| 摘要 |
A method of launching a spacecraft launch into desired orbit according to a pre-defined program of motion is based on the determination of expected deviations of the final orbital parameters from set values and their compensation by adjustment of program of motion through periodic motion refinement of respective pre-defined programs of control by means of their adjustment. In the case at least the last stage of a booster or spacecraft is equipped with main engines with variable thrust without cutoff at a constant level of specific thrust impulse. The programs of motion are defined for nominal level of second flow rate of fuel m, which corresponds to the middle range of its adjustment, at the constant level of specific thrust impulse. During flight with said main engine expected final deviations from the trajectory, corresponding to a predetermined program of motion, are defined relatove to range &Dgr;D and time &Dgr;t, for compensation of which a two-level diagram is formed of fuel flow rate per second with average value of these levels, which corresponds to the nominal value m, and its deviation for a absolute value of adjustment &Dgr;m and time moment of change of levelsT, and lateral displacement is compensated by adjustments of the program of yaw angle. In the case refinement of the program flow rate of fuel per second after passing moment of time T is stopped. |
