Suppose that a space probe is in a circular orbit at an alti

Suppose that a space probe is in a circular orbit at an altitude of 160 mi above the surface of the Earth. Use v = squareroot GM/r_0 to find its speed. Assume the Earth to be a sphere of radius 4000 mi and the Earth value of GM = 1.24 Times 10^12 mi^3/h^2. Round your answer to the nearest integer. Speed ~~ mi/h During a very short period of time, a thruster rocket on the space probe is fired to increase the speed of the probe by 600 mi/h in its direction of motion. To three decimal places, find the eccentricity of the resulting elliptical orbit, and use r_min = a(1 - e) and r_max = a(1 + e), where a is the semimajor axis and e is the eccenticity. to find the apogee altitude to the nearest mile. Eccentricity ~~ Altitude ~~ mi

Solution

speed = 19.6