Calculate Speed and Time to Revolve Around the Moon

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SUMMARY

The discussion focuses on calculating the speed and time required for a command module to revolve around the Moon at an altitude of 60 miles. The mass of the Moon is given as 7.35 x 1022 kg, and the radius of the Moon is 1.74 x 106 m. The calculated orbital speed (Vcm) of the command module is 1.679 meters/second, derived from the formula Vcm2 = G * Mm/Ro. To determine the time for one complete revolution, the discussion suggests using Kepler's Third Law with the formula P = 2π√(a3/μ).

PREREQUISITES
  • Understanding of gravitational physics and orbital mechanics
  • Familiarity with Kepler's laws of planetary motion
  • Knowledge of the gravitational constant (G = 6.673 x 10-11 N(m/kg)2)
  • Ability to perform unit conversions (e.g., miles to meters)
NEXT STEPS
  • Learn how to apply Kepler's Third Law for different orbital scenarios
  • Research the gravitational parameter (μ) for various celestial bodies
  • Explore the implications of altitude on orbital speed and period
  • Study the effects of orbital eccentricity on revolution time
USEFUL FOR

Aerospace engineers, physics students, and anyone interested in orbital mechanics and satellite dynamics will benefit from this discussion.

cowgiljl
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if the command module is 60 miles above the surface of the moon it wants me to calculate the speed of the module adn the time it takes to complete one revolutionaround the mooon?
givens

mass moon = 7.35 * 10 to the 22 power
radius moon = 1.74 * 10 to the 6 power
altitude above the surface of the moon = 60 miles

converted the 60 miles to meters which was 96540 m

Ro = Rm + h
Ro = 1.74E6 + 96540
Ro = 1.74E22

Vcm is the command module

Vcm^2 = G * Mm/ro
Vcm^2 = 6.673E-11 * 7.35E22/1.74E22
Vcm = 1.679 meters/sec

and not sure if this is right and don't know what to use to figure out the time it took to make 1 revolution

thanks
 
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on the time part of it should i use kelpters law?
 
Period can be found by using this formula:

[tex] <br /> P = 2\pi \sqrt{\frac{a^3}{\mu}}}<br /> [/tex]

Where a is the semimajor axis (the radius for circular orbits, like your problem)
and mu is the gravitational parameter, or G*M
 

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