I Can a Satellite Maintain its Angular Velocity with Continuous Low Thrust?

AI Thread Summary
In a discussion about whether a satellite can maintain its angular velocity while undergoing continuous low thrust, it is suggested that Satellite 2 may transition to an elliptical or outward spiraling orbit due to the thrust. The thrust vector is assumed to be perpendicular to the line connecting Satellite 2 to Satellite 1 and the Sun, indicating tangential thrust. The challenge lies in determining if angular velocity can be preserved as the satellite accelerates, particularly since increasing tangential velocity could affect the radius and thus the angular velocity. A numerical simulation demonstrated that increasing the distance from the Sun without adjusting orbital velocity results in the satellite escaping the solar system. The conversation emphasizes the need to understand the relationship between gravity, centrifugal force, and orbital dynamics.
dansmith170
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Can a satellite that undergoes a low continuous thrust maintain the same angular velocity as a satellite that does not undergo said thrust?
Suppose two satellites are in a circular heliocentric orbit with radius R and with angular velocity O'. Satellite 2 then undergoes a low continuous thrust. Can Satellite 2 (the one that undergoes the continuous low thrust) maintain the same angular velocity O' about the sun?

It seems that Satellite 2 may now be in an elliptic orbit (or outward spiraling orbit) and presumably its thrust vector is perpendicular to a line connecting Satellite 2 to Satellite 1, to the Sun. (Tangential thrust).

How might one go about proving that angular velocity (O') can be maintained as Satellite 2 accelerates (if it is possible at all)?

P.S. I think I am confused about whether increasing tangential velocity increases radius in a way that would prohibit O' from being maintained by the accelerating satellite.
 
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I did a quick & dirty numerical simulation... First I put a James Webb in a circular orbit around the sun at 1AU (with no planets). Next I doubled the distance to 2AU without changing the orbital velocity. The spacecraft at 2AU with enough orbital velocity for a 1AU circular orbit escapes the Sun (no orbit).

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Or if you start with a circular orbit at 1AU then double the orbital speed, you also leave the solar system (no orbit)...
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Look up (Google?) how gravity varies with distance.
Then look up how centrifugal force varies with orbital speed or distance.

Have Fun and Learn Much!
Tom
 
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