- Rocket total mass is split into 'dryMass' and 'propellantMass'
-- each mass type has a corresponding calculation method in MassCalculator
- Calculating Inertias and Center-of-Mass FOR MOTORS assume:
- time-invariant x-coordinate
- time-decreasing density
- mass correctly tracks propellant usage, as measured by thrustCurves
- elimated MassCalcType enum: was not actually solving a problem.
- simply use motorTime: 0 for launch Double.MAX_VALUE for burnout
- NO_MOTORS is represented by a configuration without attached motors
-- try: "rocket.setSelectedConfiguration( rocket.getEmptyConfiguration())"
- 'dry mass' vs 'total mass': 90% of the time, a caller wanted 'total mass'
- total_mass = dry_mass + propellant_mass
- mass @ simulation time wasn't represented by the enum, had existing overloads anyway
- get vs calculate methods:
-- gets revalidate the cache, then retreive specific information
-- calculate simple calculate the desired information, and ignore the cache.
--- I'm particularly confident about cache reliability:
particularly as it doesn't account for changing time during simulation.
- reduced / simplified debugging messages
-Changed default Motor Ignition event to AUTOMATIC
-enabled swing-test path under intellij
-fixed some simple compile errors in swing/test ... IntegrationTest
Separate swing application code from core code. Moved a bunch of sources
and libraries around. Created new eclipse project.
Further refinements to make it build.
Update gitignore.
