RCAIDE.Library.Mission.Segments.Cruise.Constant_Mach_Constant_Altitude_Loiter.initialize_conditions#
- initialize_conditions(segment)[source]#
Initializes conditions for constant Mach loiter at fixed altitude
- Parameters:
segment (Segment) –
- The mission segment being analyzed
- altitudefloat
Loiter altitude [m]
- timefloat
Loiter duration [s]
- mach_numberfloat
Mach number to maintain [-]
- sideslip_anglefloat
Aircraft sideslip angle [rad]
- state:
- numerics.dimensionless.control_pointsarray
Discretization points [-]
- conditionsData
State conditions container
- analyses:
- atmosphereModel
Atmospheric model for property calculations
- Returns:
- Updates segment conditions directly:
conditions.frames.inertial.velocity_vector [m/s]
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 loiter segment with constant Mach number and constant altitude. The true airspeed is determined from the Mach number and local speed of sound.
- Calculation Process
Get atmospheric properties at altitude
- Calculate true airspeed from Mach number:
- V = M * a where:
M is Mach number
a is speed of sound
Discretize time points
Decompose velocity into components using sideslip angle
- Major Assumptions
Constant Mach number
Constant altitude
Standard atmosphere model
Small angle approximations
Quasi-steady flight
No wind effects