Articulating sunshield
Techniques for articulating a sunshield to shade portions of a spacecraft are disclosed. In one aspect, a spacecraft includes a body and an articulable sunshield. The spacecraft is configured to operate in an orbital plane, such that the spacecraft has a yaw axis 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 sunshield is configured to rotate about an axis substantially parallel to the pitch axis such that a selected location of an exterior portion of the body is shaded from the Sun by a surface of the sunshield irrespective of seasonal and diurnal variations in orientation of the spacecraft with respect to the Sun.
1. A system comprising:
a spacecraft including a controller, a body and an articulable sunshield; wherein, during operation on-orbit:
the spacecraft is disposed in an orbital plane of a geosynchronous orbit of Earth and has (i) a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, (ii) a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and (iii) a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin;
the sunshield is disposed with respect to a selected location of an exterior portion of the body; and
the controller provides control signals to cause:
rotation of the sunshield about an axis that is substantially parallel to and offset from the pitch axis such that the selected location is shaded from the Sun by a surface of the sunshield irrespective of seasonal and diurnal variations in orientation of the spacecraft with respect to the Sun.
2. The system of claim 1 , wherein the sunshield is mechanically coupled with a counterweight that rotates with the sunshield such that a center of gravity of the spacecraft remains substantially constant during rotation of the sunshield.
3. The system of claim 1 , the controller further configured to provide control signals to cause:
transitioning the sunshield from a launch configuration to an on-orbit configuration, wherein:
in the launch configuration, the surface of the sunshield is substantially parallel to a sidewall of the body, and
in the on-orbit configuration, the surface of the sunshield is substantially orthogonal to the sidewall of the body.
4. The system of claim 1 , wherein the selected location includes a radiator of an infra-red imager.
5. The system of claim 1 , wherein the selected location includes a low noise amplifier (LNA).
6. The system of claim 1 , wherein the spacecraft further comprises a plurality of solar arrays.
7. The system of claim 6 , wherein:
each solar array includes 6 panels;
the selected location is disposed on a north-facing or south-facing sidewall of the body, and a maximum daily thermal load absorbed by the selected location does not exceed 95 Watts per meter squared.
8. A method comprising:
operating a spacecraft in an orbital plane of a geosynchronous orbit of Earth, such that the spacecraft has a yaw axis 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;
deploying a sunshield of the spacecraft such that the sunshield is disposed with respect to a selected location of an exterior portion of the spacecraft; and
rotating the sunshield about an axis that is substantially parallel to and offset from the pitch axis
to shade the selected location from the Sun by a surface of the sunshield irrespective of seasonal and diurnal variations in orientation of the spacecraft with respect to the Sun.
9. The method of claim 8 , wherein the sunshield is mechanically coupled with a counterweight configured to translate during rotation of the sunshield such that a center of gravity of the spacecraft remains substantially constant during rotation of the sunshield.
10. The method of claim 8 , the method wherein deploying the sunshield includes transitioning the sunshield from a launch configuration to an on-orbit configuration, wherein:
in the launch configuration, the surface of the sunshield is substantially parallel to a sidewall of the body, and
in the on-orbit configuration, the surface of the sunshield is substantially orthogonal to the sidewall of the body.
11. The method of claim 8 , wherein the selected location includes a radiator of an infra-red imager.
12. The method of claim 8 , wherein the selected location includes a low noise amplifier (LNA).
13. The method of claim 8 , wherein the spacecraft further comprises a plurality of solar arrays.