StabilityDerivatives¶
Outputs the stability derivatives of a free-flying aircraft
Warning
Under Development
- To Do:
- Coefficient of stability derivatives
- Option to output in NED frame
The settings that this solver accepts are given by a dictionary, with the following key-value pairs:
Name Type Description Default print_info
bool
Display info to screen True
folder
str
Output directory ./output/
u_inf
float
Free stream reference velocity 1.0
S_ref
float
Reference planform area 1.0
b_ref
float
Reference span 1.0
c_ref
float
Reference chord 1.0
Stability derivatives calculated using the transfer function of the UVLM projected onto the structural degrees of freedom at zero frequency (steady state).
Returns: - matrix containing the steady state values of the transfer function between the force output
- (columns) and the velocity / control surface inputs (rows).
Return type: np.array