This patent presents an attitude determination and control system based on a Quaternion Kalman Filter (QKF) with an extendable number of sensors and actuators. Furthermore, it is compatible with the spherical motor as its attitude actuator. The system includes a processor with a QKF, at least one direct attitude actuator, and at least two environmental sensors. Firstly, system dynamics calculates a first propagation attitude determination result. Next, update the first propagation with the attitude sensor measurements. Then, control the satellite's attitude via the attitude actuator closer to the attitude command provided by the user. The proposed system dynamic model could adjust the number of actuators and sensors freely without reprogramming the algorithms for new missions with new configurations on the actuators and sensors. Moreover, if some components fail, the algorithm can automatically remove those related sequences to avoid the overall failure of the system.

A satellite module for attitude determination includes a containment body comprising at least one data acquisition board and a connection interface, at least one first-type sensor selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, in communication with the data acquisition board and at least one second-type sensor, different from the first type, selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, and in communication with the data acquisition board. The connection interface may be mounted on a first face of the containment body, the first-type sensor may be mounted on a second face of the containment body, and the second-type sensor may be mounted on a third face of the containment body.

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.

The invention concerns a method (1) for detecting and tracking objects orbiting around the earth (for example space debris) by means of on-board processing of images acquired by a space platform (for example a satellite, a space vehicle or a space station) by one or more optical sensors, preferably one or more star trackers.

Techniques for improving the quality of images captured by a remote sensing overhead platform such as a satellite. Sensor shifting is employed in an open-loop fashion to compensate for relative motion of the remote sensing overhead platform to the Earth. Control signals are generated for the sensor shift mechanism by an orbital motion compensation calculation that uses the predicted ephemeris (including orbit dynamics) and image geometry (overhead platform to target). Optionally, the calculation may use attitude and rate errors that are determined from on-board sensors.

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.

The invention concerns a method for estimating the angular velocity (and, preferably, also the attitude) of a space platform (for example, a satellite, a space vehicle, or a space station) using only the information provided by one or more optical sensors, such as one or more star trackers, one or more colour and/or black and white cameras or video cameras, one of more infrared sensors, etc.

A wide field-of-view celestial sighting system and method are provided. The method includes orienting an imaging optic to collect light from at least one light source, such as at least one celestial body, the imaging optic being secured to a platform. The method further includes selectively collecting light from the at least one celestial body through a selective light collector secured to the platform and positioned in an imaging surface, such as an imaging plane, of the imaging optic. The method further includes combining forward scattered light from the at least one celestial body to provide a combined forward scattered light, and detecting a light intensity of the combined forward scattered light. Systems for performing the method are provided.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.