Do not copy and paste from another Chegg expert, this violates the plagiarism policy and will get reported. Answers for CHECKING WORK ONLY:

a) inclination: 49.9, RA of ascending node: 143.6, argument of perigee: 248.4, eccentricity: 0.847; b) perigee altitude: 2160.0 km

The geocentric equatorial position vector of an earth satellite at a given instant in km is given by: R1 = (80001 15003 4200K) km (4) Thirty minutes later, the position is: R2 = (-3000 + 9000 6500 ) km (5) Solve Lambert's problem: (a) Determine the inclination, right ascension of the ascending node, argument of perigee and the eccentricity of the orbit. (b) What is the perigee altitude of the satellite? The geocentric equatorial position vector of an earth satellite at a given instant in km is given by: R1 = (80001 15003 4200K) km (4) Thirty minutes later, the position is: R2 = (-3000 + 9000 6500 ) km (5) Solve Lambert's problem: (a) Determine the inclination, right ascension of the ascending node, argument of perigee and the eccentricity of the orbit. (b) What is the perigee altitude of the satellite