Source code for RCAIDE.Library.Mission.Segments.Climb.Constant_Dynamic_Pressure_Constant_Rate

# RCAIDE/Library/Missions/Segments/Climb/Constant_Dynamic_Pressure_Constant_Rate.py
# 
# 
# Created:  Jul 2023, M. Clarke

# ----------------------------------------------------------------------------------------------------------------------
#  IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE 
from RCAIDE.Library.Mission.Common.Update.atmosphere import atmosphere

# Package imports  
import numpy as np
 
# ----------------------------------------------------------------------------------------------------------------------
#  Initialize Conditions
# ----------------------------------------------------------------------------------------------------------------------


def initialize_conditions(segment):
    """
    Initializes conditions for constant dynamic pressure climb segment

    Parameters
    ----------
    segment : Segment
        The mission segment being analyzed

    Notes
    -----
    This function sets up the initial conditions for a climb segment with constant
    dynamic pressure and constant rate of climb. It computes true airspeed based
    on the dynamic pressure constraint as altitude changes.

    **Required Segment Components**

    segment:
        - climb_rate : float
            Rate of climb [m/s]
        - dynamic_pressure : float
            Dynamic pressure to maintain [Pa]
        - altitude_start : float
            Initial altitude [m]
        - altitude_end : float
            Final altitude [m]
        - sideslip_angle : float
            Aircraft sideslip angle [rad]
        - state:
            numerics.dimensionless.control_points : array
                Discretization points [-]
            conditions : Data
                State conditions container
        - analyses:
            atmosphere : Model
                Atmospheric model for property calculations

    **Calculation Process**
    1. Compute atmospheric properties at altitude
    2. Calculate true airspeed from dynamic pressure:
       V = sqrt(2q/ρ) where:
       - q is dynamic pressure
       - ρ is air density
    3. Decompose velocity into components

    **Major Assumptions**
        * Constant dynamic pressure
        * Constant rate of climb
        * Standard atmosphere model
        * Small angle approximations
        * Quasi-steady flight

    Returns
    -------
    None
        Updates segment conditions directly:
        - conditions.frames.inertial.velocity_vector [m/s]
        - conditions.frames.inertial.position_vector [m]
        - conditions.freestream.altitude [m]

    See Also
    --------
    RCAIDE.Framework.Mission.Segments
    RCAIDE.Library.Mission.Common.Update.atmosphere
    """        
    
    # unpack
    climb_rate = segment.climb_rate
    q          = segment.dynamic_pressure
    alt0       = segment.altitude_start 
    altf       = segment.altitude_end
    t_nondim   = segment.state.numerics.dimensionless.control_points
    conditions = segment.state.conditions
    beta       = segment.sideslip_angle
    rho        = conditions.freestream.density[:,0]
    
    # Update freestream to get density
    atmosphere(segment)
    rho = conditions.freestream.density[:,0]   

    # check for initial altitude
    if alt0 is None:
        if not segment.state.initials: raise AttributeError('initial altitude not set')
        alt0 = -1.0 * segment.state.initials.conditions.frames.inertial.position_vector[-1,2]

    # discretize on altitude
    alt = t_nondim * (altf-alt0) + alt0
    

    # check for initial velocity
    if q is None: 
        if not segment.state.initials: raise AttributeError('dynamic pressure not set')
        v_mag = np.linalg.norm(segment.state.initials.conditions.frames.inertial.velocity_vector[-1])
    else: 
        # process velocity vector
        v_mag = np.sqrt(2*q/rho)
    v_z   = -climb_rate # z points down
    v_xy  = np.sqrt( v_mag**2 - v_z**2 )
    v_x   = np.cos(beta)*v_xy 
    v_y   = np.sin(beta)*v_xy 
    
    # pack conditions    
    conditions.frames.inertial.velocity_vector[:,0] = v_x
    conditions.frames.inertial.velocity_vector[:,1] = v_y
    conditions.frames.inertial.velocity_vector[:,2] = v_z
    conditions.frames.inertial.position_vector[:,2] = -alt[:,0] # z points down
    conditions.freestream.altitude[:,0]             =  alt[:,0] # positive altitude in this context