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The issue with launch window wasn't whether the launch vehicle could get the object into space or even to L1, it's whether the last stage can still insert the object into a semi-stable orbit about L1. The c3 of the rocket was way more than enough. If you launch at the wrong time of day, you need to use more fuel but it also means you approach L1 at a "...


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$\newcommand{\r}{\mathbf{r}}$ $\newcommand{\i}{\mathbf{i}}$ Lagrange's set of solutions for the three-body problem is more general than just the points, which are special cases of a broader family of possibilities. The conditions under which they exist are very restrictive, but less so than the standard assumptions you list. Everything here is for the full ...


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