StaticTrimsolver determines the longitudinal state of trim (equilibrium) for an aeroelastic system in static conditions. It wraps around the desired solver to yield the state of trim of the system, in most cases the
It calculates the required angle of attack, elevator deflection and thrust required to achieve longitudinal equilibrium. The output angles are shown in degrees.
The results from the trimming iteration can be saved to a text file by using the save_info option.
The settings that this solver accepts are given by a dictionary, with the following key-value pairs:
Print info to screen
Solver to run in trim routine
Solver settings dictionary
Maximum number of iterations of trim routine
Tolerance in vertical force
Tolerance in horizontal force
Tolerance in pitching moment
Index of control surfaces that move to achieve trim
Nodes at which thrust is applied
Initial angle of attack
Initial control surface deflection
Initial thrust setting
Initial change of control surface deflection
Initial thrust setting change
Save trim results to text file
Trim algorithm method
The trim condition is found iteratively.
array of trim values for angle of attack, control surface deflection and thrust.
- Return type: