RCAIDE.Library.Mission.Segments.Transition.Constant_Acceleration_Constant_Angle_Linear_Climb
Constant_Acceleration_Constant_Angle_Linear_Climb#
Functions
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Initializes conditions for transition segment with constant acceleration and climb angle |
- initialize_conditions(segment)[source]#
Initializes conditions for transition segment with constant acceleration and climb angle
- Parameters:
segment (Segment) –
- The mission segment being analyzed
- altitude_startfloat
Initial altitude [m]
- altitude_endfloat
Final altitude [m]
- climb_anglefloat
Fixed climb angle [rad]
- air_speed_startfloat
Initial true airspeed [m/s]
- accelerationfloat
Constant acceleration [m/s^2]
- sideslip_anglefloat
Aircraft sideslip angle [rad]
- pitch_initialfloat
Initial pitch angle [rad]
- pitch_finalfloat
Final pitch angle [rad]
- state:
- numerics:
- dimensionless:
- control_pointsarray
Discretization points [-]
- 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.body.inertial_rotations [rad]
conditions.frames.inertial.time [s]
- Return type:
None
Notes
This function sets up the initial conditions for a transition segment with constant acceleration, constant climb angle, and linear pitch variation. The segment handles the transition between different flight phases while climbing.
- Calculation Process
Check required inputs
- Calculate trajectory geometry:
Ground distance = (alt_f - alt_0)/tan(γ)
True distance = sqrt((alt_f - alt_0)^2 + ground_distance^2)
where γ is climb angle 3. Calculate time required:
t = (-V0 + sqrt(V0^2 + 2ax))/ax
- where:
V0 is initial velocity
ax is acceleration
- Compute velocity components:
vx = V*cos(β)*cos(γ)
vy = V*sin(β)*cos(γ)
vz = V*sin(γ)
Linear pitch transition
- Major Assumptions
Constant acceleration
Constant climb angle
Linear pitch variation
Coordinated flight
Small angle approximations
See also