Control Model for Maneuvering Flight for Application to a Computer Flight Testing Program

摘要

A computer-flight-testing (CFT) program for helicopters was developed to evaluate helicopter dynamics and handling and control qualities. The nonlinear 6 degrees of freedom helicopter model is driven by control inputs by a specially developed control model (or pseudo pilot). This is an adaptation of a linear optimal control model as used in human factor analysis. The helicopter model is based on two dimensional strip aerodynamics and steady-state rotor blade dynamics using only out-of-plane bending mode shapes, which are suitable for various types of rotor articulation. The pilot model consists of a flight path generation (FPG) model and a stabilization (STAB) model. The FPG model is based on linearized system dynamics using terminal optimal control, generating both the required flight path and the control inputs to achieve it. These controls are input into the helicopter model. The two flight paths are compared, and differences are fed back to the STAB model to generate corrective control inputs of such a nature that the helicopter-model-generated flight path tracks the required flight path generated by the FPG model. Also the STAB model is based on linearized system dynamics. As an example, two flare maneuvers are 'flown', and the results discussed. The pseudo-pilot model merforms well, provided that helicopter dynamics do not change much during a specific maneuver.