Source code for RCAIDE.Framework.Mission.Segments.Transition.Constant_Acceleration_Constant_Pitchrate_Constant_Altitude
# RCAIDE/Framework/Analyses/Mission/Segments/Transition/Constant_Acceleration_Constant_Pitchrate_Constant_Altitude.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from RCAIDE.Framework.Core import Units
from RCAIDE.Framework.Mission.Segments.Evaluate import Evaluate
from RCAIDE.Library.Mission import Common,Segments
# ----------------------------------------------------------------------------------------------------------------------
# Constant_Acceleration_Constant_Pitchrate_Constant_Altitude
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Constant_Acceleration_Constant_Pitchrate_Constant_Altitude(Evaluate):
""" Vehicle accelerates at a constant rate between two airspeeds.
Assumptions:
None
Source:
None
"""
def __defaults__(self):
""" This sets the default solver flow. Anything in here can be modified after initializing a segment.
Assumptions:
Prop-rotor pitch command is automatically applied linearly throughout segment
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
# --------------------------------------------------------------
# User Inputs
# --------------------------------------------------------------
self.altitude = None
self.acceleration = 1. * Units['m/s/s']
self.air_speed_start = None
self.air_speed_end = 1.0 * Units['m/s']
self.pitch_initial = None
self.pitch_final = 0.0 * Units['rad']
self.true_course = 0.0 * Units.degrees
# --------------------------------------------------------------------------------------------------------------
# Mission specific processes
# --------------------------------------------------------------------------------------------------------------
initialize = self.process.initialize
initialize.conditions = Segments.Transition.Constant_Acceleration_Constant_Pitchrate_Constant_Altitude.initialize_conditions
iterate = self.process.iterate
iterate.residuals.flight_dynamics = Common.Residuals.flight_dynamics
return
