EMC test between execution system and missile-borne electronic equipment:
When the missile-borne equipment is fully online, the electrical products of the
execution system, such as the explosive tube, electric igniter, turbogenerator,
electromagnetic spring lock, pressure relay, electromagnetic hydraulic switch,
electro-hydraulic servo valve, linear potentiometer, and integrated amplifier, are
required to work normally without the influence of radio frequency interference of
the missile-borne electronic equipment. Similarly, the work of electrical products of
this system should not affect the normal operation of missile-borne electronic
equipment, especially computers, strapdown inertial navigation units, seekers, and
electric fuzes.
(6) Flight test
The flight test related to the control execution system is the missile flight test in the
independent loop state and the closed-loop state. Independent open loop means that
the damp loop and the acceleration loop are disconnected. Because of the
non-damped stability and acceleration feedback, the trajectory changes dramatically. For the control execution system, both hinge moment and rudder deflection
speed are the most serious conditions. Because of the stability of damping and the
feedback of acceleration, the trajectory of the independent closed loop changes
smoothly and the trajectory condition changes slightly. Closed loop refers to the
missile guidance loop in a closed state, and the closest state to the actual combat is
the combat telemetry state, aiming at fuze-warhead coordination research of missiles. The independent circuit mainly examines the signal response characteristics,
power drive characteristics, anti-counter maneuvering ability, and the adaptability
of the corresponding energy trajectory conditions of the execution system. At the
same time, the correctness of launch control and flight control timing is further
verified. The closed loop mainly examines the EMC capability, energy interconnection and isolation capability of the system, and the reliability of the control and
execution system in the real climate and mechanical environment, in the complex
flight and electronic environment.
9.1.4.5 Summary
(1) Control Actuation System
The control actuation system has been combined with digital autopilot and strapdown inertial navigation system (both controlled by missile-borne computer). The
rudder system is still based on position control servo system and is developing in
the direction of digital control. Most of the rudder systems can work under the
control surface counter-maneuvering state, and the speed requirement of the rudder
is also reduced appropriately. The types of steering gear are still diverse and traditional. Hydraulic steering gear is the most common type of large missiles, followed by air-conditioned steering gear, while gas steering gear and electric steering
gear are used simultaneously for small missiles. Electric steering gear, because of
94
9 High-Temperature and High-Speed Gas Turbine Pump …
When the missile-borne equipment is fully online, the electrical products of the
execution system, such as the explosive tube, electric igniter, turbogenerator,
electromagnetic spring lock, pressure relay, electromagnetic hydraulic switch,
electro-hydraulic servo valve, linear potentiometer, and integrated amplifier, are
required to work normally without the influence of radio frequency interference of
the missile-borne electronic equipment. Similarly, the work of electrical products of
this system should not affect the normal operation of missile-borne electronic
equipment, especially computers, strapdown inertial navigation units, seekers, and
electric fuzes.
(6) Flight test
The flight test related to the control execution system is the missile flight test in the
independent loop state and the closed-loop state. Independent open loop means that
the damp loop and the acceleration loop are disconnected. Because of the
non-damped stability and acceleration feedback, the trajectory changes dramatically. For the control execution system, both hinge moment and rudder deflection
speed are the most serious conditions. Because of the stability of damping and the
feedback of acceleration, the trajectory of the independent closed loop changes
smoothly and the trajectory condition changes slightly. Closed loop refers to the
missile guidance loop in a closed state, and the closest state to the actual combat is
the combat telemetry state, aiming at fuze-warhead coordination research of missiles. The independent circuit mainly examines the signal response characteristics,
power drive characteristics, anti-counter maneuvering ability, and the adaptability
of the corresponding energy trajectory conditions of the execution system. At the
same time, the correctness of launch control and flight control timing is further
verified. The closed loop mainly examines the EMC capability, energy interconnection and isolation capability of the system, and the reliability of the control and
execution system in the real climate and mechanical environment, in the complex
flight and electronic environment.
9.1.4.5 Summary
(1) Control Actuation System
The control actuation system has been combined with digital autopilot and strapdown inertial navigation system (both controlled by missile-borne computer). The
rudder system is still based on position control servo system and is developing in
the direction of digital control. Most of the rudder systems can work under the
control surface counter-maneuvering state, and the speed requirement of the rudder
is also reduced appropriately. The types of steering gear are still diverse and traditional. Hydraulic steering gear is the most common type of large missiles, followed by air-conditioned steering gear, while gas steering gear and electric steering
gear are used simultaneously for small missiles. Electric steering gear, because of
94
9 High-Temperature and High-Speed Gas Turbine Pump …