An object is to assist an appropriate avoidance action when a collision between space objects in outer space is foreseen in advance. A storage unit (140) stores orbit forecast information (51), which is a forecast value of an orbit of each of a plurality of space objects. An alert control unit (120) determines whether space objects whose locations at the same time are in a dangerous relationship exist as danger-anticipated objects among the plurality of space objects, based on the orbit forecast information (51). When it is determined that the danger-anticipated objects exist, the alert control unit (120) outputs a danger alert indicating existence of the danger-anticipated objects. When the danger alert is output, an avoidance decision unit (150) decides an avoidance space object, which is a space object to perform an avoidance operation, out of space objects included in the danger-anticipated objects.

An object is to more accurately assist avoidance of a collision between space objects such as satellites or space debris in outer space. A recorder processing unit (110) acquires flight forecast information (401) indicating a flight forecast of each of a plurality of space objects (60) from a management business device (40) used by a management business operator that manages the plurality of space objects (60). Based on the acquired flight forecast information (401), the recorder processing unit (110) sets a forecast epoch of an orbit of each of the plurality of space objects (60), a forecast orbital element that identifies the orbit, and a forecast error that is forecast for the orbit, as orbit forecast information (51). The recorder processing unit (110) stores a space information recorder (50) including the orbit forecast information (51) in a storage unit (140).

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 multi-user satellite system provides communication services to external satellites. This satellite system provides in-orbit access points that can be used by the external satellites to offload data instead on relying directly on ground stations. One approach to such communication is to use a set of interface satellites (“converter satellites”) that provide a gateway between a constellation of satellites that together provide communication services to one or more ground stations, but that do not necessarily have the communication capabilities to communicate with external satellites. In this way, the interface satellites can be put in compatible orbits with external satellites and provide communication gateways that can be used to offload data from the external satellites to ground stations. As external satellites change their communication methods, the interface satellites can be reconfigured or new compatible interface satellites can be launched, without having to modify the constellation of satellites.

A satellite constellation forming system (600) forms a satellite constellation having a plurality of orbital planes in each of which a plurality of satellites fly at the same average orbital altitude. A satellite constellation forming unit (11) forms a passage region for a space object to pass through before the space object passes through an orbital altitude of the satellite constellation from above the satellite constellation. After the space object has passed through the passage region, the satellite constellation forming unit (11) restores the satellite constellation to a state before the passage region is formed.

A satellite constellation forming system (600) forms a satellite constellation which is composed of a satellite group that cooperatively provides a communication service, and has a plurality of orbital planes in each of which a plurality of satellites fly at the same orbital altitude. Each satellite of the satellite group includes inter-satellite communication means and satellite-ground communication means. A satellite constellation forming unit (11) forms the satellite constellation which has ten or more orbital planes with different normal directions, and in which at least one relative angle in an azimuth direction of adjacent orbital planes of the plurality of orbital planes is arranged to be uneven and satellite-ground communication means of satellites flying in orbital planes spaced unevenly have a communication range that achieves complete ground coverage above the equator.

An object is to appropriately manage disclosure of information on the orbit of a satellite constellation. An information management device (1000) is installed in at least one of a plurality of management business devices each of which conducts a management business for a plurality of space objects flying in space. A storage unit (1400) stores orbit forecast information (51) including an orbit forecast, which is a forecast value of an orbit of each of the plurality of space objects, and a forecast error that is forecast for the orbit. An information disclosure unit (1100) determines whether the orbit forecast information (51) is to be disclosed to a different information management device, based on a disclosure threshold (141) for determining whether the orbit forecast information (51) is to be disclosed and the forecast error.

The present disclosure provides a method for controlling orbital trajectories of a plurality of spacecraft in a multi-spacecraft swarm. In one aspect, the method includes deploying a DRL agent including a plurality of trajectory control models to the multi-spacecraft swarm, the trajectory control models corresponding to swarm configurations of the multi-spacecraft swarm; determining a state vector of said plurality of spacecraft in the multi-spacecraft swarm; transmitting a collective command to the multi-spacecraft swarm, such that said plurality of spacecraft in the multi-spacecraft swarm are to be distributed in one of the swarm configurations; determining actions of said plurality of spacecraft based on the state vector and the collective command; and maneuvering the multi-spacecraft swarm in accordance with the actions.

The present invention relates to a single-board processor card configured for use in a 1U CubeSat payload form-factor multi-purpose architecture, including: a field-programmable-gate-array (FPGA) which is reconfigurable in flight; wherein a configuration memory of the FPGA can be scrubbed in flight to correct errors or upsets; and a radiation-hardened monitor (RHM) which provides radiation mitigation and system monitoring of the single-board processor card, and which reconfigures said FPGA during flight, scrubs the configuration memory, and monitors a health of the FPGA. The 1U CubeSat payload form-factor multi-purpose architecture includes a backplane having a plurality of slots, one of the plurality of slots which accommodates the single-board processor card, wherein the backplane routes signals to a plurality of standard-sized processor cards, interchangeably disposed in any of the plurality of slots.

A modular and scalable system to transfer space articles between space orbits. In one embodiment, the system employs a rendezvous vehicle which docks with a space article in an initial orbit, the connected stack then docking with a locomotive vehicle which maneuvers to a targeted orbit where the space article is detached. In one feature, the rendezvous vehicle and locomotive vehicle use a common propellant and the space article is a satellite.