| 摘要 |
FIELD: ground optimization and tests of spacecraft control systems. ^ SUBSTANCE: proposed method consists in physical simulation of spacecraft simulator on stand provided with gas suspension and turntable with drive. Proposed method includes matching the centers of mass of gas of pneumatic system and spacecraft simulator with center of its rotation and simulation of energy fluxes from stars, Sun and ground for external information sensors of system being optimized. Angular motion of spacecraft simulator is controlled in turn by means of system being optimized and technological control system. Turntable with ground energy flux simulator is set in rotation at orbital angular velocity. Increments of disturbing moments are determined in zero position and in position turned relative to horizontal axis before and after stabilization of spacecraft simulator at increased flow rate of gas. Shift of center of mass is calculated by these increments and total duration of switching-on of gas jet engines and center of mass of gas is matched with center of rotation of spacecraft simulator. Possibility of holding the spacecraft simulator within tolerable range of deflection angles from vertical by means of system being optimized is estimated. In case deflection is beyond tolerable limits, optimization is discontinued. ^ EFFECT: enhanced accuracy; reduced labor consumption; cut costs. ^ 3 cl, 4 dwg |
