A supersynchronous orbit is any orbit in which the orbital period of a satellite or celestial body is greater than the rotational period of the body which contains the barycenter of the orbit. It will necessarily lie beyond the orbital altitude of synchronous orbits for that celestial body.
Geocentric supersynchronous orbits
One particular supersynchronous orbital regime of significant economic value to Earth commerce is a band of near-circular Geocentric orbits beyond the Geosynchronous belt—with perigee altitude above 36,100 kilometres (22,400 mi), approximately 300 kilometres (190 mi) above synchronous altitude —called the geo graveyard belt.
The geo graveyard belt orbital regime is valuable as a storage and disposal location for derelict satellite space debris after their useful economic life is completed as Geosynchronous communication satellites. Artificial satellites are left in space because the economic cost of removing the debris would be high, and current public policy does not require nor incentivize rapid removal by the party that first inserted the debris in outer space and thus created a negative externality for others. One public policy proposal to deal with growing space debris is a "one-up/one-down" launch license policy for Earth orbits. Launch vehicle operators would have to pay the cost of debris mitigation. They would need to build the capability into their launch vehicle-robotic capture, navigation, mission duration extension, and substantial additional propellant – to be able to rendezvous with, capture and deorbit an existing derelict satellite from approximately the same orbital plane.
An additional common use of supersynchronous orbits are for the launch and transfer orbit trajectory of new commsats intended for geosynchronous orbits. The placement into a supersynchronous transfer orbit enables an inclination plane change with a lower subsequent expenditure of propellant by the satellite's kick motor.
In this approach, the launch vehicle places the satellite into a supersynchronous elliptical Geostationary transfer orbit, an orbit with a somewhat larger apogee than the more typical Geostationary transfer orbit (GTO) typically utilized for communication satellites.
This technique was used, for example, on the launch and transfer orbit injection of the first two SpaceX Falcon 9 v1.1 GTO launches in December 2013 and January 2014, SES-8 and Thaicom 6 (90,000 kilometers (56,000 mi)-apogee), respectively. In both cases, the satellite owner uses the propulsion built into the satellite to reduce the apogee and circularize the orbit to a geostationary orbit.
Non-Geocentric supersynchronous orbits
A number of satellites and celestial bodies in the Solar system are in supersynchronous orbits.
The Earth's Moon is in a supersynchronous orbit around the Earth. Deimos is in supersynchronous orbit around Mars. By contrast, the other Martian moon Phobos is in a subsynchronous orbit of Mars with an orbital period of only 0.32 days.
The Mars Orbiter Mission—currently orbiting Mars—is placed into highly elliptical supersynchronous orbit around Mars, with a period of 76.7 hours and a planned periapsis of 365 km (227 mi) and apoapsis of 80,000 km (50,000 mi).
- "U.S. Government Orbital Debris Mitigation Standard Practices". United States Federal Government. Retrieved 2013-11-28.
- Luu, Kim; Sabol, Chris (October 1998). "Effects of perturbations on space debris in supersynchronous storage orbits". Air Force Research Laboratory Technical Reports (AFRL-VS-PS-TR-1998-1093). Retrieved 2013-11-28.
- Frank Zegler and Bernard Kutter, "Evolving to a Depot-Based Space Transportation Architecture", AIAA SPACE 2010 Conference & Exposition, 30 August-2 September 2010, AIAA 2010–8638.
- de Selding, Peter B. (6 January 2014). "SpaceX Delivers Thaicom-6 Satellite to Orbit". Space News. Retrieved 7 January 2014.
- Svitak, Amy (2013-11-24). "Musk: Falcon 9 Will Capture Market Share". Aviation Week. Retrieved 2013-11-28.
- Lodders, Katharina; Fegley, Bruce (1998). The planetary scientist's companion. Oxford University Press US. pp. 190, 198. ISBN 0-19-511694-1.
- "Trajectory Design" (PDF (5.37Mb)). Indian Space Research Organisation (ISRO ). October 2013. Retrieved 2013-10-08.