A method for estimating a direction of a satellite in the transfer phase. The direction of the satellite is estimated relative to a measurement antenna by executing steps for measuring the reception power, by the measurement antenna, of a target signal emitted by the satellite, for different pointing directions of the measurement antenna. The target signal has a substantially sinusoidal component referred to as a single-frequency component. Each power measurement step includes a transposition in the frequency domain of a digital signal, obtained from a signal supplied by the measurement antenna, to obtain a frequency spectrum of the digital signal over a predetermined frequency band having the single-frequency component. The power measurement for the pointing direction being considered is determined based on a maximum value of the frequency spectrum.

A method for estimating a direction of a satellite in the transfer phase. The direction of the satellite is estimated relative to a measurement antenna by executing steps for measuring the reception power, by the measurement antenna, of a target signal emitted by the satellite, for different pointing directions of the measurement antenna. The target signal has a substantially sinusoidal component referred to as a single-frequency component. Each power measurement step includes a transposition in the frequency domain of a digital signal, obtained from a signal supplied by the measurement antenna, to obtain a frequency spectrum of the digital signal over a predetermined frequency band having the single-frequency component. The power measurement for the pointing direction being considered is determined based on a maximum value of the frequency spectrum.

A method for predicting trajectory of an object includes constructing a training data set using past actual orbital information of a target object, wherein the training data set includes a plurality of pairs of input sequence data corresponding to a trajectory in a first section before a reference point, and output sequence data corresponding to a trajectory in a second section after the reference point, training an object trajectory prediction model using the training data set, and predicting the trajectory of the prediction target object after the reference point, by inputting input sequence data corresponding to an actual trajectory of the prediction target object before the reference point into the object trajectory prediction model.

A method for predicting trajectory of an object includes constructing a training data set using past actual orbital information of a target object, wherein the training data set includes a plurality of pairs of input sequence data corresponding to a trajectory in a first section before a reference point, and output sequence data corresponding to a trajectory in a second section after the reference point, training an object trajectory prediction model using the training data set, and predicting the trajectory of the prediction target object after the reference point, by inputting input sequence data corresponding to an actual trajectory of the prediction target object before the reference point into the object trajectory prediction model.

An object is to notify an appropriate intrusion alert by determining whether debris will intrude into an orbit area of a satellite constellation. A passage determination unit (110) determines whether debris will pass through a satellite orbit area, based on satellite orbit forecast information in which a forecast value of an orbit of a satellite is set and debris orbit forecast information in which a forecast value of an orbit of debris is set. When it is determined that debris will pass through the satellite orbit area, an alert generation unit (120) generates an intrusion alert (111) including a predicted time, predicted location coordinates, and predicted velocity vector information that relate to passage of the debris. An alert notification unit (130) notifies the intrusion alert (111) to a management business device (40) used by a management business operator that manages a satellite that flies in the satellite orbit area.

A flying body, which prevents others from measuring precise position of the flying body and allows friends to measure precise position of the flying body, is provided. The flying body (10) is provided with a reflector (100), a controller (300) and an anti-reflection section (200). The reflector (100) is provided with a reflective surface, arranged in an aperture, which reflects a radiated laser. The controller (300) generates a control signal on a basis of a state of the flying body. The anti-reflection section (200) prevents a reflection of the laser by the reflective surface on a basis of the control signal.

A flying body, which prevents others from measuring precise position of the flying body and allows friends to measure precise position of the flying body, is provided. The flying body (10) is provided with a reflector (100), a controller (300) and an anti-reflection section (200). The reflector (100) is provided with a reflective surface, arranged in an aperture, which reflects a radiated laser. The controller (300) generates a control signal on a basis of a state of the flying body. The anti-reflection section (200) prevents a reflection of the laser by the reflective surface on a basis of the control signal.

An improved debris generator that can be used as part of a space object modeling (SOM) system to turn any active spacecraft into a debris sensor for characterizing and cataloging space debris. The space debris generator includes an extractor which extracts satellite sensor data into a sensor store, an impact agent which estimates “on the fly” new debris field objects generated by the collision, and an injector which stores the enhanced object data on a central server for near-term mitigation of impact driven breakup events. The impact agent is an artificial neural network trained using a large number of simulations of impact events.

An improved debris generator that can be used as part of a space object modeling (SOM) system to turn any active spacecraft into a debris sensor for characterizing and cataloging space debris. The space debris generator includes an extractor which extracts satellite sensor data into a sensor store, an impact agent which estimates “on the fly” new debris field objects generated by the collision, and an injector which stores the enhanced object data on a central server for near-term mitigation of impact driven breakup events. The impact agent is an artificial neural network trained using a large number of simulations of impact events.

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.