I have come across a problem that has had me stumped for a while now.
A spacecraft is in a Sun-synchronous Earth orbit with a =1.40 R⊕ and e = 0.2. The argument of periapsis is ω = 0◦ , and the Right Ascension of the Ascending Node, Ω, is equal to the Sun’s Right Ascension plus 12 hours. Calculate the length of time per orbit for which the spacecraft is in Earth’s shadow, assuming that the Earth is at an equinox.
I'm not fully sure how to interpret this, as everywhere I read, Sun-synchronous orbits are always sunlit?
Any help or a point in the right direction would be much appreciated.