FIELD: astronautics.
SUBSTANCE: invention relates to space engineering in the field of spacecraft control, which performs remote Earth sensing. Control method consists in automatic installation in orbit of solar batteries along solar sensor in fixed position relative to spacecraft body to obtain maximum illumination thereof, which guarantees positive energy balance in case of any failures in operation of orientation system, in orientation of spacecraft on a given orbit using an angular velocity sensor unit, a microcomputer, an orientation sensor in the form of a device for orientation on Earth or a three-dimensional magnetometer included in the strapdown inertial unit, operating with a block of stellar sensors in different modes; sufficient current value of residual capacity of accumulator battery for target operation and passage of shadow section by spacecraft, high reliability of components of orientation system of Earth remote sensing spacecraft due to justified complex and combined use of reservation, redundancy, majorization, as well as providing a rational algorithm and sequence of components of the orientation system in case of failures.
EFFECT: higher reliability and survivability of Earth remote sensing spacecraft.
1 cl, 1 dwg
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Authors
Dates
2020-06-02—Published
2019-11-12—Filed