METHOD FOR DETERMINING SPACE VEHICLE INERTIA TENSOR IN FLIGHT

摘要

A method for determining the inertia tensor of a spacecraft in flight, including the inertial orientation and turns of the spacecraft, characterized in that the spacecraft is oriented by stabilizing its construction axis in the inertial coordinate system, which is closest to the axis corresponding to the maximum moment of inertia, and spin the spacecraft around this building axis with an angular velocity Ω of at least 2%, they measure in the construction coordinate system of the spacecraft the directions to the recorded stars and the angle the speed of the spacecraft up to the time T = T + Δt, where, where T is the time of the spin of the spacecraft; Δt is the time interval of the weakly perturbed motion of the spacecraft; Ω is the angular velocity of the spin around the construction axis nearest the axis of the maximum moment of inertia; R - radius of the orbit; µ is the Earth’s gravitational parameter; K is the reliability coefficient, the registered stars are recognized, the directions to the identified stars are determined in the inertial coordinate system and the inertia tensor of the spacecraft is determined from measured and determined on the time interval Δt directions to recognized stars and measurements of the angular velocity of the spacecraft.