机载发动机药柱在温度循环载荷下的力学响应分析

Aiming at actual situation of solid rocket motor in airborne missile in storage under room temperature and flying under high-altitude cool loading, the thermal stain caused by the cyclic temperature loading during multiple takeoffs and landings of the HTPB propellant grain was simulated by means of ABAQUS. The dependences of temperature field and strain field on increase of cyclic number and flying time have been studied. The changes of temperature and strain of several characteristic points with the increase of cyclic number and flying time have been analyzed, based on which the grain structural integrity assessment has been discussed. The results show that the outer surface of combustion chamber is up to the lowest temperature at the end of the flying phase, whereas the maximum strain always lies on the inside surface of the inner bore of the grain. Within a certain number of cycles, the thermal strain increases with the number of times. The thermal strain also increases with the increase of the storage time, which has a more significant impact on the structure. The results have practical reference significance for the propellant test and the safety design of the solid motor under the flying conditions.