An exploration method includes: a step of exploring a natural resource on a satellite, a minor planet, or a planet; a step of acquiring the natural resource detected by the exploration; and a step of storing the acquired natural resource.

The invention discloses a preferable short arc initial orbit determining method based on Gauss solution cluster, and belongs to the astrodynamics field, including: grouping the observation data, using Gauss method to obtain the target state vector at the corresponding time point for each group of data, forming a solution set of preliminary estimation; dividing the solution set of preliminary estimation into a position component vector solution set and a velocity component vector solution set for clustering to obtain a position component vector solution cluster and a velocity component vector solution cluster; based on the position component vector solution cluster and the velocity component vector solution cluster, generating a two-dimensional trajectory solution set; evaluating each of the two-dimensional trajectories by using a trajectory optimal method, calculating the number of root of orbits corresponding to the optimal two-dimensional trajectory, thereby completing determination of initial orbit.

The invention discloses a preferable short arc initial orbit determining method based on Gauss solution cluster, and belongs to the astrodynamics field, including: grouping the observation data, using Gauss method to obtain the target state vector at the corresponding time point for each group of data, forming a solution set of preliminary estimation; dividing the solution set of preliminary estimation into a position component vector solution set and a velocity component vector solution set for clustering to obtain a position component vector solution cluster and a velocity component vector solution cluster; based on the position component vector solution cluster and the velocity component vector solution cluster, generating a two-dimensional trajectory solution set; evaluating each of the two-dimensional trajectories by using a trajectory optimal method, calculating the number of root of orbits corresponding to the optimal two-dimensional trajectory, thereby completing determination of initial orbit.

A system carried on a satellite in orbit around the earth is configured to detect an object on a collision or near collision course with the satellite, to determine that the object is a hostile attacker and, if so, to timely deploy one or more countermeasures to defeat, deflect, or destroy such an attacker autonomously.

Various embodiments are directed to telescopic apparatus, systems and methods for daylight imaging of satellites and other objects, a platform/telescope configured for daylight imaging of satellites and other objects, as well as modifications thereto configured to perform specific functions individually and/or in conjunction with other platforms/devices (e.g., radar tracking devices).

Various embodiments are directed to telescopic apparatus, systems and methods for daylight imaging of satellites and other objects, a platform/telescope configured for daylight imaging of satellites and other objects, as well as modifications thereto configured to perform specific functions individually and/or in conjunction with other platforms/devices (e.g., radar tracking devices).

An orbit analysis unit (431) of a collision avoidance assistance business device analyzes an orbit of a specific space object. When it is foreseen that the specific space object will intrude into an orbital altitude region where a satellite group of a satellite constellation flies, a notification unit (432) of the collision avoidance assistance business device notifies a satellite constellation business operator of an intrusion alert and non-public orbit information of the specific space object via a communication line that is kept secret. A collision analysis unit (411) of a satellite constellation business device analyzes a collision between the specific space object and an individual satellite in the satellite group of the satellite constellation. A countermeasure planning unit (412) of the satellite constellation business device plans a collision avoidance countermeasure when a collision is foreseen.

An orbit analysis unit (431) of a collision avoidance assistance business device analyzes an orbit of a specific space object. When it is foreseen that the specific space object will intrude into an orbital altitude region where a satellite group of a satellite constellation flies, a notification unit (432) of the collision avoidance assistance business device notifies a satellite constellation business operator of an intrusion alert and non-public orbit information of the specific space object via a communication line that is kept secret. A collision analysis unit (411) of a satellite constellation business device analyzes a collision between the specific space object and an individual satellite in the satellite group of the satellite constellation. A countermeasure planning unit (412) of the satellite constellation business device plans a collision avoidance countermeasure when a collision is foreseen.

A space information recorder (100) includes two or more categories of a category, acquired from a mega-constellation business device, of different constellations formed at nearby altitudes by the same business operator, a category of a satellite group of each constellation that flies at the same nominal altitude and cooperatively realizes the same mission, a category of orbital planes, a category of each orbital plane of the orbital planes, and a category of an individual satellite. The space information recorder (100) includes information on upper and lower limit values of an orbital altitude or on a nominal altitude and an altitude fluctuation width for each category.

A space traffic management device (100) mounted in a mega-constellation business device (41) specifies one to a plurality of representative satellites from a mega-constellation satellite group flying on orbits having the same nominal orbital altitude, and has quasi-real-time high-accuracy orbital information of the representative satellite and orbital information relative values of constituent satellites other than the representative satellite, relative to the representative satellite. The space traffic management device (100) shares the quasi-real-time high-accuracy orbital information of the representative satellite and the orbital information relative values of the constituent satellites relative to the representative satellite, with the space traffic management devices (100) mounted in a plurality of business devices.