RCAIDE.Library.Mission.Segments.Cruise.Constant_Pitch_Rate_Constant_Altitude.initialize_conditions#
- initialize_conditions(segment)[source]#
Initializes conditions for constant pitch rate maneuver at fixed altitude
- Parameters:
segment (Segment) –
- The mission segment being analyzed
- altitudefloat
Cruise altitude [m]
- pitch_initialfloat
Initial pitch angle [rad]
- pitch_finalfloat
Final pitch angle [rad]
- pitch_ratefloat
Constant pitch rate [rad/s]
- state:
- numerics.dimensionless.control_pointsarray
Discretization points [-]
- conditionsData
State conditions container
- initialsData, optional
Initial conditions from previous segment
- Returns:
- Updates segment conditions directly:
conditions.frames.body.inertial_rotations [rad]
conditions.frames.inertial.position_vector [m]
conditions.freestream.altitude [m]
conditions.frames.inertial.time [s]
- Return type:
None
Notes
This function sets up the initial conditions for a cruise segment with constant pitch rate and constant altitude. The pitch angle varies linearly with time between initial and final values.
- Calculation Process
- Calculate time required for pitch change:
- t = (θf - θ0)/θ_dot where:
θf is final pitch angle
θ0 is initial pitch angle
θ_dot is pitch rate
Discretize time points
- Calculate pitch angle profile:
θ(t) = θ_dot * t + θ0
- Major Assumptions
Constant pitch rate
Constant altitude
Linear pitch angle variation
No coupling with other rotational axes
Quasi-steady flight
See also