1. The problem statement, all variables and given/known data A landing craft with mass 1.22×10^4 kg is in a circular orbit a distance 5.50×10^5 m above the surface of a planet. The period of the orbit is 5100 s . The astronauts in the lander measure the diameter of the planet to be 9.50×10^6 m . The lander sets down at the north pole of the planet. What is the weight of an astronaut of mass 84.1 kg as he steps out onto the planet's surface? 2. Relevant equations circular motion speed: v = √GM/r g: GM/r2 T = 2πr/v 3. The attempt at a solution I tried to solve for the speed by using the period. 5100 = 2π(5.50*10^5)/v v = 677.6 m/s and using the circular motion speed equation, I tried to solve for M, where the radius i used is the radius of the planet: 677.6 = √6.67*10^-11*M/4.75*10^6 M = 3.27*10^22 and then i used GM/r^2 to solve for G. 6.67*10^-11*3.27*10^22/(4.75*10^6) and i got a really small g. I think I'm missing something. Especially because I haven't used the space satellite's mass.