METHOD FOR STRENGTH TEST OF AUTOPILOT UNIT OF GUIDED MISSILE WITH HOMING HEAD AND DEVICE FOR ITS REALIZATION Russian patent published in 2001 - IPC

FIELD: guided artillery missiles fired from guns. SUBSTANCE: method consists in setting the autopilot unit in the OFF position in a process fixture, fastening of the process fixture on the carriage of the dynamic test bench and action of a single impact on the unit in the X-axis. Before the impact the resistance of electric circuits is measured and the leak-proofness of the autopilot unit is checked. A short- circuit of the primer circuit of the release mechanism of the central surfaces is applied, the short-circuit of the primer circuit of the electronic equipment battery is removed. An overall and weight simulator of the homing head is installed in the nose section of the autopilot unit. Sensors of direct and reverse overloads in the X-axis are installed in the process fixture. The protective process ring is removed from the surface of the autopilot unit. After the impact and removal of the autopilot unit from the dynamic test bench and process fixture the protective ring is installed on the unit body. Visual inspection is carried out, the resistance of the electric circuits is measured, the magnitudes of the direct and reverse overloads acting in the X-axis are determined, and the analysis of the results of inspection and measurements is carried out. The device for strength test of the autopilot unit has a cylinder-shaped body of high- strength steel, whose outside diameter corresponds to the inside diameter of the adjusting case of the dynamic test bench carriage. The body head has a stepped cylinder shape with holes for installation and attachment by the bottom section of the unit under test. The body bottom section is mated for installation and attachment of the device in the case of the dynamic test bench carriage. In the longitudinal direction the device has two cylinder-shaped blind chambers closed by stoppers. One chamber is provided with an opening on the side of the device head section, the other - on the side of the bottom section. Installed in each chamber is a measuring element in the form of a cylinder with a tapered head section, and a standard weight. A cylindrical recess is made on the side of the device head section, it accommodates a process board with mating seats for the contacts of the autopilot unit board. EFFECT: enhanced self-descriptiveness and reliability of tests of the autopilot unit of the missile in the conditions of maximum approximation to the real ones. 3 cl, 2 dwg