RCAIDE.Library.Mission.Segments.Single_Point.Set_Speed_Set_Altitude_AVL_Trimmed
Set_Speed_Set_Altitude_AVL_Trimmed#
Functions
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Initializes conditions for fixed speed and altitude trim analysis using AVL |
- initialize_conditions(segment)[source]#
Initializes conditions for fixed speed and altitude trim analysis using AVL
- Parameters:
segment (Segment) –
- The mission segment being analyzed
- altitudefloat
Flight altitude [m]
- air_speedfloat
True airspeed [m/s]
- sideslip_anglefloat
Aircraft sideslip angle [rad]
- linear_acceleration_xfloat
Acceleration in x-direction [m/s^2]
- linear_acceleration_yfloat
Acceleration in y-direction [m/s^2]
- linear_acceleration_zfloat
Acceleration in z-direction [m/s^2]
- roll_ratefloat
Aircraft roll rate [rad/s]
- pitch_ratefloat
Aircraft pitch rate [rad/s]
- yaw_ratefloat
Aircraft yaw rate [rad/s]
- state:
- conditionsData
State conditions container
- initialsData, optional
Initial conditions from previous segment
- Returns:
- Updates segment conditions directly:
conditions.freestream.altitude [m]
conditions.frames.inertial.position_vector [m]
conditions.frames.inertial.velocity_vector [m/s]
conditions.frames.inertial.acceleration_vector [m/s^2]
conditions.static_stability.roll_rate [rad/s]
conditions.static_stability.pitch_rate [rad/s]
conditions.static_stability.yaw_rate [rad/s]
- Return type:
None
Notes
This function sets up the initial conditions for a single point analysis with fixed speed and altitude. It includes trim state variables for AVL (Athena Vortex Lattice) aerodynamic analysis.
- Calculation Process
Check initial conditions
- Decompose velocity into components using sideslip angle:
v_x = V * cos(β)
v_y = V * sin(β)
- where:
V is true airspeed
β is sideslip angle
Set position and altitude
Set acceleration vector
Set angular rates for trim analysis
- Major Assumptions
Steady state trim condition
Small angle approximations
Linear aerodynamics
No atmospheric variations
See also
RCAIDE.Framework.Mission.Segments,RCAIDE.Methods.Aerodynamics.AVL