Abstract: A method includes obtaining a plurality of conflict lists including a conflict list for each communication device. The method also includes obtaining resource requirement values. A resource requirement value indicates a number of orthogonal channels that are required to satisfy demand associated with a communication device. The method includes determining that two or more communication devices are associated with a particular resource requirement value. The method also includes selecting a particular communication device by using the conflict lists to perform a maximum independent set analysis based on the two or more communication devices. The method further includes assigning a set of orthogonal channels to the particular communication device. The set of orthogonal channels include a number of orthogonal channels that is based on the particular resource requirement value.

Abstract: A method includes obtaining a plurality of conflict lists including a conflict list for each communication device. The method also includes obtaining resource requirement values. A resource requirement value indicates a number of orthogonal channels that are required to satisfy demand associated with a communication device. The method includes determining that two or more communication devices are associated with a particular resource requirement value. The method also includes selecting a particular communication device by using the conflict lists to perform a maximum independent set analysis based on the two or more communication devices. The method further includes assigning a set of orthogonal channels to the particular communication device. The set of orthogonal channels include a number of orthogonal channels that is based on the particular resource requirement value.

Abstract: Apparatus and methods for determining orbital parameters for spacecraft are provided. A computing device can receive a first plurality of orbital parameters defining a first orbit by a first spacecraft of a particular object. The first orbit can have a corresponding first ground track over the particular object. The computing device can receive a following time for a second spacecraft. The computing device can determine a second plurality of orbital parameters for a second orbit by the second spacecraft of the particular object based on the first plurality of orbital parameters and the following time. The second orbit can have a corresponding second ground track over the particular object that follows the first ground track. The computing device can generate an output that includes the second plurality of orbital parameters.

Abstract: Apparatus and methods for determining orbital parameters for spacecraft are provided. A computing device can receive a first plurality of orbital parameters defining a first orbit by a first spacecraft of a particular object. The first orbit can have a corresponding first ground track over the particular object. The computing device can receive a following time for a second spacecraft. The computing device can determine a second plurality of orbital parameters for a second orbit by the second spacecraft of the particular object based on the first plurality of orbital parameters and the following time. The second orbit can have a corresponding second ground track over the particular object that follows the first ground track. The computing device can generate an output that includes the second plurality of orbital parameters.

Abstract: A method for minimizing the amount of propellant required to be carried onboard the satellites of an Earth orbiting satellite constellation to maintain the minimum angle of elevation between a selected geographical area of the Earth and at least one satellite of the constellation during the life of the constellation includes establishing an optimal initial inclination and RAAN of each satellite of the constellation. The method enables the satellites of the constellation to carry additional hardware and other payload mass, or alternatively, the design life of the constellation to be increased.

Abstract: A method for minimizing the amount of propellant required to be carried onboard the satellites of an Earth orbiting satellite constellation to maintain the minimum angle of elevation between a selected geographical area of the Earth and at least one satellite of the constellation during the life of the constellation includes establishing an optimal initial inclination and RAAN of each satellite of the constellation. The method enables the satellites of the constellation to carry additional hardware and other payload mass, or alternatively, the design life of the constellation to be increased.