RCAIDE.Library.Mission.Segments.Climb.Constant_Dynamic_Pressure_Constant_Rate
Constant_Dynamic_Pressure_Constant_Rate#
Functions
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Initializes conditions for constant dynamic pressure climb segment |
- initialize_conditions(segment)[source]#
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_ratefloat
Rate of climb [m/s]
- dynamic_pressurefloat
Dynamic pressure to maintain [Pa]
- 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 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
Decompose velocity into components
- Major Assumptions
Constant dynamic pressure
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