Dayside-only roll steering
A method of roll steering of a spacecraft to align an aspect of the spacecraft, such as the surface of solar arrays carried by the spacecraft, to the sun, is described. The roll steering occurs only when the sun is at an angle (β) relative to the orbital plane of the spacecraft and when the spacecraft is not eclipsed by a body it is orbiting. This dayside-only roll steering of the spacecraft increases the power efficiency of the spacecraft. A spacecraft may include a controller which causes an attitude control subsystem to steer the spacecraft about a roll axis to position the surface of the solar array such that an axis normal to the surface of the solar array is aligned with the direction to a sun when the sun is visible to the spacecraft, and maintain a fixed orientation of the spacecraft about the roll axis when the sun is not visible to the spacecraft.
1. A method of orienting a spacecraft that orbits about a primary body, the spacecraft having a solar array having a surface, comprising: establishing an orbital path of the spacecraft about the primary body, the spacecraft having a direction of orbital motion having along the orbital path; determining a portion of the orbital path during which the spacecraft is in eclipse; and roll steering the spacecraft about an axis in the direction of orbital motion to position the surface of the solar array such that an axis normal to the surface of the array is aligned at a minimum roll angle with respect to the direction to a sun only when the spacecraft is not in eclipse by selectively applying a force to the spacecraft that rotates the spacecraft body about the axis in the direction of orbital motion, wherein the method further includes maintaining a fixed attitude of the spacecraft when the spacecraft is in eclipse.
2. The method of claim 1 wherein the orbital path forms an orbital plane and a Beta angle is formed between the orbital plane and a ray from the primary body in a direction to the sun, and the roll angle is determined by the Beta angle.
3. The method of claim 1 wherein the roll steering has a maximum roll rate magnitude about the axis in the direction of orbital motion which is relatively constant for all Beta angles.
4. The method of claim 1 wherein the roll steering has a maximum roll acceleration about an axis in the direction of orbital motion which is relatively constant for all Beta angles.
5. The method of claim 1 wherein the method includes performing spacecraft maneuvers at any time in a forward and aft direction along the axis in the direction of orbital motion while roll steering is performed.
6. The method of claim 1 wherein the orbit has an orbital period, wherein the orbital path forms an orbital plane and a Beta angle is formed between the orbital plane and an axis from the orbital body toward the sun, and roll steering is suspended when the Beta angle magnitude is less than a threshold value.
7. A method of rotating a body of a spacecraft with solar arrays around a roll axis comprising an axis in a direction of orbital motion of the spacecraft, an orbital motion following an orbital path defining an orbital plane, the method comprising:
determining a portion of the orbital path during which the spacecraft is in eclipse by a primary body; and
steering the spacecraft about the roll axis to position a surface of a solar array of the spacecraft such that an axis normal to the surface of the solar array is aligned in a direction to a sun when the sun is visible to the spacecraft by selectively applying a force to the spacecraft that rotates the body of the spacecraft about the roll axis; and
maintaining a fixed orientation of the spacecraft about the roll axis when the sun is not visible to the spacecraft.
8. The method of claim 7 wherein the orbital path forms an orbital plane and a Beta angle is formed between the orbital plane and a ray from the primary body in a direction to the sun, and the steering has a maximum roll rate magnitude about the roll axis which is relatively constant for all Beta angles.
9. The method of claim 7 wherein the orbital path forms an orbital plane and a Beta angle is formed between the orbital plane and a ray from the primary body in a direction to the sun, and the steering has a maximum roll acceleration about roll axis which is relatively constant for all Beta angles.
10. The method of claim 7 wherein the method includes performing spacecraft maneuvers at any time in a forward and aft direction along the roll axis in the direction of orbital motion while roll steering is performed.
11. The method of claim 1 wherein the orbital path forming an orbital plane and having an orbital period, and wherein the roll steering is suspended when the orbital plane and an axis between the primary body and the sun form a Beta angle which has a magnitude less than threshold value.
12. A spacecraft, comprising:
a solar array having at least one surface;
a propulsion subsystem;
an attitude control subsystem; and
a controller connected to the propulsion subsystem and an inertial control subsystem, the controller configured to cause the propulsion subsystem and inertial control subsystem to propel the spacecraft along an orbital path in orbital motion around a primary body, and the controller configured to cause the attitude control subsystem to rotate the spacecraft around a roll axis comprising an axis in a direction of orbital motion of the spacecraft, the orbital motion defining an orbital plane, the controller causing the inertial control subsystem to
steer the spacecraft about the roll axis to position the surface of the solar array such that an axis normal to the surface of the solar array is at a minimum angle in the direction to a sun when the sun is visible to the spacecraft; and
maintain a fixed orientation of the spacecraft about the roll axis when the sun is not visible to the spacecraft.
13. The spacecraft of claim 12 wherein the orbital path forms an orbital plane and an axis between the primary body and the sun form a second angle, and the roll angle is determined by the second angle.
14. The spacecraft of claim 12 wherein the controller configured to cause the attitude control subsystem to rotate the spacecraft at a maximum roll rate magnitude about the roll axis which is relatively constant for all roll angles.
15. The spacecraft of claim 12 wherein the orbital path forms an orbital plane and a Beta angle is formed between the orbital plane and a ray from the primary body in a direction to the sun, and the controller configured to cause the attitude control subsystem to rotate the spacecraft at a maximum roll rate acceleration about the roll axis which is relatively constant for all Beta angles.
16. The spacecraft of claim 12 wherein the controller configured to cause the inertial control subsystem and the propulsion control subsystem to perform spacecraft maneuvers at any time in a forward and aft direction along the orbital path the direction of orbital motion while the controller causing the attitude control subsystem to steer the spacecraft about the roll axis.
17. The spacecraft of claim 12 wherein the orbit has an orbital period, wherein the orbital path forms an orbital plane and a Beta angle is formed between the orbital plane and an axis from the primary body toward the sun, and wherein the controller configured to cause the attitude control subsystem to suspend the steering when the magnitude of the Beta angle is less than about 10 degrees.
18. The spacecraft of claim 13 wherein the orbit has an orbital period, wherein the orbital path forms an orbital plane and a Beta angle is formed between the orbital plane and an axis from the primary body toward the sun, and wherein the controller configured to cause the attitude control subsystem to suspend the steering when the magnitude of the Beta angle is less than about 10 degrees.