# RCAIDE/Library/Missions/Common/Initialize/weights.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# Initialize Weights
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def weights(segment):
"""
Initializes vehicle mass properties for mission segment analysis
Parameters
----------
segment : Segment
The mission segment being analyzed
Notes
-----
This function sets up the initial mass values for the vehicle. It determines
the initial mass through a priority system and maintains mass continuity
between segments.
The function follows this priority for mass initialization:
1. Previous segment final mass (if initials exist)
2. Vehicle takeoff mass (if weight analysis exists)
3. Network mass properties (fallback option)
**Required Segment State Variables**
If segment.state.initials exists:
state.initials.conditions.weights:
- mass.total : array
Previous segment final mass [kg]
state.conditions.weights:
- mass.total : array
Current segment mass array [kg]
**Required Analysis Components**
Either:
segment.analyses.weights:
- vehicle.mass_properties.takeoff : float
Vehicle takeoff mass [kg]
Or:
segment.analyses.vehicle.networks:
- mass_properties.mass : float
Network mass properties [kg]
**Major Assumptions**
* Continuous mass tracking when using initials
* Valid mass values (positive)
* At least one mass property source available
* Mass measured in kilograms
Returns
-------
None
Updates segment conditions directly
See Also
--------
RCAIDE.Framework.Mission.Segments
"""
if segment.state.initials:
m_initial = segment.state.initials.conditions.weights.vehicle.mass[-1,0]
segment.state.conditions.weights.vehicle.mass[:,0] = segment.state.initials.conditions.weights.vehicle.mass[-1,0]
segment.state.conditions.weights.vehicle.global_center_of_gravity[:,0] = segment.state.initials.conditions.weights.vehicle.global_center_of_gravity[-1,0]
segment.state.conditions.weights.vehicle.mass_rate[0,:] = segment.state.initials.conditions.weights.vehicle.mass_rate[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Ixx[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Ixx[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Ixy[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Ixy[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Ixz[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Ixz[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Iyx[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Iyx[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Iyy[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Iyy[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Iyz[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Iyz[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Izx[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Izx[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Izy[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Izy[-1,0]
segment.state.conditions.weights.vehicle.moments_of_inertia_Izz[0,:] = segment.state.initials.conditions.weights.vehicle.moments_of_inertia_Izz[-1,0]
for tag,item in segment.state.initials.conditions.weights.components.mass.items():
if segment.analyses.weights.settings.run_center_of_gravity_analysis:
segment.state.conditions.weights.components.mass[tag][:,0] = segment.state.initials.conditions.weights.components.mass[tag][-1,0]
segment.state.conditions.weights.components.global_center_of_gravity[tag][:,0] = segment.state.initials.conditions.weights.components.global_center_of_gravity[tag][-1,0]
if segment.analyses.weights.settings.run_moments_of_inertia_analysis:
segment.state.conditions.weights.components.moments_of_inertia_Ixx[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Ixx[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Ixy[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Ixy[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Ixz[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Ixz[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Iyx[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Iyx[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Iyy[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Iyy[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Iyz[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Iyz[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Izx[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Izx[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Izy[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Izy[tag][-1,0]
segment.state.conditions.weights.components.moments_of_inertia_Izz[tag][:,0] = segment.state.initials.conditions.weights.components.moments_of_inertia_Izz[tag][-1,0]
else:
m_initial = segment.analyses.vehicle.mass_properties.takeoff
m_current = segment.state.conditions.weights.vehicle.mass
segment.state.conditions.weights.vehicle.mass[:,:] = m_current + (m_initial - m_current[0,0])
return
