| 摘要 |
A system of fail-safe deceleration of axisymmetric spacecraft contains a longitudinal angular rate sensor, sensors of the first and second transverse angular rates, a control unit of actuators of longitudinal channel, control units of actuators of the first and second transverse channels, actuators of longitudinal, first and second transverse channels. Between each sensor and control unit are introduced a unit of connection of corresponding sensor, a unit of determining the beginning of deceleration of longitudinal angular rate, a unit of determining the required longitudinal angular velocity, a unit of minimization of consumption of working fluid. For increasing the reliability a unit of testing the first transverse channel and a unit of testing the second channel of actuators control are additionally introduced. |
