低燃速HTPB复合推进剂过载情况下燃烧性能试验研究

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

利用固体火箭发动机离心试验方法,研究了低燃速（4 mm/s,4 MPa）、高铝粉含量的HTPB复合推进剂在过载情况下的燃烧加速度敏感性。试验分2组进行,第1组试验发动机平均工作压强为4 MPa,第2组为12 MPa,分别在0、5gn、8gn、15gn离心加速度条件下进行试验。通过对试验机理和试验数据分析发现,此类HTPB复合推进剂的燃速对过载加速度非常敏感。在较低加速度情况下,垂直于加速度的燃面处燃速出现了增加;同一压强（4 MPa）下,在0~15gn范围内,燃速与加速度近似呈线性关系。

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 0,5gn,8gn,15gn.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 15gn at the same pressure（4 MPa） condition.