A satellite in orbit around a planetary body includes a bus and a drag flap coupled to the bus. The drag flap is used to increase the drag torque applied to the satellite. The bus may house sensors and actuators, such as a star tracker, a gyroscope, a reaction wheel, and a global position system (GPS) receiver to monitor the attitude of the satellite in response to the applied drag torque. The measurements from the sensors and actuators may be used to determine the drag torque applied to the satellite. An estimate of the atmospheric density may be then be determined based on the drag torque. Compared to conventional approaches, the satellite and methods described herein estimates the atmospheric density at comparable, if not better, resolution and bandwidth. The atmospheric density estimates may also be acquired in real-time using a cheaper, lighter, and smaller satellite.

Apparatus and methods for determining orbital parameters for spacecraft are provided. A computing device can receive a first plurality of orbital parameters defining a first orbit by a first spacecraft of a particular object. The first orbit can have a corresponding first ground track over the particular object. The computing device can receive a following time for a second spacecraft. The computing device can determine a second plurality of orbital parameters for a second orbit by the second spacecraft of the particular object based on the first plurality of orbital parameters and the following time. The second orbit can have a corresponding second ground track over the particular object that follows the first ground track. The computing device can generate an output that includes the second plurality of orbital parameters.

Apparatus and methods for determining orbital parameters for spacecraft are provided. A computing device can receive a first plurality of orbital parameters defining a first orbit by a first spacecraft of a particular object. The first orbit can have a corresponding first ground track over the particular object. The computing device can receive a following time for a second spacecraft. The computing device can determine a second plurality of orbital parameters for a second orbit by the second spacecraft of the particular object based on the first plurality of orbital parameters and the following time. The second orbit can have a corresponding second ground track over the particular object that follows the first ground track. The computing device can generate an output that includes the second plurality of orbital parameters.

The invention concerns a suborbital space traffic control system that comprises: a radar system configured to monitor a predetermined suborbital region and detect and track objects in the predetermined suborbital region. The objects include vehicles and space debris; and a suborbital space traffic monitoring system configured to: receive, from the radar system, tracking data related to the objects detected and tracked by the radar system; monitor, on the basis of the tracking data, trajectories of the objects in the predetermined suborbital region using one or more predetermined machine-learning techniques to detect potentially hazardous situations for the vehicles in the predetermined suborbital region; and, if it detects a potentially hazardous situation for one or more given vehicles, transmit corresponding alarm messages to the given vehicle(s).

The invention concerns a suborbital space traffic control system that comprises: a radar system configured to monitor a predetermined suborbital region and detect and track objects in the predetermined suborbital region. The objects include vehicles and space debris; and a suborbital space traffic monitoring system configured to: receive, from the radar system, tracking data related to the objects detected and tracked by the radar system; monitor, on the basis of the tracking data, trajectories of the objects in the predetermined suborbital region using one or more predetermined machine-learning techniques to detect potentially hazardous situations for the vehicles in the predetermined suborbital region; and, if it detects a potentially hazardous situation for one or more given vehicles, transmit corresponding alarm messages to the given vehicle(s).

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 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.

Provided is a system for a satellite business proprietor that facilitates acquisition of information regarding a retrieved ground station. An information processing device according to the present technology includes a user interface section that performs a process of presenting a specification page for specifying a search condition with respect to a channel of a downlink and an uplink between a satellite station and a ground station, a process of presenting a search result page that presents a list of ground stations retrieved as a result of a search based on a condition entered on the specification page, the search result page allowing a ground station to be specified and entered, and a process of presenting a communication plan page that displays a communication plan employing one or more ground stations specified on the search result page.

A method, computer program product and system where a processor(s) configures sensor(s) on an unmanned aircraft system, to capture data related to a surface of a defined geographic area. The processor(s) navigate the unmanned aircraft system in a repeatable defined travel path proximate to the defined geographic area, such that the sensor(s) capture surface data related to the defined geographic area during the navigating, wherein a position of the unmanned aircraft system in the travel path is within a satellite view geometry of a satellite. The processor(s) maintain the unmanned aircraft system at a distance from the surface at which atmosphere does not obscure the data and obtain the data collected by the sensor(s). The processor(s) compares the data collected by the sensor(s) to data collected by one or more instruments on the satellite related to the defined geographic area to determine is the instrument(s) of the satellite are calibrated.

A method, computer program product and system where a processor(s) configures sensor(s) on an unmanned aircraft system, to capture data related to a surface of a defined geographic area. The processor(s) navigate the unmanned aircraft system in a repeatable defined travel path proximate to the defined geographic area, such that the sensor(s) capture surface data related to the defined geographic area during the navigating, wherein a position of the unmanned aircraft system in the travel path is within a satellite view geometry of a satellite. The processor(s) maintain the unmanned aircraft system at a distance from the surface at which atmosphere does not obscure the data and obtain the data collected by the sensor(s). The processor(s) compares the data collected by the sensor(s) to data collected by one or more instruments on the satellite related to the defined geographic area to determine is the instrument(s) of the satellite are calibrated.