METHOD FOR CHECKING OF FUNCTIONING OF AIR-DYNAMIC CONTROL ACTUATOR OF GUIDED MISSILES OR ROCKETS AND DEVICE FOR ITS REALIZATION Russian patent published in 2003 - IPC

FIELD: defense equipment, guided missiles. SUBSTANCE: the method is based on monitoring and check of operation of the actuator with the simulator of hinge-joint load on the control surfaces on compressed air at follow-up of the preset control signals. The check is performed in the conditions of likeness of the temperature and power effect on the elements of structure of the compressed-air actuator and the temperature and pressure corresponding to the stagnation temperature and excess pressure of air flow at the inlet of the air intake in flight. The actuator with unfolded control surfaces and open air intake, with the sensors of the air temperature and pressure at its inlet, in its working cavities and the temperature of the walls of the cavities, preliminarily installed in it, are installed and secured on the loading stand, the control surfaces are loaded with the hinge-joint load corresponding to the load on the control surfaces from the air flow. After a foreblow of the actuator supply pneumatic system with compressed air and joining of it to the actuator a check test of actuator functioning is performed at the follow-up of the preset control signals in the cold air with the temperature of the pneumatic supply source and the pressure corresponding to the excess pressure of the air flow at the inlet of the air intake in flight of the missile or rocket with determination of the pressure loss of the pneumatic system according to the difference of the preset and inlet pressures and the parameters of the actuator. Then, heated air at a temperature and pressure corresponding to the stagnation temperature and the excess pressure of the air flow at the inlet of the air intake in flight is fed to the actuator inlet by a shock, with a simultaneous supply of control signals to the actuator. Operation of the actuator is registered according to the preset program, the air temperature and pressure at the inlet of the control actuator are determined and compared for compliance with the preset ones, the dynamic and precision parameters of the control actuator are determined for compliance with the required ones. By the obtained air temperature in the actuator cavities, the temperature of the walls of the cavities the allowance in the temperature for the structural materials used in the control actuator is carried out, a check disassembly of the actuator into units and parts is performed, and their strength, durability and serviceability are estimated. EFFECT: enhanced self- descriptiveness and quality of check of functioning of the air-dynamic control actuator, reduced terms and cost of experimental follow-up of control actuators and autopilots. 2 cl, 2 dwg