11. A system to calculate an attitude of a craft as a function of measurements of phase differences of radio-electric signals, comprising:
at least three non-aligned reception antennas on the craft for receiving the radio-electric signals;
a processing unit comprising at least one processor configured to:
obtain respective positions of the craft and a pair of satellites situated at a given instant in a radio-electric field of view of the craft, and calculate an inter-satellite angular distance of said pair of satellites as a function of the respective positions of the craft and said pair of satellites to obtain a theoretical inter-satellite angular distance;
calculate respective directions of incidence of said pair of satellites with respect to the craft as a function of phase measurements of radio-electric signals received from said pair of satellites by the three non-aligned reception antennas of the craft, and calculate the inter-satellite angular distance of said pair of satellites as a function of the respective directions of incidence of said pair of satellites with respect to the craft to obtain a calculated inter-satellite angular distance;
calculate the spatial errors for the respective directions of incidence of the said pair of satellites with respect to the craft as a function of the theoretical inter-satellite angular distance and of the calculated inter-satellite angular distance determined for said pair of satellites; and
compensate the spatial errors calculated during a calculation of the attitude of the craft.

12. The attitude estimation system as claimed in claim 11 , wherein the three non-aligned reception antennas are antennas of receivers of a global satellite navigation system.

13. A spacecraft comprising an attitude estimation system as claimed in claim 11 .

14. The spacecraft as claimed in claim 13 , further comprising a body comprising a plurality of substantially plane external faces; and wherein the three non-aligned reception antennas are arranged on same external face of said body.

Assignees

• Airbus Defence & Space Sas
• Centre Nat D'Etudes Spatiales Cnes

Inventors

• Broquet Renaud
• Polle Bernard
• Montel Johan

Classifications

• G01S19/22

  Multipath-related issues · CPC title

• G01S19/54

  using carrier phase measurements; using long or short baseline interferometry · CPC title

• G01S5/0247

  Determining attitude · CPC title

• G01S19/53

  Determining attitude · CPC title

• G01S5/06

  Position of source determined by co-ordinating a plurality of position lines defined by path-difference measurements (G01S5/12 takes precedence) · CPC title