@@ -777,6 +777,9 @@ def __simulate(self, verbose):
777777 lambda self , parachute_porosity = parachute .porosity : setattr (
778778 self , "parachute_porosity" , parachute_porosity
779779 ),
780+ lambda self , ka = parachute .ka : setattr (
781+ self , "parachute_ka" , ka
782+ ),
780783 ]
781784 self .flight_phases .add_phase (
782785 node .t + parachute .lag ,
@@ -1041,6 +1044,9 @@ def __simulate(self, verbose):
10411044 "parachute_porosity" ,
10421045 parachute_porosity ,
10431046 ),
1047+ lambda self , ka = parachute .ka : setattr (
1048+ self , "parachute_ka" , ka
1049+ ),
10441050 ]
10451051 self .flight_phases .add_phase (
10461052 overshootable_node .t + parachute .lag ,
@@ -1995,13 +2001,6 @@ def u_dot_parachute(self, t, u, post_processing=False):
19952001 # Get the mass of the rocket
19962002 mp = self .rocket .dry_mass
19972003
1998- # Define constants
1999- ka = 1.068 * (
2000- 1
2001- - 1.465 * self .parachute_porosity
2002- - 0.25975 * self .parachute_porosity ** 2
2003- + 1.2626 * self .parachute_porosity ** 3
2004- )
20052004 # to = 1.2
20062005 # eta = 1
20072006 # Rdot = (6 * R * (1 - eta) / (1.2**6)) * (
@@ -2013,7 +2012,7 @@ def u_dot_parachute(self, t, u, post_processing=False):
20132012
20142013 # Calculate added mass
20152014 ma = (
2016- ka
2015+ self . ka
20172016 * rho
20182017 * (4 / 3 )
20192018 * np .pi
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