| 摘要 |
FIELD: space engineering; methods of control of spacecraft in near-round orbit. SUBSTANCE: proposed method includes separation and removal of spacecraft from space object. After separation, position of manned spacecraft is noted and removal pulse is furnished. Then local vertical coinciding with axis of visual observation is plotted by performing successive turns of manned spacecraft around their own axes perpendicular to axis of visual observation. Then, angle of turn of manned spacecraft relative to last axis is determined which is necessary for plotting orbital system of coordinates on board manned spacecraft. After turn through said angle, correction pulse is furnished in direction of orbital velocity if angle is lesser than 90 deg. or opposite orbital velocity if angle exceeds 90 deg. Magnitude of correction pulse is selected by static simulation such that ensuring guaranteed distance between manned spacecraft and space object in free flight and in sending deceleration pulse for orbital departure of manned spacecraft. Proposed method ensures autonomous departure of manned spacecraft from nonoriented space object at absence of information pertaining to their relative position reducing time required for correction at guaranteed safety for objects at all stages of maneuver. EFFECT: enhanced efficiency and reliability. 5 dwg |
