RCAIDE.Library.Mission.Segments.Climb.Linear_Mach_Constant_Rate.initialize_conditions#
- initialize_conditions(segment)[source]#
Initializes conditions for linear Mach number climb segment
- Parameters:
segment (Segment) – The mission segment being analyzed
Notes
This function sets up the initial conditions for a climb segment with linearly varying Mach number and constant rate of climb. The Mach number varies linearly between the start and end values.
Required Segment Components
- segment:
- climb_ratefloat
Rate of climb [m/s]
- mach_number_startfloat
Initial Mach number [-]
- mach_number_endfloat
Final Mach number [-]
- 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
- Calculation Process
Discretize altitude profile
Get atmospheric properties for speed of sound
Calculate velocity from Mach number variation
- Decompose velocity into components using:
Climb rate constraint
Sideslip angle
Linear Mach profile
- Major Assumptions
Linear Mach number variation
Constant rate of climb
Standard atmosphere model
Small angle approximations
Quasi-steady flight
- 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