An attitude estimation method for an on-orbit three-dimensional space object comprises an offline feature library construction step and an online attitude estimation step. The offline feature library construction step comprises: according to a space object three-dimensional model, acquiring multi-viewpoint characteristic views of the object, and extracting geometrical features therefrom to form a geometrical feature library, where the geometrical features comprise an object main body height-width ratio, an object longitudinal symmetry, an object horizontal symmetry, and an object main-axis inclination angle. The online attitude estimation step comprises: preprocessing an on-orbit object image to be tested and extracting features, and matching the extracted features in the geometrical feature library, where an object attitude characterized by a characteristic view corresponding to a matching result is an attitude estimation result. A dimension scale and position relationship between various components of an object are accurately acquired in a three-dimensional modeling stage, thereby ensuring subsequent relatively high matching precision. An attitude estimation system for an on-orbit three-dimensional space object is also provided.

A three-point propulsion system of an orbital deployment space module for at least one satellite including: chassis including exactly three first housings shaped to each receive a propulsion unit and at least one second housing shaped to receive a tank, at least one liquid fuel tank disposed in a second housing, and exactly three propulsion units, each propulsion unit being disposed in one of the first housings, and each propulsion unit including at least one thruster.

Described herein are spacecraft flight and mission managers and systems, methods, and computing apparatuses for dynamically maneuvering a spacecraft towards a target area for synthetic aperture radar (SAR) capture based on antenna availability. In an embodiment, a flight and mission manager obtains user inputs for a spacecraft mission related to a synthetic aperture radar request of a target area and maneuvers for a spacecraft to reach that target area. An orbit path is determined based on user inputs and telemetry of the spacecraft. A visibility schedule of antennas of a ground station provider is obtained corresponding to the orbit path. Then, a tasking plan is generated to perform the user inputs and maintain the orbit path.

A method, apparatus and system for controlling an attitude of a spacecraft, the spacecraft including an attitude control system operatively associated with a ground-based spacecraft control system. According to an exemplary embodiment, the spacecraft attitude control system uses a B-spline interpolator for commanding the spacecraft and a Kalman filtering process is used to estimate B-spline interpolator coefficients. The methods and systems disclosed herein can be implemented in, for example, executable machine code and/or integrated circuit hardware.

The present disclosure relates to a method of generating auxiliary data for controlling a satellite travelling in orbit around Earth, the method comprising: receiving tracking data for the satellite; applying an orbit determination algorithm including: estimating an orbit for the satellite based on the tracking data; and predicting, based on the estimated orbit, future ephemerides data of the satellite; generating auxiliary data comprising predicted future ephemerides data; and transmitting the auxiliary data to the satellite for use in the satellite's attitude and orbit control.

A hybrid magnetometer and attitude determination and control system (hybrid magnetometer attitude determination and control system). Many scientific and commercial satellites in low-Earth orbit (LEO) use attitude determination and control systems that enable control and knowledge of the spacecraft's attitude (the orientation the spacecraft). The hybrid magnetometer and attitude determination and control system is a single package that can be integrated into small satellites, such as CubeSats, and consists of a three-axis search coil AC magnetometer and three-axis quad-mag DC magnetometer. The search coil sensors also act as torque rods for part of the orbit. Noise cancellation algorithms enable scientific grade magnetic measurements from the system without needing a sensor boom.

A method for inserting a spacecraft into a desired orbit around an astronomical body includes determining control input for the spacecraft as it travels through an atmosphere of the astronomical body to achieve a desired state for the spacecraft when the spacecraft exits the atmosphere of the astronomical body, the determining including determining a bank angle for the spacecraft as the spacecraft travels through the atmosphere of the astronomical body with a substantially fixed angle of attack, determining an updated angle of attack for the spacecraft as the spacecraft travels through the atmosphere of the astronomical body with the determined bank angle, wherein the spacecraft traveling through the atmosphere of the astronomical body with the bank angle and updated angle of attack substantially achieves the desired state for the spacecraft when the spacecraft exits the atmosphere.

The invention relates to a satellite comprising: a satellite body including at least one radiative surface configured to emit satellite heat to space; and an attitude determination and control ADCS system for controlling an orientation of the satellite travelling in orbit around Earth, wherein the ADCS system is configured to change the orientation of the satellite with respect to the sun between a first position in which the radiative surface points away from the sun and a second position in which the radiative surface is exposed to the sun. The invention further relates to a method of controlling thermal radiation heat transfer of a satellite.

A device (1) for controlling the angular velocity of an out-of-service spacecraft including: a stator (3) and a rotor (4) movable about an axis (A21) of rotation with respect to the stator. The stator (3) includes an electrically conductive and non-ferromagnetic body (6) while the rotor (4) includes a magnetized system (7) configured to induce, in the stator (3), eddy currents for braking a relative movement of the rotor (4) with respect to the stator (3); and a magnetic-suspension magnet (11) configured to cooperate with a magnetic field generated by an external source to suspend the rotor (4) magnetically with respect to the stator (3). The device (1) includes one or more non-ferromagnetic materials in a zone (11ZI) of influence of the magnetic field generated by the magnetic-suspension magnet.

A vehicle capable of computing an optimal attitude path that provides increased solar power generation through snap-roll events during orbital transfer maneuvers. A vehicle may include a memory and processor, including instructions, when executed can perform the steps of generate an attitude profile of the vehicle during an orbital transfer; identify, from the attitude profile, a snap-roll event; and generate instructions to adjust an angular velocity of the vehicle during a time period corresponding to the snap-roll event to satisfy a target angular velocity.