Source code for RCAIDE.Library.Mission.Segments.Single_Point.Set_Speed_Set_Altitude_No_Propulsion
# RCAIDE/Library/Missions/Segments/Single_Point/Set_Speed_Set_Altitude_No_Propulsion.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# Initialize Conditions
# ----------------------------------------------------------------------------------------------------------------------
import numpy as np
# ----------------------------------------------------------------------------------------------------------------------
# Set_Speed_Set_Altitude_No_Propulsion
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def initialize_conditions(segment):
"""Sets the specified conditions which are given for the segment type.
Assumptions:
A fixed speed and altitude
Source:
N/A
Inputs:
segment.altitude [meters]
segment.air_speed [meters/second]
segment.z_accel [meters/second^2]
Outputs:
conditions.frames.inertial.acceleration_vector [meters/second^2]
conditions.frames.inertial.velocity_vector [meters/second]
conditions.frames.inertial.position_vector [meters]
conditions.freestream.altitude [meters]
conditions.frames.inertial.time [seconds]
Properties Used:
N/A
"""
# unpack
alt = segment.altitude
air_speed = segment.air_speed
sideslip = segment.sideslip_angle
linear_acceleration_x = segment.linear_acceleration_x
linear_acceleration_y = segment.linear_acceleration_y
linear_acceleration_z = segment.linear_acceleration_z
roll_rate = segment.roll_rate
pitch_rate = segment.pitch_rate
yaw_rate = segment.yaw_rate
# check for initial altitude
if alt is None:
if not segment.state.initials: raise AttributeError('altitude not set')
alt = -1.0 *segment.state.initials.conditions.frames.inertial.position_vector[-1,2]
# pack
air_speed_x = np.cos(sideslip)*air_speed
air_speed_y = np.sin(sideslip)*air_speed
segment.state.conditions.freestream.altitude[:,0] = alt
segment.state.conditions.frames.inertial.position_vector[:,2] = -alt # z points down
segment.state.conditions.frames.inertial.velocity_vector[:,0] = air_speed_x
segment.state.conditions.frames.inertial.velocity_vector[:,1] = air_speed_y
segment.state.conditions.frames.inertial.acceleration_vector = np.array([[linear_acceleration_x,linear_acceleration_y,linear_acceleration_z]])
segment.state.conditions.static_stability.roll_rate[:,0] = roll_rate
segment.state.conditions.static_stability.pitch_rate[:,0] = pitch_rate
segment.state.conditions.static_stability.yaw_rate[:,0] = yaw_rate
return
