Calculation of time-optimal maneuvers of a spacecraft in case of changing modes of orientation

The author considers angular movement of a space vehicle. The spiro consists of two phases: workable control (in an apogee vicinity) during which the device is to solve a target problem, and duty control phase During duty control phase of the orbit the problems of orbit correction performance are solved with the help of electrojet engines and gravitational unload of accumulated angular momentum of operating members, namely, flywheels. At the process, for transition to orbit correction modes or for transition into demanded orientation on workable control phase, program maneuvers of a space vehicle are made. From the point of view of increase in time taken for gravitational unload is expedient to minimize durations of maneuvers of a space vehicle. Comparison of two ways of maneuvers of a space vehicle, optimum on speed [1, 2], is made. Comparison is made by the results of mathematical modeling at various sets of initial data.