RCAIDE.Library.Mission.Segments.Climb.Constant_Mach_Linear_Altitude

Constant_Mach_Linear_Altitude

Functions

initialize_conditions(segment)

Initializes conditions for constant Mach climb with linear altitude change

initialize_conditions(segment)

Initializes conditions for constant Mach climb with linear altitude change

Parameters:

segment (Segment) – The mission segment being analyzed

Notes

This function sets up the initial conditions for a climb segment with constant Mach number and linear altitude variation. The climb angle is determined by the distance and altitude change.

Required Segment Components

segment:

• mach_numberfloat

  Mach number to maintain [-]

• altitude_startfloat

  Initial altitude [m]

• altitude_endfloat

  Final altitude [m]

• distancefloat

  Ground distance to cover [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. Calculate climb angle from altitude change and distance

2. Get atmospheric properties for speed of sound

3. Calculate true airspeed from Mach number

4. Decompose velocity into components using:

   • Computed climb angle

   • Sideslip angle

   • Constant Mach requirement

Major Assumptions

• Constant Mach number

• Linear altitude change

• 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

See also

RCAIDE.Framework.Mission.Segments, RCAIDE.Library.Mission.Common.Update.atmosphere