The application prospects of gas turbopump depend on the level of solid charge
and turbine development, and on whether the overall and system designers can
understand the ballistic conditions and improve the ballistic conditions. Gas turbopump hydraulic system and electric system have their own characteristics. From
the point of view of easy maintenance, reliability, and simplification of auxiliary
energy on missile, electric steering gear is suitable, especially for small field air
defense missiles and ship-borne defense missiles.
9.2 Power Matching Design of Steering System
9.2.1 Load Model of Steering System
There are several kinds of loads to be overcome in the hydraulic steering system.
First, the moment generated by the aerodynamic force on the rudder surface,
namely the hinge moment, is related to the flight altitude, Mach number, angle of
attack, rudder deflection angle, and rudder surface angular velocity of the missile. It
is a variable parameter in the flight process. The second is the inertia moment of
rudder surface and transmission mechanism, which is related to the inertia of rudder
surface, rudder shaft, piston, and transmission mechanism. The third is the friction
moment produced by the transmission mechanism, including the dry friction
moment. In addition, there are viscous damping moments, i.e., aerodynamic
damping moments, which are related to the angular velocity and mass of rudder
surface. The stiffness of the connector also has some influence. When hydraulic
steering gear system works normally, it not only needs to overcome the above load
force, but also needs to achieve a certain load speed. The relationship between load
force and load speed is called load characteristics. Here the typical load forms are
inertia load and the overlapping load of inertia load and elastic load, ignoring the
damping force and friction force.
9.2.1.1 Load Trajectory
The load that hydraulic actuator needs to overcome is
F ¼ m €
Y þ KY
ð9:1Þ
where
m m 1 þ m 2 , m 1 is piston mass, m 2 is equivalent mass of rudder surface and
transmission mechanism (kg);
K Comprehensive elastic coefficient (N=m);
Y Piston displacement (m).
9.1 Electro-Hydraulic Servo Control Technology of Aircraft Gas Turbine Pump
115
and turbine development, and on whether the overall and system designers can
understand the ballistic conditions and improve the ballistic conditions. Gas turbopump hydraulic system and electric system have their own characteristics. From
the point of view of easy maintenance, reliability, and simplification of auxiliary
energy on missile, electric steering gear is suitable, especially for small field air
defense missiles and ship-borne defense missiles.
9.2 Power Matching Design of Steering System
9.2.1 Load Model of Steering System
There are several kinds of loads to be overcome in the hydraulic steering system.
First, the moment generated by the aerodynamic force on the rudder surface,
namely the hinge moment, is related to the flight altitude, Mach number, angle of
attack, rudder deflection angle, and rudder surface angular velocity of the missile. It
is a variable parameter in the flight process. The second is the inertia moment of
rudder surface and transmission mechanism, which is related to the inertia of rudder
surface, rudder shaft, piston, and transmission mechanism. The third is the friction
moment produced by the transmission mechanism, including the dry friction
moment. In addition, there are viscous damping moments, i.e., aerodynamic
damping moments, which are related to the angular velocity and mass of rudder
surface. The stiffness of the connector also has some influence. When hydraulic
steering gear system works normally, it not only needs to overcome the above load
force, but also needs to achieve a certain load speed. The relationship between load
force and load speed is called load characteristics. Here the typical load forms are
inertia load and the overlapping load of inertia load and elastic load, ignoring the
damping force and friction force.
9.2.1.1 Load Trajectory
The load that hydraulic actuator needs to overcome is
F ¼ m €
Y þ KY
ð9:1Þ
where
m m 1 þ m 2 , m 1 is piston mass, m 2 is equivalent mass of rudder surface and
transmission mechanism (kg);
K Comprehensive elastic coefficient (N=m);
Y Piston displacement (m).
9.1 Electro-Hydraulic Servo Control Technology of Aircraft Gas Turbine Pump
115