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Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same
Low energy method for changing the inclinations of orbiting satellites using weak stability boundaries and a computer process for implementing same
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机译:利用弱稳定边界改变轨道卫星倾角的低能方法及其实现的计算机过程
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摘要
A fuel efficient technique for changing the inclination, with respect to the Earth's equator, for a satellite includes first maneuvering the satellite to the moon on a BCT (Ballistic Capture Transfer). At the moon, the satellite is in the so-called fuzzy boundary or weak stability boundary. A negligibly small maneuver can then bring it back to the Earth on a reverse BCT to the desired Earth inclination. Another maneuver puts it into the new ellipse at the earth. In the case of satellites launched from Vandenberg AFB into LEO in a circular orbit of an altitude of 700 km with an inclination of 34°, approximately 6 km/s is required to change the inclination to 90°. The previous flight time associated with this method was approximately 170 days. A modification of this method also achieves a significant savings and unexpected benefits in energy as measured by Delta-V, where the flight time is also substantially reduced to 88 or even 6 days. Various alternative embodiments are disclosed.
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机译:一种用于更改卫星相对于地球赤道的倾斜度的省油技术,包括首先在BCT(弹道捕获传输)上将卫星操纵到月球。在月球上,卫星位于所谓的模糊边界或弱稳定边界中。可以忽略不计的小机动将其以与期望的地球倾角相反的BCT返回地球。另一种策略是将其放入地球的新椭圆形。对于从范登堡空军基地以700公里的圆形轨道,倾角为34°的轨道从LEO发射的卫星,将倾角更改为90°大约需要6 km / s。与该方法相关的先前飞行时间约为170天。通过Delta-V测量,此方法的改进还可以节省大量能源并带来意想不到的好处,因为飞行时间也大大减少了88天甚至6天。公开了各种替代实施例。
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