Inclined geosynchronous orbit spacecraft constellations

A method comprising:

• executing a stationkeeping strategy for a constellation of Earth-orbiting spacecraft, wherein:
• the constellation includes a first spacecraft disposed in a first orbit and a second spacecraft disposed in a second orbit;
• each of the first orbit and the second orbit is substantially circular with a radius of approximately 42,164 km;
• the first orbit and the second orbit have a respective inclination with respect to the equator within a range of 5° to 20°;
• a separation between a first right ascension of ascending node (RAAN1) of the first orbit and a second RAAN (RAAN2) of the second orbit is approximately 90°;
• and
• the stationkeeping strategy includes maintaining the separation at an approximately constant value of 90° while otherwise allowing RAAN1 and RAAN2 to drift.

A constellation of Earth-orbiting spacecraft, the constellation comprising:

• a first plurality of spacecraft disposed in a first orbit and a second plurality of spacecraft disposed in a second orbit, wherein:
• each of the first orbit and the second orbit is substantially circular with a radius of approximately 42,164 km;
• the first orbit and the second orbit have a respective inclination with respect to the equator within a range of 5° to 20°;
• and
• the first orbit has a first right ascension of ascending node (RAAN1) and the second orbit has a second RAAN (RAAN2) of approximately RAAN1+90°.