day06additionalsatelliteprob

day06additionalsatelliteprob - 10 J 3 A rocket ship of mass...

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HANDOUT – Additional Satellite Problems 1. An artificial Earth satellite, of mass 2.00 x 10 3 kg, has an elliptical orbit, with a mean altitude of 400. km. a) What is its mean value of gravitational potential energy while in orbit? b) What is its mean value of orbital kinetic energy? c) What is its total energy while in orbit? d) If its perogee 9s 280 km, what is its orbital velocity at perogee? (Answers: -1.18 x 10 11 J, 5.88 x 10 10 J, -5.88 x 10 10 J, 7.78 x 10 3 m/s) 2. A 500. kg satellite is in circular orbit 200. km above the Earth’s surface. Calculate the following: a) the gravitational potential energy of the satellite. b) the kinetic energy of the satellite. (-3.03 x 10 10 J, 1.52 x 10 10 J, 1.52 x 10
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Unformatted text preview: 10 J) 3. A rocket ship, of mass 1.00 x 10 4 kg is located 1.00 x 10 10 m from the centre of the Earth. a) Determine its gravitational potential energy at this point, considering only the Earth. b) How much kinetic energy must it have, at this point, to be capable of escaping from the Earth’s gravitational field? c) What is its escape velocity from Earth, at this point? (Answers: -3.99 x 10 8 J, >3.99 x 10 8 J, 2.82 x 10 2 m/s) NOTE: Perogee is that point in an elliptical orbit where it most closely approaches the orbited body. The apogee is that point in an elliptical orbit where it is furthest from the orbited body. A:\sph4u1\chap6\day06additionalsatelliteprob.doc...
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This note was uploaded on 10/27/2011 for the course PHYSICS 1028 taught by Professor C.jones during the Spring '09 term at UWO.

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