| 摘要 |
A control system of aircraft contains a control lever connected by mechanical guide to valve rod of control drive, servo drive in parallel connected to the valve rod and electrically connected to the angle sensor mounted into the control guide, backup loading spring and spring device of negative hardness, which consists of precompressed spring and rocker, sensor of angular velocity, sensor of angular acceleration of control lever, whose outputs are connected to the control unit. For increasing the accuracy of control the system of compensation of nonlinearity impact is introduced, which contains series-connected control input selector, first, second adders, linear dynamic and nonlinear parts of actuating element, shaper of output signal, negative feedback connected to the second input of the first adder, observer of state of control, which input is connected to the output of the second adder, and output through the first inputs of third and fourth adders is connected to the input of iterative inverse filter, which output is connected to the second input of the second adder. Output signal is connected through the observer of the state of the output parameter to the second input of the third adder and directly to the second input of the fourth adder. |
