high-speed motor without rotating blades. Four servo valves receive digital electrical signals from the controller and control eight working chambers of the power
vector motor. They can swing positively and negatively and drive the rudder surface through the transmission mechanism. No feedback device, direct use of
computer for guidance and control, zero drift of ambient temperature is small.
9.1.4 Design Method of Air Defense Missile Control
Execution System
Air defense missile control actuation system (CAS) refers to the execution system
of missile control system, which mainly consists of steering gear and its energy,
control mechanism, and control surface, also known as steering gear control system.
Its working principle is shown in Fig. 9.10.
The command control signal generated by the formation device of the intermediate and terminal guidance commands of the air defense missile control execution system is superimposed with the automatic stabilization signal feedback
from acceleration, damping, and rolling loops, and is used as the input signal of the
rudder system. Compared with the feedback signal of the rudder system itself, the
error signal is formed. Then it is amplified synthetically by the integrated amplifier
and transmitted to the steering gear. Under the input power of the energy on the
missile, the steering gear provides the control moment, drives by the control
mechanism and overcomes the load moment, deflects the control surface according
to the polarity and amplitude of the control command, and makes the missile fly
according to the predetermined control trajectory until it hits the target.
Energy
Control signal
Stable signal
Energy
Integrated
amplifier
Steering
engine
Manipulator
Control Actuation
System
Control
surface
Feedback
potentiometer
Feedback
mechanism
Rudder
system
Fig. 9.10 Working principle diagram of air defense missile control actuation system
76
9 High-Temperature and High-Speed Gas Turbine Pump …
vector motor. They can swing positively and negatively and drive the rudder surface through the transmission mechanism. No feedback device, direct use of
computer for guidance and control, zero drift of ambient temperature is small.
9.1.4 Design Method of Air Defense Missile Control
Execution System
Air defense missile control actuation system (CAS) refers to the execution system
of missile control system, which mainly consists of steering gear and its energy,
control mechanism, and control surface, also known as steering gear control system.
Its working principle is shown in Fig. 9.10.
The command control signal generated by the formation device of the intermediate and terminal guidance commands of the air defense missile control execution system is superimposed with the automatic stabilization signal feedback
from acceleration, damping, and rolling loops, and is used as the input signal of the
rudder system. Compared with the feedback signal of the rudder system itself, the
error signal is formed. Then it is amplified synthetically by the integrated amplifier
and transmitted to the steering gear. Under the input power of the energy on the
missile, the steering gear provides the control moment, drives by the control
mechanism and overcomes the load moment, deflects the control surface according
to the polarity and amplitude of the control command, and makes the missile fly
according to the predetermined control trajectory until it hits the target.
Energy
Control signal
Stable signal
Energy
Integrated
amplifier
Steering
engine
Manipulator
Control Actuation
System
Control
surface
Feedback
potentiometer
Feedback
mechanism
Rudder
system
Fig. 9.10 Working principle diagram of air defense missile control actuation system
76
9 High-Temperature and High-Speed Gas Turbine Pump …