US 10,464,694 B1Granted

Asymmetric thruster gimbal configuration

AssigneeSpace Systems/Loral, Inc.

InventorsRobert Erik Schwarz, Jason J. Chiang, Xenophon H. Price, Darren R. Stratemeier, Eric V. Werner

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Abstract

A spacecraft includes at least a first thruster support mechanism (TSM) and a second TSM, each TSM including a pointing arrangement, an elongated structural member and thruster for performing orbit raising north-south stationkeeping, east-west stationkeeping, and momentum management. A first pointing arrangement is articulable only by way of first and second revolute joints, the first revolute joint being rotatable about a first axis fixed with respect to the spacecraft. The second pointing arrangement is articulable only by way of third and fourth revolute joints, the third revolute joint being rotatable about a third axis fixed with respect to the spacecraft. The first axis and the third axis are asymmetrically arranged with respect to a spacecraft coordinate system origin such that the first and third axis are at acute angles to a spacecraft pitch axis and the acute angle of the first axis is less than that of the third axis.

Claims20

Dependent claims

A spacecraft comprising:

a first thruster support mechanism (TSM), including a first pointing arrangement and a first elongated structural member, the first structural member having a long dimension defining a first structural member axis, a proximal portion of the first structural member being attached to the first pointing arrangement, a distal portion of the first structural member being fixed coupled with a first set of one or more thrusters;
and
a second TSM, including a second pointing arrangement and a second elongated structural member, the second structural member having a long dimension defining a second structural member axis, a proximal portion of the second structural member being attached to the second pointing arrangement, a distal portion of the second structural member being fixed coupled with a second set of one or more thrusters;
wherein
the first pointing arrangement is articulable only by way of a first revolute joint and a second revolute joint, the first revolute joint being rotatable about a first axis that is fixed with respect to the spacecraft and the second revolute joint being rotatable about a second axis, the second axis having a substantial component that is orthogonal to each of the first axis and the first structural member axis;
the second pointing arrangement is articulable only by way of a third revolute joint and a fourth revolute joint, the third revolute joint being rotatable about a third axis that is fixed with respect to the spacecraft and the fourth revolute joint being rotatable about a fourth axis, the fourth axis having a substantial component that is orthogonal to each of the third axis and the second structural member axis;
with respect to an orbital plane, in an on-orbit configuration, the spacecraft has a yaw axis disposed within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin, the spacecraft coordinate system origin being located proximal to the spacecraft center of mass;
the first axis and the third axis are asymmetrically arranged with respect to the spacecraft coordinate system origin;
and
the first axis and the third axis are each disposed at an acute angle to the spacecraft pitch axis such that the acute angle of the first axis is less than the acute angle of the third axis.

7 more elements

A method comprising:

raising an orbit of a spacecraft;
and
performing one or more of north-south stationkeeping, east-west stationkeeping, and momentum management;
wherein:
a first thruster support mechanism (TSM), including a first pointing arrangement and a first elongated structural member, the first structural member having a long dimension defining a first structural member axis, a proximal portion of the first structural member being attached to the first pointing arrangement, a distal portion of the first structural member being fixed coupled with a first set of one or more thrusters;
and
a second TSM, including a second pointing arrangement and a second elongated structural member, the second structural member having a long dimension defining a second structural member axis, a proximal portion of the second structural member being attached to the second pointing arrangement, a distal portion of the second structural member being fixed coupled with a second set of one or more thrusters;
wherein
the first pointing arrangement is articulable only by way of a first revolute joint and a second revolute joint, the first revolute joint being rotatable about a first axis that is fixed with respect to the spacecraft and the second revolute joint being rotatable about a second axis, the second axis having a substantial component that is orthogonal to each of the first axis and the first structural member axis;
the second pointing arrangement is articulable only by way of a third revolute joint and a fourth revolute joint, the third revolute joint being rotatable about a third axis that is fixed with respect to the spacecraft and the fourth revolute joint being rotatable about a fourth axis, the fourth axis having a substantial component that is orthogonal to each of the third axis and the second structural member axis;
with respect to an orbital plane, in an on-orbit configuration, the spacecraft has a yaw axis disposed within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin, the spacecraft coordinate system origin being located proximal to the spacecraft center of mass;
the first axis and the third axis are asymmetrically arranged with respect to the spacecraft coordinate system origin;
and
the first axis and the third axis are each disposed at an acute angle to the spacecraft pitch axis such that the acute angle of the first axis is less than the acute angle of the third axis.

11 more elements

Dependencies are inferred from the claim text.