FIELD: space.
SUBSTANCE: invention relates to determination of mass-inertia characteristics of spacecraft. According to method if direction to the Sun coincides with spacecraft orbit plane, construction axis of spacecraft, responsible for its maximum moment of inertia, is aligned with said direction. Solar panels fixed relative to spacecraft are set perpendicular to said axis, with active side towards the Sun. Spacecraft is spun around this axis with angular speed of not less than 2°/s. Spacecraft angular velocity, current of solar panels and angle between axis and direction to the Sun are measured. When said angle reaches a value of not less than 10° spacecraft inertia tensor is determined from measured values of angular velocity and solar panel current.
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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