The invention belongs to the control technology of an unmanned aerial vehicle with flying wing configuration, and particularly relates to a control method for an application resistance rudder of an unmanned aerial vehicle with flying wing configuration. The control method comprises the following steps: when the unmanned aerial vehicle is stable in course and control, within each control period T, a flight control computer calculates a course channel control signal, wherein T ranges from 5ms to 100ms; when the unmanned aerial vehicle is in a hybrid operation mode of manpower and flight control, the flight control computer superposes the control signal calculated by a stability augment control rule to manual control according to the control authority K sigma-r-c, generates a course channel control signal and drives the resistance rudder to deflect, wherein K sigma-r-c ranges from 10% to 70%; when the unmanned aerial vehicle is in a automatic light mode, the flight control computer directly takes the signal calculated by the flight control rule as the course channel control signal to drive the resistance rudder to deflect. The control method disclosed by the invention can be used for guaranteeing the stability and the controllability of the unmanned aerial vehicle course channel in the hybrid operation of manpower and flight control as well as automatic flight control of the unmanned aerial vehicle with flying wing configuration, is simple to operate, practical and convenient, and relatively high in practical application value.
Control method for application resistance rudder of unmanned aerial vehicle with flying wing configuration
2015-06-10
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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