egg changed the topic of #principia to: Logs: https://esper.irclog.whitequark.org/principia | <scott_manley> anyone that doubts the wisdom of retrograde bop needs to get the hell out | https://xkcd.com/323/ | <egg> calculating the influence of lamont on Pluto is a bit silly…
<queqiao->
⟨YaBoiAnt⟩ whats the smartest way to set up my first communication sats? I know principia can make things difficult as orbits change
<queqiao->
⟨Itspats (solid lv enthusiast)⟩ ⟪YaBoiAnt⟫ whats the smartest way to set up my […] ⮪ comm networks are pretty irrelevant early on
<queqiao->
and the contract is easy to do
<queqiao->
⟨YaBoiAnt⟩ ok cool when do you think ill need em? what point of progression?
<queqiao->
⟨Itspats (solid lv enthusiast)⟩ ⟪YaBoiAnt⟫ ok cool when do you think ill need em? […] ⮪ ehh
<queqiao->
tbh ive never found actual use for them other than contract
<queqiao->
but if you really do want them i'd say about apollo era is where it is actually usefull (as your comms are better and you will go deeper in space )
<queqiao->
⟨YaBoiAnt⟩ ⟪Itspats (solid lv enthusiast)⟫ ehh tbh ive never found actual use for […] ⮪ ok thanks... seperate question how different is getting into geostationary orbit with principia itll be my first time doing it
<queqiao->
⟨Itspats (solid lv enthusiast)⟩ ⟪YaBoiAnt⟫ ok thanks... seperate question how […] ⮪ the only difference is that you can't use mj
<queqiao->
other than that its the same
<queqiao->
⟨egg⟩ telecoms are not very deeply modelled in RO at this time, so that, as I understand it, they are not really difficult, and in any case fail to teach anything. #σκοπός is a project which might eventually make them interesting.
<queqiao->
⟨YaBoiAnt⟩ ⟪Itspats (solid lv enthusiast)⟫ the only difference is that you can't […] ⮪ ok cool thanks... im still getting used to no mechjeb by having much more rcs for orbital adjustmants
<queqiao->
⟨test_account⟩ Is this normal? Haven't seen such errors before
<queqiao->
⟨egg⟩ sichelgaita is that reanimation?
<queqiao->
⟨sichelgaita⟩ I don't think so. The current time is very close to 1951, so there is not much past to reconstruct, and the times in the error message are in 1954, quite far in the future. We probably run into the maximum number of steps when prolonging the ephemeris. This has been reported before in https://github.com/mockingbirdnest/Principia/issues/2583 but at the time we weren't even sure what the error was. Now it's clearer. We...
<queqiao->
... should probably handle this better. test_account could you please open an issue and include any logs/save you might have?
<queqiao->
⟨test_account⟩ Current time is 1954-09-05
<queqiao->
⟨test_account⟩ But I can replicate it again after deleting the flight plan, creating a new one and increasing plan length. After it was increased from 14 days to 24 days, the error appeared again.
<queqiao->
⟨sichelgaita⟩ I don't think so. The current time is 1954-09-05 and the times in the error message are around 1954-09-19, i.e., in the future. We probably run into the maximum number of steps when prolonging the ephemeris. This has been reported before in https://github.com/mockingbirdnest/Principia/issues/2583 but at the time we weren't even sure what the error was. Now it's clearer. We should probably handle this better. test_account...
<queqiao->
... could you please open an issue and include any logs/save you might have?
<queqiao->
⟨test_account⟩ This is probably a better screenshot, I will attach it to the issue. Shows current time, it's visible that the orbit is fine (no collision), the plan just stops with error somewhere near the Moon's orbit.
<queqiao->
⟨test_account⟩ But I can replicate it again after deleting the flight plan, creating a new one and increasing plan length. After it was increased from 14 days to 24 days, the error appeared again. Changing maneuver time, the error is gone; extending plan length to 34 days, the error appears again.
