Velocity needed to maintain orbit

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SUMMARY

An Earth satellite at a distance of 6104 km from the center of the Earth requires a velocity of approximately 4042.06 m/s to maintain its orbit. The calculations involved using the gravitational constant (6.67 x 10^-11 N m²/kg²) and the mass of the Earth (5.88 x 10^24 kg). The correct formula for orbital velocity is derived from the centripetal force equation, leading to the conclusion that the velocity can be calculated using v = sqrt(GM/(R+h)), where R is the radius and h is the altitude above the Earth's surface.

PREREQUISITES
  • Understanding of gravitational force and centripetal force concepts
  • Familiarity with the universal gravitational constant and its application
  • Knowledge of basic orbital mechanics and satellite motion
  • Ability to manipulate algebraic equations and solve for variables
NEXT STEPS
  • Study the derivation of the orbital velocity formula v = sqrt(GM/(R+h))
  • Learn about the implications of altitude on satellite velocity and orbital stability
  • Explore the differences between circular and elliptical orbits
  • Investigate real-world applications of satellite velocity calculations in aerospace engineering
USEFUL FOR

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

BoldKnight399
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An Earth satellite remains in orbit at a distance of 6104 km from the center of the Earth. What speed would it have to maintain? The universal gravitational constant is 6.67X10^-11 N m^2/kg^2. The mass of the Earth it 5.88X10^24 kg. Answer in units of m/s.

So again, missed the class. I'm crying. Most of my classmates are crying. (the few exceptions finding everything else to do in the world BUT help...) I tried this:
I knew that it had to go into the equation:
Vt=2piR/T
since I didn't have T i used the equation:
R= [(G x m x T^2)/(4pi)^2]^(1/3)
sooo that became:

6104000m=[(6.67X10^-11)(5.98X10^24kg)(T^2)/(4pi)^2]^(1/3)
(2.274X10^20)= (3.98866X10^14)(T^2)/(4pi)^2
T=9488.369sec
so then plugging back in I got:

Vt=(2pi)(6104000m)/9488.369sec
thus the answer was 4042.06066 m/s

guess what? That was wrong.

If anyone has any ideas where I messed up or if I just had a "100% FAIL" moment, I would love to hear it.
 
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Centripetal force on the satellite is
G*M*m/(R+h)^2 = m*v^2/(R+h)
S0 v=sqrt[GM/(R+h)]
Now solve.
 
Thank You!
 

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