Propulsion system for controlling the orbit and controlling the attitude of a satellite

Patent metadata

Field	Value
Publication number	US-9573703-B2
Application number	US-201313902678-A
Country	US
Kind code	B2
Filing date	May 24, 2013
Priority date	May 25, 2012
Publication date	Feb 21, 2017
Grant date	Feb 21, 2017

Abstract

A propulsion system for controlling the orbit of a satellite in earth orbit comprises a thruster suitable for delivering a force along an axis F, and a motor-driven mechanism linked on the one hand to the thruster and on the other hand to a structure of the satellite, said motor-driven mechanism being suitable for displacing the thruster on either side of the plane of the orbit and suitable for orienting the thruster so as to make it possible to control a component perpendicular to the orbit of the force in two opposite directions, to control the inclination of the satellite, and in that said motor-driven mechanism is suitable for displacing the thruster along an axis V parallel to the velocity of the satellite, and suitable for orienting the thruster so as to make it possible to control a component of the force on the axis V, to control orbit.

First claim

The invention claimed is:

1. A propulsion system for controlling the orbit of a satellite in earth orbit that has a kinetic moment accumulation capacity, and for the generation of torques helping to control the kinetic moment, said satellite being driven by a displacement velocity tangential to the earth orbit, the propulsion system comprising:
a thruster for delivering a force along an axis F, and a motor-driven mechanism linked at a first end to the thruster and at a second end to a structure of the satellite,
said motor-driven mechanism configured to displace the thruster on either side of the plane of the orbit and configured to orient the thruster so as to make it possible to control a component of the force perpendicular to the orbit in two opposite directions, to control the inclination of the satellite,
said motor-driven mechanism configured to displace the thruster along an axis V parallel to the velocity of the satellite, and configured to orient the thruster so as to make it possible to control:
a component of the force on the axis V, to control orbit,
an amplitude and a direction of torque in a plane perpendicular to the axis F, to control the kinetic moment;
wherein the propulsion system can control six orbital parameters of the satellite, and the motor-driven mechanism includes:
(i) at least five axes of rotation between the structure of the satellite and the thruster,
(ii) at least two rigid offset arms, and
(iii) at least three motor-driven links interconnecting said at least two rigid offset arms with said thruster, and
wherein at least two of the motor-driven links allow rotation about two axes of rotation.

2. The propulsion system according to claim 1 , wherein the at least two rigid offset arms and the at least three motor driven links are positioned in series between the structure of the satellite and the thruster in the following order:
a first motor-driven link, allowing a rotation about an axis (R 1 ) substantially parallel to the axis V,
a first rigid offset arm,
a second motor-driven link, allowing a rotation about an axis (R 3 ) substantially parallel to the axis V, and a rotation about an axis (R 2 ) substantially perpendicular to both the axis V and the axis F,
a second rigid offset arm,
a third motor-driven link, allowing a rotation about an axis (R 4 ) substantially parallel to the axis V, and a rotation about an axis (R 5 ) substantially perpendicular to the axis F and to the axis V.

3. The propulsion system according to claim 1 , wherein the motor-driven mechanism comprises means for supplying energy from the structure of the satellite to the thruster and/or the motor-driven mechanism.

4. The satellite in earth orbit provided with a propulsion system according to claim 1 , wherein the propulsion system is, in a configuration suited to orbit transfer, positioned and oriented in such a way that the force delivered by the thruster generates a thrust on the satellite in a desired direction and a controlled torque; the purpose of the torque generation being to assist in controlling the attitude of the satellite or in controlling the kinetic moment of the satellite.

5. The propulsion system according to claim 1 , wherein the at least two rigid offset arms and the at least three motor driven links are positioned in series between the structure of the satellite and the thruster in the following order:
a first motor-driven link, allowing a rotation about an axis (R 1 ) substantially parallel to the axis V, and a rotation about an axis (R 2 ) substantially perpendicular both to the axis V and to the axis F,
a first rigid offset arm,
a second motor-driven link, allowing a rotation about an axis (R 3 ) substantially parallel to the axis V,
a second offset arm,
a third motor-driven link, allowing a rotation about an axis (R 4 ) substantially parallel to the axis V, and a rotation about an axis (R 5 ) substantially perpendicular to the axis F and to the axis V.

6. The propulsion system according to claim 5 , wherein the third motor-driven link is linked to the thruster via a third rigid offset arm.

7. A satellite in earth orbit provided with a propulsion system according to claim 1 , further comprising a parallelepipedal structure, and the thruster and the motor-driven mechanism are held, in a storage configuration, against one of one or more faces of the structure of the satellite; the thruster and the motor-driven mechanism being released then reoriented in an operational configuration.

8. The satellite in earth orbit according to claim 7 , wherein a first motor-driven link is fastened proximate to a middle of an edge of the structure, and first and second offset arms are held in storage configuration against a face of the structure adjacent to this edge.

9. The satellite in earth orbit according to claim 8 , wherein the first offset arm is held in storage configuration against a first face of the structure, adjacent to this edge, and the second offset arm and the thruster are held in storage configuration against a second face of the structure, adjacent to the first face.

10. The propulsion system according to claim 1 , wherein the at least three motor driven links comprise:
a first motor-driven link, allowing a rotation about an axis substantially parallel to the axis V, and a rotation about an axis substantially perpendicular both to the axis V and to the axis F,
a second motor-driven link, allowing a rotation about an axis substantially parallel to the axis V,
a third motor-driven link, allowing a rotation about an axis substantially parallel to the axis V, and a rotation about an axis substantially perpendicular to the axis F and to the axis V.

11. The propulsion system according to claim 10 , wherein the motor-driven mechanism comprises a first rigid offset arm connecting the first and second motor-driven links and a second offset arm connecting the second and the first motor-driven links.

Assignees

• Thales Sa

Inventors

• Celerier Bruno

Classifications

• F02K9/84 Primary

  using movable nozzles · CPC title

• B64G1/264

  mounted on adjustable booms or the like · CPC title

• B64G1/2429

  Station keeping · CPC title

• B64G1/2425

  Geosynchronous orbits · CPC title

• F05D2270/12

  to maintain desired vehicle trajectory parameters · CPC title