VEC MECH 180-DAT EBOOK ACCESS(STAT+DYNA)

12th Edition

ISBN: 9781260916942

Author: BEER

Publisher: MCG

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Textbook Question

Chapter 13.2, Problem 13.112P

Show that the values v_A and v_P of the speed of an earth satellite at the apogee A and the perigee P of an elliptic orbit are defined by the relations

v A 2 = ( 2 G M r A + r P r P r A ) v P 2 = 2 G M r A + r P r A r P

where M is the mass of the earth, and r_A and r_P represent, respectively, the maximum and minimum distances of the orbit to the center of the earth.

Fig. P13.112 and P13.113

Chapter 13.2, Problem 13.112P, Show that the values vA and vP of the speed of an earth satellite at the apogee A and the perigee P

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Chapter 13.2, Problem 13.111P

Chapter 13.2, Problem 13.113P

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Chapter 13 Solutions

VEC MECH 180-DAT EBOOK ACCESS(STAT+DYNA)

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Solution Summary: The author demonstrates the values of (v_A) and () 'left' of the speed of an earth satellite at apogee A and perigee P

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