A satellite configuration includes a plurality of individual satellite buses each having a number of side panels that form a polygonal shape, where the individual satellite buses collectively fit together to form the satellite configuration having a regular polygon shape. A method of producing the satellite configuration includes forming a plurality of individual satellite buses each having a polygonal shape, and fitting the individual satellite buses together to form the satellite configuration in a regular polygonal shape.

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.

According to an embodiment, a system includes a controller configured to determine a set of background light intensities associated with a satellite, where each background light intensity corresponds to at least one of an orientation and a position of a light source relative to the satellite, to determine a set of relative orientations of the light source corresponding to the set of background light intensities, and to generate an image of the satellite based, at least in part, on the determined set of background light intensities and the determined set of relative orientations of the light source.

A satellite orbiting in one of a plurality of orbital planes of a satellite constellation system at an altitude range corresponding to low earth orbit includes at least one processor configured to generate satellite state data, and to generate a navigation signal based on the satellite state data. The satellite includes at least one transmitter configured to transmit the navigation signal for receipt by at least one client device on earth. Each of the plurality of orbital planes includes a corresponding one of a plurality of satellite subsets of a plurality of satellites of the satellite constellation system. Each of the plurality of orbital planes is within the altitude range, and the plurality of orbital planes includes a set of inclined orbital planes at a non-polar inclination.

A space device includes: an adhesion part to adhere to a target existing in the space; and a propulsion part to obtain propulsion power. The space device that adheres to the target at the adhesion part moves together with the target by the propulsion part, thereby conveying the target to a predetermined target position.

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 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.

A spacecraft including a spacecraft bus and a set of thrusters for changing a pose of the spacecraft. Wherein at least two thrusters are mounted on a gimbaled boom assembly connecting the two thrusters with the spacecraft bus, such that the two thrusters are coupled thrusters sharing the same gimbal angle. A model predictive controller to produce a solution for controlling thrusters of the spacecraft by optimizing a cost function over multiple receding horizons. The cost function is composed of a cost accumulated over the multiple receding horizons, including a cost accumulated over a first horizon using a dynamics governing a north-south position of the spacecraft, and a cost accumulated over a second horizon using a model of dynamics of the spacecraft governing an east-west position. A thruster controller to operate the thrusters according to their corresponding signals.

A device for determining the attitude or variation in attitude of a satellite fitted with an attitude control system comprising at least one inertial actuator. The inertial actuator comprises a rotary element mounted to rotate about an axis of rotation. The rotation of the rotary element is controlled to generate a torque to control controlling the attitude of the satellite. The angular sensor of the device measures the angular rotation of the rotary element about its axis of rotation. The computation unit determines the attitude or variation in attitude of the satellite induced by the rotation of the rotary element as a function of the measurements of angular rotation of the rotary element by the angular sensor. A satellite carrying such a device and a method for determining the attitude or variation in attitude.

Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.