发明名称 |
CONTROL OVER SPACECRAFT AT ITS ASCENT TO EARTH ARTIFICIAL SATELLITE ORBIT |
摘要 |
FIELD: aircraft engineering.SUBSTANCE: invention relates to aerospace engineering and can be used for and can be used for control over spaceship flight-in path control in the orbit of the Earth artificial satellite with atmosphere. Claimed process comprises the aerodynamic deceleration of spaceship and reactive correction of its orbit at the out-of-atmosphere section. Depressed aerocapture is performed at the target aerocapture angle computed such that the spaceship required speed is reached at its ricochet from atmosphere (at termination of aerodynamic deceleration) at a definite altitude. Multiple passage through the upper atmosphere decreased the spaceship orbit apocentre to permissible level. At said apocentre the impulse of characteristic velocity of its ascent to the orbit of artificial satellite.EFFECT: higher efficiency of control over aerodynamic and reactive means without application of high-precision system and control algorithms.1 dwg |
申请公布号 |
RU2573695(C1) |
申请公布日期 |
2016.01.27 |
申请号 |
RU20140137608 |
申请日期 |
2014.09.16 |
申请人 |
FEDERAL'NOE GOSUDARSTVENNOE UNITARNOE PREDPRIJATIE "TSENTRAL'NYJ NAUCHNO-ISSLEDOVATEL'SKIJ INSTITUTMASHINOSTROENIJA" (FGUP TSNIIMASH) |
发明人 |
SOKOLOV NIKOLAJ LEONIDOVICH;KARTSEV JURIJ ALEKSANDROVICH;SELEZNEVA IRINA ALEKSANDROVNA;SOBOLEVA OL'GA VLADIMIROVNA |
分类号 |
B64G1/10;B64G1/62 |
主分类号 |
B64G1/10 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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