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What is the specific energy of a spacecraft in an elliptical orbit around earth? Given, apogee and perigee distance from the surface of earth are 6250 km and 525 km respectively. The radius and standard gravitational parameter of earth are 6378 km and 398,600 km3/s2.

Correct Answer: -30.3 km3/s2
Given, Standard gravitational parameter (μ) = 398,600 km3/s2 Radius of earth (RE) = 6378 km Semi-major axis (a) = (525 + 6250 + 6378)/2 = 6576.5 km Specific energy (ε) = -μ/(2a) = -398,600/(2*6576.5) = -30.3 km3/s2

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