Improvement of Combustion Heat Testing Equipment of Fuel-Rich Propellant Based on Boron

摘要

Referring to the combustion heat testing method of GJB 770A— 97, adopting oxygen bomb calorimeter models GR 3500, the problems in the combustion heat test of fuel-rich propellant based on boron were investigated. The temperature distributing trend was given by the method of numerical simulation. The results show that the combustion ablation of oxygen bomb parts and the sample’s un-fully combustion must be resolved in the combustion heat testing of fuel-rich propellant based on boron. Feasible experimental method was put forward in the paper, the results show: the oxygen bomb parts were not ablated by combusting and the ingredient in the propellant can be combusted completely in the improved oxygen bomb. The parallel error of the testing results is 1.992%.