- #1
stefanbanev
- 50
- 1
Case 1)
Two rockets (no Earth involved) have an exactly the same acceleration profile/flight-plan during round trip but they dispatched to opposite directions. At the start both rockets are docked to the same space station...both rockets have an identical engine operation plan during the round trip (engine vector/thrust plans are identical along the trip). After the trip both rockets docked ISS back and compare their G-record files they acquired/recorded during their trips.
Case 2)
one observer stays on the Earth another observer started from the Earth orbit. Let make sure that the profile of rocket engine thrust (vector and force) and astronaut orientations inside the rocket during the trip are arranged in such way that observer/astronaut in the rocket experiences all the time a vertical steady (from his perspective) 1G acceleration exactly the same 1G as observer on the Earth. After a round trip, the rocket get back to the same original position before the trip - a low Earth orbit; during radio session with Huston they may compare the watches and acceleration profile along time of trip - they should be identical. This case is not a perfectly symmetric so may have some loopholes though...
It seems that once the setup is perfectly G-force/vector symmetric the only way to avoid paradox is to have an identical record files of of G-meters readings for both observers along the trip. The alternative would be to accept that paradox indeed takes place and both observers meet with different counterpart - let call it an "Everett-3 twin solution" ;o))
I have no difficulty to see how math works for SR and so I see no paradox at all for SR compatible setups but I failed so see the solution for symmetric cases (not compatible with SR). I'm sure there is a consensus among experts in this area about a perfectly symmetric cases and I would appreciate if someone helps me to comprehend how paradox could be solved for _perfectly_ symmetric cases.
Thank you,
Stephan
Two rockets (no Earth involved) have an exactly the same acceleration profile/flight-plan during round trip but they dispatched to opposite directions. At the start both rockets are docked to the same space station...both rockets have an identical engine operation plan during the round trip (engine vector/thrust plans are identical along the trip). After the trip both rockets docked ISS back and compare their G-record files they acquired/recorded during their trips.
Case 2)
one observer stays on the Earth another observer started from the Earth orbit. Let make sure that the profile of rocket engine thrust (vector and force) and astronaut orientations inside the rocket during the trip are arranged in such way that observer/astronaut in the rocket experiences all the time a vertical steady (from his perspective) 1G acceleration exactly the same 1G as observer on the Earth. After a round trip, the rocket get back to the same original position before the trip - a low Earth orbit; during radio session with Huston they may compare the watches and acceleration profile along time of trip - they should be identical. This case is not a perfectly symmetric so may have some loopholes though...
It seems that once the setup is perfectly G-force/vector symmetric the only way to avoid paradox is to have an identical record files of of G-meters readings for both observers along the trip. The alternative would be to accept that paradox indeed takes place and both observers meet with different counterpart - let call it an "Everett-3 twin solution" ;o))
I have no difficulty to see how math works for SR and so I see no paradox at all for SR compatible setups but I failed so see the solution for symmetric cases (not compatible with SR). I'm sure there is a consensus among experts in this area about a perfectly symmetric cases and I would appreciate if someone helps me to comprehend how paradox could be solved for _perfectly_ symmetric cases.
Thank you,
Stephan
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