Study on acceleration-based combustion for low-burning rate HTPB propellant

The effects of acceleration on combustion characteristics for the composite propellant with aluminum of low-burning rate(4 mm/s, 4 MPa) was investigated. The method used in the study is known as the solid rocket motor centrifugal test. The test solid rocket motors were divide into two groups. The average action pressure of the motors in first group was 4 MPa, and that in second group was 12 MPa. Every group of motors was tested at the different centrifugal acceleration value of 0, 5 g_n, 8 g_n, 15 g_n. From the experiment, it was found that the burning-rate was very sensitive to the acceleration condition, and at low acceleration the burning-rate on the burning plane normal to the acceleration was increased. The burning-rate was approximately linear-increased with the acceleration from 0 to 15 g_n at the same pressure(4 MPa) condition.