| 摘要 |
FIELD: physics. ^ SUBSTANCE: invention relates to control of motion of an upper-stage rocket (USR) when taking to a reference orbit. After separation of the USR from the carrier rocket (CR), data on control parametres and orbit formed on delta-velocity manoeuvre are read from the mission task (MT). After launching the cruise engine, the program for orientation of the USR on the pitch is developed. The orientation program is corrected on the delta-velocity manoeuvre. The cruise engine is switched off when the given energy functional is achieved. The invention is characterised by that, after separation of from the CR, the radius of apogee of the formed CR orbit is calculated from values of velocity vectors and radius vector of the USR at the moment of separation from the CR and from the value of its deviation from the nominal value, the value of the initial angle of the program for changing pitch on the delta-velocity manoeuvre, rate of its change, the focal parametre of the formed orbit, its eccentricity, the given energy functional and value of elements of two rows of a matrix which defines orientation of the orbit after delta-velocity manoeuvre are recalculated. ^ EFFECT: owing to recalculation of parametres of the program of orientation on the pitch and parametres of the formed reference orbit applied to conditions after separation of the upper-stage rocket from the carrier rocket given in the mission task for nominal flight conditions, power consumption for the USR on delta-velocity manoeuvre is reduced, which enables to increase weight of the payload. ^ 2 tbl |
