Satellites and Satellite Fleet Implementation Methods and Apparatus
0 Assignments
0 Petitions
Accused Products
Abstract
A method for implementing a satellite fleet includes launching a group of satellites within a launch vehicle. In an embodiment, the satellites are structurally connected together through satellite outer load paths. After separation from the launch vehicle, nodal separation between the satellites is established by allowing one or more of the satellites to drift at one or more orbits having apogee altitudes below an operational orbit apogee altitude. A satellite is maintained in an ecliptic normal attitude during its operational life, in an embodiment. The satellite'"'"'s orbit is efficiently maintained by a combination of axial, radial, and canted thrusters, in an embodiment. Satellite embodiments include a payload subsystem, a bus subsystem, an outer load path support structure, antenna assembly orientation mechanisms, an attitude control subsystem adapted to maintain the satellite in the ecliptic normal attitude, and an orbit maintenance/propulsion subsystem adapted to maintain the satellite'"'"'s orbit.
-
Citations
38 Claims
-
1-14. -14. (canceled)
-
15. A satellite comprising:
an outer load path support structure, which includes a substantially cylindrical structure having an interior cavity adapted to contain at least one satellite subsystem. - View Dependent Claims (16, 17, 18, 19, 20)
-
21. A satellite comprising:
-
a payload subsystem; a bus subsystem coupled to the payload subsystem; an outer structure that substantially surrounds the payload subsystem and the bus subsystem; one or more solar array panels attached to the outer structure; and an attitude control subsystem adapted to maintain the satellite in an ecliptic normal attitude during an operational life of the satellite so that the one or more solar array panels are approximately perpendicular to the sun throughout a year, resulting in a thermal boundary that is approximately constant throughout the operational life of the satellite. - View Dependent Claims (22, 23, 24, 25, 26)
-
-
27. A satellite having a primary axis and an outer cylinder, the satellite comprising:
-
a payload subsystem; a bus subsystem coupled to the payload subsystem, wherein the bus subsystem includes at least one booster rocket and one or more fuel tanks; at least one booster rocket adapted to impart impulses substantially parallel to the primary axis; and an orbit maintenance subsystem adapted to correct for orbital deviations during an operational life of the satellite, wherein the orbit maintenance subsystem includes a plurality of axial thrusters, radial thrusters, and canted thrusters. - View Dependent Claims (28, 29, 30, 31, 32, 33, 36, 37)
-
-
38. A satellite comprising:
-
a payload subsystem, which includes a downlink antenna adapted to produce an antenna pattern that is a figure of revolution; a bus subsystem coupled to the payload subsystem, wherein the bus subsystem includes at least one booster rocket and one or more fuel tanks; an outer load path support structure coupled to the bus subsystem, wherein the outer load path support structure substantially surrounds the payload subsystem and the bus subsystem, wherein the outer load path support structure includes a substantially cylindrical structure, and wherein the outer load path support structure is adapted to couple to a second outer load path of a second satellite and to bear a load of a second satellite stacked above the satellite; at least one booster rocket adapted to impart impulses substantially parallel to the primary axis; and an attitude control subsystem adapted to maintain the satellite in an ecliptic normal attitude during an operational life of the satellite; and an orbit maintenance subsystem to correct for orbital deviations during an operational life of the satellite, wherein the attitude control subsystem and the orbit maintenance subsystem includes a plurality of axial thrusters, radial thrusters, and canted thrusters.
-
Specification