Multi-mode attitude determination method for remote sensing micro nano statellite

Abstract

The invention relates to a multi-mode attitude determination method for a remote sensing micro nano satellite, and belongs to the technical field of spacecraft attitude control. The method comprises the steps that a magnetometer, a sun sensor and three star sensors serve as original attitude measurement data sources, according to a telemetry command received by the satellite and by combining withthe working state of the sensor, two attitude determination modes are designed, and the two modes are the sun pointing attitude determination mode and the remote sensing imaging posture determinationmode. For the sun pointing attitude determination mode, the magnetometer and the sun sensor serve as measurement input, in combination with the Calman filtering method, the sun pointing attitude determination mode has the advantages of being low in power consumption and high in reliability, and certain precision attitude determination can be provided to meet the control requirements of the micro nano satellite sailboard sun pointing. The remote sensing imaging attitude determination mode uses the three star sensors as the measurement input, in combination with the three-star sensitive attitudefusion method, high-precision micro nano satellite attitude and angular velocity determination can be achieved, and the high-precision attitude control requirements of micro nano satellite remote sensing imaging are met.

Description

technical field [0001] The invention relates to a multi-mode attitude determination method for remote sensing micro-nano satellites, belonging to the technical field of spacecraft attitude control. Background technique [0002] For satellites as remote sensing payload platforms, in order to obtain high-resolution remote sensing images, it is necessary to maintain a stable satellite attitude during remote sensing. The stable attitude keeping control depends on high-precision satellite attitude data, which needs to be guaranteed by the high stability and high precision of the attitude determination system. On traditional satellites, it can be achieved by combining high-power, high-precision gyroscopes with large-scale high-precision attitude sensors. For micro-satellites, the size and energy are limited, which requires attitude measurement sensors with low power consumption, small size and high precision, and a good attitude determination method to obtain high-precision satel...

AI Technical Summary

Problems solved by technology

[0004] Most of the above-mentioned existing satellite attitude determination methods do not consider the power consumption limitation of the micro-nano satellite platform, and use multi-sensors such as gyroscopes and radars with high power consumption and high cost for attitude measurement

Even using low-power horizons, sun sensors, and magnetometers for attitude determination, the high-precision attitude determination requirements required by payload tasks are not considered

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