FIELD: space.
SUBSTANCE: invention relates to definition of mass-inertia characteristics of spacecraft. Method involves measuring acute angle between direction of the Sun and plane of orbit of spacecraft. When said angle reaches a maximum, construction axis of spacecraft is set, where said axis meets maximum moment of inertia, perpendicular to orbit plane. Solar panels fixed with respect to spacecraft are directed by active side towards the Sun. Method then includes spinning spacecraft around said axis with angular speed of not less than 2°/s. Spacecraft angular velocity and solar panel current is measured during rotation of spacecraft around the Earth. Measured values are used to determine tensor of inertia of spacecraft.
EFFECT: technical result consists in improvement of reliability of determination of tensor of inertia of spacecraft, including in absence of onboard inertial actuators.
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|
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