Escape Speed for Solar System Probe

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Homework Help Overview

The discussion revolves around calculating the escape speed for a probe launched from a space station orbiting the sun at the same distance as Earth. Participants are exploring the implications of the problem's setup and the relevant physics principles involved.

Discussion Character

  • Mixed

Approaches and Questions Raised

  • Participants discuss the formula for escape velocity and question the appropriate radius to use in calculations, debating whether to use the radius of the sun or the distance from the sun to Earth. There are attempts to clarify the constants involved and the implications of the calculations presented.

Discussion Status

There is an ongoing examination of the calculations and constants used, with some participants suggesting corrections and others expressing uncertainty about the results. Multiple interpretations of the problem setup are being explored, and guidance has been offered regarding the correct values to use for the calculations.

Contextual Notes

Participants note discrepancies in the values used for the radius and mass in their calculations, indicating a need for careful consideration of the problem's parameters. There is mention of a professor's feedback on the correctness of the results, adding to the complexity of the discussion.

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QUESTION:
A space station orbits the sun at the same distance as the Earth but on the opposite side of the sun. A small probe is fired away from the station. What minimum speed (m/s) does the probe need to escape the solar system?

MY UNDERSTANDING AND SOLUTION:
The escape speed v from a sphere of radius R and mass M is given by the energy-conservation equation as follows: (from "Schaum's 3000 Solved Problems in Physics" book, page 101)

(1/2)*m*v^2 = G*M*m / R where;

M: mass of the sun (=1.98*10^30 kg)
m: mass of the small probe
R: Radius of the sun (=6.95*10^8 m)
G: Universal Gravitation Constant [=6.67*10^(-11) Nm^2/kg^2]

From the equation typed in bold above;

v = sqrt(2*G*M / R) and using the numerical values v is found about

616479 m/s .

What do you think?

Thanks.
 
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Six hundred kilometers per second?

Does that sound reasonable?

Always use your head to check your answers.



Without examining too closely, one thing I note is that you haven't calc'd the escape velocity from Earth orbit, you've calc'ed the escape velocity from the surface of the Sun: R = 695,000km. R should be Earth's orbit.
 
That's why I had to ask.

Okay, let us take R as the distance between the sun and Earth since the problem says "A space station orbits the sun at the same distance as the Earth but on the opposite side of the sun", then v is found

51,393.77 m/s. What about this one?

Is this reasonable? Our professor says yes, but it is incorrect. So what?
 
Are you sure your numbers were right? You're in the ballpark, but definitely wrong.

The heliocentric gravitational constant (GM) is 1.32712442076 x 10^11 km

One astronomical unit (average radius of the Earth's orbit) is 1.49597871 x 10^8 km

Just eyeballing it tells you your escape velocity will be a little less than the square root of 2000, which puts you in 40's of km/sec.
 
your equation is right,

vescape = [2*G*M/R].5

your constants must be off

be sure to use:
G = 6.67x10-11
M = (mass of the sun) = 1.99x1030 kg
R = (mean disntance from the Earth to the sun) = 1.5x1011 meters

that should give you the right answer
 
by the way, the answer should be 4.21x104 m/s
 
That's great but if he's still struggling with this after five years, he's got bigger problems... :wink:
 

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