An object is to prevent satellites constituting a mega-constellation from remaining in outer space in large numbers after completing their missions. An artificial satellite includes a propulsion device. The artificial satellite has propellant to be used by the propulsion device, and the propellant is in an amount required for the artificial satellite to operate in orbit for a first period of L1 years, which is a satellite design life, and then enter the atmosphere within a period less than the first period of years after deorbit. A ground facility controls the artificial satellite so that the artificial satellite has the amount of propellant required to operate in orbit for the first period of L1 years, which is the satellite design life, and then enter the atmosphere within a period of less than the first period of L1 years after deorbit.

A satellite constellation (100) includes a plurality of artificial satellites (111 to 116) that number a multiple of 6. Each of the plurality of artificial satellites orbits in an inclined circular orbit a plurality of times a day. Normals to a plurality of orbital planes corresponding to the plurality of artificial satellites are shifted by an equal angle from each other in an azimuth direction. The plurality of orbital planes make up one or more orbital plane sets each consisting of six orbital planes. Timings at which the six artificial satellites orbit on the six orbital planes of each orbital plane set are synchronized with each other.

Methods and apparatus for Real-time Satellite Imaging System (10) are disclosed. More particularly, one embodiment of the present invention an imaging sensor (14) on a geostationary satellite having one or more co-collimated telescopes (18). The telescopes (18) illuminate local planes (22) which are sparsely populated with focal plane arrays (24). The focal plane arrays (24) record the entire observable Earth hemisphere at one time, at least once every ten seconds.

A method for controlling a satellite using magnetics only, and a control system for implementing the method. The method involves assessing a current attitude of a satellite at a current time and location using magnetometry; setting a desired attitude for the satellite at a future time in a future location; developing a set of waypoints that provide the attitude of the satellite at plural locations between the current location and the future location; and actuating a plurality of magnetorquers to induce torques that achieve a small as possible difference between the attitude of the satellite between each waypoint and achieving the desired attitude at the future location, the magnetorquers being the sole means of inducing rotation of the satellite to attain the desired attitude.

A satellite visibility assignment device (1) includes a visibility unit setter (21), a visibility unit selector (22), and an optimization calculator (23). The visibility unit setter (21) sets visibility units each including a combination of a satellite and a station to communicate with the satellite, a lower limit of a visibility start time, and an upper limit of a visibility end time. The optimization calculator (23) determines whether the visibility start time and the visibility end time are settable for each of the one or more combinations of the visibility units within a range satisfying a set constraint and calculates the visibility start time and the visibility end time through an optimization calculation. The visibility unit selector (22) selects, from the combinations of the visibility units, a combination of the visibility units to be used based on determination of the optimization calculator (23).

A separation adapter for attaching a payload onto a payload dispenser is provided. The separation adapter comprise a rigid structure comprising: a plurality of payload attachment, each payload attachment means operates separately from the other payload attachments means, and is adapted to securely fasten the payload to the rigid structure in a releasable manner, and at least one payload dispenser attachment means, the at least one payload dispenser attachment means is adapted to securely attach the rigid structure to the payload dispenser in a non-releasable fixed manner A method for attaching a payload onto a payload dispenser using a separation adapter and a payload dispenser for carrying a payload of a satellite launch vehicle are also provided.

Systems and methods are provided for scheduling objects having pair-wise and cumulative constraints. The systems and methods presented can utilize a directed acyclic graph to increase or maximize a utilization function. The objects can comprise satellites in a constellation of satellites. In some implementations, the satellites are imaging satellites, and the systems and methods for scheduling can use human collaboration to determine events of interest for acquisition of images. In some implementations, dominant edges are removed from the directed acyclic graph. In some implementations, dynamic weights are assigned to nodes associated with downlink events in the directed acyclic graph.

A satellite constellation forming system (100) forms a satellite constellation which is composed of a satellite group and in which the satellite group cooperatively provides a service. The satellite constellation has a plurality of orbital planes in each of which a plurality of satellites fly at the same nominal orbital altitude. A satellite constellation forming unit (110) continues providing the service while avoiding a collision between satellites by both or one of control of an orbital altitude and control of a passage timing of a satellite group flying in a region where the plurality of orbital planes intersect.

A method of communication with a non-GEO constellation of satellites, includes providing an Earth-based terminal configured for communication with a satellite constellation, and establishing communication between the Earth-based terminal and a non-GEO constellation of satellites, the non-GEO constellation of satellites including a first plurality of satellites orbiting at a first inclination, wherein each of the satellites in the first plurality of satellites is in a discrete planar orbit to form a first snake of satellites, the first snake of satellites including adjacent satellites in adjacent orbits having adjacent RAAN (Right Ascension of the Ascending Node), wherein the Earth-based terminal is positioned and configured for continuous communication with at least one satellite from the non-GEO constellation of satellites.

Aspects of the subject disclosure may include, for example, a device that has a processing system including a processor; and a memory that stores executable instructions that, when executed by the processing system, facilitate performance of operations, including receiving a request for an observation of an overhead viewing area from an observer location; discovering an interference of a satellite with the observation of the overhead viewing area; determining possible solutions to the interference; selecting a solution of the possible solutions; receiving the observation from one or more satellites responding to the solution selected; and providing a response to the request including the observation received. Other embodiments are disclosed.