{"push_id":568580205,"size":1,"distinct_size":1,"ref":"refs/heads/patch-1","head":"66019d0dd1bfb29eaf71514be32eb8cc9bbeaca4","before":"6fd735e0060b14461272f5bb68e7d1e78d2eae80","commits":[{"sha":"66019d0dd1bfb29eaf71514be32eb8cc9bbeaca4","author":{"email":"377d82a3d7a4c93a3ce6b5040a591efc04918f0c@gmail.com","name":"Henry"},"message":"Added missing conversion functions\n\nOops, forgot to add conversion functions. As you may notice, MtoE() requires iterating. This is apparently a problem with orbital mechanics themselves. If anyone know any better method for orbit propagation please weigh in. I'm using the mean anomaly to eccentric anomaly to true anomaly, FYI.","distinct":true,"url":"https://api.github.com/repos/HenryRasia/MossSatSim/commits/66019d0dd1bfb29eaf71514be32eb8cc9bbeaca4"}]}