Entity

Time filter

Source Type

Harbin, China

Zhang L.,Nnit 93199 of PLA | Sun H.,Nnit 93199 of PLA | Li H.,Nnit 93199 of PLA | Liu J.,Nnit 93199 of PLA | Wu G.,Nnit 93199 of PLA
Xitong Fangzhen Xuebao / Journal of System Simulation | Year: 2014

The controlling loop of a general helicopter dynamical system was analyzed. A simulation mathematics model was advanced which took account of the coupling between the rotor speed and the gas turbine-control of the engine. The model of gas turbine was divided into a startup-state model and a advance-state model and a control-state model on the whole and three parts solve respectively. Among them, the control-state model was based on the PID controller technology. An example of the controlling loop was set up according to the presented model for a type of helicopter simulator. The result shows that the model can simulate dynamic characteristic flight of the helicopter which takes account of the coupling between the rotor speed and the gas turbine -control of the engine realistically, especially being the characteristic flight of the helicopter with single engine after an air engine stops and the fuel conditioning system can't keep the rotor speed in a rating. Source

Discover hidden collaborations