Method of following a transfer orbit or a phase of orbital placement of a space vehicle, in particular an electric propulsion vehicle, and apparatus for the implementation of such a method

Patent metadata

Field	Value
Publication number	US-10054449-B2
Application number	US-201514633512-A
Country	US
Kind code	B2
Filing date	Feb 27, 2015
Priority date	Feb 28, 2014
Publication date	Aug 21, 2018
Grant date	Aug 21, 2018

Abstract

A method of following a transfer orbit or a phase of orbital placement of a continuous-thrust space vehicle comprises the following steps: a) tracking at least one GNSS signal and using it to determine at least one pseudorange between the space vehicle and one or more GNSS satellites transmitting the signal; b) using an estimation model to jointly estimate a set of state parameters of the space vehicle comprising a plurality of position parameters, a plurality of velocity parameters and at least one thrust error parameter characterizing a discrepancy between an actual thrust force of the space vehicle and a nominal thrust force by taking the pseudorange or pseudoranges as input datum of the estimation model. An apparatus for the implementation of such a method is also provided.

First claim

The invention claimed is:

1. A method of following a transfer orbit or a phase of orbital placement of a space vehicle, the phase of orbital placement of a space vehicle being performed using a continuous thrust, the method comprising the following steps:
tracking at least one Global Navigation Satellite System (GNSS) signal and using the at least one GNSS signal to determine at least one pseudorange between said space vehicle and one or more GNSS satellites transmitting said at least one GNSS signal;
using an estimation model to jointly estimate a set of state parameters of said space vehicle, the set of state parameters comprising:
a plurality of position parameters,
a plurality of velocity parameters,
at least one clock parameter, and
at least two continuous thrust error parameters, each of the at least two continuous thrust error parameters characterizing a discrepancy between a direction of an actual continuous thrust force of said space vehicle and a nominal continuous thrust force, and, at one and the same time, an error of estimation of an attitude of said space vehicle,
wherein the using the estimation model includes taking said at least one pseudorange as an input of said estimation model, and said actual continuous thrust force is of an electric type; and

applying, for a determined duration, a thrust nominally directed along a direction linking said space vehicle to a GNSS satellite transmitting the GNSS signal tracked during said tracking step.

2. The method according to claim 1 , wherein said tracking step comprises recovering a navigation message of the one or more GNSS satellites by assistance from a ground station.

3. The method according to claim 2 , wherein said tracking step comprises tracking at least one pilot GNSS signal and not transmitting any navigation message, said tracking of at least one pilot GNSS signal being carried out by a coherent correlation of said at least one pilot GNSS signal.

4. The method according to claim 2 , wherein said tracking step comprises erasing said navigation message recovered by assistance from the ground station.

5. The method according to claim 1 , wherein said set of state parameters further comprises at least one clock error parameter, characterizing an offset or a drift of a clock of a GNSS receiver onboard said space vehicle and used to implement said tracking step.

6. The method according to claim 1 , wherein said estimation model is a Kalman filter or an extended Kalman filter characterized by a transition matrix or function depending on time and on the position of said space vehicle so as to take into account the gravitational forces acting on said space vehicle and a thrust force.

7. The method according to claim 1 , further comprising the following step of using said estimation model and said state parameters to determine corrections of an orbit and/or the thrust of said space vehicle subsequent to an initial determination of orbit and thrust.

8. A method of following a transfer orbit or a phase of orbital placement of a space vehicle, the method comprising the following steps:
tracking at least one Global Navigation Satellite System (GNSS) signal and using the at least one GNSS signal to determine at least one pseudorange between said space vehicle and one or more GNSS satellites transmitting said at least one GNSS signal;
using pseudoranges measured in the past, as well as corresponding estimations of state parameters, to update a covariance matrix of an estimation model;
using the estimation model to jointly estimate a set of state parameters of said space vehicle, the set of state parameters comprising:
a plurality of position parameters,
a plurality of velocity parameters,
at least one clock parameter,
an error of estimation of an attitude of said space vehicle, and
at least two continuous thrust error parameters, each of the at least two continuous thrust error parameters characterizing a discrepancy between a direction of an actual continuous thrust force of said space vehicle and a nominal continuous thrust force, and, at one and the same time, an error of estimation of an attitude of said space vehicle,
wherein the using the estimation model includes taking said at least one pseudorange as an input of said estimation model, and said actual continuous thrust force is of an electric type; and

applying, for a determined duration, a thrust nominally directed along a direction linking said space vehicle to a GNSS satellite transmitting the GNSS signal tracked during said tracking step.

9. The method according to claim 8 , wherein said tracking step comprises recovering a navigation message of the one or more GNSS satellites by assistance from a ground station.

10. The method according to claim 9 , wherein said tracking step comprises tracking at least one pilot GNSS signal and not transmitting any navigation message, said tracking of said at least one pilot GNSS signal being carried out by a coherent correlation of said at least one pilot GNSS signal.

11. The method according to claim 9 , wherein said tracking step comprises erasing said navigation message recovered by assistance from the ground station.

12. The method according to claim 8 , wherein said set of state parameters further comprises at least one clock error parameter, characterizing an offset or a drift of a clock of a GNSS receiver onboard said space vehicle and used to implement said tracking step.

13. The method according to claim 8 , wherein said estimation model is a Kalman filter or an extended Kalman filter characterized by a transition matrix or function depending on time and on the position of said space vehicle so as to take into account the gravitational forces acting on said space vehicle and a thrust force.

14. The method according to claim 8 , further comprising using said estimation model and said state parameters to determine corrections of an orbit and/or a thrust of said space vehicle subsequent to an initial determination of orbit and thrust.

15. A method of following a transfer orbit or a phase of orbital placement of a space vehicle, the method comprising the following steps:
tracking at least one Global Navigation Satellite System (GNSS) signal and using the at least one GNSS signal to determine at least one pseudorange between said space vehicle and one or more GNSS satellites transmitting said at least one GNSS signal;
using an estimation model to jointly estimate a set of state parameters of said space vehicle, the set of state parameters comprising:
a plurality of position parameters,
a plurality of velocity parameters,
at least one clock parameter,
an error of estimation of an attitude of said space vehicle, and
at least two continuous thrust error parameters, each of the at least two continuous thrust error parameters characterizing a discrepancy between a direction of an actual continuous thrust force of said space vehicle and a nominal continuous thrust force, and, at one and the same time, an error of estimation of an attitude of said space vehicle,
wherein the using the estimation model includes taking said at least one pseudorange as an input of said estimation model, and said actual continuous thrust force is of an electric type;

using said at least one GNSS signal, an ephemerides of a GNSS satellite that transmitted the GNSS signal, and a position of the space vehicle estimated by means of said estimation model to estimate a radiation pattern of a transmitting antenna of said GNSS satellite; and
applying, for a determined duration, a thrust nominally directed along a direction linking said space vehicle to a GNSS satellite

Assignees

• Thales Sa

Inventors

• Calmettes Thibaud
• Rozo-Quillere Fabien
• Serant Damien

Classifications

• G01S19/14

  specially adapted for specific applications · CPC title

• G01S19/05

  providing aiding data · CPC title

• G01C21/24 Primary

  specially adapted for cosmonautical navigation · CPC title

• B64G1/007

  Operations & Transport · mapped topic

• G01S19/10

  providing dedicated supplementary positioning signals · CPC title