| 摘要 |
A method of launching a spacecraft by a booster into desired orbit according to a pre-defined program of motion is based on determination of expected deviations of final orbital parameters from set values and their compensation by changing program of motion by improvement of corresponding control programs by their corrections. Expected deviations of range and time are compensated by adjustment of booster thrust levels, and final deviations of other parameters of the orbit due to such changes and disturbances are compensated by adjustment of angular control programs, in particular, the lateral slip is compensated by adjustment of the program of yaw angle, for which the booster shall be equipped with at least two stages with controlled primarily propulsions, which thrusts are adjusted, and for each of these stages, except for the last one, current deviations from the program of range of motion and time are determined, according to them the adjustments to the control program are formed. Moreover, if the next stage is the last of the stages with controlled setting, its adjustment is determined by last valuesandof last but one such stage, which were adopted to adjust the thrust program, and the adjustment for program value of yaw angle is defined, for example, according to the ratio,where,- coefficients, which are determined from the condition of compensation of finite deviations. |
