FIELD: aircraft engineering.
SUBSTANCE: invention relates to control over spacecraft centre of gravity in flight to collinear points of libration L1 or L2 of the "Sun-Earth" system. Proposed method comprises spacecraft start (2) from initial round near-earth orbit (1) with transfer to flight path to libration point. At said path, spacecraft is stabilised by spinning it around lengthwise axis directed to reference point (the Sun). Results of measurements of spacecraft centre of gravity motion are used to correct the flight path by applying correction pulses along spacecraft stabilisation axis. In spacecraft start (2), acceleration unit is used to impart too high velocity pulse to decrease maximum possible onboard fuel consumption required for correction of placing errors. Said pulse is determined with due allowance for ballistic parameters and spacecraft speed error dispersion at correction first point (3). Decrease in fuel consumption increases onboard fuel store for correction of spacecraft instable orbit nearby libration point.
EFFECT: reduced consumption of spacecraft onboard power, longer life nearby libration point.
2 dwg
