RCAIDE.Library.Mission.Segments.Climb.Constant_EAS_Constant_Rate.initialize_conditions#
- initialize_conditions(segment)[source]#
Initializes conditions for constant equivalent airspeed climb segment
- Parameters:
segment (Segment) – The mission segment being analyzed
Notes
This function sets up the initial conditions for a climb segment with constant equivalent airspeed (EAS) and constant rate of climb. It handles the conversion between EAS and true airspeed accounting for density variations with altitude.
Required Segment Components
- segment:
- climb_ratefloat
Rate of climb [m/s]
- equivalent_air_speedfloat
Equivalent airspeed [m/s]
- altitude_startfloat
Initial altitude [m]
- altitude_endfloat
Final altitude [m]
- sideslip_anglefloat
Aircraft sideslip angle [rad]
- state:
- numerics.dimensionless.control_pointsarray
Discretization points [-]
- conditionsData
State conditions container
- analyses:
- atmosphereModel
Atmospheric model for property calculations
- Conversion Process
Compute atmospheric properties at altitude
Convert EAS to true airspeed (TAS) using density ratio
Decompose TAS into velocity components
- Major Assumptions
Constant equivalent airspeed
Constant rate of climb
Standard atmosphere model
Small angle approximations
Incompressible flow
- Returns:
Updates segment conditions directly: - conditions.frames.inertial.velocity_vector [m/s] - conditions.frames.inertial.position_vector [m] - conditions.freestream.altitude [m]
- Return type:
None