Satellites and satellite fleet implementation methods and apparatus

• US 8,016,240 B2
• Filed: 03/29/2007
• Issued: 09/13/2011
• Est. Priority Date: 03/29/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Rosen, Harold A., Fowler, Harmon C., Caplin, Glenn N.
• Primary Examiner(s): Michener; Joshua J
• Application Number:
  US11/693,645
• Publication Number:
  US 20080237399A1
• Time in Patent Office: 1,629 Days
• Field of Search: 244/158.1, 244/158.4, 244/158.5, 244/158.8, 2441731-1733, 244/164, 244/169, 701/13, 701/226, 455/12.1, 455/13.1, 455/427, 455/13.2, 455/63.4, 455/25, 455/431, 455/3.02, 455/3.03, 455/73, 455/517, 455/3.06, 725/68, 725/69, 725/71, 725/100, 725/64, 725/63, 725/78, 725/8, 370/316
• US Class Current: 244/158.5
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/26 using jets
• CPC Class Codes: B64G 1/643 for arranging multiple satellites in a single launcher

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.

Claims

1. A method for implementing a satellite fleet, wherein the satellite fleet includes multiple-satellites whose orbital planes have separated nodes, the method comprising:

launching a first launch vehicle, which contains a first group of the multiple satellites within a first payload fairing of the first launch vehicle;

releasing the first group from the first payload fairing into an initial orbit;

performing a first series of one or more orbit changes to transition a first satellite of the first group from the initial orbit to an a first operational orbit having a first operational orbit apogee altitude that is higher than an initial orbit apogee altitude;

performing a second series of one or more orbit changes to transition a second satellite of the first group from the initial orbit to the a second operational orbit, wherein performing the second series includes establishing a first desired nodal separation between the first satellite and the second satellite by allowing the second satellite to drift for one or more first drift time periods at one or more orbits having apogee altitudes below a second operational orbit apogee altitude;

placing into operation, proximate to the Earth within a coverage area of a plurality of aimed beams from the first group, an uplink hub transmitting uplink television signals toward the first satellite and the second satellite and a plurality of direct television antennas configured to receive a plurality of downlink television signals from the first group; and

broadcasting, by the plurality of aimed beams from the first group, the plurality of downlink television signals to the plurality of direct television antennas in response to receiving the plurality of uplink television signals.

2. The method of claim 1, further comprising:

when the first group includes at least one additional satellite, performing at least one additional series of one or more orbit changes to transition the at least one additional satellite from the initial orbit to a third operational orbit, until each of the multiple satellites of the first group have been transitioned into a corresponding operational orbit.

3. The method of claim 1, further comprising:

prior to launching, stacking the satellites of the first group in the first payload fairing to form a satellite stack, wherein the satellites are stacked so that an outer load path support structure of a lower satellite of the satellite stack bears the load of any higher satellites of the satellite stack.

4. The method of claim 1, wherein:

performing the first series of one or more orbit changes includes firing a booster rocket of the satellite to perform each of the one or more orbit changes.

5. The method of claim 1, further comprising:

imparting an axial rotation to the first group at the initial orbit.

6. The method of claim 1, wherein the first desired nodal separation is in a range of about 10 degrees to about 180 degrees.

7. The method of claim 1, wherein performing the first series of orbit changes comprises:

performing at least some of the orbit changes when the first satellite is in a vicinity of perigee.

8. The method of claim 1, further comprising:

after performing the first series of one or more orbit changes, preparing for system operations by de-spinning a communications payload subsystem of the first satellite.

9. The method of claim 1, further comprising:

after performing the first series of one or more orbit changes, preparing for system operations by adjusting an attitude of the first satellite to place the first satellite in an ecliptic normal attitude.

10. The method of claim 9, wherein preparing for the system operations further comprises:

orienting an antenna assembly of the first satellite in a direction to support downlink signal transmission into a desired coverage area using at least two control axes, wherein a first control axis is a primary axis, and wherein a second control axis is an elevation adjustment axis that is substantially orthogonal to the primary axis.

11. The method of claim 10, wherein orienting the antenna assembly comprises:

orienting the antenna assembly with respect to the primary axis using a despin control mechanism adapted to provide a 360 degree range adjustment around the primary axis, orienting the antenna assembly with respect to the elevation adjustment axis using an elevation adjustment mechanism adapted to provide about a 90 degree range adjustment around the elevation adjustment axis.

12. The method of claim 1, further comprising:

after performing the first series of one or more orbit changes, actively performing satellite orbit maintenance to correct for orbital deviations using a plurality of axial thrusters, radial thrusters, and canted thrusters.

13. The method of claim 1, further comprising:

after performing the first series of one or more orbit changes, actively performing satellite orbit maintenance to maintain the first satellite in a Molniya orbit with an orbital period of about 12 hours, an angle of inclination of about 63.4 degrees, and a desired nodal separation of the first satellite, with respect to other satellites within the satellite fleet, of 360 degrees divided by a total number of satellites in the satellite fleet.

14. The method of claim 1, further comprising:

launching a second launch vehicle, which contains a second group of the multiple satellites within a second payload fairing of the second launch vehicle;

releasing the second group from the second payload fairing into the initial orbit;

sequentially transitioning each satellite of the second group of satellites to a second plurality of operational orbits so that desired nodal separations are established between satellites of the first group and satellites of the second group and so that each of the second plurality of operational orbits has the same ground path as the first plurality of orbits.

15. The method of claim 1 further comprising:

receiving, by each of the plurality of direct television antennas, the plurality of downlink signals transmitted by the first satellite in the first operational orbit and the second satellite in the second operational orbit.

16. The method of claim 1 further comprising:

wherein each of the plurality of direct television antennas do not include a tracking mechanism configured to dynamically point toward and track a satellite from which each antenna is receiving the plurality of downlink television signals.

17. The method of claim 1 further comprising:

configuring the first operational orbit and the second operational orbit to track along a substantially fixed path on the surface of the Earth over which each satellite in the first group travels during its orbit.

18. The method of claim 1 further comprising:

configuring the first operational orbit and the second operational orbit to be phased so that the second satellite enters an active orbit segment of the second satellite and initiates a transmission of a plurality of downlink signals as the first satellite exits an active orbit segment of the first satellite and ceases the transmission of the plurality of downlink signals, wherein the active orbit segment is centered about an apogee and has a duration of a sidereal day divided by a total number of satellites in the plurality of satellites.

19. The method of claim 1 further comprising:

wherein each satellite in the first group receives, at a feed horn in the antenna assembly, the plurality of uplink television signals; and

wherein the feed horn produces the plurality of downlink television signals, and projects the plurality of downlink television signals toward a reflector in the antenna assembly which reflect the downlink signals in a beam direction determined by a position of the antenna assembly.