9.1.4.3 Main Criterion
(1) Rudder System
1. The frequency bandwidth of rudder system. The rudder system is essentially
a low-pass filter. In order to ensure a certain frequency bandwidth of the
rudder system, it is not necessary to increase the gain of the integrated
amplifier, the speed of the rudder, and the transmission ratio of the control
mechanism as much as possible. Because this will make the system work
unstable, the energy power becomes very large, and the equivalent force
arm becomes too small. The method of introducing inertial feedback network can be considered to solve this problem.
2. Electrical differential synchronization. The rudder aileron system will
inevitably cause additional effects, i.e., additional aileron effect or rudder
effect, because the two rudder systems are not synchronized. Generally
speaking, this kind of additional effect is small, and there is a certain margin
of control surface comprehensive deflection angle, rudder circuit will not be
blocked, so the problem is not serious. In order to improve the asynchronism
of the two rudder systems caused by electric differential, technical measures
such as characteristic selection, slope adjustment and sum–difference
cross-feedback can be adopted in the design of rudder system when the
additional effect is large and the comprehensive deflection margin is small.
3. Electric zero lock. The rudder system using zero return signal as control
surface locking has the following conditions: the rudder system is in normal
working condition, stalling moment must be greater than maximum locking
System Mass/kg
Working hours T/s
Output power(×0.735kw)
Fig. 9.12 Control actuation system weight optimum work band (1/3 load cycle). A-Gas execution
system (solid–gas generator size according to 100% load cycle) and cold gas execution system;
B-Gas and cold gas pressurized discharge hydraulic actuating system; C-Gas turbine pump cyclic
hydraulic execution system; D-Battery motor pump cyclic hydraulic execution system; E-Gas
motor pump cyclic hydraulic execution system (energy comprehensive utilization)
9.1 Electro-Hydraulic Servo Control Technology of Aircraft Gas Turbine Pump
83
(1) Rudder System
1. The frequency bandwidth of rudder system. The rudder system is essentially
a low-pass filter. In order to ensure a certain frequency bandwidth of the
rudder system, it is not necessary to increase the gain of the integrated
amplifier, the speed of the rudder, and the transmission ratio of the control
mechanism as much as possible. Because this will make the system work
unstable, the energy power becomes very large, and the equivalent force
arm becomes too small. The method of introducing inertial feedback network can be considered to solve this problem.
2. Electrical differential synchronization. The rudder aileron system will
inevitably cause additional effects, i.e., additional aileron effect or rudder
effect, because the two rudder systems are not synchronized. Generally
speaking, this kind of additional effect is small, and there is a certain margin
of control surface comprehensive deflection angle, rudder circuit will not be
blocked, so the problem is not serious. In order to improve the asynchronism
of the two rudder systems caused by electric differential, technical measures
such as characteristic selection, slope adjustment and sum–difference
cross-feedback can be adopted in the design of rudder system when the
additional effect is large and the comprehensive deflection margin is small.
3. Electric zero lock. The rudder system using zero return signal as control
surface locking has the following conditions: the rudder system is in normal
working condition, stalling moment must be greater than maximum locking
System Mass/kg
Working hours T/s
Output power(×0.735kw)
Fig. 9.12 Control actuation system weight optimum work band (1/3 load cycle). A-Gas execution
system (solid–gas generator size according to 100% load cycle) and cold gas execution system;
B-Gas and cold gas pressurized discharge hydraulic actuating system; C-Gas turbine pump cyclic
hydraulic execution system; D-Battery motor pump cyclic hydraulic execution system; E-Gas
motor pump cyclic hydraulic execution system (energy comprehensive utilization)
9.1 Electro-Hydraulic Servo Control Technology of Aircraft Gas Turbine Pump
83