Synthesis of control laws for airplane automatic touchdown on the chassis
The resulting formation law of unperturbed unmanned aircraft alignment trajectory that guarantees equality of the contact point parameters to given values, and allows parametric changes, wind disturbance, difficulty trajectory is offered. As the criterion for the synthesis was elected the lowest average vertical velocity at the last 30% of the trajectory. This allowed small vertical velocity when touching, even in cases of early or delayed landing. Methods of stabilize laws analytical designing of the aircraft on landing trajectory is obtained. It provides effective control laws implemented by the limited use of controls. The technique is based on the proposed additional quality criterion and search algorithm of its extremum. This criterion is to minimize the error variance of the slope angle of the trajectory and maximum rudder deflection height. It is shown that this heuristic criterion increases the accuracy of the aircraft stabilizing on landing trajectory. It was established that the automated search algorithm of heuristic quality criterion global extremum on the set of Kalman-Letov functional parameters has improved reliability and increased performance. This algorithm can be used for other tasks extremum search. Its effectiveness is confirmed by testing for problems with known solutions. The results of simulation modeling for automatic landing of unmanned aircraft with inaccurately known parameters of the mathematical model with the action of wind shows enough quality of obtained control laws and usefulness of the proposed methods.