system depends on the arrangement of the missile position, the aerodynamic
layout and the structure of the solid rocket motor nozzle.
(2) Whether the rudder system adopts angular position feedback or angular velocity
feedback or hinge moment feedback mainly depends on missile type, control
mode, rudder type, and quality requirements. Most common air defense missiles
use angular feedback (such as Sparrow and Sam 2), which is characterized by
high positioning accuracy and good control rigidity. Hinge moment feedback is
often used in small missiles and is combined with gas actuators (e.g., American
Chaparral) to simplify the missile-borne control system.
(3) The type of rudder depends on the control response and load power of the
rudder system, and to a large extent, it is related to the comprehensive utilization of missile-borne auxiliary energy, whether there is counter manipulation during flight and the structure space of the rudder cabin, etc. Usually,
hydraulic actuators are the preferred type to provide high response and high
power, which are used by American Patriots, Hookers, and Sea Sparrows. If
the comprehensive utilization of missile-borne auxiliary energy can be considered, the weight of missile can be effectively reduced. In addition, flight test
practice has proved that if air-conditioned actuator is used, the phenomenon of
control surface counter control should be avoided absolutely. Whether the
actuator, servo valve, and feedback potentiometer in the rudder torsion
structure adopt the whole structure or the bulk structure generally depends on
the shape and size of the structure space provided by the rudder cabin.
(4) The type of control mechanism is the same as the type of steering gear
structure, which mainly depends on the structure space provided by the rudder
cabin. Usually, the linear feedback structure of the integral steering gear is
matched with the push–pull linkage mechanism and installed in the larger
cylindrical structure space (such as Sam 2, Sam 3) in the hollow. The angular
feedback structure of the decentralized steering gear is matched with the push–
push lever mechanism, and is installed in a small cylindrical structure space
(e.g., Sea Sparrows, Aspide) in the hollow. The solid (long nozzle of engine)
annular cylindrical structure space, according to tradition and need, has integrated actuator push–pull actuator (such as British Sea Javelin) and decentralized actuator push–pull actuator (such as Patriot). Likewise, due to the
limitation of effective space, the installation of pitch and yaw two-way control
mechanism is often asymmetrical to the integral steering gear. In this way, if
the two control systems are completely symmetrical, the polarity of the
steering gear (or the polarity of the guidance command) must be changed in
order to coordinate the polarity of the two control surfaces. Whether the rudder
system adopts mechanical differential or electric differential, it can be
cross-matched with integral or decentralized rudder.
(5) Is the actuator energy of the control execution system co-source or sub-source
with the seeker antenna energy? Is it integrated with other missile-borne
auxiliary energy or provided independently? From the point of view of
reducing weight, reducing volume and making design more economical and
reasonable, generally speaking, as long as conditions permit, common source
9.1 Electro-Hydraulic Servo Control Technology of Aircraft Gas Turbine Pump
79
layout and the structure of the solid rocket motor nozzle.
(2) Whether the rudder system adopts angular position feedback or angular velocity
feedback or hinge moment feedback mainly depends on missile type, control
mode, rudder type, and quality requirements. Most common air defense missiles
use angular feedback (such as Sparrow and Sam 2), which is characterized by
high positioning accuracy and good control rigidity. Hinge moment feedback is
often used in small missiles and is combined with gas actuators (e.g., American
Chaparral) to simplify the missile-borne control system.
(3) The type of rudder depends on the control response and load power of the
rudder system, and to a large extent, it is related to the comprehensive utilization of missile-borne auxiliary energy, whether there is counter manipulation during flight and the structure space of the rudder cabin, etc. Usually,
hydraulic actuators are the preferred type to provide high response and high
power, which are used by American Patriots, Hookers, and Sea Sparrows. If
the comprehensive utilization of missile-borne auxiliary energy can be considered, the weight of missile can be effectively reduced. In addition, flight test
practice has proved that if air-conditioned actuator is used, the phenomenon of
control surface counter control should be avoided absolutely. Whether the
actuator, servo valve, and feedback potentiometer in the rudder torsion
structure adopt the whole structure or the bulk structure generally depends on
the shape and size of the structure space provided by the rudder cabin.
(4) The type of control mechanism is the same as the type of steering gear
structure, which mainly depends on the structure space provided by the rudder
cabin. Usually, the linear feedback structure of the integral steering gear is
matched with the push–pull linkage mechanism and installed in the larger
cylindrical structure space (such as Sam 2, Sam 3) in the hollow. The angular
feedback structure of the decentralized steering gear is matched with the push–
push lever mechanism, and is installed in a small cylindrical structure space
(e.g., Sea Sparrows, Aspide) in the hollow. The solid (long nozzle of engine)
annular cylindrical structure space, according to tradition and need, has integrated actuator push–pull actuator (such as British Sea Javelin) and decentralized actuator push–pull actuator (such as Patriot). Likewise, due to the
limitation of effective space, the installation of pitch and yaw two-way control
mechanism is often asymmetrical to the integral steering gear. In this way, if
the two control systems are completely symmetrical, the polarity of the
steering gear (or the polarity of the guidance command) must be changed in
order to coordinate the polarity of the two control surfaces. Whether the rudder
system adopts mechanical differential or electric differential, it can be
cross-matched with integral or decentralized rudder.
(5) Is the actuator energy of the control execution system co-source or sub-source
with the seeker antenna energy? Is it integrated with other missile-borne
auxiliary energy or provided independently? From the point of view of
reducing weight, reducing volume and making design more economical and
reasonable, generally speaking, as long as conditions permit, common source
9.1 Electro-Hydraulic Servo Control Technology of Aircraft Gas Turbine Pump
79