METHOD OF spacecraft orientation with fixed solar panels In the experiments performed into orbit from the maximum duration of the shadow areas

摘要

Method spacecraft attitude control with fixed solar panels when performing experiments on orbits with the maximum length of the shadow portion comprising gravitational spacecraft orientation of the longitudinal axis along the local vertical and twist about its longitudinal axis corresponding to the minimum moment of inertia performed at the angle between the direction to the Sun and the plane of the orbit has not to exceed a predetermined value, characterized in that the determined and fixed time passing spacecraft sunscreen point revolution orbit, deploying the spacecraft about the longitudinal axis until the time twist angle between the projection of a normal to the active surface of the solar cell to the local horizon plane and normal to the orbit of the values ​​90 ° · (1-k) plane + k · | Δt | · i · 360 ° / T and the angle between the projection of a normal to the active surface of the solar cell to the local horizon plane and the vector of the spacecraft velocity values ​​where Δt - the time from the point of passage of sunscreen round the orbit until the twist; T - the period of revolution of the spacecraft in orbit; k = ± 1; i - a positive odd integer, the value of which is chosen from the condition of maintaining the stability of the gravitational orientation of the spacecraft and the spacecraft spin is performed at the time of achieving the above-defined angle with the angular values ​​skorostyupri positive direction of the reference angular velocity of the center of the Earth.