A method of determining a precise orbit of a satellite through estimation of a parallactic refraction scale factor is proposed, the method including inputting an initial estimate including initial orbit information of a satellite with respect to an observation epoch and the parallactic refraction scale factor; performing orbit propagation using a high-precision orbit propagator by applying a dynamics model; performing observer-centered satellite optical observation modeling including the parallactic refraction scale factor; calculating an observation residual between actual optical observation data and observation data calculated via the observation modeling reflecting the parallactic refraction; and precisely determining the orbit of the satellite by estimating the parallactic refraction scale factor and a satellite state vector using a batch least square estimation algorithm.

A space vehicle system includes a first star tracker disposed at a first location on or near the space vehicle, the first star tracker configured to obtain first images of a space object and stars and a second star tracker disposed at a second location on or near the space vehicle, at a distance D from the first location. The second star tracker is configured to obtain second images of the space object and the stars and the first images and the second images being stereoscopic images. The system also includes a processor configured to determine an estimate of a range from the space vehicle to the space object based on the first images and the second images.

A space vehicle system includes a first star tracker disposed at a first location on or near the space vehicle, the first star tracker configured to obtain first images of a space object and stars and a second star tracker disposed at a second location on or near the space vehicle, at a distance D from the first location. The second star tracker is configured to obtain second images of the space object and the stars and the first images and the second images being stereoscopic images. The system also includes a processor configured to determine an estimate of a range from the space vehicle to the space object based on the first images and the second images.

A method of determining a precise orbit of a satellite through estimation of a parallactic refraction scale factor is proposed, the method includes inputting an initial estimate including initial orbit information of a satellite with respect to an observation epoch and the parallactic refraction scale factor; performing orbit propagation using a high-precision orbit propagator by applying a dynamics model; performing observer-centered satellite optical observation modeling including the parallactic refraction scale factor; calculating an observation residual between actual optical observation data and observation data calculated via the observation modeling reflecting the parallactic refraction; and precisely determining the orbit of the satellite by estimating the parallactic refraction scale factor and a satellite state vector using a batch least square estimation algorithm.

A method of determining a precise orbit of a satellite through estimation of a parallactic refraction scale factor is proposed, the method includes inputting an initial estimate including initial orbit information of a satellite with respect to an observation epoch and the parallactic refraction scale factor; performing orbit propagation using a high-precision orbit propagator by applying a dynamics model; performing observer-centered satellite optical observation modeling including the parallactic refraction scale factor; calculating an observation residual between actual optical observation data and observation data calculated via the observation modeling reflecting the parallactic refraction; and precisely determining the orbit of the satellite by estimating the parallactic refraction scale factor and a satellite state vector using a batch least square estimation algorithm.

A reconnaissance rover configured for multiple agile and autonomous landings over a small body or moon. The reconnaissance rover comprises a detection unit, a processing unit, a control unit and a drive unit. The detection unit is configured to detect at least an environment in front of the reconnaissance rover, in the direction of a trajectory of the reconnaissance rover over a surface of the small body or moon. The detection unit is further configured to provide environmental data based on the detected environment. The processing unit is configured to update the trajectory based upon the provided environmental data. The control unit interacts with the drive unit to move the reconnaissance rover according to the updated trajectory.

A reconnaissance rover configured for multiple agile and autonomous landings over a small body or moon. The reconnaissance rover comprises a detection unit, a processing unit, a control unit and a drive unit. The detection unit is configured to detect at least an environment in front of the reconnaissance rover, in the direction of a trajectory of the reconnaissance rover over a surface of the small body or moon. The detection unit is further configured to provide environmental data based on the detected environment. The processing unit is configured to update the trajectory based upon the provided environmental data. The control unit interacts with the drive unit to move the reconnaissance rover according to the updated trajectory.

A master control system for a remote-sensing satellite image processing device, the system including: a master control management module, a first FPGA module, and a second FPGA module. The master control management module is in connection and communication with the first FPGA module, the second FPGA module, and a housekeeping computer. The first FPGA module is in connection and communication with the second FPGA module and a remote-sensing satellite image processing device. The master control management module is adapted to perform assignment of tasks. The first FPGA module is adapted to communicate with a processor in the satellite image processing device, monitor an operation state of the satellite image processing device, send the operation state information to the master control management module, receive a task assignment command issued by the master control management module, and transmit the task assignment command to the satellite image processing device.

A master control system for a remote-sensing satellite image processing device, the system including: a master control management module, a first FPGA module, and a second FPGA module. The master control management module is in connection and communication with the first FPGA module, the second FPGA module, and a housekeeping computer. The first FPGA module is in connection and communication with the second FPGA module and a remote-sensing satellite image processing device. The master control management module is adapted to perform assignment of tasks. The first FPGA module is adapted to communicate with a processor in the satellite image processing device, monitor an operation state of the satellite image processing device, send the operation state information to the master control management module, receive a task assignment command issued by the master control management module, and transmit the task assignment command to the satellite image processing device.

A device for determining an attitude of a satellite is disclosed, the satellite having an attitude control system comprising a gyroscopic actuator including a flywheel mounted so as to be rotatable around an axis of rotation and carried by a gimbal articulated to rotate around an axis of rotation. The device includes an attitude sensor configured to measure the attitude of the satellite, a position sensor configured to measure the angular position of the gimbal around its axis of rotation, a speed sensor configured to measure the rotational speed of the flywheel, and a processing circuit configured to determine the attitude of the satellite by using the measurement of the angular position of the gimbal, the measurement of the rotational speed of the flywheel, and the measurement of the attitude of the satellite.