Instead of users (e.g., independent owners/operators of different satellites) having to calculate orbit determination for each satellite themselves, an orbit determination service automatically calculates the orbit determination (OD) based on a user request. The calculated OD can then be used by a satellite ground station service to determine appropriate orientations for a ground station antenna in order to communicate with the satellite. In some embodiments, the OD service uses information from the calculations of ODs for multiple satellites and users to update a model used in the OD calculation, for example, to provide a more accurate model for Earth's atmosphere to be applied in subsequent OD calculations. In some embodiments, the OD service uses a user-provided computer-aided drawing (CAD) file of the satellite to produce or tune models specific to the satellite, for example, to generate more accurate models for solar radiation pressure and ballistic drag.

Instead of users (e.g., independent owners/operators of different satellites) having to calculate orbit determination for each satellite themselves, an orbit determination service automatically calculates the orbit determination (OD) based on a user request. The calculated OD can then be used by a satellite ground station service to determine appropriate orientations for a ground station antenna in order to communicate with the satellite. In some embodiments, the OD service uses information from the calculations of ODs for multiple satellites and users to update a model used in the OD calculation, for example, to provide a more accurate model for Earth's atmosphere to be applied in subsequent OD calculations. In some embodiments, the OD service uses a user-provided computer-aided drawing (CAD) file of the satellite to produce or tune models specific to the satellite, for example, to generate more accurate models for solar radiation pressure and ballistic drag.

For generating a points-of-interest plan, a method generates communication graph nodes for at least one satellite. The method calculates communication graph edges from the communication graph nodes, wherein the communication graph nodes and the communication graph edges comprise a communication graph. The method solves the communication graph to yield a communication plan. The method generates a points-of-interest plan from the communication plan.

For generating a points-of-interest plan, a method generates communication graph nodes for at least one satellite. The method calculates communication graph edges from the communication graph nodes, wherein the communication graph nodes and the communication graph edges comprise a communication graph. The method solves the communication graph to yield a communication plan. The method generates a points-of-interest plan from the communication plan.

Various embodiments of the disclosed subject matter provide systems, methods, architectures, mechanisms, apparatus, computer implemented method and/or frameworks configured for tracking Earth orbiting objects and adapting SSN tracking operations to improve tracking accuracy while reducing computational complexity and resource consumption associated with such tracking.

Various embodiments of the disclosed subject matter provide systems, methods, architectures, mechanisms, apparatus, computer implemented method and/or frameworks configured for tracking Earth orbiting objects and adapting SSN tracking operations to improve tracking accuracy while reducing computational complexity and resource consumption associated with such tracking.

A vehicle for intercepting a target object orbiting in space is provided, comprising a launching portion for driving the vehicle into an orbit, and an interception portion for intercepting a target object when the vehicle is in orbit, wherein the interception portion comprises means for engaging with the target object and wherein the launching portion is arranged to drive the vehicle into a first elliptical orbit and the vehicle is arranged to adopt a second elliptical orbit when engaged with the target object in which the first elliptical orbit is arranged so as to intersect the orbit of the target object at an interception point, and the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object. A method of controlling a vehicle for intercepting a target object orbiting in space is also provided, comprising controlling the vehicle to be driven into a first elliptical orbit to intersect the orbit of the target object at an interception point and controlling the vehicle to engage with the target object at the interception point and to adopt a second elliptical orbit when engaged with the target object in which the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object.

A vehicle for intercepting a target object orbiting in space is provided, comprising a launching portion for driving the vehicle into an orbit, and an interception portion for intercepting a target object when the vehicle is in orbit, wherein the interception portion comprises means for engaging with the target object and wherein the launching portion is arranged to drive the vehicle into a first elliptical orbit and the vehicle is arranged to adopt a second elliptical orbit when engaged with the target object in which the first elliptical orbit is arranged so as to intersect the orbit of the target object at an interception point, and the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object. A method of controlling a vehicle for intercepting a target object orbiting in space is also provided, comprising controlling the vehicle to be driven into a first elliptical orbit to intersect the orbit of the target object at an interception point and controlling the vehicle to engage with the target object at the interception point and to adopt a second elliptical orbit when engaged with the target object in which the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object.

A method of predicting the orbit of a satellite of a satellite positioning system, including: associating first and second types of satellites with first and second models of celestial mechanics forces, respectively; storing first ephemerides data of a satellite, associated to first time intervals and second ephemerides data associated to second time intervals. Further, the method comprises: calculating reference satellite positions based on the first ephemerides data; estimating first and second satellite positions in the first time intervals by using the second ephemerides data and the first and second forces models, respectively; determining first and second estimate errors by comparing the reference positions with the first and second positions, respectively; and detecting the type of satellite between the first and second types by an analysis of the first and second errors.

A method of predicting the orbit of a satellite of a satellite positioning system, including: associating first and second types of satellites with first and second models of celestial mechanics forces, respectively; storing first ephemerides data of a satellite, associated to first time intervals and second ephemerides data associated to second time intervals. Further, the method comprises: calculating reference satellite positions based on the first ephemerides data; estimating first and second satellite positions in the first time intervals by using the second ephemerides data and the first and second forces models, respectively; determining first and second estimate errors by comparing the reference positions with the first and second positions, respectively; and detecting the type of satellite between the first and second types by an analysis of the first and second errors.