Calculating Time Interval of Two Earth Satellites in Circular Orbits

  • Thread starter Thread starter NEILS BOHR
  • Start date Start date
  • Tags Tags
    Circular Orbits
Click For Summary
SUMMARY

The discussion centers on calculating the time interval between two Earth satellites in circular orbits with radii r and r - Δr, where Δr is significantly smaller than r. The mass of the Earth is given as M = 6 x 1024 kg, and the radius is specified as r = 7000 km with Δr = 70 km. The key formula used is T = 2π√(r3/GM), which determines the orbital period. The concept of the synodic period is introduced to understand the periodic approaches of the satellites, emphasizing the need to clarify the meaning of "over the min. distance."

PREREQUISITES
  • Understanding of circular orbital mechanics
  • Familiarity with gravitational constant (G) and its application
  • Knowledge of the synodic period concept
  • Ability to manipulate and solve equations involving orbital periods
NEXT STEPS
  • Research the concept of synodic period in celestial mechanics
  • Study the gravitational constant (G) and its role in orbital calculations
  • Explore the differences in orbital periods for satellites in circular orbits
  • Learn how to calculate closest approach distances between orbiting bodies
USEFUL FOR

Astronomy students, physics enthusiasts, and professionals in aerospace engineering who are interested in satellite dynamics and orbital mechanics.

NEILS BOHR
Messages
79
Reaction score
0

Homework Statement


Two satellites of the Earth move in a common plane along circular orbits , the radii being r and r-\Deltar ( \Deltar << r ). What is the time interval b/w their periodic approaches to each other over the min. distance . Take M to be the mass of the Earth
M = 6 * 10 24 kg , r = 7000 km , \Deltar = 70 km ).


Homework Equations





The Attempt at a Solution


i m unable to understand the quesn...
 
Physics news on Phys.org


Which part of the question do you not understand?
Which parts do you understand?
 


i mean what's the meaning of by time interval b/w their periodic approaches to each other over the min. distance??

uptill now i m doing this :

T = 2\pi<sup>1/2</sup>( r3 / GM)

so dT = 2 pi / root of GM * 3/2 r1/2 dr

so i have found dT / T and hence dT...

what to do next??
 


NEILS BOHR said:
i mean what's the meaning of by time interval b/w their periodic approaches to each other over the min. distance??

uptill now i m doing this :

T = 2\pi<sup>1/2</sup>( r3 / GM)

so dT = 2 pi / root of GM * 3/2 r1/2 dr

so i have found dT / T and hence dT...

what to do next??

Perhaps you were going for the formula for the period of a circular orbit?

T = \frac{2 \pi}{\sqrt{G M}}r^{3/2}

Bodies in circular orbits with different radii will have different periods. Inner ones have shorter periods than the outer ones. In the present case, this means that the satellite with the smaller orbit will periodically "lap" (pass) the outer one.

The problem is asking for you to compute that time period. I must admit that the phrase, "over the min. distance" is a bit vague. It could be that they want you to divide the period by the distance between the satellites when they're at closest approach. On the other hand, it could imply something a bit more devious -- what if the directions of the orbits are not the same (one going clockwise, the other counterclockwise)? Then the distance traveled along the orbit from meeting to meeting would be minimized.

Which ever way it turns out, the concept in play is what is known as the synodic period. A web search will turn up some adequate material.
 


hmmm
still confused with what the quesn is asking exactly??:confused:
 

Similar threads

Replies
5
Views
3K
  • · Replies 6 ·
Replies
6
Views
3K
Replies
1
Views
2K
  • · Replies 3 ·
Replies
3
Views
2K
  • · Replies 3 ·
Replies
3
Views
2K
Replies
37
Views
3K
Replies
5
Views
3K
  • · Replies 1 ·
Replies
1
Views
2K
Replies
5
Views
2K
  • · Replies 3 ·
Replies
3
Views
2K