摘要
采用了航天器在行星上层大气中进行高超声速飞行时的轨道动力学方程,针对航天器从地球静止轨道转移到一个共面圆形低地轨道的变轨过程,进行了气动力辅助变轨过程的模拟。在变轨过程中,航天器从地球静止轨道开始,经过8次大气路径,耗时43.7小时,到达圆形低地轨道,与霍曼转移进行对比,其所消耗的推进剂质量仅为霍曼转移的41%。研究结果表明:气动力辅助变轨技术能够在降低推进剂消耗的情况下实现航天器的轨道转移。
The orbital dynamic equations of spacecraft for hypersonic atmospheric flight in the upper atmosphere of planets were employed, carried out the orbital transfer simulation aiming at the orbital transfer of spacecraft that got to circular low earth orbit, starting from the geostationary orbit. During the orbital transferring, the spacecraft achieved the circular low-earth orbit using a total of eight atmospheric passes and about 43.7 hours, then compared with Hohmann transfer, the propellant mass that expended is only 41% of that consumed in Hohmann transfer. The result shows that the aeroassisted orbital transfer technology can carry out the orbital transfer of spacecraft with an expenditure of propellant mass signifi- cantly small.
出处
《力学季刊》
CSCD
北大核心
2010年第1期8-14,共7页
Chinese Quarterly of Mechanics
基金
航天科技CAST基金资助(CAST2006023)
关键词
气动力辅助变轨
轨道动力学
稀薄气体动力学
轨道模拟
aeroassisted orbital transfer
orbital dynamics
rarefied gas dynamics
orbital simulation
