57 results about "Micro satellites" patented technology

A satellite-to-satellite on-orbit docking and locking device is used for docking a service satellite with a non-cooperative target satellite, and comprises a guide structure, a locking device, and a positioning pin, wherein the guide structure is mounted on the service satellite, the guide structure comprises a tapered surface for eliminating the deviation in the axial tilt angle of docking posture with the non-cooperative target satellite, the guide structure further comprises a sectioned notch with a bevel edge, and the sectioned notch is used for correcting the deviation in circumferential rotation angle with respect to a docking ring of the non-cooperative target satellite; the locking device is mounted on the service satellite, the locking device comprises a cam wheel, two clamping claws stretch out from the edge of the cam wheel, and a bayonet is formed between the two clamping claws, so as to restrain the inner edge of the docking ring of the non-cooperative target satellite. The positioning pin is arranged on the guide structure and is matched with a positioning pin hole on the docking ring of the non-cooperative target satellite, so as to precisely guide and restrain the relative position between the service satellite and the non-cooperative target satellite. The satellite-to-satellite on-orbit docking and locking device is applicable to all satellites with the docking ring; and the satellite-to-satellite on-orbit docking and locking device is substantially wide in application range, including large satellites, small satellites, and micro satellites.

The invention relates to a phased array data transmission guide control method based on onboard real-time planning and relates to the field of spacecraft attitude determination and control. The method realizes a function of achieving fast data transmission after imaging of micro satellites and performing data transmission while imaging. The method comprises the following steps: if an imaging mode is used, setting the imaging priority and the data transmission priority as 1 and 0 respectively; if data transmission is simultaneously performed by two data transmission stations, ranking the priorities of the digital transmission stations, setting the priority of the digital transmission station with high priority as 1 and the other one as 0; if a single data transmission station performs the data transmission, setting the priority of the data transmission station as 1; calculating the expected orientation, the azimuthal angle and the off-axis angle of a phased array antenna; if the off-axis angles satisfies a constraint condition, requiring no posture maneuver, otherwise, setting a mode with a priority of 1 as dominant; and in the case of the mode with a priority of 1 as dominant, if the off-axis angle satisfies the constraint condition, enabling the satellite not to require attitude maneuver, otherwise using the data transmission station with high priority as an expectation and enabling the phased array antenna to point to a target point by controlling the attitude of the satellite. The method can realize fast data transmission and data transmission during imaging.

The system and method represents a high-resolution, three-dimensional, multi-static precipitation RADAR approach that employs agile microsatellites, in formation and remotely coupled, via a new high-precision, ultra-low power, remote timing synchronization technology. This system and method uses multi-static RADAR interferometric methods implemented via a microsatellite formation to synthesize an effectively large (e.g., 15 m) aperture to provide about 1 km horizontal resolution and about 125 m vertical resolution in the Ku-band.

The invention provides a spacecraft fluid ring reaction performing mechanism. The spacecraft fluid ring reaction performing mechanism comprises a mounting base used for mounting a fluid ring and corresponding devices, the fluid ring used for generating angular momentum, an electromagnetic pump assembly which mainly comprises a permanent magnet or an electromagnet and an electrode board pair and is used for driving liquid in the fluid ring to do controllable-speed flowing, a filling liquid which employs a conductive liquid material, is mounted in the fluid ring and flows under the driving action of the electromagnetic pump assembly, and a shielding box which covers outside an electromagnetic pump and is used for shielding an electric field and a magnetic field to prevent interference of external devices. The spacecraft fluid ring reaction performing mechanism utilizes the electromagnetic pump to drive the liquid ring to generate angular momentum to realize attitude control of a spacecraft, can provide multi-axial control moments for attitude control of spacecrafts especially micro satellites, requires no mechanical rotation bearing part and further has properties of high reliability, simple structure and small energy consumption.