High capacity spacecraft
View Patent ↗A spacecraft includes a first deployable module and a second deployable module and is reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable module is adjacent to the second deployable module. The first deployable module includes a first solar array, the first solar array being rotatable, in the on-orbit configuration, about a first axis of rotation, and the second deployable module includes a second solar array, the second solar array being rotatable, in the on-orbit configuration, about a second axis of rotation, the second axis of rotation being separated by a substantial distance from the second axis of rotation.
1. A spacecraft comprising:
a first deployable module and a second deployable module, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration; wherein:
in the launch configuration, the first deployable module is adjacent to the second deployable module;
with respect to an orbit plane, in the on orbit configuration, the spacecraft has a yaw (Z) axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch (Y) axis orthogonal to the orbit plane and passing through the spacecraft coordinate system origin, and a roll (X) axis orthogonal to the Y axis and the Z axis and passing through the spacecraft coordinate system origin;
the first deployable module includes a first solar array, the first solar array being rotatable, in the on-orbit configuration, about a first axis of rotation parallel to the Y-axis, and the second deployable module includes a second solar array, the second solar array being rotatable, in the on-orbit configuration, about a second axis of rotation parallel to the Y-axis, the second axis of rotation being separated by a substantial distance, in a direction transverse to one or both of the first axis and the second axis, from the first axis of rotation; and
in the on-orbit configuration, neither the first solar array nor the second solar array cross a plane defined by the X axis and the Z axis.
2. The spacecraft of claim 1 , further comprising a central structural portion, wherein:
in the launch configuration, both the first deployable module and the second deployable module are disposed forward of the central structural portion; and
in the on orbit configuration, the central structural portion is disposed approximately between the first deployable module and the second deployable module.
3. The spacecraft of claim 2 , wherein one or both of the first deployable module and the second deployable module is hingedly coupled with the central structural portion.
4. The spacecraft of claim 2 , wherein one or both of the first deployable module and the second deployable module is slidably coupled with the central structural portion.
5. The spacecraft of claim 1 , wherein a transition between the launch configuration and the on orbit configuration includes a rotary motion of one or both of the first deployable module and the second deployable module.
6. The spacecraft of claim 1 , wherein a transition between the launch configuration and the on orbit configuration includes a linear motion of one or both of the first deployable module and the second deployable module.
7. The spacecraft of claim 1 , wherein reconfiguring from the launch configuration to the on-orbit configuration includes imparting relative motion to the first deployable module and the second deployable module, an initial direction of the relative motion being substantially orthogonal to adjacent surfaces of the first deployable module and the second deployable module.
8. The spacecraft of claim 1 , wherein reconfiguring from the launch configuration to the on-orbit configuration includes imparting a relative motion to the first deployable module and the second deployable module, an initial direction of the relative motion being substantially parallel to adjacent surfaces of the first deployable module and the second deployable module.
9. The spacecraft of claim 1 , wherein,
reconfiguring from the launch configuration to the on-orbit configuration includes imparting relative motion to the first deployable module and the second deployable module whereby an effective length of the spacecraft along the roll axis is increased.
10. The spacecraft of claim 9 , wherein:
at least one of the first deployable module and the second deployable module includes a first sidewall area and a third sidewall area substantially disposed, in the on-orbit configuration, orthogonal to the pitch axis and facing toward opposite directions; and a second sidewall area and a fourth sidewall area substantially disposed, in the on-orbit configuration, respectively, orthogonal to the roll axis; and
a first combined area of the first sidewall area and the third sidewall area is substantially larger than a second combined area of the second sidewall area and the fourth sidewall area.
11. The spacecraft of claim 10 , wherein the first combined area is at least two times as large as the second combined area.
12. The spacecraft of claim 1 , wherein each of the first deployable module and the second deployable module includes a respective payload element.
13. The spacecraft of claim 1 , wherein
at least a portion of each the first deployable module and the second deployable module has a substantially ‘U’ shaped configuration, including a central recess, and two outboard segments; and
at least one outboard segment of the first deployable module is disposed, in the launch configuration, within the central recess of the second deployable module.
14. The spacecraft of claim 1 , wherein:
the spacecraft includes an aft surface including a launch vehicle adapter; and
in the on orbit configuration, the spacecraft is oriented with the aft surface and at least one payload element disposed so as to be Earth facing.
15. The spacecraft of claim 1 , wherein:
the spacecraft includes an aft surface including a launch vehicle adapter; and
in the on orbit configuration, the spacecraft is disposed such that a normal to the aft surface is substantially parallel to the first axis of rotation.
16. The spacecraft of claim 1 , wherein:
pressure due to solar radiation impingement on the first deployable module and the second deployable module results in approximately balanced solar torque.
17. The spacecraft of claim 1 , further comprising at least one thruster, wherein:
the spacecraft has a center of mass and the at least one first thruster is configured to produce a thrust vector passing through or proximate to the center of mass the thrust vector being approximately parallel to the first axis of rotation.
18. The spacecraft of claim 17 , further comprising a thruster support mechanism (TSM) with one or more degrees-of-freedom, wherein the TSM is articulable over a range of positions and orientations such that the at least one thruster may be selectably disposed so as to impart to the spacecraft a velocity change, a torque, or both for a selected one or both of orbit control and momentum management.
19. The spacecraft of claim 1 , further comprising a launch vehicle adapter, wherein the first deployable module includes a first portion of the launch vehicle adapter, and the second deployable module includes a second portion of the launch vehicle adapter.
20. The spacecraft of claim 19 , wherein, in the on-orbit configuration, the first deployable module and the second deployable module are non-abutting.