1. The problem statement, all variables and given/known data Hi, I have a textbook problem from a course that I need help with Question: You’ve just completed an analysis of where the Space Shuttle must be when it performs a critical maneuver. You know the shuttle is in a circular prograde orbit and has a position vector of ro=6275.396î+2007.268j +1089.857k In 55 minutes, you predict the orbital parameters are (ER=1 Earth radius): a= 1.0470357 ER (apogeum) , e=0.000096 (eccentricity) i=28.5 degrees (inclination) , M=278.94688 degrees (mean anomaly) Comments: The initial orbit is circular, but the final orbit has eccentricity different from 0, but it is small, perhaps caused by disturbances. Is your analysis correct? Answer with either of the two beginnings a) The analysis can’t be correct, because .... b) The analysis is correct, provided that periapsis has been created at ..... 2. Relevant equations See below 3. The attempt at a solution Here is my attempt to solve this problem: I first began to find the position by calculating the absolute value of the position vector ro given earlier: r=|ro|= 6678.13657 km Then, we know that 55*60= 3300 seconds, which can be used to calculate the period: p= 3300/1.002737 3290.989 seconds (1.0002737 is how many seconds it is in 1 solar day) The semi major axis can be calculated by using the formula for a period: p= 2*pi*sqrt(a3/my) (my=gravitational parameter= 398600.4418 km3/(solar sec)2 I change the equation to get the semi-major axis: a=((p/2*pi)2)3 I inserted the numbers and got a=4782.0080 km. Divide this with the Earth radius and one gets: a=0.7497 ER This is less than a=1.0470357 ER from above, which means that the analysis isn't correct, i.e. my answer is a). But my solution is wrong and I don't know what to do. I would appreciate if someone could explain (and maybe show a solution of) this problem. Thanks!