A projection unit (12) of an interference power estimation device (1) projects an orbit of a satellite onto a map representing a ground surface. A range acquisition unit (13) determines a plurality of ranges on the map so that the projected orbit is included in the ranges. An altitude calculation unit (14) calculates an altitude of the orbit of the satellite in each of the ranges. A range interference calculation unit (16) calculates, for each of the ranges, an interference power between the satellite at a position determined by a latitude and a longitude of the range and the altitude calculated for the range and a radio station installed on the ground surface. An estimation result calculation unit (17) selects, as an estimation result, a maximum value among the interference powers calculated for each of the ranges.

A framework for interfacing a blockchain-based ground system with flight software and satellite orbit analysis applications is disclosed. A blockchain application (e.g., a web application) for secure management of satellites has three components—a client, a server, and a private and permissioned-based blockchain network (e.g., a Hyperledger Fabric™ network). The client allows users to configure satellite parameters. The server facilitates the communication between the client and the blockchain. The blockchain allows the secure management and storage of satellite configuration data on blockchain ledgers. For instance, SECCON provides a blockchain-based framework that can be a potential candidate for next generation ground system applications. SECCON allows secure configuration management of satellites, and has been interfaced with OpenSatKit, a software tool kit that can interact with the cFS. SECCON also provides secure communication of orbital data between trusted organizations and allows the satellite configuration parameters to be exported and viewed in SOAP.

A framework for interfacing a blockchain-based ground system with flight software and satellite orbit analysis applications is disclosed. A blockchain application (e.g., a web application) for secure management of satellites has three components—a client, a server, and a private and permissioned-based blockchain network (e.g., a Hyperledger Fabric™ network). The client allows users to configure satellite parameters. The server facilitates the communication between the client and the blockchain. The blockchain allows the secure management and storage of satellite configuration data on blockchain ledgers. For instance, SECCON provides a blockchain-based framework that can be a potential candidate for next generation ground system applications. SECCON allows secure configuration management of satellites, and has been interfaced with OpenSatKit, a software tool kit that can interact with the cFS. SECCON also provides secure communication of orbital data between trusted organizations and allows the satellite configuration parameters to be exported and viewed in SOAP.

Metamaterials are described which can be employed with satellites, e.g., small sats, to increase the observability of such satellites. Any type of suitable metamaterial can be used. In exemplary embodiments fractal-based patterns or structures may be used.

Metamaterials are described which can be employed with satellites, e.g., small sats, to increase the observability of such satellites. Any type of suitable metamaterial can be used. In exemplary embodiments fractal-based patterns or structures may be used.

A satellite constellation forming system forms a satellite constellation (20) having N orbital planes (21) (N being a natural number) with mutually different normal directions. A satellite constellation forming unit forms the satellite constellation (20) in which each orbital plane (21) of the N orbital planes is an elliptical orbit with the same eccentricity and the same major axis. In the satellite constellation (20), an elevation angle of a major axis of each orbital plane (21) of the N orbital planes has a relative angle of 360/N degrees with respect to each other. In the satellite constellation (20), an azimuth direction of each orbital plane (21) of the N orbital planes has a relative angle of 180/N degrees with respect to each other.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

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.

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.