Starting equinoctial orbital element state equations
TO-XXX functions now return the state followed by values for more convenient conversion. Addind equinocital orbital element formulation. Tweaked RVBASIS. Added fixed attitude examples. COE state with sail isn't working right.
Updated document with T derivative, instead of T0, which isn't integrating consistent with the spinor formulation.
Fixed recoverrotor3d. Bunch of other stuff. Seems to be working well. Pointing and accel functions now generic with methods.
added RECOVERROTOR2D, as 3D version didn't work for 2D. Put examples into hash tables to batch runs. Table version not consistent between cartesian and spinor/KS yet.
Lookup table is working - S and TM are only the same in circular orbits with normalized radius, velocity, and gravitational parameter.
Sail class now has the output cartesian coordinate data file in it, so propagate writes to it by default