Escape Velocity from Solar System

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Homework Help Overview

The discussion revolves around a celestial mechanics problem concerning the escape velocity required for a spacecraft to leave the solar system, specifically addressing the gravitational influences of the Earth and the Sun. The original poster presents a formula for calculating this escape velocity and questions the role of Earth's orbital velocity in the context of the problem.

Discussion Character

  • Conceptual clarification, Assumption checking, Mathematical reasoning

Approaches and Questions Raised

  • The original poster attempts to understand how the Earth's orbital velocity contributes to the escape velocity from the solar system, particularly questioning the necessity of including v_0 in the escape velocity equation. Some participants suggest that v_0 provides additional energy that aids in the escape process. Others explore the implications of launching from different points on Earth and the direction of the escape relative to the Earth's orbital velocity.

Discussion Status

The discussion is ongoing, with participants exploring various interpretations of the problem and the role of different velocities. Some guidance has been offered regarding the significance of v_0, but confusion remains about the implications of launch direction and the assumptions made in the calculations.

Contextual Notes

Participants are considering the effects of gravitational influences from both the Earth and the Sun while ignoring other celestial bodies. There is also uncertainty regarding how the launch position on Earth might affect the escape velocity calculations.

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Here is a celestial mechanics problem I can't seem to solve:To escape the solar system, an interstellar spacecraft must overcome the gravitational attraction of both the Earth and Sun. Ignore the effects of the other bodies in the solar system. Show that the escape velocity is

[tex]v = \sqrt{v_E^2 + (v_S - v_0)^2}[/tex]

where [itex]v_E[/itex] is the escape velocity from the Earth; [itex]v_S = \sqrt{2GM_S/r_{SE}}[/itex] is the escape velocity from the gravitational field of the Sun at the orbit of the Earth but far from the Earth's influence ([itex]M_S[/itex] is the mass of the Sun and [itex]r_{SE}[/itex] is the Sun-Earth distance); and [itex]v_0[/itex] is the Earth's orbital velocity about the Sun.

The thing I don't understand here is how the orbital velocity of the Earth plays a role. Suppose I took the Earth out of the picture and the spacecraft is orbitting the sun with orbital velocity equal to that of Earth's. Isn't the escape velocity from the sun just [itex]v_S[/itex]. What do I need [itex]v_0[/itex] for?
 
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[itex]v_0[/itex] gives you some extra energy at the beginning of the trip, so naturally it'll take less to get away.

cookiemonster
 
cookiemonster said:
[itex]v_0[/itex] gives you some extra energy at the beginning of the trip, so naturally it'll take less to get away.

cookiemonster
If you happen to escape in the same direction as the orbital velocity vector, then I guess it would help.

I think this all depends on where on Earth I am taking of from. Or does it make no difference? I'm still confused.
 
From the equation for v, it seems that

[tex]\vec{v} = (v_E, v_S - v_0) = \vec{v}_E + \vec{v}_S - \vec{v}_0[/tex]

where [itex]\vec{v}_E = (v_E, 0)[/itex], [itex]\vec{v}_S = (0, v_S)[/itex], and [itex]\vec{v}_0 = (0, v_0)[/itex]. This is interesting since the escape velocity vector from the Sun has the same direction as the Earth's orbital vel. vector and both of these vectors are perpendicular to Earth's escape vel. vector. I guess when you make these assumptions, it is easy to show what the escape velocity is. I really don't know how one would come to these sorts of conclusions though.
 

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