<queqiao->
⟨test_account⟩ The logs are full of this
<queqiao->
I1224 15:04:01.996944 15700 vessel.cpp:1072] Prognostication from 1954-09-05T06:48:55,9045240879058838 (TT) finished at 1954-09-05T18:30:20,0669851303100586 (TT) with ABORTED: Reached maximum step count 1000 at time 1954-09-05T18:30:20,0669851303100586 (
<queqiao->
⟨test_account⟩ * 15:06:58.983846 15700 vessel.cpp:1072] Prognostication from 1954-09-05T06:51:40,3044896125793457 (TT) finished at 1954-09-05T18:33:04,4611377716064453 (TT) with ABORTED: Reached maximum step count 1000 at time 1954-09-05T18:33:04,4611377716064453 (TT); requested t_final is 1954-10-09T08:00:00,0000000000000000 (TT). for 0010_Luna-1 (9f2d5495-fc2c-49a9-97b
<queqiao->
⟨test_account⟩ * 15:05:34.877122 15700 vessel.cpp:1072] Prognostication from 1954-09-05T06:50:22,1645059585571289 (TT) finished at 1954-09-05T18:31:46,3253035545349121 (TT) with ABORTED: Reached maximum step count 1000 at time 1954-09-05T18:31:46,3253035545349121 (TT); requested t_final is 1954-10-09T08:00:00,0000000000000000 (TT). for 0010_Luna-1 (9f2d5495-fc2c-49a9-97be-c1fd6e822412)
<queqiao->
⟨YaBoiAnt⟩ im trying to get my first geo stationary orbit with principia... ive done it multiple times without principia using mechjeb but have no idea how to now... any tips?
<queqiao->
⟨test_account⟩ !geo
<queqiao->
⟨Nazfib⟩ ⟪YaBoiAnt⟫ im trying to get my first geo […] ⮪ The first burn is exactly the same as without Principia, around 2450 m/s prograde (adjust until your apoapsis is 35,786 km) in the ECI frame.
<queqiao->
For the second burn, switch the manoeuvre and plotting frames to ECEF, the burn is then around 1850 m/s (depends on your parking orbit's inclination, i.e. your launch site) purely retrograde. It should be really obvious when the orbit after the manoeuvre is geosynchronous, it will look like small repeating loops in ECEF. Adjust your manoeuvre to make those loops completely overlapping and as small as possible for a geostationary orbit.
<queqiao->
⟨lpg⟩ it had never occurred to me to use the ECEF frame for circularizing + plane change
<queqiao->
⟨Butcher⟩ I use it for geo.
<queqiao->
⟨nvv⟩ do you usually directly capture into a moon's orbit (e.g phobos or deimos), or do you go into the planet's orbit first (e.g mars) and then do a transfer into the moon's orbit?
<queqiao->
⟨pEdro⟩ direct capture is more efficient than orbit and then capture, but with some noodling around, low energy capture around the primary, then low energy capture around the secondary is technically best
<queqiao->
⟨Kirk (He/Him)⟩ Good luck doing direct capture of phobos or deimos
<queqiao->
⟨Marsh⟩ I go direct into mars orbit via aero braking. The timing is going to have to be almost perfect to actually be in Phobos or Deimos orbit from interplanetary speeds
<queqiao->
⟨pEdro⟩ ever since i figured out how to do ballistic capture around mars is stopped bothering with aerocaptures
<queqiao->
⟨Butcher⟩ For my Jovian moon probes I tended to capture songs jupiter then brake/assist into orbit around the moon.
<queqiao->
⟨Butcher⟩ * around
_whitelogger has joined #principia
<queqiao->
⟨egg⟩ Happy Newton’s birthday
<paculino>
Julian birthday in the Gregorian calendar, but not the Julian birthday in the Julian calendar (7-Jan Gregorian) or the Gregorian birthday in the Gregorian calendar (4-Jan)
<queqiao->
⟨Vlood⟩ Quoting a close friend of mine: "whatever, close enough, nerd"