3/276 The Mars orbiter for the Viking mission was de- signed to make one complete trip around the planet in exactly the same time that it takes Mars to revolve once about its own axis. This time is 24 h, 37 min, 23 s. In this way, it is possible for the or- biter to pass over the landing site of the lander capsule at the same time in each Martian day at the orbiter's minimum (periapsis) altitude. For the Viking I mission, the periapsis altitude of the or- biter was 1508 km. Make use of the data in Table D/2 in Appendix D and compute the maximum (apoapsis) altitude ha for the orbiter in its elliptical path. ha h,= 1508 km

University Physics Volume 1
18th Edition
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Author:William Moebs, Samuel J. Ling, Jeff Sanny
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Chapter13: Gravitation
Section: Chapter Questions
Problem 86CP: Using Figure 13.9, carefull sketch a free body diagram for the case of a simple pendulum hanging at...
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Answer: ha= 32 600 km

3/276 The Mars orbiter for the Viking mission was de-
signed to make one complete trip around the
planet in exactly the same time that it takes Mars
to revolve once about its own axis. This time is 24 h,
37 min, 23 s. In this way, it is possible for the or-
biter to pass over the landing site of the lander
capsule at the same time in each Martian day at
the orbiter's minimum (periapsis) altitude. For the
Viking I mission, the periapsis altitude of the or-
biter was 1508 km. Make use of the data in Table
D/2 in Appendix D and compute the maximum
(apoapsis) altitude ha for the orbiter in its elliptical
path.
ha
h,= 1508 km
Problem 3/276
Transcribed Image Text:3/276 The Mars orbiter for the Viking mission was de- signed to make one complete trip around the planet in exactly the same time that it takes Mars to revolve once about its own axis. This time is 24 h, 37 min, 23 s. In this way, it is possible for the or- biter to pass over the landing site of the lander capsule at the same time in each Martian day at the orbiter's minimum (periapsis) altitude. For the Viking I mission, the periapsis altitude of the or- biter was 1508 km. Make use of the data in Table D/2 in Appendix D and compute the maximum (apoapsis) altitude ha for the orbiter in its elliptical path. ha h,= 1508 km Problem 3/276
PROBLEMS
(Unless otherwise indicated, the velocities mentioned in
the problems which follow are measured from a nonrotat-
ing reference frame moving with the center of the attract-
ing body. Also, aerodynamic drag is to be neglected unless
stated otherwise. Use g = 9.825 m/s² (32.23 ft/sec²) for the
absolute gravitational acceleration at the surface of the
earth and treat the earth as a sphere of radius R = 6371 km
(3959 mi).)
Transcribed Image Text:PROBLEMS (Unless otherwise indicated, the velocities mentioned in the problems which follow are measured from a nonrotat- ing reference frame moving with the center of the attract- ing body. Also, aerodynamic drag is to be neglected unless stated otherwise. Use g = 9.825 m/s² (32.23 ft/sec²) for the absolute gravitational acceleration at the surface of the earth and treat the earth as a sphere of radius R = 6371 km (3959 mi).)
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