Height and Acceleration of a Satellite in Orbit

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SUMMARY

The discussion focuses on calculating the height and acceleration of a satellite in orbit using gravitational equations. The gravitational force equation, Eg = Gme/r^2, was applied to derive the radius (r) of the orbit, resulting in a height (h) of approximately 3,030 km above Earth's surface. The participants confirmed that the direction of acceleration for a satellite in circular motion is towards the center of the Earth, aligning with the concept of centripetal acceleration. The calculations were validated, indicating that a height of over 3,000 km is consistent with gravitational principles.

PREREQUISITES
  • Understanding of gravitational force equations, specifically Eg = Gme/r^2
  • Knowledge of centripetal acceleration and its relationship to gravitational force
  • Familiarity with the concept of uniform circular motion
  • Basic understanding of vector quantities and their directional properties
NEXT STEPS
  • Study gravitational force calculations using Newton's law of universal gravitation
  • Learn about centripetal acceleration and its applications in orbital mechanics
  • Explore the relationship between radius and gravitational force in satellite motion
  • Investigate the effects of altitude on gravitational acceleration and satellite stability
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Students and professionals in physics, aerospace engineering, and anyone interested in satellite dynamics and gravitational calculations.

benca
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Homework Statement
A satellite is designed to orbit earth at an altitude above its surface that will place it in a gravitational field with a strength of 4.5 N/Kg

a) Calculate the distance above the surface of the earth at which the satellite must orbit

b) Assuming the orbit is circular, calculate the acceleration of the satellite and its direction

c) at what speed must the satellite travel in order to maintain this orbit?
Relevant Equations
Eg = Gme/r^2

me = mass of the earth
a)

Eg = Gme/r^2
r = √Gme/Eg
r = √[(6.67x10^-11 N*m^2*kg^2)(5.98x10^24 kg)]/(4.5 N/kg)
r = 9.41x10^6 m

h = r2 - r1
h = 9.41x10^6 m - 6.38x10^6 m
h = 3.03x10^6 m

that's over 3000 km. Did I not use for right equation? Is Eg not 4.5 N/kg?

Also for b), isn't the force of gravity the centripetal acceleration? so wouldn't it be the same equation? ac = Gme/r^2

and I don't know what it means by direction. isn't it accelerating in a circular motion? This one has really got me confused.
 
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benca said:
that's over 3000 km. Did I not use for right equation? Is Eg not 4.5 N/kg?

Also for b), isn't the force of gravity the centripetal acceleration? so wouldn't it be the same equation? ac = Gme/r^2

and I don't know what it means by direction. isn't it accelerating in a circular motion? This one has really got me confused.

Why do you think over 3000km is wrong?

Acceletration is a vector, and has a direction. What is the directioin for uniform circular motion?
 
PeroK said:
Why do you think over 3000km is wrong?

Acceletration is a vector, and has a direction. What is the directioin for uniform circular motion?

Well in examples provided the satellites were much less. I guess I thought it should have been similar. And now that I say it, the direction of acceleration is towards the centre of the Earth (?)
 
benca said:
Well in examples provided the satellites were much less. I guess I thought it should have been similar. And now that I say it, the direction of acceleration is towards the centre of the Earth (?)
Yes. That's what "centripetal" means.

By the way, you can get the radius by noticing that the gravitational force is inversely proportional to the square of the distance. So:

##\frac{r^2}{R^2} = \frac{g_R}{g_r}##

The force you were given was just under half the Earth's surface gravity, so ##r \approx 1.5 R##. ##R \approx 6,000km##, so ##h \approx 3,000 km## looks about right.
 

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